ISRO · Doc. No. ISRO/ISAC/Prop‐Tanks/RFP/001 Issue‐0 ISRO REQUEST FOR PROPOSAL 265L (Nominal) Propellant Tanks February 2018 ISRO SATELLITE CENTRE

Doc. No. ISRO/ISAC/Prop‐Tanks/RFP/001

Issue‐0

ISRO

REQUEST FOR PROPOSAL

265L (Nominal) Propellant Tanks

February 2018

ISRO SATELLITE CENTRE

Indian Space Research Organization

Bengaluru, 560017

ISRO



SCHEDULE‐A

PREAMBLE

REQUEST FOR PROPOSAL ISRO/ISAC/Prop‐Tanks/RFP/001

SCHEDULE–A – PREAMBLE Issue‐0 February 2018

Page A‐1

Contents

1. INTRODUCTION ...................................................................................................... 2

1.1. SCOPE ............................................................................................................... 2

1.2. STRUCTURE OF THE RFP ................................................................................... 2

2. INSTRUCTIONS TO BIDDERS ................................................................................... 3

2.1. BIDDER PROFILE ................................................................................................ 3

2.2. SUBMISSION OF PROPOSALS ............................................................................ 3

2.2.1 TECHNO‐COMMERCIAL BID ........................................................................ 3

2.2.2 PRICE BID .................................................................................................... 3

2.3. CONTENTS OF THE PROPOSALS ........................................................................ 3

2.3.1 LANGUAGE ................................................................................................... 3

2.3.2 TECHNO‐COMMERCIAL BID .......................................................................... 3

2.3.3 PRICE BID ...................................................................................................... 4

2.4. VALIDITY OF PROPOSALS .................................................................................. 4

2.5. RETENTION OF PROPOSALS / CONFIDENTIALITY .............................................. 4

2.6. EVALUATION OF PROPOSALS ........................................................................... 4

2.7. AWARD OF CONTRACT ..................................................................................... 5

2.8. NON‐DISCLOSURE AND END USE CERTIFICATE ................................................. 5



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1. INTRODUCTION

ISRO Satellite Centre (ISAC) is the lead centre in India for design, development, integration and

testing of spacecraft. ISRO’s portfolio includes over eighty communications, remote sensing,

meteorological, scientific and interplanetary satellites to meet both domestic and international

civilian requirements.

ISAC is interested in procurement of 265L (Nominal) Propellant / Fuel Tanks for use in the

propulsion system of ISRO’s geostationary spacecraft.

The proposals are sought for delivery of 265L (Nominal) Propellant / Fuel Tanks from competent

vendors. This Request for Proposal (RFP) provides the necessary information to assist vendors to

prepare proposals in response to this RFP.

1.1. SCOPE This schedule provides the structure of this RFP and general instructions for the bidders.

1.2. STRUCTURE OF THE RFP

PREAMBLE SCHEDULE A

TECHNICAL SPECIFICATION REQUIREMENTS SCHEDULE B

CONTRACTUAL TERMS AND CONDITIONS SCHEDULE C

COMPLIANCE MATRIX ANNEXURE 1& 2



Page A‐3

2. INSTRUCTIONS TO BIDDERS The following instructions shall be followed by the bidders for submitting proposals in response to

this RFP.

2.1. BIDDER PROFILE The bidder and its sub Vendors shall have previous history of supplying tanks for spacecraft

of reputed space agencies.

2.2. SUBMISSION OF PROPOSALS

The proposals shall be submitted in two parts: i) Techno‐commercial bid and ii) Price bid.

2.2.1 TECHNO‐COMMERCIAL BID

2.2.1.1 The Techno‐commercial bid shall be submitted online onto the ISRO’s portal.

2.2.1.2 The techno‐commercial bid shall also include a format of the price bid (masking

the price values) indicating the various options and description of line items

being offered by the bidder. Techno‐commercial proposal should not contain

any price details.

2.2.1.3 Previous history of delivery of tanks to other reputed international space

agencies and the flight heritage to be provided.

2.2.2 PRICE BID

Price bid shall be submitted online onto the ISRO’s portal. The price bid shall give a

detailed price break‐up including details for the 265 L (nominal) Propellant tanks.

2.3. CONTENTS OF THE PROPOSALS 2.3.1 LANGUAGE

The proposals (techno‐commercial and price bid) and all communications related to this

RFP shall be in the English language.

2.3.2 TECHNO‐COMMERCIAL BID

The techno‐commercial bid shall consist of the following parts:

a) Volume I: Executive Summary

The executive summary shall consist of a brief introduction of the company, a summary

of the proposed 265 L (nominal) Propellant tanks and its heritage in terms of delivery of

a similar system. This volume shall not contain any commercial information.

b) Volume II: Response to RFP Schedules

Detailed and elaborated responses to the schedules B and C of this RFP shall be

provided.

c) Volume III: Compliance Matrix

The bidder shall provide an item‐wise compliance for the Schedules A to C of this RFP. In

case of partial compliance of any specification / schedule, the Vendor shall provide



Page A‐4

reason / justification / alternate solution indicating why the particular partial compliance

will not impact the intended overall performance. ISAC’s decision in this regard will be

final. The bidder is at liberty to provide additional information/ data in order to provide

a comprehensive compliance package.

d) Volume IV: Commercial Proposal

The commercial proposal shall include details of cost break up (masking the prices) for

the hardware realization, testing, analysis, documentation requirements and any other

deliverables. The bidder shall clearly bring out the financial considerations (if any) for

submission of additional reports, analysis, tests etc.

2.3.3 PRICE BID

Detailed price break‐up for each item of supply shall be provided. Whenever options are

quoted, the same should also be indicated with quantity and unit rate separately. The

prices are to be mentioned both in figures and in words. In the event of any discrepancy in

the price between figures and words, the price indicated in words shall prevail and

considered valid.

2.4. VALIDITY OF PROPOSALS The bids shall be valid for 6 months from the date of price bid opening. In case the vendor

bids through an agent or dealer, an authorization letter duly signed by the OEM shall be

provided failing which the bids shall be considered invalid.

2.5. RETENTION OF PROPOSALS / CONFIDENTIALITY All documents submitted in response to the RFP shall become the whole and sole property

of ISAC. Any information in such documents that is proprietary to the Vendor should be

specified clearly.

Any technical information passed on to the Vendor shall be treated as confidential by the

Vendor and shall not be disclosed directly or indirectly to third parties, without the prior

consent of ISAC. Assurance of confidentiality from any sub‐contractors shall be the

responsibility of the Vendor.

2.6. EVALUATION OF PROPOSALS The evaluation criteria shall include, but not limited to, technical compliance, delivery

schedule, payment terms and price. Preference shall be given to the bidders who have

experience and heritage of Propellant tanks similar to the one specified in this RFP. The

Vendor should address all these aspects in the proposal.



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2.7. AWARD OF CONTRACT

ISAC reserves the right to award a contract for the whole or any part of the work required

by the RFP or to make no award.

ISAC shall assign the overall responsibility of contract execution on a single Vendor (prime

Vendor). Dependencies on any sub‐vendors shall be managed by the prime Vendor and

shall not have any bearing whatsoever on the execution of the final contract.

The proposal should contain details of sub‐contracts, if any, proposed to be awarded by the

Vendor for some part of the system or subsystem to another supplier/Vendor. The details

should include, but not limited to, information like work/business profile of such a supplier,

experience in executing/supplying similar type of system/subsystem for which the

subcontract is being awarded, etc.,

2.8. NON‐DISCLOSURE AND END USE CERTIFICATE ISAC provides a non‐disclosure certificate certifying that the technical details and data

submitted by the bidder will not be disclosed to third party. Further it is certified that the

procured hardware, technical documentation and analysis details shall not be utilized for

other applications such as defence, missile, nuclear reactors, classified programs and resale

for commercial gains. ISAC confirms that the procured items will be used for civil and

societal space applications in ISRO satellite programs.

Page i

Doc no: LPSC/LBF/SCCP/PMSG/DD/626/18

ISRO



SCHEDULE‐B

TECHNICAL SPECIFICATION REQUIREMENTS

LIQUID PROPULSION SYSTEMS CENTRE

Indian Space Research Organization

Bengaluru, 560017

Page ii

Doc no: LPSC/LBF/SCCP/PMSG/DD/626/18

ISRO



SCHEDULE‐B

TECHNICAL SPECIFICATION REQUIREMENTS

ISSUE 0 1 2 3

DATE 13/02/2018

REQUEST FOR PROPOSAL LPSC/LBF/SCCP/PMSG/DD/626/18

SCHEDULE–B – TECHNICAL SPECIFICATION REQUIREMENTS Issue‐0 February 2018

Page 1-1

CONTENTS

1. SCOPE ........................................................................................................................................ 1‐5 2. APPLICABLE DOCUMENTS ........................................................................................................ 2‐1 3. REQUIREMENTS ........................................................................................................................ 3‐1

3.1. Interfaces ............................................................................................................................ 3‐1 3.1.1. Mechanical Interfaces ............................................................................................... 3‐1 3.1.2. Electrical Interfaces ................................................................................................... 3‐2 3.1.3. Accelerometer provision ........................................................................................... 3‐2

3.2. Component Function .......................................................................................................... 3‐2 3.3. Performance Requirements ............................................................................................... 3‐3

3.3.1. Tank pressure conditions .......................................................................................... 3‐3 3.3.1.1. Tank Pressure ........................................................................................................ 3‐3 3.3.1.2. Depressurization ................................................................................................... 3‐4 3.3.1.3. External pressure .................................................................................................. 3‐4 3.3.2. Working Medium ...................................................................................................... 3‐4 3.3.3. Fluid Temperatures ................................................................................................... 3‐4 3.3.4. Propellant Flow Rates ............................................................................................... 3‐4 3.3.5. Expulsion Capability .................................................................................................. 3‐4 3.3.6. Pressure Drop ............................................................................................................ 3‐4 3.3.7. External Leakage ....................................................................................................... 3‐4 3.3.8. Step Start Pressure Surge .......................................................................................... 3‐4 3.3.9. Tank Capacity ............................................................................................................ 3‐4 3.3.10. Propellant Loading ................................................................................................ 3‐5 3.3.11. Filling Rate ............................................................................................................. 3‐5 3.3.12. Slosh Analysis ........................................................................................................ 3‐5

3.4. Life Requirements .............................................................................................................. 3‐5 3.4.1. Storage Life ................................................................................................................ 3‐5 3.4.2. On Orbit Operating Life ............................................................................................. 3‐5 3.4.3. Cycle Life ................................................................................................................... 3‐5 3.4.4. Launch abort ............................................................................................................. 3‐5

3.5. Environmental Conditions .................................................................................................. 3‐5 3.5.1. Non‐Operating Conditions .................................................................................... 3‐5 3.5.1.1. Relative Humidity .................................................................................................. 3‐6 3.5.1.2. Barometric Pressure .............................................................................................. 3‐6 3.5.1.3. Temperature ......................................................................................................... 3‐6 3.5.1.4. Transportability ..................................................................................................... 3‐6 3.5.2. Operating Conditions ................................................................................................ 3‐6 3.5.2.1. Temperature ......................................................................................................... 3‐6 3.5.2.2. Ambient Pressure .................................................................................................. 3‐6 3.5.2.3. Relative Humidity .................................................................................................. 3‐6 3.5.2.4. Random Vibration ................................................................................................. 3‐6 3.5.2.5. Sine Vibration ........................................................................................................ 3‐6 3.5.2.6. Acceleration .......................................................................................................... 3‐6 3.5.2.7. Mathematical Models ........................................................................................... 3‐7 3.5.2.8. Shock ..................................................................................................................... 3‐7

3.6. Physical Characteristics ...................................................................................................... 3‐7



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3.6.1. Configuration ............................................................................................................ 3‐7 3.6.2. Mass .......................................................................................................................... 3‐8 3.6.3. Proof Pressure/Burst Pressure .................................................................................. 3‐8 3.6.4. Pressure Cycles .......................................................................................................... 3‐8 3.6.5. Collapse Pressure ...................................................................................................... 3‐8 3.6.6. Connections ............................................................................................................... 3‐8 3.6.7. Compatibility ............................................................................................................. 3‐8 3.6.8. Cleanliness ................................................................................................................. 3‐8 3.6.9. Maintainability .......................................................................................................... 3‐9 3.6.10. Transportation ...................................................................................................... 3‐9 3.6.10.1. Before Integration to Spacecraft .......................................................................... 3‐9 3.6.10.2. Integration into Spacecraft ................................................................................... 3‐9 3.6.11. Interchangeability ................................................................................................. 3‐9 3.6.12. Surface Finish ........................................................................................................ 3‐9 3.6.13. Fungus Resistance ................................................................................................. 3‐9 3.6.14. Corrosion of Materials ........................................................................................ 3‐10 3.6.15. Dissimilar Metals ................................................................................................. 3‐10 3.6.16. Stiffness ............................................................................................................... 3‐10 3.6.17. Interface Loads .................................................................................................... 3‐10 3.6.18. Identification and Marking .................................................................................. 3‐10 3.6.19. Traceability .......................................................................................................... 3‐11 3.6.20. Workmanship ...................................................................................................... 3‐11 3.6.21. Reliability ............................................................................................................. 3‐11 3.6.22. Safety ................................................................................................................... 3‐11 3.6.23. Items Subject to Wear out and Degradation ...................................................... 3‐12

4. QUALITY ASSURANCE PROVISIONS ......................................................................................... 4‐1 4.1. General Requirements ....................................................................................................... 4‐1

4.1.1. Test philosophy ......................................................................................................... 4‐1 4.1.2. Responsibility for Inspection and Tests .................................................................... 4‐1 4.1.3. Verification of Compliance ........................................................................................ 4‐1 4.1.4. Heritage ..................................................................................................................... 4‐2

4.2. Qualification ....................................................................................................................... 4‐2 4.2.1. Test Requirements .................................................................................................... 4‐2 4.2.2. Test Sequence ........................................................................................................... 4‐2 4.2.3. Failure Criteria ........................................................................................................... 4‐3 4.2.4. Qualification Test Report .......................................................................................... 4‐3

4.3. Proto‐flight Tests ................................................................................................................ 4‐3 4.3.1. Test Requirements .................................................................................................... 4‐3 4.3.2. Test Sequence ........................................................................................................... 4‐3 4.3.3. Failure Criteria ........................................................................................................... 4‐4 4.3.4. Proto‐flight Test Report ............................................................................................ 4‐4

4.4. Acceptance Tests ................................................................................................................ 4‐4 4.4.1. Test Sample ............................................................................................................... 4‐4 4.4.2. Test Requirement ...................................................................................................... 4‐4 4.4.3. Test Sequence ........................................................................................................... 4‐4



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4.4.4. Failure Criteria ........................................................................................................... 4‐5 4.4.5. Test Limitations ......................................................................................................... 4‐5 4.4.6. Acceptance Test Report ............................................................................................ 4‐5

4.5. Test Conditions ................................................................................................................... 4‐5 4.5.1. Environmental Conditions ......................................................................................... 4‐5 4.5.2. Measurement Tolerances ......................................................................................... 4‐5 4.5.3. Calibration ................................................................................................................. 4‐6 4.5.4. Test Reports .............................................................................................................. 4‐6 4.5.5. Test Data ................................................................................................................... 4‐6

4.6. Test Fluids ........................................................................................................................... 4‐6 4.7. Test Methods ..................................................................................................................... 4‐6

4.7.1. Initial Inspection ........................................................................................................ 4‐6 4.7.2. Non‐destructive Inspections ..................................................................................... 4‐6 4.7.2.1. For Tank and PMD ................................................................................................. 4‐6 4.7.2.2. Penetrant Inspection ............................................................................................. 4‐6 4.7.2.3. Other Methods ...................................................................................................... 4‐7 4.7.3. Proof Pressure Test ................................................................................................... 4‐7 4.7.4. Internal Volume ........................................................................................................ 4‐7 4.7.5. Physical Parameters of Tanks .................................................................................... 4‐7 4.7.6. Pressure Cycling ........................................................................................................ 4‐7 4.7.6.1. Internal Pressure Cycling ....................................................................................... 4‐7 4.7.7. External Leakage Test................................................................................................ 4‐7 4.7.8. Cleanliness ................................................................................................................. 4‐7 4.7.9. PMD Health Check .................................................................................................... 4‐8 4.7.9.1. Bubble Point Test .................................................................................................. 4‐8 4.7.9.2. Expulsion Efficiency ............................................................................................... 4‐8 4.7.10. Sustained Acceleration .......................................................................................... 4‐8 4.7.11. Random Vibration Test ......................................................................................... 4‐9 4.7.12. Sine Vibration Test ................................................................................................ 4‐9 4.7.13. Shock Tests ............................................................................................................ 4‐9 4.7.14. Burst Pressure Test ............................................................................................... 4‐9 4.7.15. Dryness Check ....................................................................................................... 4‐9 4.7.16. Final Inspection ..................................................................................................... 4‐9 4.7.17. Preparation for Data Review & End Item Acceptance ........................................ 4‐10

5. DELIVERY OF PROPELLANT TANKS ........................................................................................... 5‐1 5.1. Preservation and Packaging ............................................................................................... 5‐1

5.1.1. Retention and cleanliness ......................................................................................... 5‐1 5.1.2. Identification and Marking ........................................................................................ 5‐1

5.2. Marking for Shipment and Storage .................................................................................... 5‐1 5.3. Handling, Integration and utilization ................................................................................. 5‐2

5.3.1. Filling and Ground Operations .................................................................................. 5‐2 5.3.2. Handling/Handling provision .................................................................................... 5‐2

5.4. List of reviews and deliverables ......................................................................................... 5‐2 5.4.1. Milestones for Reviews ............................................................................................. 5‐2 5.4.2. List of Documents & Analysis reports ....................................................................... 5‐2 5.4.3. Hardware Delivery Schedule ..................................................................................... 5‐4

6. ACCELERATIONS & PROPELLANT FLOW RATES APPLICABLE TO PMD .................................... 6‐1



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6.1. Launch Phase ...................................................................................................................... 6‐2 6.2. Transfer Orbit 3‐Axis Stabilization ..................................................................................... 6‐2 6.3. LAM Burn ............................................................................................................................ 6‐2 6.4. Station Acquisition‐ East‐West Station Keeping ................................................................ 6‐3 6.5. North‐South Station Keeping ............................................................................................. 6‐4 6.6. On Orbit Mode ................................................................................................................... 6‐5 6.7. On‐ Orbit Attitude Loss/Recovery ...................................................................................... 6‐5

7. MODES, CONDITIONS & ACCELERATIONS LEVELS FOR SPACECRAFT TRANSPORTATION ..... 7‐17.1. Steady state acceleration ................................................................................................... 7‐1 7.2. Sine and Random vibration ................................................................................................ 7‐1 7.3. Shock .................................................................................................................................. 7‐1 7.4. Other Environments ........................................................................................................... 7‐1

8. TRANSPORTABILITY AFTER INTEGRATION WITH SPACECRAFT .............................................. 8‐19. NOTCHING CRITERIA FOR RANDOM VIBRATION TEST............................................................ 9‐110. NOTCHING CRITERIA FOR SINE VIBRATION TEST .................................................................. 10‐111. TABLE OF ABBREVIATIONS ..................................................................................................... 11‐112. DEFINITIONS ........................................................................................................................... 12‐113. PROPELLANT TANK ICD .......................................................................................................... 13‐1

LIST OF TABLES

Table 2‐1 Applicable Documents ........................................................................................... 2‐1 Table 3‐1 Propellant Tanks ‐ Expected Load Cycles(After Delivery To ISRO) ....................... 3‐13 Table 3‐2 Random Vibration Levels ..................................................................................... 3‐16 Table 3‐3 Sine Vibration Levels ............................................................................................ 3‐17 Table 3‐4 Shock Test Levels (All Three Axes) ....................................................................... 3‐18 Table 4‐1 Tank Requirement Verification* .......................................................................... 4‐11 Table 4‐2 Tank Qualification/Proto‐flight Test Matrix ......................................................... 4‐13 Table 4‐3 Test Acceptance test matrix ................................................................................ 4‐14 Table 5‐1 Review Milestones ................................................................................................. 5‐2 Table 5‐2 List of Deliverables & Analysis reports ................................................................... 5‐2 Table 5‐3 Hardware Delivery Schedule ................................................................................. 5‐4 Table 9‐1 Notching criteria for Random Vibration Test ......................................................... 9‐1 Table 10‐1 Notching criteria for Sine Vibration Test ........................................................... 10‐1

LIST OF FIGURES

Figure 3‐1: Typical Tank dimensions and Interface details. .................................................................. 3‐1 Figure 6‐1 Tank Configuration and Spacecraft axes definition ............................................................. 6‐1 Figure 6‐2 Launch Phase ....................................................................................................................... 6‐2 Figure 6‐3 LAM Burn ............................................................................................................................. 6‐3 Figure 6‐4 Acquisition & E‐W Station Keeping ...................................................................................... 6‐3 Figure 6‐5 North South Station Keeping ............................................................................................... 6‐4 Figure 6‐6 On‐Orbit Attitude Loss ......................................................................................................... 6‐5 Figure 13‐1: Propellant Tank ICD ........................................................................................................ 13‐1 Figure 13‐2 Typical Tank dimensions and Interface details. ............................................................... 13‐2



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1. SCOPE

This specification establishes the requirements for the design, performance, fabrication and test of propellant storage tanks for use in the propulsion system of ISRO’s Geo‐Imaging spacecraft. The propellant tank shall utilize surface tension device and helium pressurant to expel vapour‐free Fuel (MMH) upon demand. The propellant tank together with the Propellant Management device (PMD) will be referred hereafter as the “Tank”.

The tank should be total communication and single compartment type with the PMD capable of acquiring propellant anywhere from the tank and supplying gas free propellant to the engines.



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2. APPLICABLE DOCUMENTS

The following documents in their latest revision form part of this specification. In the event of conflict between this specification and documents referred here, this conflict shall be notified to ISRO.

Table 2‐1 Applicable Documents

2(a) Propellant tank and interface drawings and CAD models

To be provided by Vendor in *.dwg/*.dxf and *.iges/*.stp formats

2(b) Intentionally left blank

2(c) Monomethyl Hydrazine (MMH) MIL‐P‐27404

2(d) Titanium alloy (6Al‐4V) MIL‐T‐9047

2(e) Argon MIL‐A‐18455

2(f) Propellant pressurizing agent (Nitrogen)

MIL‐P‐27401

2(g) Propellant pressurizing agent (Helium)

MIL‐P‐27407

2(h) Iso‐Propyl Alcohol TT‐I‐735

2(i) Intentionally left blank

2(j) De‐ionized water JSC‐SPEC‐C‐20C

2(k) Penetrant Inspection ASTM‐E‐1417

2(l) Radiographic Inspection & UT inspection

MIL‐STD‐453 / NAS‐1514 ASTM‐E‐2375

2(m) Procedure for determining surface contamination levels

ARP‐598

2(n) Safety Standards NSS/HP 1740.1/ MIL‐ 1522

2(o) Applicable Launch vehicle safety documents

GSLV, Proton, Atlas, Land launch, Sea Launch, Ariane‐5, Soyuz, Falcon



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3. REQUIREMENTS

3.1. Interfaces

3.1.1. Mechanical Interfaces

The Tank shall be of side mounting support as Interface to Spacecraft structure fixation.

The Tank interface shall be as given below in the sketch and the associated table gives the detail of support conditions.

Figure 3‐1: Typical Tank dimensions and Interface details.



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The Support conditions are put in the following table

Vendor shall provide mounting interfaces with all dimensional details along with the offer. Vendor shall also provide the ICD of tanks including the details of side mount location, struts/interface joints with spacecraft with overall clear dimensions.

The height of tank shall be fixed to meet volume requirements according to para 3.3.9 & 3.3.10. Maximum height (H) of the dry tank shall be within 1500mm to 1600mm including all projections and as per figure 3‐1. Free gas/propellant tube lengths in figure 3.1 LI & L2 shall be from 50mm to 75mm beyond the flex plate and its end fittings.

The overall tank diameter shall never exceed the interface diameter (D) of 540 ± 10 mm on any point, at any time and under any conditions seen by the tank integrated in the satellite (pressure, temperature, vibrations, etc.)

3.1.2. Electrical Interfaces

Grounding shall be possible by connecting the tank to the S/C structure via bonding straps.

3.1.3. Accelerometer provision

The accelerometers will be mounted on the tank for ground tests and will be flown. The accelerometers will be bonded with Hysol EA 9309 or Hysol EA 9392 or Araldite 2014 compound. The external interfaces shall be compatible with the above said adhesive.

3.2. Component Function

The propellant tanks described herein (henceforth referred to as tanks) shall provide vapour free Fuel (MMH) to the Liquid Apogee Motor (LAM) and Attitude and Orbit Control System Thrusters (AOCS) upon demand commencing from launch vehicle separation to the end of life of spacecraft.

Two tanks will be used per spacecraft as shown in Fig. 6‐1.

Also described herein are the design requirements and test requirements associated with a qualification tank and the requirements are shown in Para 4.2.

Tank Interfaces Interface Locations Support Conditions

1 2 3

Refer Figure 3.1

Spacecraft Interface 1 is side mounting type.

It has to primarily bear the axial loads and

laterally flexing.

Spacecraft Interfaces 2 and 3 are with flexure

type interface. This interface has to bear

primarily lateral loads and axially flexing.



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3.3. Performance Requirements

3.3.1. Tank pressure conditions

3.3.1.1. Tank Pressure

The tank shall be able to function at the pressures & temperatures specified below during/after exposure to environment as specified in para 3.5. The maximum expected operating pressure (MEOP) is 16.3bar differential internal pressure.

Propellant flow is required during events (d) and (e).

* Non‐nominal case of operation

Pressure and temperature requirements for nominal operational phases:

Phase Fill factor Pressure at 20°C Temperature range

0 System vibration test Up to 95% 6 bar differential internal

Ambient

I Propellant loading, transport from filling area to launcher

Max. 95%

Min. 85%(2)

upto MEOP

20 to 26°C

II Launch preparation, launch until separation

Up to 95%

Min. 85%(2)

upto MEOP

15 to 26°C

III In‐flight pressurization(5) Up to 95 % upto MEOP 15 to 26°C

IV Transfer (AKM/PKM) phase(5)

Up to 95% to end LAM

16.3 bar regulated

10 to 26°C

V On‐station Phase(5) End of LAM to Hold up volume (3)

16.3 to9.0(1) bar in blow‐down

10 to 35°C (BOL)

10 to 50°C (EOL)

Note:

1) Minimum pressure at end of life including non‐nominal cases.

2) Vendor shall note the fill fractions could be 85% to 95% for the horizontal transportation of

the spacecraft. Subject to confirmation by the vendor through analysis for minimum fill

fraction for horizontal transportation.

3) Vendor shall specify the unusable propellant volume in the tank.

Phase Pressure

(a) Ground handling and pre‐launch Ambient to MEOP (16.3bar)

(b) Launch base Upto MEOP(16.3bar)

(c) Launch at lift‐off Upto MEOP(16.3bar)

(d) Transfer orbits and Apogee burn MEOP(16.3bar)

(e) Geo synchronous orbit MEOP(16.3bar) + 1 bar *



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4) All pressure values are internal differential pressure

5) Safe sustenance pressure (at least 1.25 times MEOP)

3.3.1.2. Depressurization

The unit shall be able to withstand an external depressurization from atmospheric pressure to 1x10‐10Torr.

3.3.1.3. External pressure

The unit shall be able to withstand the free space vacuum of 10‐10 Torr.

3.3.2. Working Medium

a. Gaseous helium in accordance with applicable document 2(g)

b. MMH in accordance with applicable document 2(c)

3.3.3. Fluid Temperatures

a. Helium temperature will be between ‐40C and +65C

b. Propellant temperature will be between 0C and +50C.

3.3.4. Propellant Flow Rates

Propellant flow rates have to be guaranteed with respect to

a. Flow rate demand

b. No Helium/Vapors ingestion in propellant at any time, as per the mission constraints given in Chapter 6.

Propellant flow rates are detailed in Chapter 6.

3.3.5. Expulsion Capability

Gas free propellant delivery shall be provided under all conditions of operations indicated in Chapter 6.

Maximum unusable residual volume in orbit shall be specified by the vendor.

3.3.6. Pressure Drop

The tank pressure drop under any flow specified in Chapter 6 shall not exceed 0.2 bar.

3.3.7. External Leakage

With the tank pressurized to MEOP with gaseous helium, the external leak rate shall not exceed 1x10‐6 scc/s of helium. There shall be no propellant leakage from the tank at any pressure up to and including burst pressure.

3.3.8. Step Start Pressure Surge

At system start‐up the tank (at MEOP) shall be capable of discharging into a line volume of 2.0 L maximum, initially at 0 bar at the rate of 690 cm3/s per tank.

3.3.9. Tank Capacity

The total nominal volume excluding PMD shall be minimum 265 ltr. in unpressurised ambient conditions. Vendor may also provide the corresponding volume @ MEOP for information.



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3.3.10. Propellant Loading

Tank design for the nominal case shall be such that it can accommodate the following propellant fill quantities under unpressurised condition.

a. MMH in accordance with applicable document 2(c)

Maximum: 95% of propellant tank volume (based on density values at 20°C of 875 Kg/m3)

3.3.11. Filling Rate

In the vertical attitude (outlet port down) the tanks shall be capable of being filled with MMH [as per applicable doc 2(c)], Iso‐Propyl alcohol [as per applicable document 2(h)] or de‐ionized water [as per applicable doc 2(j)] at any rate up to 4.8 L per minute minimum. Filling procedure to be specified by vendor. The tank ullage pressure shall be in the range 2 bar to 10 bar absolute during the filling operation. The tank shall be designed for gravity draining to residual volume of less than 0.2L when outlet ports are in a vertical attitude. It shall be a design objective to minimize the residuals.

3.3.12. Slosh Analysis

The tank design shall be such that a damping factor (applicable to propellant sloshing movement) ≥0.1% shall be assured during orbit raising and station keeping maneuver (SKM) after proper settlement.

Slosh analysis results for various fill fractions covering orbit raising phase, Station keeping maneuvers at BOL, MOL & EOL cases shall be provided.

3.4. Life Requirements

There shall be no degradation of tank performance resulting from any or all of the following.

3.4.1. Storage Life

The tanks shall be capable of being stored for a minimum of 10 years without, maintenance or re‐verification / re‐testing at the end of storage.

The storage temperature shall be as specified in para 3.5.1.3 with relative humidity up to 100%.

3.4.2. On Orbit Operating Life

Not less than 18 years following exposure to propellant liquid/vapour.

3.4.3. Cycle Life

After acceptance testing, the tanks shall withstand the life cycle as per Table 3‐1.

3.4.4. Launch abort

In the event of launch abort the propellant will be drained and refilled as required. Vendor may provide the procedure to be followed in case of a launch abort for draining and flushing (with recommended fluids) for MMH.

3.5. Environmental Conditions

3.5.1. Non‐Operating Conditions

The tank shall perform within specification after exposure to the following.



Page 3-6

(No propellant fill condition)

3.5.1.1. Relative Humidity

Relative humidity of up to 100%. Condensation can take place in the form of water and frost and should not affect the tank performance.

3.5.1.2. Barometric Pressure

Atmospheric pressure between sea level and @ altitude of 12200 m.

3.5.1.3. Temperature

Temperature range between ‐7C and +65 C.

3.5.1.4. Transportability

The tanks shall be compatible with pre‐flight environments as defined in Chapters 7&8 of this document.

3.5.2. Operating Conditions

The tank shall perform within specification during exposure to the following after having been filled with working medium as per paragraph 3.3.2 and pressurized as per paragraph 3.3.1.

3.5.2.1. Temperature

a. First two years: 10C to 35C with daily variation of 10C temperature.

b. Remaining 16 years Life: 10C to 50C with daily variation of 10C temperature. c. During AMF, for gas temperature, refer paragraph 3.3.3

In addition, the tank shall be able to withstand a temperature gradient of 10 C between the gas port and the propellant port with the gas port hotter.

3.5.2.2. Ambient Pressure

1 bar to 1x10‐10 Torr.

3.5.2.3. Relative Humidity

Relative humidity’s of up to 100 per cent.

3.5.2.4. Random Vibration

The random vibration environment is shown in Table 3‐2. No flow is required from the tank under this environment.

3.5.2.5. Sine Vibration

The sine vibration level and duration is shown in Table 3‐3. No flow is required from the tank when under this environment.

3.5.2.6. Acceleration

a. Steady acceleration Qualification quasi‐static accelerations at the C.G. of the tank are 18g in longitudinal direction and 8g in lateral directions

b. On orbit acceleration. (See Chapter 6)



Page 3-7

3.5.2.7. Mathematical Models Mathematical models / Finite element (FE) models of the propellant tank, along with reports, shall be provided to ISRO the following cases:

Finite element model supplied should be compatible for NASTRAN 2005 version or later

Craig‐Bampton Model: Mass and stiffness matrices (Craig‐Bampton Model) with 70%, 85% & 95% fill fractions with specific gravity of 0.878 and 0.785simulating slosh models.

Dry tank full FE model

FE model report shall contain the following o The model should be in SI units with Length in meter, Mass in kilogram, Time in second

and Angle in Radian

Required details in the report o System of co‐ordinates, Details of Tank Idealisation, COG, Mass and inertia properties,

Description of Craig‐Bampton Model, interface description o Mass and stiffness matrices (Craig‐Bampton Model) with 70%, 85% & 95% fill fractions

with specific gravity of 0.878 and 0.785 simulating slosh models. o Free Vibration characteristics, output transformation matrices for accelerations,

output transformation matrices for COG accelerations and response I/F forces, simplified restitution model for visualization, concordance tables of DOF’s and I/F grid co‐ordinates, Dry tank full FE model

3.5.2.8. Shock

The shock test environment is shown in Table 3‐4. No flow is required from the tank under this environment. Compliance to shock qualification shall be provided by one of the below with supporting documentation

a. by test b. by analysis c. test data from qualification model.

3.6. Physical Characteristics

3.6.1. Configuration

The tank shall consist of a pressure vessel and an internally mounted Propellant Management Device (PMD). The tank shall be filled with propellant (or other compatible fluids) through the propellant port. During operation, propellant shall be expelled from the tank through the propellant port. Helium gas pressure shall be supplied through the pressurant port.

The PMD will ensure the supply of gas free propellant at tank outlet interface under the conditions specified herein (including Chapter 6)

Tank shall be attached to the spacecraft structure through interface as per the table detailed in 3.1.1. The interior of the unit, including the surface tension device, shall be designed and fabricated to facilitate cleaning and prevent the entrapment of contaminants. The tank construction shall facilitate draining of fluid from the tank. Tanks shall be cleaned as per requirements of paragraph 3.6.8 and shall contain no chips, slag, particulate matter, grease or other foreign material.

Cleanliness requirements for parts, assemblies and the assembly/work area shall be established and maintained.



Page 3-8

The shell of the tank shall be constructed of 6Al‐4V Titanium alloy. Tank shell forging shall be 100% ultrasonically inspected. The PMD shall also be built out of Titanium to the extent possible with the use of corrosion resistant steel restricted to bare minimum. Use of stainless steel / Titanium wire cloth of compatible composition is allowed. However, no non‐metallic parts are allowed in propellant exposed area.

3.6.2. Mass

The tank mass shall not be more than 16.5 kg.

3.6.3. Proof Pressure/Burst Pressure

Proof pressure: Minimum 1.25 x MEOP

Burst pressure: Minimum 1.5 x MEOP

3.6.4. Pressure Cycles

The number of pressure cycles shall be derived from Table 3‐1. The number shall be used for all the analysis and verification required by the safety (fracture mechanics safe life, etc.) in accordance with MIL‐STD‐1522‐A. The tank shall be capable of withstanding 12 pressure cycles at proof pressure as specified in paragraph 3.6.3 and 50 cycles from ambient to MEOP.

3.6.5. Collapse Pressure

Vendor to provide the differential pressure level to which the tank can be evacuated when the external pressure is at ambient. The same may be supported with analysis reports.

3.6.6. Connections

The tank shall be designed with appropriate Titanium‐to‐Stainless Steel transition tubes for connection to SS 304L pipe work by welding. The pipe work dimensions shall be:

Outer Diameter Wall Thickness

Pressurant inlet 6.0+0.1 / 0.0 mm 0.7 ± 0.07 mm

Propellant outlet 10.0+0.1 / 0.0 mm 0.7 ± 0.07 mm

3.6.7. Compatibility

Exposure of the tank to MMH [(as per applicable document 2(c) in Table 2‐1] liquid or vapour for a period of 18 years shall not degrade its performance.

In addition, the tank shall also be compatible with the following:

a. Helium [as per applicable document 2(g) in Table 2‐1]

b. Nitrogen [as per applicable document 2(f) in Table 2‐1]

c. Argon [as per applicable document 2(e) in Table 2‐1]

d. Iso‐propyl alcohol [as per applicable document 2(h) in Table 2‐1]

e. De‐ionized water [as per applicable document 2(j) in Table 2‐1]

3.6.8. Cleanliness

The particulate and chemical cleanliness of the unit shall be achieved, measured and maintained in accordance with the manufacturer's specifications which are to be approved by ISRO.



Page 3-9

The chemical cleanliness must be such that necessary to ensure compatibility with the specified propellants and referee fluids.

The level of particulate contamination shall be determined by a rinse test using a fluid approved by ISRO. The cleanliness check shall be done both in normal and reverse flow directions and shall include the PMD. Samples shall be drawn from each port for particle count analysis. The maximum allowable particle count distribution, when tested in accordance with ARP‐598 standard or equivalent, shall be as per the following:

< 5 micron ‐ No limit, no silting

5‐15 micron ‐ 1200

15‐25 micron ‐ 100

25‐50 micron ‐ 30

> 50 micron ‐ None

Non volatile residue(NVR) ‐ < 1mg/100 ml

No metallic particles allowed.

3.6.9. Maintainability

No field maintenance, servicing or adjustment shall be required within the specified lifetime.

3.6.10. Transportation

3.6.10.1. Before Integration to Spacecraft

The tanks shall be designed to be transported by common carrier (including air transport) with adequate protection. The transportation environment shall be as per Chapter 7.

The tanks shall be provided with protection covering to prevent contamination during transportation outside clean areas and to protect against damage in handling. Inlet and outlet ports shall be individually protected.

3.6.10.2. Integration into Spacecraft

Vendor shall provide tank integration procedure onto the spacecraft. After the tanks are integrated to spacecraft, the tanks are required to meet the transportation environment as per Chapter 8.

3.6.11. Interchangeability

Each tank shall be directly interchangeable in form, fit, and function.

3.6.12. Surface Finish

The surface of the tank shall be adequately finished to prevent deterioration from exposure to the specified environments that might affect specified performance. No plating shall be used on any component.

The tank mounting surfaces shall be unpainted and any protective coating used shall produce a conductive finish suitable for electrical bonding.

3.6.13. Fungus Resistance

Materials which are nutrients to fungi shall not be used.



Page 3-10

3.6.14. Corrosion of Materials

a. Corrosive Materials

Materials shall be corrosion resistant type or suitably treated to resist corrosive conditions likely to be met in storage and/or normal service. It shall be ensured that metals used comply with tank life requirement specified under paragraph 3.4

b. Stress Corrosion Sensitivity

Metals and alloys, which are susceptible to stress corrosion cracking, shall not be used. Heat‐treating of alloys to obtain non‐stress corrosion sensitive conditions is allowed.

3.6.15. Dissimilar Metals

The selection and use of dissimilar metals shall conform to the requirements of avoiding galvanic corrosion. Wherever it is impracticable to avoid dissimilar metals in direct contact with each other or their exposure to electrolyte, suitable protection shall be provided by coating, or otherwise protecting one or both surfaces.

3.6.16. Stiffness

In the mounting condition as specified in section 3.1.1, the tank shall have Axial natural frequency greater than or equal to 70Hz and Lateral natural frequency greater than 50Hz under maximum filled condition. All these frequencies shall be met with the boundary conditions applied at spacecraft interface locations as specified in figure 3.1.

3.6.17. Interface Loads

Details of all Mounting interface tolerances and the maximum tolerable interface loads (including the maximum displacements on the inlet and outlet tubes) to be provided by the vendor.

3.6.18. Identification and Marking

Each hardware shall have identification markings. The identification marking shall be upon the external visible surface of the equipment by an adhesive bonded aluminium label and its location shall be noted on the interface control drawings for the tank. The label and its fixation shall not degrade tank performance or hinder further operations of the tank with the spacecraft.

MARKING: Following particulars shall be marked.

a. Part name.

b. ISRO Part number as per applicable document 2(a)

c. Specification number.

d. Item serial number.

e. Manufacturer's name.

f. Date of manufacture.

g. Contract number.

Where size limitations make it impractical to mark the complete identifying information on the tank, the information may be attached to the shipping/storage container for the tank. As a minimum, the part number and serial number shall be marked on the tank.



Page 3-11

3.6.19. Traceability

The vendor shall have written procedure for traceability of hardware linked with serial number allotted to the deliverable tanks. The hardware includes basic raw materials like billets, forgings, machined parts, test coupons, and associated elements.

The program to implement the traceability procedures including authorizations for deviations/waivers at different levels of manufacturing stages shall be provided to ISRO.

3.6.20. Workmanship

Standards of workmanship shall meet or exceed the vendor's manufacturing process standards that are documented, controlled and approved.

3.6.21. Reliability

Probability of success

Reliability of operation shall be considered of prime importance in the design and manufacture of the tank. FMECA based on performance and stress analysis is required. Achievable reliability figures are to be provided by the vendor.

To verify the following requirements, an analysis using fracture methods shall be used to assure that the largest crack or any flaw which could escape detection will not grow to failure to cause leakages exceeding the requirement of para 3.3.7 during the intended life of the tank. The size of the potentially assumed crack or any other flaw to be considered shall be defined depending on the inspection methods used.

Moreover, the influence of all the environmental parameters like temperatures, all sources of stress such as applied loads, thermal and chemical effects including residual stresses shall be accounted for.

The inspections and investigations shall cover the base metal, parts after machining, weld materials and heat effected zones due to welding activities.

A numerical approach using the stress/strength method shall make sure that the following reliability figures are achieved.

R ≥ 0.999

Reliability analysis to be a part of deliverables.

3.6.22. Safety

The tanks shall be designed and fabricated with compatible materials in such a manner that all hazards associated with the tank are eliminated or minimized and controlled. The tanks shall be designed to comply with the requirements of applicable document 2(n) complying with Leak Before Burst criteria and a Fracture control plan for the tank, which shall be prepared by the vendor and approved by ISRO.

The tanks shall be designed with positive margins of safety to meet the design and performance requirements of this specification prior to exposure, during exposure and after exposure to the environments specified herein. Environments experienced during tank fabrication, transportation and storage shall be controlled so as to be significantly less severe than the operational environments. Any data required by launch vehicle agency as part of safety submission shall be provided by the vendor even after the delivery of tanks, if required.



Page 3-12

The tank shall be in accordance with the requirements of the MIL‐STD‐1522‐A, section 5, Approach A, of the latest applicable issue (design, analysis, tests, etc.) and the latest applicable Launch Vehicle safety requirement documents of GSLV, ARIANE 5, Proton, Land Launch, Atlas, SEA Launch, Soyuz and Falcon.

3.6.23. Items Subject to Wear out and Degradation

All parts, materials and processes subject to radiation, application stresses or inherent physical processes shall be designed, fabricated, selected and used to attain performance life requirements. The design life of such items (except those meant for one‐time operation in the initial period) shall be at least 18years operation in orbit. Any item with less than the predicted 18 years orbital performance life shall be clearly identified by the vendor and these shall need approval of ISRO.



Page 3-13

Table 3‐1 Propellant Tanks ‐ Expected Load Cycles(After Delivery To ISRO)

Operation

sequence

Operation

description

Mounting /

constraint

External

environment

Internal

environment

Max localized

temp(C)

Max uniform

temp (C)

Max. sustained

ΔP (bar)

Sustained pr

duration (days)

Max. C

yclic ΔP

(bar)

Cyclic pr period

(Days)

No. o

f cycles

Man

rating

condition

Post operation

clean

ing

Post operation

inspection

Inspection

sensitivity

1 Integrate to s/c+

Integration fixture

Air GN2 / Argon

25 25 2 No limit 2 1 2 Yes No Yes N/A*

2 Proof pressure

s/c Air GHe 25 25 SSP No limit SSP No limit 1 to 2 No No Yes N/A

3 Drying s/c Air GN2 70 70 2 1 2 1 1 Yes No Dryness check

N/A

4 GHe leak test

s/c Air GHe 22 22 MEOP 1 ‐ 1 1 to 2 Yes No Yes N/A

5 Hold @MEOP

s/c Air GHe 22 22 MEOP 10 ‐ 10 1 Yes No Visual N/A

6 Transport container Air GN2/GHe 35 35 6 No limit 6 ‐ 1 Yes No No N/A

7 S/c BalancingA

S/c fixture Air GN2/GHe 22 22 6 30 6 ‐ 1 Yes No Visual N/A

8 Vibn test S/c vibn fixture

Air IPA / ETF 22 22 6 30 6 10 1 to 3 Yes No Visual N/A

9 Transport Container Air IPA / ETF 35 35 6 No limit 6 2 ‐ Yes No No N/A

10 Acoustics fixture Air IPA / ETF 35 35 6 15 6 5 1 to 3 Yes No Visual N/A

11 Transport container Air GN2 35 35 6 No limit 6 ‐ ‐ Yes No No N/A



Page 3-14

Operation

sequence

Operation

description

Mounting /

constraint

External

environment

Internal

environment

Max localized

temp(C)

Max uniform

temp (C)

Max. sustained

ΔP (bar)

Sustained pr

duration (days)

Max. C

yclic ΔP

(bar)

Cyclic pr period

(Days)

No. o

f cycles

Man

rating

condition

Post operation

clean

ing

Post operation

inspection

Inspection

sensitivity

12 Drying s/c Air GN2 70 70 <2 1 2 1 1 Yes No Dryness check

N/A

13 Transport container Air GN2 / GHe 35 35 4 30 2 30 1 Yes No No N/A

14 Storage s/c Air GHe 32 32 4 120 2 120 1 Yes No No N/A

15 Thermal cycling

s/c

Hot & cold, vacuum

GN2/GHe

‐7 to +65 non‐

operating

‐7 to +65 non‐

operating

4 10 3 10 10 No No Visual N/A

16 GHe leak test

s/c Air GHe 22 22 MEOP 1 ‐ 1 1 to 2 Yes No No N/A

17 Transport to launch site

Container Air GN2 / GHe 35 35 4 <30 2 < 30 1 Yes No No N/A

18 Storage Container Air GN2 / GHe 25 25 2 <120 2 < 120 1 Yes No No N/A

19 GHe leak test

s/c Air GHe 22 22 MEOP 2 ‐ 2 1 Yes No No N/A

20 Storage container Air GN2 / GHe 25 25 4 60 2 60 1 Yes No No N/A

21 Propellant loading

s/c Air MMH 25 25 MEOP No limit 2 1 1 Yes No Visual N/A



Page 3-15

Operation

sequence

Operation

description

Mounting /

constraint

External

environment

Internal

environment

Max localized

temp(C)

Max uniform

temp (C)

Max. sustained

ΔP (bar)

Sustained pr

duration (days)

Max. C

yclic ΔP

(bar)

Cyclic pr period

(Days)

No. o

f cycles

Man

rating

condition

Post operation

clean

ing

Post operation

inspection

Inspection

sensitivity

22 Pressurise tanks

s/c Air GHe / MMH

22 22 MEOP 90 ‐ < 1 1 Yes No No N/A

23 Launch s/c Air / vacuum

GHe / MMH

25 25 MEOP <1 hr ‐ 0 0 No No No N/A

24 Transfer orbit

s/c Vacuum

GHe / MMH

22 22 MEOP 30 0 0 0 NO No No N/A

25 GSO s/c vacuum

GHe / MMH

50 50 MEOP 6570 0.3 / 0.5 **

1 6570 No No No N/A

* N/A ‐ Not applicable + S/c ‐ Spacecraft SSP Safe Sustenance Pressure

A RPM to be decided ** Vendor to confirm



Page 3-16

Table 3‐2 Random Vibration Levels

Qualification (All Three Orthogonal Axes)

Frequency (Hz) Power Spectral Density

(PSD)g2/Hz grms Duration per axis (sec)

20‐110 110‐700 700‐2000

+6dB/octave 0.09

‐3 dB/octave 11.2 120

Proto‐flight (All Three Orthogonal Axes)


(PSD)g2/Hz grms Duration per axis (sec)

20‐110 110‐700 700‐2000

+6dB/octave 0.09

‐3 dB/octave 11.2 60

Acceptance (All Three Orthogonal Axes)


(PSD) g2/Hz grms Duration per axis (sec)

20‐110 110‐700 700‐2000

+6 dB/Octave 0.04

‐3dB/octave 7.47 60

Note: Notching criteria shall be as in Chapter 9.

Resonance Search:

A low level resonance search shall be conducted prior to performing the test specified. The transmissibility and cross‐talk of the test fixture shall be determined for each of the three orthogonal axes.

Input:

Acceleration amplitude : 0.2g

Frequency : 5 to 2000 Hz

Sweep Rate : 2 oct/min

Before and after the sinusoidal test and before and after the random vibration test a resonance search shall be carried out on the tank in each axis at input level given above. The resonant frequencies before and after each test in each axis shall be identical to great extent. Notching is allowed.



Page 3-17

Table 3‐3 Sine Vibration Levels

Qualification

Longitudinal axis (x axis) Lateral axis (y, z axis)

Frequency (Hz) Amplitude (g) Frequency (Hz) Amplitude (g)

5 ‐ 15 15 ‐ 60 60 – 80 80‐100

11 mm 10 6 3.5

5 ‐ 16 16 ‐ 75 75 ‐100

4.9 mm 5 3.5

Sweep rate: 2 octaves/min; No. of sweeps: 2 (one up and one down)

Proto‐flight



5 ‐ 15 15 ‐ 60 60 – 80 80‐100

11 mm 10 6 3.5

5 ‐ 16 16 ‐ 75 75 ‐100

4.9 mm 5 3.5

Sweep rate: 4 octaves/min; No of sweeps: One

Acceptance


Frequency (Hz) Amplitude (g) Frequency (Hz) Amplitude(g)

5 ‐ 15 15 ‐ 60 60 – 80 80‐100

7.4 mm 6.66 4

2.33

5 ‐ 11 11 ‐ 75 75 ‐100

3.7mm 3.33 2.33

Sweep rate: 4 octaves/min; No of sweeps : one




Page 3-18

Table 3‐4 Shock Test Levels (All Three Axes)

Frequency (Hz) SRS

100 – 600 15 dB / oct

600 – 4000 900 g

4000 – 10000 ‐ 6 dB / oct

Note:

1. The levels given are the qualification level.

2. Two shocks per axis.

3. The shock levels specified are with a Q=10.



Page 4-1

4. QUALITY ASSURANCE PROVISIONS

4.1. General Requirements

The metric standard system shall be used for design, manufacturing and testing.

The parts, materials, processes and workmanship shall be in accordance with manufacturing and process standards that are documented, controlled and approved as specified in the PA plan.

Welding operations shall be performed according to vendor standards approved by the customers.

The personnel involved in the manufacturing, handling and testing shall have adequate qualification.

4.1.1. Test philosophy

Vendor shall clearly bring out the differences between the proposed flight model tank to the already qualified tank, if any, including flight heritage.

Following test philosophy shall be adopted accordingly:

a. New design tank shall be subjected to all qualification tests. Qualification Philosophy: One qualification model tank shall undergo qualification tests as mentioned in paragraph 4.2. All flight model tanks (4 nos.) shall undergo acceptance tests to the requirements of paragraph 4.4.

b. Heritage tank with minor modifications shall be subjected to proto‐flight level tests. Proto‐flight Philosophy: One flight model tank shall undergo Proto‐flight tests as mentioned in paragraph 4.3. Remaining flight model tanks (3 nos.) shall undergo acceptance tests to the requirements of paragraph 4.4.

c. Already qualified heritage tank with no changes shall be subjected to acceptance level tests.

4.1.2. Responsibility for Inspection and Tests

Unless otherwise stated in the statement of work or contract, the vendor is responsible to perform all inspection and tests as specified in paragraphs 4.2, 4.3 and 4.4 of this document.

ISRO reserves the right to witness, or review the tests or documentation of any of the inspections and tests set forth in the specification where such witnessing is deemed necessary to assure that supplies and services conform to prescribed requirements.

4.1.3. Verification of Compliance

Compliance with requirements of section 3 shall be verified by any or combination of the following:

Design, Analysis, Inspection, Test and similarity as indicated in Table 4‐1.

The required inspection, Qualification, Proto‐flight and Acceptance Tests are listed in para 4.2, 4.3 and 4.4. The tank vendor shall provide positive verification from analysis, trials or in‐



Page 4-2

service experience, of the MMH compatibility with the tank to the requirements of paragraph 3.6.7.

4.1.4. Heritage

Vendor shall have adequate experience and space heritage in design and delivery of

side mount type tanks.

Vendor shall provide the flight history of side mount type tanks delivered to other

reputed international space agencies.

4.2. Qualification

The vendor shall offer a qualified tank with flight heritage. The vendor shall propose qualification tests, if any, to meet the qualification sequence shown in paragraph 4.2.2. However, the vendor may also propose qualification of the tank by similarity. For this purpose, data from existing designs and tests of comparable hardware shall be compiled and analyzed to conclusively prove that the proposed tank design complies with the test requirements set forth in paragraph 4.2.1 and the safety requirements set forth in para 3.6.22. All the above documentation shall be submitted to ISRO for review and approval.

4.2.1. Test Requirements

The Qualification by similarity shall consider the tests as in para 4.2.2 and corresponding analysis to demonstrate adequacy of the tank to meet specification. The qualification test matrix is shown in Table 4‐2. This is applicable only if the offered hardware is not proved to be already qualified.

4.2.2. Test Sequence

If already qualified, complete qualification test data shall be provided. This report shall be reviewed by ISRO for acceptance. The test sequence shall be as below.

1. Initial Inspection Para 4.7.1

2. Nondestructive Inspections Para 4.7.2

3. Proof pressure test Para 4.7.3

4. Internal volume Para 4.7.4

5. Physical measurements Para 4.7.5

6. Pressure cycling Para 4.7.6

7. Non‐Destructive Inspections Para 4.7.2

8. External leakage test Para 4.7.7

9. Cleanliness check Para 4.7.8

10. PMD Health check Para 4.7.9

11. Sustained Acceleration Para 4.7.10

12. Random Vibration test Para 4.7.11

13. Sine vibration test Para 4.7.12

14. Shock test Para 4.7.13





Page 4-3


18. Non Destructive Inspection Para 4.7.2

19. Burst pressure test Para 4.7.14

20. Dryness check Para 4.7.15

21. Final Inspection Para 4.7.16

22. Preparation for Data review & End Item Acceptance Para 4.7.17

4.2.3. Failure Criteria

Failure to meet any of the requirements under 4.2.1 shall be cause for rejection of qualification by similarity and will call for demonstration of qualification status by tests.

4.2.4. Qualification Test Report

Following completion of qualification by Test/similarity and analysis, a report shall be prepared detailing the performance obtained at each stage of analysis.

Also, Mathematical model of the propellant tank shall be provided to ISRO for the cases as detailed in section 3.5.2.7.

All reports mentioned in this paragraph shall be reviewed by ISRO for acceptance.

4.3. Proto‐flight Tests

The vendor shall propose Proto‐flight tests if there are with minor modifications with respect to already qualified tank and to meet the qualification sequence shown in paragraph 4.3.1. However, the vendor may also propose qualification of the tank by similarity. For this purpose, data from existing designs and tests of comparable hardware shall be compiled and analyzed to conclusively prove that the proposed tank design complies with the test requirements set forth in paragraph 4.3.1 and the safety requirements set forth in para 3.6.22. All the above documentation shall be submitted to ISRO for review and approval.

4.3.1. Test Requirements

One flight model tank shall undergo Proto‐flight tests as mentioned in paragraph 4.3.2. Remaining flight model tanks shall undergo acceptance tests to the requirements of paragraph 4.4. This is applicable only if the offered hardware has minor modifications with respect to already qualified.


If already qualified, complete qualification test data shall be provided. This report shall be reviewed by ISRO for acceptance. The test sequence shall be as below.











Page 4-4













Failure of test article subjected to proto‐flight tests listed in paragraph 4.3.1 and not meeting the performance requirements shall be cause for rejection of tank.

4.3.4. Proto‐flight Test Report

Following completion of qualification by Proto‐flight tests/similarity and analysis, a report shall be prepared detailing the performance obtained at each stage of analysis.

Also, Mathematical model of the propellant tank shall be provided to ISRO for cases as detailed in section 3.5.2.7.


4.4. Acceptance Tests

4.4.1. Test Sample

Every flight standard tank manufactured against this specification shall be acceptance tested to the requirements of paragraph 4.4.2

4.4.2. Test Requirement

An acceptance test shall be carried out on each flight tank as per the sequence specified in paragraph 4.4.3.


Acceptance testing shall be carried out in the sequence specified as below.

1. Initial inspection Para 4.7.1

2. Non‐Destructive Inspection Para 4.7.2





7. Sine Vibration test Para 4.7.12





Page 4-5

10. Non‐destructive inspection Para 4.7.2



13. Final inspection Para 4.7.16

14. Preparation for data review & End item acceptance Para 4.7.17


Failure of test article subjected to acceptance tests listed in paragraph 4.4.2 and not meeting the performance requirements shall be cause for rejection of flight tank.

4.4.5. Test Limitations

The acceptance inspection and test shall not degrade the tank performance or expose it to test levels or conditions, which could induce a subsequent failure.

4.4.6. Acceptance Test Report

Following completion of acceptance tests, a report shall be prepared by the vendor detailing the performance obtained at each stage of testing. This report shall be reviewed by ISRO for acceptance. Delivery of tank(s) can be done only after the acceptance of test results by ISRO.

4.5. Test Conditions

4.5.1. Environmental Conditions

Unless otherwise specified, the qualification and acceptance tests shall be carried out under closely controlled environment in order to obtain reproducible results, with a reference

temperature of 20C and a relative humidity of 50%, together with tolerances as needed to obtain the desired precision of measurement.

4.5.2. Measurement Tolerances

Unless otherwise stated, the maximum attainable tolerances of test conditions (exclusive of accuracy of instruments) shall be as follows‐

Temperature: ± 1 C Pressure +2%

Relative Humidity (RH) ±5%

Acceleration +10%

Sinusoidal Vibration Amplitude ±10%

Random Vibration:

Random Overall (grms)

Power spectral density (g²/Hz)

±10%

± 1.5 dB for 20‐300 Hz

± 3 dB for 300‐2000 Hz

Force (static tests) + 5%

The maximum allowable tolerances on data required for each tank are

Dry mass ±0.1%



Page 4-6

Internal volume ±500 cm3

Flow rate ± 1%

4.5.3. Calibration

Instruments and test equipment shall be calibrated by the vendor prior to tests. The date of calibration of the instrument or equipment used for the inspection or test shall be indicated in the corresponding report.

4.5.4. Test Reports

Following completion of formal tests, test reports shall be prepared as defined in this document.

4.5.5. Test Data

The following data shall be supplied with each delivered tank. Item (e) can be established by analysis. The mass of the inlet and outlet tube caps and fittings used for testing and which do not form part of tank shall be deducted to obtain the net dry mass of the tank.

a. Acceptance Test Data b. Net internal volume at AMBIENT, MEOP & PROOF c. Residual liquid volume d. Dry mass of tank e. Centre of gravity (CG) of dry tank

4.6. Test Fluids

All test fluids shall be as per applicable documents listed in section 2, Table 2‐1. Test fluids prior to entering the tank, shall be filtered through suitable filters to meet the requirements of cleanliness as per 3.6.7.

4.7. Test Methods

4.7.1. Initial Inspection The tank shall be inspected by vendor Quality Assurance for general compliance with requirements set forth in the inspection and test procedures. General workmanship dimensions and configuration with respect to applicable interface control drawings; identification marking etc. shall be reviewed and approved by ISRO.

4.7.2. Non‐destructive Inspections 4.7.2.1. For Tank and PMD

Propellant tank inspection to be performed according to fracture mechanics analysis requirements. This is applicable to the tank membrane and all load bearing joints.

The vendor shall propose suitable method to verify the integrity of the PMD before and after environmental tests, which shall be reviewed and approved by ISRO.

4.7.2.2. Penetrant Inspection

The entire external surface of each tank shall be inspected in accordance with applicable document 2 (l) listed in Table 2‐1 (Type I, Method A, Sensitivity level 4) with halogen free solutions.



Page 4-7

4.7.2.3. Other Methods

In the event of some part of the tank being inaccessible for the type of inspections specified under 4.7.2.1 and 4.7.2.2 or the sensitivities offered by these methods are inadequate to screen the tank for flaws, the vendor shall propose alternate methods of inspection for review and acceptance by ISRO.

4.7.3. Proof Pressure Test

The tank shall be subjected to an ambient temperature proof pressure test at minimum 1.25 times MEOP as per accepted test procedures. The proof pressure shall be maintained for a minimum of 5 seconds. The tolerance on the test pressure shall be + 2 %. The internal volume of the tank shall be recorded before, during and after pressurization. Volume measurements

shall be normalized to +20C temperature as per paragraph 4.7.4. The tank shall not exhibit permanent set greater than 0.2%. No failure, degradation or evidence of physical damage shall be permitted. The strain measurement is to be included during proof pressure testing of Flight tank deliverables.

4.7.4. Internal Volume

The net internal volume of the tank shall be determined to an accuracy of 500 cm3. The tank

interior volume shall be normalized to +20C.

4.7.5. Physical Parameters of Tanks

a. Mass of empty, dry tank shall be measured to an accuracy of 0.1% or better.

b. Centre of gravity (C.G) of empty, dry tank shall be determined by analysis/ modeling to an accuracy of 0.5 mm or better in X, Y and Z axis.

c. Mass moments of inertia of empty dry tank θx, θy and θz shall be determined by analysis/ modeling to an accuracy of ± 0.5%.

4.7.6. Pressure Cycling

Pressure cycling of tank shall be performed as follows. During qualification the pressure cycling test shall be performed in accordance with MIL‐STD‐1522 A, Approach A.

4.7.6.1. Internal Pressure Cycling

The tank shall be capable of withstanding 12 pressure cycles at proof pressure as specified in paragraph 3.6.3, minimum 50 cycles from ambient to MEOP for Qualification model tank. In case of Proto‐flight tests, the tank shall be capable of withstanding 3 proof pressure cycles as specified in paragraph 3.6.3 and minimum 12 cycles from ambient to MEOP.

4.7.7. External Leakage Test

The dry tank shall be pressurized using Helium gas to MEOP and leakage measured for compliance with paragraph 3.3.7.

4.7.8. Cleanliness

The tank shall be cleanliness checked with Iso‐propyl alcohol as per applicable document 2(h) or de‐ionized, distilled and filtered water as per applicable document 2(j). Samples of the effluent shall be withdrawn from gas port for particle count analysis. The maximum allowable number of particles per 100 ml of effluent fluid when tested in accordance with applicable document 2(m) shall meet cleanliness requirement as indicated in paragraph 3.6.8.



Page 4-8

After cleaning and drying, while the tank is still in a controlled clean room area the tank ports are to be capped off or enclosed using anti‐static nylon material and clean room tape. The tank shall then be bagged in an anti‐static nylon inner bag, which is pre‐cleaned. An outer bag of pre‐cleaned nylon/polythene material shall then be put over this as enclosure. The inner bag shall be evacuated and heat sealed. A non‐shedding type identification tag displaying caution "OPEN IN A CONTAMINATION CONTROLLED AREA ONLY" shall be placed between the inner and outer bags at a convenient location such that it is visible after opening the container. The outer bag shall then be heat‐sealed closed.

After all, cleaning procedures have been completed, the level of chemical contaminants retained in the tank will be such that correct functioning of the tank shall not be impaired or compromised throughout the operation life time.

4.7.9. PMD Health Check

4.7.9.1. Bubble Point Test

Each porous capillary element assembly in the Propellant Management Device (PMD) shall be bubble point tested to assure that gas free propellant delivery will be achieved under all specified operating conditions. The bubble point reject criteria required for this test shall be determined by analysis and incorporated in the appropriate test procedures. The tests shall be accomplished for each of three levels as follows:

Level 1 PMD sub assembly level or individual welded screen detail part level.

Level 2 PMD assembly level prior to installation into the tank assembly.

Level 3 Tank assembly level.

4.7.9.2. Expulsion Efficiency

Where the tank and PMD designs permit fluid expulsion on ground, the expulsion efficiency shall be demonstrated by test.

4.7.10. Sustained Acceleration

The tank shall be filled to maximum liquid loading with simulated propellant, pressurized to MEOP and attached to a fixture in such a manner simulating the actual mounting to the spacecraft structure. Reduction in internal pressure to satisfy the test facility safety requirements, if any, shall be proposed by the vendor with analysis data for review and acceptance by ISRO. The mounting fixture shall be attached to the centrifuge such that the tank experiences an acceleration of

18 g applied in the longitudinal direction. Note under Table 3‐2 & Paragraph 3.5.2.6 is applicable 8g applied in the lateral direction.

The differing acceleration levels imposed by the centrifuge across the tank being tested excluding inlet/outlet ports shall not vary from the specified acceleration by more than +10%. The acceleration specified shall be at the location of the centre of gravity of the loaded tank. The minimum duration of the test shall be one minute for each of two acceleration directions.

Note: This test is only to be made if levels are not covered by sine vibration qualification test.



Page 4-9

4.7.11. Random Vibration Test

The tank shall be mounted simulating the mechanical interface with spacecraft. The test fixture shall be sufficiently stiff to be considered rigid for the particular frequency ranges that are critical for the tank. Verification of the test fixture stiffness is required by analysis or test.

The tank shall be subjected to a random vibration test when filled to the maximum or minimum levels given in paragraph 3.3.10 (whichever is the worst case), using fluids to simulate the propellants and pressurized to 6bar differential using gaseous Helium or Nitrogen.

The qualification, Proto‐flight and acceptance random vibration levels and test directions are given in Table 3‐2 and Notching philosophy is as per Chapter‐9.

Specific relaxation requests, if any, have to be discussed and mutually agreed between the vendor and ISRO.

4.7.12. Sine Vibration Test

The tank shall be filled to the worst case launch propellant load (that load which generates the most critical stresses in the tank structure) with fluids to simulate the propellants and pressurized to 6bar differential with gaseous helium or nitrogen. The tank shall be mounted on a stiff mount (as per paragraph 4.7.11) and vibrated in accordance with levels shown in Table 3‐3 in each of the three orthogonal axes.

For the purpose of controlling vibration applied to the tank, calibrated control accelerometers shall be attached rigidly on the fixture near the tank‐mounting interface and trued with the axis of applied vibration. When more than one control accelerometer is used per axis, an average reading shall be used.

Notching philosophy is as per Chapter‐10.

4.7.13. Shock Tests

The shock levels are given Table 3‐4. The levels specified are the qualification level. The shock levels are for Q = 10. The qualification for shock can be shown through shock tests on a representative tank or through shock tests on critical elements and the rest by an assessment. Two shocks per axis are to be used for the shock test. If qualification model tank is not proposed, compliance shall be provided by analysis or similarity.

4.7.14. Burst Pressure Test

A burst pressure test shall be conducted on the qualification tank to demonstrate minimum 1.5 x MEOP. Burst shall not occur at a pressure ≤ minimum 1.5 x MEOP. If qualification model tank is not proposed, compliance shall be provided by analysis or similarity.

Medium: De‐ionized water.

4.7.15. Dryness Check

The tank interior shall be dried by a suitable method and the dryness established through measurement of dew point of the flush gas nitrogen. The tank dryness requirement is a dew

point of better than ‐60C.

4.7.16. Final Inspection

The tank shall be subjected to a final visual inspection to verify compliance with;



Page 4-10

a. Mechanical interface requirements

b. No handling damages

The log book and records shall be verified to ensure that all specified tests have been gone through and no open ended action items exist. The tank exterior shall be inspected for its cleanliness, and identification marking.

4.7.17. Preparation for Data Review & End Item Acceptance

The tank shall be inspected by vendor quality assurance for conformance with requirements specified. Data taken during the inspections and tests shall be compiled and required analysis and computations shall be performed. All data shall be reviewed and certified by vendor quality assurance. The data shall be submitted to ISRO for review as defined in document. Accepted item shall be appropriately sealed by the vendor’s QA and released for storage or shipment.



Page 4-11

Table 4‐1 Tank Requirement Verification*

Para #

Specification requirement Design Analysis Inspection Test

3.3. Performance Requirements

3.3.1 Tank Pressure conditions

3.3.1.1. Tank Pressure X X

3.3.1.2. Depressurization X X

3.3.1.3. External pressure X X

3.3.2. Working Medium X

3.3.3. Fluid Temperatures X

3.3.4. Propellant Flow Rates X

3.3.5. Expulsion Capability X

3.3.6. Pressure Drop X X

3.3.7. External Leakage X

3.3.8. Step Start Pressure Surge X

3.3.9. Tank Capacity X X X

3.3.10. Propellant Loading X X X

3.3.11. Filling Rate X

3.3.12. Damping Factor X

3.4. Life Requirements

3.4.1. Storage Life X

3.4.2. Operating Life X X

3.4.3. Cycle Life X X

3.4.4. Launch abort X X X X

3.5. Environmental Conditions

3.5.1. Non‐Operating Conditions

3.5.1.1. Relative Humidity X X

3.5.1.2. Barometric Pressure X

3.5.1.3. Temperature X X

3.5.1.4. Transportability X

3.5.2. Operating Conditions

3.5.2.1. Temperature X X

3.5.2.2. Ambient Pressure X X

3.5.2.3. Relative Humidity X

3.5.2.4. Random Vibration X X

3.5.2.5. Sine Vibration X X

3.5.2.6. Acceleration X X

3.5.2.8. Shock X X

3.6. Physical Characteristics

3.6.1. Configuration X X

3.6.2. Mass X X

3.6.3. Proof Pressure/Burst Pressure X X

3.6.4. Pressure Cycles X X

3.6.5. Collapse Pressure X

3.6.6. Connections X X



Page 4-12

Para #

Specification requirement Design Analysis Inspection Test

3.6.7. Compatibility X X

3.6.8. Cleanliness X

3.6.9. Maintainability X

3.6.9.1. Transportation X X

3.6.9.2. Before Integration to Spacecraft X X

3.6.10. After Integration to Spacecraft X X

3.6.11. Interchangeability X X

3.6.12. Surface Finish X

3.6.13. Fungus Resistance X

3.6.14. Corrosion of Materials X

3.6.15. Dissimilar Metals X

3.6.16. Stiffness X X X

3.6.17. Interface Loads X X

3.6.18. Identification and Marking X X

3.6.19. Traceability X X

3.6.20. Workmanship X

3.6.21. Reliability X X

3.6.22. Safety X X

3.6.23. Items Subject to Wear out and Degradation

X

* All qualification tests, wherever relevant, will be verified by similarity/analysis by mutual agreement.



Page 4-13

Table 4‐2 Tank Qualification/Proto‐flight Test Matrix**

#

TEST PARAMETERS

INSPECTION / TEST SEQUENCE

Physical param

eters

Inspection for Dam

age

Workmanship

Proof Pressure

Volume

Physical Conditions

Leakage Rate

Particle Count

PMD Bubble Points

Expulsion Efficiency

Pressure Drops

Sustained

Acceleration

Random Vibration

Sine Vibration

Burst Pressure

Dew

Point

1 Initial Inspection X X X

2 Non‐destructive Inspections X X

3 Proof‐Pressure Test X X

4 Internal Volume X

5 Physical Measurements X X

6 Pressure cycling X X


8 External Leakage Test X

9 Cleanliness check X X

10 PMD Health check X X X X

11 Sustained Acceleration X X

12 Random Vibration Test X X

13 Sine Vibration Test X X





18 Burst Pressure Test X X

19 Dryness check X

20 Final Inspection X X

21 Mounting interface load test X

** All qualification / proto‐flight tests, wherever relevant, will be verified by similarity/analysis by mutual agreement.



Page 4-14

Table 4‐3 Tank Acceptance Test Matrix

Sl No TEST PARAMETERS INSPECTION / TEST SEQUENCE P

hysical Param

eters

Inspection for Dam

ages

Workmanship

Proof Pressure

Volume

Physical Conditions

Leakage Rate

Particle Count

PMD Bubble Points

Expulsion Efficiency

Pressure Drops

Random Vibration

Sine Vibration

Burst Pressure

Dew

Point

Mass, CG & M

I

1 Initial Inspection X X X

2 Proof pressure test X X

3 Internal Volume X


5 Physical measurements X

6 Random vibration test X X

7 Sine vibration test X X





12 Dryness check X

13 Final Inspection X X



Page 5-1

5. DELIVERY OF PROPELLANT TANKS

5.1. Preservation and Packaging

Preservation and packaging of the tank shall be accomplished in a manner, which will ensure protection against mechanical damage, deterioration and contamination. Double bagged units shall be packaged within each shipping container with cellulose cushioning material such as pads, fillers, or other acceptable packaging aids which will centralize and provide protection to tank ports and prevent contact, shifting or rotation of the tank within the container.

The shipping container shall be designed and constructed to provide sufficient strength and protection of the tank during the handling and environmental hazards which may be encountered when transported by common carrier. The inside dimensions of the container shall permit a minimum of 50mm spacing between any surface of the tank and inside surface of the container which shall be filled with cushioning materials.

5.1.1. Retention and cleanliness

The units shall be sealed for retention of cleanliness using pre‐cleaned bags as port closures. The bags shall be retained by pressure sensitive tape, applied over the bags. The tape shall not contact the fitting end.

The sealed tank shall be double bagged in anti‐static polyethylene or polymatic film (50‐micron total thickness minimum) and shall then be packed according to commercial practice in a manner which will provide adequate protection against hazards encountered during shipping, handling and/or storage.

To provide constant cleanliness inside the tank, it must be kept permanent positive pressure during transport (approx. 2 bar)

5.1.2. Identification and Marking

The identification shall be visible when the unit is mounted and its location shall be also noted on ICD/ICS. The identification shall be legible from 0.5m distance with unaided eye. The S/C axis shall be permanently identifiable on the tank.

5.2. Marking for Shipment and Storage

All markings on containers shall be clearly legible from a distance of one meter and may be applied by stencil, rubber stamp, or lacquer over coated gummed labels. Upright position to be clearly marked on the container. Following caution shall be marked on the container:

ITEMS FOR SPACE FLIGHT USE

In addition, all interior packages and exterior shipping containers shall be marked as follows.

a. Part Number

b. Quantity

c. Serial number

d. Contract number

e. Gross weight of packaged tank (Marked on outside of package only)

f. Warning: “open only in clean environment under supervision”

g. Vendor’s name or trade mark



Page 5-2

5.3. Handling, Integration and utilization

5.3.1. Filling and Ground Operations In the normal position (+X‐axis up, the tank “equator welds” in a plane Y‐Z) the tanks shall be capable to be filled to its nominal volume and to be emptied (axis definition shown in Fig 6‐1).

The tank, when loaded with propellant to 85% fill level minimum or 95% maximum will be transported in vertical / horizontal condition connected with the launcher up to the launch place. Possible un‐loading if necessary, down to mission fill level will be performed thereafter in vertical position.

5.3.2. Handling/Handling provision Vendor to specify/provide the following:

Tank handling procedure.

Tank handling and safety precautions, if any, during assembly to the spacecraft.

Handling interface on tanks.

Needed hardware for handling to be supplied.

5.4. List of reviews and deliverables

5.4.1. Milestones for Reviews The proposed milestone for the reviews is as per the Table 5‐1

Table 5‐1 Review Milestones

# Activity Schedule

1 Finalization of specification and award of contract T0

2 Preliminary design review (PDR) / EQSR T0 + 2 months

3 Critical design review (CDR) T0 + 5 months

4 Test readiness review (TRR) T0 + 6 months

5 Delivery Review Board (DRB) clearance T0 + 10 months

Vendor shall intimate ISRO the reviews dates 30 days in prior and submit the respective

review documents to ISRO at least 15 days in prior to the reviews.

5.4.2. List of Documents & Analysis reports

(i) The list of deliverable documents and analysis as part of procurement contract is listed in table 5.2. If any of the document from the following list is not part of standard deliverable, bidder may quote for it separately. If any of the documents cannot be offered, reason for the same shall be provided.

Table 5‐2 List of Deliverables & Analysis reports

# Description Delivery Schedule

1. Propellant Tank Specification finalization and award of contract T0

2. Tank ICD with clear dimensions and interfaces

Mathematical models of the propellant tank, along with reports, as per the section 3.5.2.7

T0 + 1 month



Page 5-3


3. Technical Design Description PDR/EQSR

4. Parts, Materials & Processes List PDR/EQSR

5. Equipment Qualification Status Review (EQSR) PDR/EQSR

6.

CG & MI of the dry tank and at various fill levels for propellants at following conditions as equations

CG & MI of the dry tank.

CG & MI of tank with propellant from fill levels 95% to 5% in normal acceleration condition (in steps of 10%).

CG & MI of tank with propellant from fill levels 35% to 1% in lateral acceleration condition (in steps of 2%).

PDR/EQSR

7. Propellant Tank Design Verification Matrix PDR/EQSR

8. Reliability Prediction of the Propellant Tank PDR/EQSR

9. Manufacturing and Inspection Flow Chart of the Propellant Tank PDR/EQSR

10. Structural Mechanics Qualification Verification Data PDR/EQSR

11. Functional Performance Analysis of Propellant Tank PDR/EQSR

12. Stress & Stability Analysis of the Propellant Tank CDR

13. Fracture Analysis CDR

14. Qualification / QBS (Qualification by Similarity) Report CDR

15. Shock qualification/assessment report CDR

16. Slosh analysis results for various fill fractions covering AMF phase, Station keeping maneuvers at BOL, MOL & EOL cases

CDR

17. Failure Modes, Effects and Criticality Analysis CDR

18. Analytical Prediction for Vibration Acceptance Tests CDR

19. Random Vibration Acceptance Test Procedure TRR

20. Proof Pressure Test Procedure TRR

21. Functional Performance Test Procedure TRR

22. Handling procedure for the propellant tank PDR/EQSR

23. Forging and raw material details including source of supply document

PDR/EQSR

24. Tank as built summary, CIDL TRR

25. Listing of all NCR’s, discussions and dispositions TRR

26. User Manual for the Propellant Tank

DRB

27. Report for: Mass, Volume, C.O.G and Moment of Inertia

28. NDI reports and dispositions

29. Proof Pressure Test Report with strain data

30. Test Report of Vibration Acceptance

31. Functional Acceptance Test Report

32. External Leak & Cleanliness test reports

(ii) Comprehensive Acceptance Data Package – e Copy+ 5 sets of hard Copy



Page 5-4

5.4.3. Hardware Delivery Schedule Hardware delivery schedule shall be as provided bellow in Table 5‐3. LD clause as explained in Schedule C of the RFP shall be applicable in the event of not meeting the hardware delivery dates.

Table 5‐3 Hardware Delivery Schedule

# Activity Schedule


2 First set of Two (2) nos of flight Tanks with

Mounting hardware (struts, flex plates etc. as shown in figure 3.1)

Handling accessories for one tank.

EIDPs*.

T0 + 12 months

3 Second set of Two (2) nos of flight Tanks with

Mounting hardware (struts, flex plates etc. as shown in figure 3.1).

EIDPs*

T0 + 14 months

*EIDPs shall contain test report of all the tests conducted on the tank including NDT, Environmental test, functional test etc. as per applicable sections 4.2.1/4.3.1/4.4.2.



Page 6-1

6. ACCELERATIONS & PROPELLANT FLOW RATES APPLICABLE TO PMD

Following is a summary of Acceleration and propellant flow rates expected of fuel (MMH) tanks during the various phases of the mission. Appropriate design/safety margins shall be considered over these figures for PMD design.

Please ref to Fig. 6‐1 for overall location of tanks on structure and for definition of reference axes.

Figure 6‐1 Tank Configuration and Spacecraft axes definition



Page 6-2

6.1. Launch Phase

The situation at lift off is shown in the figure 6‐2 below. No flow is required from the tanks during this phase.

Figure 6‐2 Launch Phase

6.2. Transfer Orbit 3‐Axis Stabilization

Spacecraft in the Sun‐pointing mode with 1/s rate about pitch axis (+Y axis) or in the earth acquisition mode with 3 ‐ axis control. Three numbers of AOCS thrusters on East/West face and one of roll thruster (anti‐earth face) may be firing simultaneously for attitude control.

Fill fraction 80 – 95%

Acceleration along X axis 1.1 x 10‐3 g

Acceleration along ±Z axis 1.1 x 10‐3 g

Acceleration along Y axis 9.71 x 10‐4 g

Radial Acceleration along Y axis 2.17 x 10‐4 rad/sec2

Fuel flow rate per tank 16.95 g/s

Fuel Consumption per tank 1.5 L

6.3. LAM Burn

The LAM burn situation as shown in the figure 6‐3 below. This maneuver consumes approximately 80% propellants with a 440 N thruster burning continuously. Attitude maintained with 22 N thrusters with as many as six thrusters fired at a time for roll, pitch and yaw attitude control.



Page 6-3

Figure 6‐3 LAM Burn

Initial acceleration along X axis 2.1 x 10‐2 g

Final acceleration along X axis 3.7 x 10‐2 g

Fuel flow rate per tank 80 cc/s

6.4. Station Acquisition‐ East‐West Station Keeping

During station acquisition and station keeping maneuvers the spacecraft attitude is controlled in 3 axis using thrusters. The roll attitude is controlled by either the south face thrusters (acceleration along Z axis) or thrusters on anti‐earth face (acceleration along X axis)

The pitch and yaw attitude is controlled in off‐ modulation mode by the respective thrusters on East/West face. These conditions are depicted as shown in the figure 6‐4 below.

Figure 6‐4 Acquisition & E‐W Station Keeping



Page 6-4

The thruster duty cycle for East/West off‐modulation rate would be approximately 30 to 50 ms off and 150 to 200 ms on and for anti‐earth / south face thrusters typically 150 to 200 ms off and 30 to 50 ms on.

Corrections performed with four East/West face thrusters in the off modulation mode. Station keeping maneuvers to be performed periodically during spacecraft life.

6.5. North‐South Station Keeping

Maneuver with two roll thrusters on the south face of the spacecraft in off modulation, as typically shown in Fig 6‐5.

Attitude maintained with 2 x 22 N thrusters with as many as three from East/West face for pitch / Yaw control. The maneuver to be performed periodically during the spacecraft life of 18 years.

Figure 6‐5 North South Station Keeping

Acceleration along ± Z axis 4.4 X 10‐3 g

Acceleration along ± Y axis 1.0 X 10‐3 g



Duration between successive maneuvers

1 day


Acceleration along X axis 2.2 X 10‐3 g


Fuel Consumption per tank 1 L

Duration between successive maneuvers

1 day



Page 6-5

6.6. On Orbit Mode

Thrusters on East/ West face will be used for momentum dumping with pulse duration of 10 ms, and 10 to 20 pulses per day.

Acceleration along ± Y axis 2.0 x 10‐3 g

6.7. On‐ Orbit Attitude Loss/Recovery

During the attitude loss, the spacecraft may experience attitude rates up to 3° per second in roll/yaw and 10° per second in pitch axis for a maximum period of 2 minutes before attitude recovery procedure starts. After the start of attitude recovery procedure, spacecraft will be in the Sun‐pointing mode with 1° per second rate about roll axis (Y axis) or in the earth acquisition mode with 3‐axis control. Three AOCS thrusters on East/West face and one of the roll thrusters (On the anti‐earth or south face) may be firing simultaneously in pulse mode for the attitude control. Propellant consumption from attitude loss to achieving Sun‐pointing mode would be approximately 1 kg per tank.

Figure 6‐6 On‐Orbit Attitude Loss



Page 6-6

Accelerations during attitude loss and the recovery

Radial acceleration along X‐ axis 3.85 x 10‐3 rad/s2

Radial acceleration along Y‐ axis 2.0 x 10‐3 rad/s2

Radial acceleration along Z‐ axis 2.0 x 10‐3 rad/s2



Fuel consumption per tank 1 kg



Page 7-1

7. MODES, CONDITIONS & ACCELERATIONS LEVELS FOR SPACECRAFT TRANSPORTATION 7.1. Steady state acceleration

Transportation containers and their method of transportation shall be such as to ensure that levels experienced by the tanks are less severe than those specified in the table below.

Condition Acceleration (g)

Air transportation Vertical

Horizontal

1.50

1.00

Ground transportation Vertical

Horizontal

3.00

2.00

Rail transportation

(for Proton and Land launch case‐tanks filled with propellants‐horizontal

transportation)

Vertical

Horizontal

3.00

2.00

Ship transportation

(For sea launch case – tanks filled with propellants‐horizontal transportation)

Horizontal 2.00

Note: The minimum fill fraction for the tanks is 85%

7.2. Sine and Random vibration

Transportation containers shall be designed to ensure that the load levels on tanks are limited to the constant acceleration levels defined in the Table above.

7.3. Shock

The transportation containers shall be designed to ensure that the flight tank contained within is protected from a drop of 100 mm on to concrete.

7.4. Other Environments

The transportation container may experience extremes of temperature, pressure, etc during transportation and shall be designed to withstand the environments as specified in paragraph 3.5.1 of the main part of this document.



Page 8-1

8. TRANSPORTABILITY AFTER INTEGRATION WITH SPACECRAFT

(a) Attitude of tanks Vertical/ Horizontal

(b) Liquid Load:

224 kg max. Simulant Fluid

or

224 kg max. (for 95%) / 201kg ( for 85%) of MMH

(c) Internal Pressure 6 bar differential (with Simulant Fluids)

MEOP (with propellant)

4 bar differential (without propellant / simulant fluid)

(d) Transportation Loads:

(i) Steady acceleration due to ground / air / ship / rail transportation

Vertical:

Horizontal:

3 g

2 g

(ii) Sine and Random vibration levels limited to constant acceleration levels mentioned under (i)



Page 9-1

9. NOTCHING CRITERIA FOR RANDOM VIBRATION TEST

The test input can be reduced in small frequency bands at major resonances to limit COG responses as per Table 9.1.

Table 9‐1 Notching criteria for Random Vibration Test

Output Limitations:

Shell limit : 4.4 g2/Hz ± 3 dB (20 ‐ 2000 Hz)

At COG Qualification / Proto‐flight level aax. C.O.G. = 18 g

alat. C.O.G. = 8 g

At COG Acceptance level aax. C.O.G. = 12 g

alat. C.O.G. = 5.33 g



Page 10-1

10. NOTCHING CRITERIA FOR SINE VIBRATION TEST

The input levels can be reduced if required in small frequency bands covering major resonances to limit COG response as per table 10‐1

Table 10‐1 Notching criteria for Sine Vibration Test

Output Limitations:


alat. C.O.G. = 8 g


alat. C.O.G. = 5.33 g



Page ‐ 11‐1

11. TABLE OF ABBREVIATIONS

ABM Apogee Boost Maneuver

AKM Apogee Kick Maneuver

AOCS Attitude and Orbit Control System

ARO After Receipt of Order

ARP Aerospace Recommended Practice

BOL Beginning of Life

CDR Critical Design Review

COG Centre of Gravity

dB Decibel

DRB Delivery Review Board

EOL End of Life

EIDP End Item Data Package

FMECA Failure Modes Effects and Criticality Analysis

GHe Gaseous Helium

GN2 Gaseous Nitrogen

GSO Geo Stationary Orbit

ICD Interface Control Document/Drawing

IPA Iso‐Propyl Alcohol

ISRO Indian Space Research Organisation

LAM Liquid Apogee Motor

MEOP Maximum Expected Operating Pressure

MIL‐STD Military Standard

MMH Mono Methyl Hydrazine

MOL Middle of Life

NAS National Aerospace Standard

NVR Non Volatile Residue

PDR Preliminary Design Review

PKM Perigee Kick Maneuver

PMD Propellant Management Device

QBS Qualification by Similarity

SCC Standard Cubic Centimeter

SKM Station Keeping Maneuver

SRS Shock Response Spectrum

SS Stainless Steel

TRB Test Article Review Board



Page ‐ 12‐1

12. DEFINITIONS

The definitions of some key parameters used in the document are as follows.

MEOP

The Maximum Expected Operating Pressure (MEOP) is the maximum pressure at which the system or component is actually operated in a particular application.

MEOP shall include effects like temperature, transient peaks, vehicle acceleration, relief valve tolerances, etc.

Tank Net Volume

The tank net volume is the internal fluid usable volume, i.e. internal volume; the tank shell minus the volume of the PMD, internal tubing, etc. in unpressurised condition.

Pressures

Unless explicitly specified, all the pressure values mentioned in this document are differential internal pressure values.

Safe Sustenance Pressure

The maximum pressure at which a component can continuously operate based on fracture strength, allowable stress values and functional capabilities.



Page ‐ 13‐1

13. PROPELLANT TANK ICD

TO BE PROVIDED BY VENDOR

Figure 13‐1: Propellant Tank ICD



Page ‐ 13‐2

Figure 13‐2 Typical Tank dimensions and Interface details.

ISRO



SCHEDULE ‐C

CONTRACTUAL TERMS AND CONDITIONS


SCHEDULE–C – CONTRACTUAL TERMS AND CONDITIONS Issue‐0 February 2018

Page C‐1

Contents

1. INVITATION FOR BIDS .................................................................................................................... 2

2. BID SUBMISSION ............................................................................................................................ 2

3. REJECTION OF BID .......................................................................................................................... 2

4. LOWEST OFFER ............................................................................................................................... 2

5. TRANSPARENCY ............................................................................................................................. 2

6. PARTICIPATION OF INDIAN AGENTS .............................................................................................. 2

7. AGENCY COMMISSION ................................................................................................................... 2

8. PAYMENT TERMS ........................................................................................................................... 3

9. BANK CHARGES .............................................................................................................................. 3

10. EARNEST MONEY DEPOSIT (EMD) / BID SECURITY ..................................................................... 3

11. SECURITY DEPOSIT ...................................................................................................................... 4

12. TAXES AND DUTIES ..................................................................................................................... 4

13. PERFORMANCE BANK GUARANTEE ............................................................................................ 4

14. VENDOR'S DEFAULT LIABILITY .................................................................................................... 5

15. REPLACEMENT ............................................................................................................................ 6

16. SUBLETTING CONTRACT.............................................................................................................. 6

17. TERMS OF CANCELLATION .......................................................................................................... 6

18. LIQUIDATED DAMAGES ............................................................................................................... 7

19. APPROVALS, GOVERNMENT & REGULATORY CLEARANCES ....................................................... 7

20. FORCE MAJEURE ......................................................................................................................... 7

21. COUNTERTERMS AND CONDITIONS OF BIDDER /VENDOR ........................................................ 8

22. ARBITRATION .............................................................................................................................. 8

23. APPLICABLE LAW ......................................................................................................................... 9

24. PLACE OF DELIVERY: .................................................................................................................... 9



Page C‐2

1. INVITATION FOR BIDS

1.1 Vendors shall submit a Firm and Fixed Price quotation (inclusive of all taxes and duties) for

propellant tanks.

2. BID SUBMISSION

2.1 The proposals shall be submitted in two parts: i) Techno‐commercial bid and ii) Price bid.

2.2 The bidder shall, at their own cost, submit the bid in response to this RFP and also participate

in any negotiations that may be called for. No obligations, financially or otherwise, in this

regard shall be acceptable to ISAC.

3. REJECTION OF BID

3.1 ISAC reserves the right to accept or reject any offer in part or full without assigning any reason

thereof.

3.2 Canvassing by the Bidder in any form, unsolicited letter and post‐tender correction may

invoke summary rejection of Bids. Conditional Tenders will be rejected.

4. LOWEST OFFER

4.1 The Lowest offer (L‐1) shall be decided based on the aggregate value of all deliverables and

services put together for which quotation have been called for, wherever necessary.

4.2 In case of advance payment, the bids are evaluated by suitably loading interest component

@ 11% per annum on the advance amount (or) applicable rate declared by the Government

of India which are in force at the time of advancing.

5. TRANSPARENCY

5.1 Vendors are free to clarify with ISAC for the Bidding conditions, Process and/or Rejection of

bids etc., during the procurement process.

6. PARTICIPATION OF INDIAN AGENTS

6.1 Either the Indian Agent on behalf of Principal/OEM or Principal/OEM itself can bid. But both

cannot bid simultaneously. If an Agent submit bid on behalf of Principal/OEM, the same Agent

shall not submit a bid on behalf of another Principal/OEM.

7. AGENCY COMMISSION

7.1 The amount of Commission included in the price and payable to the Indian Agent of the

Vendor shall be paid directly to the Indian Agent[s] by ISAC in equivalent Indian Rupees on



Page C‐3

the basis of an Invoice from the Indian Agent by applying T.T. buying rate of exchange ruling

on the date of placement of the Purchase Order/Contract and within 30 days from the date

of receipt and acceptance of the hardware and services.

7.2 The Vendor shall Invoice only for the net amount payable to him, after deducting the amount

of Agency Commission included in the Invoice which would be paid to the Indian Agent[s]

directly by ISAC. However, the Vendor[s] quote should separately reflect the amount of

Commission payable to his Indian Agent.

7.3 As per the Compulsory Enlistment Scheme of the Department of Expenditure, Ministry of

Finance, it is compulsory for Indian Agents who desired to quote directly on behalf of their

Foreign Principals to get themselves enlisted with the Central Purchase Organization

[Eg: DGS&D].

8. PAYMENT TERMS

8.1 ISAC payment terms are; payment within 30 days after the completion of the delivery and

acceptance by ISAC.

9. BANK CHARGES

9.1 While ISAC shall bear the Bank Charges payable within India, the vendor shall bear the Bank

Charges payable outside India.

10. EARNEST MONEY DEPOSIT (EMD) / BID SECURITY

10.1 The Techno‐commercial Bid should be accompanied with an Earnest Money Deposit

(Refundable) of Rs. 5.00 Lakhs [Indian Rupees Five Lakhs Only] in a single instalment through

Demand Draft/Banker’s Cheque/Fixed Deposit Receipts or Bank Guarantee from any of the

Nationalized/Scheduled Banks executed on non‐judicial stamp paper of appropriate value. In

case of bank guarantee, it should be valid for a period of 45 days beyond the final tender

validity date. EMD in the form of Demand Draft/Bank Draft should be drawn in favour of

Accounts Officer, ISAC, Bengaluru. EMD in the form of Bank Guarantee shall be submitted

while submitting the proposal.

10.2 The Earnest Money Deposit in respect of the Bidders who do not qualify the Technical Bid

[First Stage] / Financial Bid [Second Competitive Stage] shall be returned to them without any

interest. However, the EMD in respect of the successful Bidder shall be adjusted towards the

Security Deposit.

10.3 EMD of a Bidder shall be forfeited if the Bidder withdraws or amends his tender or deviates

from the tender in any respect within the period of validity of the tender. Failure to furnish

security deposit/performance bond by the successful Bidder within the specified period shall

also result in forfeiture of EMD.



Page C‐4

10.4 Foreign vendors, registered vendors or vendors who have already applied for renewal of

registration, Central PSUs/PSEs/Autonomous Bodies, Micro and Small Enterprises, National

Small Industries Corporation, etc., are exempted from the payment of EMD.

10.5 Any tender not accompanied with EMD shall be treated as invalid tender and rejected.

10.6 Bidders seeking exemption from payment of EMD, under the above mentioned Category shall

submit necessary proof for claiming such exemption.

10.7 EMD shall be refunded to all the unsuccessful Bidders within thirty days after entering into

Contract with successful Bidder. EMD shall be refunded to the successful Bidder/Vendor after

receipt of the Security Deposit or may be adjusted against the Security Deposit. EMD shall be

refunded to all the participants in cases where the tender is cancelled or withdrawn by ISAC,

within thirty days from the date of such cancellation or withdrawal.

11. SECURITY DEPOSIT

11.1 The Successful vendor shall execute Security Deposit for 10% of the value of the Purchase

Order/Contract towards satisfactory execution of the Purchase Order/Contract. The Security

Deposit shall be executed through Demand Draft/Bankers Cheque/Fixed Deposit Receipts or

Bank Guarantee issued by a Nationalized Bank/Scheduled Bank valid till the Purchase

Order/Contract is completely executed.

11.2 In case the vendor fails to furnish the Security Deposit within 20 days after the receipt of PO

or on signing of the Contract or any extension thereof, the Purchase Order/ Contract shall be

cancelled or terminated. The Earnest Money Deposit if any executed shall be forfeited and

appropriate penal action shall be initiated.

11.3 The Security Deposit will not carry any interest and shall be returned after completion of all

the obligations of the Contract.

12. TAXES AND DUTIES

12.1 Applicable taxes and duties shall be specified in the bid. The percentage of Taxes, Duties, etc.,

where legally leviable and intended to be claimed shall be calculated and indicated.

13. PERFORMANCE BANK GUARANTEE

13.1 The Vendor shall guarantee for satisfactory performance of the delivered product and

services as per the terms and conditions of the Purchase Order/Contract. Towards this, the

Vendor shall furnish Performance Bank Guarantee (PBG) for 10% of the deliverables on a non‐

judicial stamp paper of Rs.200/‐ issued by Nationalized/Scheduled Bank which shall cover the

following:

i. The satisfactory performance of product covered under this Purchase Order, under the

conditions and for the services specified.

ii. Guarantee the product as represented and specified.



Page C‐5

iii. Guarantees against any and all defects in material and workmanship. Upon written

notice by ISAC, undertakes to replace or fully remedy free of expenses to ISAC such

defects as developed under normal operation of the propellant tanks for a period of 12

months from the date of receipt and acceptance by ISAC or until the launch of the

satellite where it is integrated, whichever is later.

iv. The PBG shall be issued preferably by State Bank of India, ISRO Branch, Airport Road,

Bengaluru – 560 017, India or by an internationally reputed bank or any bank approved

by Reserve Bank of India and made payable to ISAC for due performance and completion

of contract in all respects. PBG shall be returned to the Vendor after successful

completion of all contractual obligations without any interest.

14. VENDOR'S DEFAULT LIABILITY

14.1 ISAC may upon written notice of default to the Vendor, may terminate the Contract by giving

30 days prior notice in whole or in part in circumstances detailed hereunder:

i. If in the judgment of ISAC, the Vendor fails to fulfil their contractual obligations within

the time specified in the Contract/agreement or within the period for which extension

has been granted by ISAC to the Vendor.

ii. If in the judgment of ISAC, the Vendor fails to comply with any of the other provisions

of this Contract.

14.2 In the event ISAC terminates the Contract in whole or in part as provided in the Contract, ISAC

reserves the right to get the services, upon such terms and in such a manner as ISAC may

deem appropriate, services similar to that terminated and the Vendor shall be liable to ISAC

for any additional costs for such similar services and/or for liquidated damages for delay as

defined in the Contract until such reasonable time as may be required for the final Service.

14.3 If this Contract is terminated as provided in the Contract, ISAC in addition to any other rights

provided in this Clause, may require the Vendor to transfer title and provide service under

any of the following clauses in the manner and as directed by ISAC:

i. Any completed service.

ii. Such partially completed services, information and Contract rights as the Vendor has

specifically acquired for the performance of the Contract was terminated. ISAC shall pay

to the Vendor the Contract price for the completed services provided to and accepted,

by ISAC.

14.4 In the event ISAC does not terminate the Contract as provided above, the Vendor shall

continue the performance of the Contract in which case he shall be liable to ISAC for

liquidated damages as set out in the Contract until the services are accepted.



Page C‐6

15. REPLACEMENT

15.1 If the delivered hardware or any portion thereof, is damaged or lost during the transit, the

vendor shall give notice to ISAC setting forth particulars of such hardware damaged or lost

during transit. The replacement of such hardware shall be effected by the vendor within a

reasonable time to avoid unnecessary delay in the intended usage of the hardware. The

payment for the replacement of hardware shall be in accordance with the responsibilities as

per INCOTERMS 2010.

15.2 In case of damage or malfunctioning of any supplied item during assembly, integration and

testing process or during launch base operations due to the vendor, replacements shall be

made by the Vendor at no additional cost.

16. SUBLETTING CONTRACT

16.1 The Contract shall not be sublet, transferred or assigned to any other firm/agencies/person,

etc., without the prior written permission of ISAC. In case of violation of this clause, the

Service Provider/Vendor shall be solely responsible for any legal action besides termination

of Contract.

17. TERMS OF CANCELLATION

17.1 Under the normal circumstances, Termination/Short Closing of the PO/Contract is not

foreseen. However, in case of repeated non‐performance of the PO/Contract, ISAC reserves

the right to terminate the Contract in whole or in part by giving 30 days prior notice under

the following circumstances

i. For repeated non‐performance in the execution of P.O/Contract.

ii. If the Vendor fails to deliver the final Product within the stipulated delivery

schedule or any extension thereof, granted by the Purchaser.

iii. If the final Product does not pass inspection and quality requirements of

P.O/Contract.

iv. If the Vendor fails to perform any other obligations under P.O/Contract.

v. If the Vendor becomes bankrupt or otherwise insolvent.

vi. Owing to deficiency of service, breach of Contract.

vii. For inefficiency, indiscipline, irregularity, insincerity, indifference in work,

disobedience, doubtful credentials/integrity, etc., at any point of time during the

Contract period.

viii. To terminate the PO/Contract at any time by giving 30 days’ prior notice.



Page C‐7

18. LIQUIDATED DAMAGES

18.1 If the vendor fails to deliver the hardware as per the delivery schedule specified in this RFP,

ISAC shall recover from the vendors Liquidated Damages a sum of one‐half of one percent

(0.5%) on the cost of undelivered part for delay of each calendar week or part of the calendar

week. The total liquidated damages shall not exceed 10% of the relevant cost.

18.2 The hardware will be deemed to have been delivered only when all its relevant deliverables

are delivered in full.

18.3 Liquidated Damages (LD) is proposed to be levied after contracted delivery period. However,

this shall exclude any Force Majeure reasons or valid technical reasons beyond the control of

the Vendor. The Vendor may foresee any of the Force Majeure / technical reasons and submit

the offer with due explanations to remove any uncertainty in the future.

18.4 In case of delay in delivery of the hardware beyond the delivery date stipulated in the

Purchase Order/Contract or any extension thereof, such hardware shall be received under

protest. The hardware shall be accepted without prejudice to the terms and conditions of the

Purchase Order/Contract.

19. APPROVALS, GOVERNMENT & REGULATORY CLEARANCES

19.1 It shall be the responsibility of the vendor to obtain all the necessary clearances from its

government for submission of technical data related to the proposal and for supplying the

propellant tanks. The vendor shall submit a declaration of acceptance in this regard along

with the bid and shall obtain the necessary governmental clearances before signing of the

contract in the event of being chosen as the successful bidder.

19.2 Any other contractual / statutory requirements either governmental or procedural issues

which influence the contract implementation by the vendor may be explicitly brought out.

The vendor shall obtain all the necessary governmental licenses that are required to provide

for supply of the tanks. In case any undertaking / statement is required for submitting the bid,

ISAC shall provide the same.

19.3 All costs pertaining to custom clearance and other incidentals shall be borne by the Vendor

while transporting subsystems, components, etc., to India. ISAC will provide end user

certificate and all possible document support in obtaining custom clearance.

20. FORCE MAJEURE

20.1 Neither party shall bear responsibility complete or partial non‐performance of any of his

obligations [except for failure to pay any sum which has become due on account of receipt of

goods under the provisions of the Purchase Order/Contract] if the non‐performance results

from such force majeure circumstances such as, but not restricted to, flood, fire, earthquake,

civil commotion, sabotage, explosion, epidemic, quarantine restriction, strike, lock out,



Page C‐8

freight embargo, acts of the Government either in its sovereign or its contractual capacity,

hostility, acts of public enemy and other acts of God as well as war or revolution, military

operation, blockade, acts or actions of state authorities or any other circumstances beyond

the control of the parties that have arisen after the conclusion of Purchase Order/Contract.

In such circumstances, the time stipulated for the performance of an obligation under the

Purchase Order/Contract may be proportionately extended.

20.2 The party for whom it has become impossible to meet the obligation under this contract due

to force majeure condition will notify the other party in writing not later than 21 days from

the date of commencement of unforeseeable event. Unless agreed by both the parties, in

writing, the Vendor shall continue to perform his obligations under the Purchase

Order/Contract as far as is practical and shall seek all reasonable alternative means for

performance not prevented by the force majeure event.

20.3 Any Certificate issued by the Chamber of Commerce or any other competent authority or

organization of the respective country shall be sufficient proof of commencement and

cessation of the above circumstances. In case of failure to carryout complete or partial

performance of an obligation for more than 60 days, either party shall reserve the right to

terminate the Contract totally or partially. A prior written notice of 30 days to the other party

will be given informing of the intention to terminate without any liability.

21. COUNTERTERMS AND CONDITIONS OF BIDDER /VENDOR

21.1 Where counter terms and conditions / printed or cyclostyled conditions have been offered by

the Bidder, the same shall not be deemed to have been accepted by ISAC, unless specific

written acceptance thereof is obtained.

22. ARBITRATION

22.1 In the event of any dispute/s, difference/s or claim/s arising out of or relating to the

interpretation and application of the Contract, such dispute/s or difference/s or claim/s shall

be settled amicably by mutual consultations of the good Offices of the respective Parties and

recognizing their mutual interests attempt to reach a solution satisfactory to both the parties.

If such a resolution is not possible, within 30 days from the date of receipt of written notice

of the existence of such dispute/s, then the unresolved dispute/s or difference/s or claim/s

shall be referred to the Sole Arbitrator appointed by President of the International Chamber

of Commerce in accordance with the rules and procedures of Arbitration and Conciliation Act

1996 together with amendments thereto or any modification thereof. The expenses for the

Arbitration shall be paid as may be determined by the Arbitrator. The considered and written

decision of the Arbitrator shall be final and binding between the Parties. The Seat for

Arbitration shall be “Bengaluru” and the Arbitration proceedings shall be conducted in

“English” Language only.



Page C‐9

22.2 Work under the contract shall be continued by the Contractor during the pendency of

Arbitration proceedings, without prejudice to a final adjustment in accordance with the

decision of the Arbitrator unless otherwise directed in writing by the Purchaser or unless the

matter is such that the work cannot be possibly continued until the decision (whether final or

interim) of the Arbitrator is obtained.

23. APPLICABLE LAW

23.1 The vendor shall be interpreted, construed and governed by the Laws of India.

24. PLACE OF DELIVERY:

Hardware shall be delivered to ISRO at its campus at the address mentioned below.

STORES OFFICER,

ISRO SATELLITE CENTRE,

VIMANAPURA POST,

HAL AIRPORT ROAD,

BENGALURU 560017,

INDIA.

Page 1 of 50

COMPLIANCE MATRIX FORMAT

TECHNICAL ANNEXURE ‐1

Page 2 of 50

Section Title

Compliance

(C)

Non‐

compliance

(NC)

Partial

compliant

(PC)

1.0

SCOPE

This specification establishes the requirements for the design, performance, fabrication and test of propellant storage tanks for use

in the propulsion system of ISRO telecommunication spacecraft. The propellant tanks utilize surface tension device and helium

pressurant to expel vapour‐free Fuel (MMH) upon demand. The propellant tank together with the Propellant Management device

(PMD) will be referred hereafter as the “Tank”.

The tank should be total communication and single compartment type with the PMD capable of acquiring propellant anywhere from

the tank and supplying gas free propellant to the engines.

2.0

APPLICABLE DOCUMENTS

The following documents in their latest revision form part of this specification. In the event of conflict between this specification and

documents referred here, this conflict shall be notified to ISRO.

Table 2‐1 Applicable Documents

2(a) Propellant tank and interface drawings and CAD models To be provided by Vendor in

*.dwg/*.dxf and *.iges/*.stp formats

2(b) Intentionally left blank

2(c) Monomethyl Hydrazine (MMH) MIL‐P‐27404

2(d) Titanium alloy (6Al‐4V) MIL‐T‐9047

2(e) Argon MIL‐A‐18455

2(f) Propellant pressurizing agent (Nitrogen) MIL‐P‐27401

2(g) Propellant pressurizing agent (Helium) MIL‐P‐27407

2(h) Iso‐Propyl Alcohol TT‐I‐735

2(i) Intentionally left blank

2(j) De‐ionized water JSC‐SPEC‐C‐20C

2(k) Penetrant Inspection ASTM‐E‐1417

2(l) Radiographic Inspection & UT inspection MIL‐STD‐453 / NAS‐1514

ASTM‐E‐2375

2(m) Procedure for determining surface contamination levels ARP‐598

2(n) Safety Standards NSS/HP 1740.1/ MIL‐ 1522

2(o) Applicable Launch vehicle safety documents GSLV, Proton, Atlas, Land launch, Sea Launch,

Ariane‐5, Soyuz , Falcon

Page 3 of 50

Section Title

Compliance

(C)

Non‐

compliance

(NC)

Partial

compliant

(PC)

3.0 REQUIREMENTS

3.1 Interfaces

3.1.1

Mechanical Interfaces

The Tank shall be of side mounting support as Interface to Spacecraft structure fixation.

The Tank interface shall be as given below in the sketch and the associated table gives the detail of support conditions.

The Support conditions are put in the following table

Figure 3‐1: Typical Tank dimensions and Interface details.

Tank Interfaces Interface Locations

Support Conditions 1 2 3

Refer Figs.3.1

Spacecraft Interface 1 is side mounting type. It has to primarily bear the axial loads and laterally flexing.

Spacecraft Interfaces 2 and 3 are with flexure type interface. This interface has to bear primarily lateral loads and axially flexing.

Page 4 of 50

Section Title

Compliance

(C)

Non‐

compliance

(NC)

Partial

compliant

(PC)

Vendor shall provide mounting interfaces with all dimensional details along with the offer. Vendor shall also provide the ICD of tanks

including the details of side mount location, struts/interface joints with spacecraft with overall clear dimensions.

The height of tank shall be fixed to meet volume requirements according to para 3.3.9 & 3.3.10. Maximum height (H) of the dry tank

shall be within 1500mm to 1600mm including all projections and as per figure 3‐1. Free gas/propellant tube lengths in figure 3.1 LI

& L2 shall be from 50mm to 75mm beyond the flex plate and its end fittings.

The overall tank diameter shall never exceed the interface diameter (D) of 540 ± 10 mm on any point, at any time and under any

conditions seen by the tank integrated in the satellite (pressure, temperature, vibrations, etc.)

3.1.2 Electrical Interfaces

Grounding shall be possible by connecting the tank to the S/C structure via bonding straps.

3.1.3

Accelerometer provision

The accelerometers will be mounted on the tank for ground tests and will be flown. The accelerometers will be bonded with Hysol EA

9309 or Hysol EA 9392 or Araldite 2014 compound. The external interfaces shall be compatible with the above said adhesive.

3.2

Component Function

The propellant tanks described herein (henceforth referred to as tanks) shall provide vapour free Fuel (MMH) to the Liquid Apogee

Motor (LAM) and Attitude and Orbit Control System Thrusters (AOCS) upon demand commencing from launch vehicle separation to

the end of life of spacecraft.

Two tanks will be used per spacecraft as shown in Fig. 6‐1.

Also described herein are the design requirements and test requirements associated with a qualification tank and the requirements

are shown in Para 4.2

3.3

3.3.1

Performance Requirements

Tank Pressure Conditions

3.3.1.1

Tank pressure conditions

The tank shall be designed to function at the pressures & temperatures specified below during/after exposure to environment as

specified in para 3.5. The maximum expected operating pressure (MEOP) is 16.3 bar differential internal pressure.

Phase Pressure

(a) Ground handling and pre‐launch Ambient to MEOP (16.3bar)

(b) Launch base Upto MEOP(16.3bar)

(c) Launch at lift‐off Upto MEOP(16.3bar)

(d) Transfer orbits and Apogee burn MEOP(16.3bar)

Page 5 of 50

Section Title

Compliance

(C)

Non‐

compliance

(NC)

Partial

compliant

(PC)

Propellant flow is required during events (d) and (e).

* Non nominal case of operation

Pressure and temperature requirements for nominal operational phases:

Phase Fill factor Pressure at 20°C Temperature range

0 System vibration test Up to 95% 6 bar differential

internal

Ambient

I Propellant loading, transport

from filling area to launcher

Max. 95%

Min. 85%(2)

upto MEOP

20 to 26°C

II Launch preparation, launch

until separation

Up to 95%

Min. 85%(2)

upto MEOP

15 to 26°C

III In‐flight pressurization(5) Up to 95 % upto MEOP 15 to 26°C

IV Transfer (AKM/PKM) phase(5) Up to 95% to end

LAM

16.3 bar regulated 10 to 26°C

V On‐station Phase(5) End of LAM to Hold

up volume (3)

16.3 to 9.0(1) bar in

blow‐down

10 to 35°C (BOL)

10 to 50°C (EOL)

Note:

1) Minimum pressure at end of life including non‐nominal cases.

2) Contractor shall note the fill fractions could be 85% ‐ 95% for the horizontal transportation of the

spacecraft. Subject to confirmation by the Contractor through analysis for minimum fill fraction for

horizontal transportation.

3) Contractor shall specify the unusable propellant volume in the tank.

4) All pressure values are internal differential pressure

5) Safe sustenance pressure (at least 1.25 times MEOP)

(e) Geo synchronous orbit MEOP(16.3bar) + 1 bar *

3.3.1.2 Depressurization

The unit shall be able to withstand an external depressurization from atmospheric pressure to 1x10‐10 Torr.

3.3.1.3 External pressure

The unit shall be able to withstand the free space vacuum of 10‐10 Torr.

3.3.2 Working Medium

Page 6 of 50

Section Title

Compliance

(C)

Non‐

compliance

(NC)

Partial

compliant

(PC)

a) Gaseous helium in accordance with applicable document 2(g).

b) MMH in accordance with applicable document 2(c)

3.3.3

Fluid Temperatures

a) Helium temperature will be between ‐40C and +65 C b) Propellant temperature will be between 0C and +50 C.

3.3.4

Propellant Flow Rates

Propellant flow rates have to be guaranteed with respect to

a) Flow rate demand

b) No Helium/Vapors ingestion in propellant at any time, as per the mission constraints given in Chapter 6

Propellant flow rates are detailed in Chapter 6.

3.3.5

Expulsion Capability

Gas free propellant delivery shall be provided under all conditions of operations indicated in Chapter 6.

Maximum unusable residual volume shall be specified by the Contractor.

3.3.6 Pressure Drop

The tank pressure drop under any flow specified in Chapter 6 shall not exceed 0.2 bar.

3.3.7

External Leakage

With the tank pressurized to MEOP with gaseous helium, the external leak rate shall not exceed 1x10‐6 scc/s of helium. There shall be

no propellant leakage from the tank at any pressure up to and including the burst pressure.

3.3.8

Step Start Pressure Surge

At system start‐up the tank (at MEOP) shall be capable of discharging into a line volume of 2.0 L maximum, initially at 0 bar at the rate

of 690 cm3/sec per tank.

3.3.9

Tank Capacity

The total nominal volume excluding PMD shall be 265 L in unpressurised at ambient conditions. Contractor may also provide the

corresponding volume @ MEOP for information.

3.3.10

Propellant Loading

Tank design for the nominal case shall be such that it can accommodate the following propellant fill quantities under unpressurised

condition.

a) MMH in accordance with applicable document 2(c)

Maximum: 95% of propellant tank volume (based on density values at 20°C of 875 Kg/m3)

3.3.11 Filling Rate

Page 7 of 50

Section Title

Compliance

(C)

Non‐

compliance

(NC)

Partial

compliant

(PC)

In the vertical attitude (outlet port down) the tanks shall be capable of being filled with either MMH [as per applicable doc 2(c)], Iso‐

Propyl alcohol [as per applicable document 2(h)] or de‐ionized water [as per applicable doc 2(j)] for dynamic testing as per applicable

doc 2(i) at any rate up to 4.8 L per minute or as per filling procedure to be specified by Contractor. The tank ullage pressure shall be

in the range 2 bar to 10 bar absolute during the filling operation. The tank shall be designed for gravity draining to residual volume of

less than 0.2 L when outlet ports are in a vertical attitude. It shall be a design objective to minimize the residuals.

3.3.12

Slosh Analysis

The tank design shall be such that a damping factor (applicable to propellant sloshing movement) ≥0.1% shall be assured during ABM

and SKM after proper settlement.

Slosh analysis results for various fill fractions covering AMF phase, Station keeping maneuvers at BOL, MOL & EOL cases shall be

provided.

3.4 Life Requirements

There shall be no degradation of tank performance resulting from any or all of the following.

3.4.1

Storage Life

The tanks shall be capable of being stored for a minimum of 10 years without, maintenance or re‐verification / re‐testing at the end

of storage.

The storage temperature shall be as specified in para 3.5.1.3 with relative humidity up to 100%.

3.4.2 On orbit Operating Life

Not less than 18 Years following exposure to propellant liquid/vapour.

3.4.3 Cycle Life

After acceptance testing, the tanks shall withstand the life cycle as per Table 3‐1.

3.4.4

Launch abort

In the event of launch abort either or both the propellant will be drained and refilled as required. Contractor may provide the

procedure to be followed in case of a launch abort for draining and flushing (with recommended fluids) for MMH.

3.5 Environmental Conditions

3.5.1 Non‐Operating Conditions

The tank shall perform within specification after exposure to the following. (No propellant fill condition)

3.5.1.1

Relative Humidity

Relative humidity of up to 100%. Condensation can take place in the form of water and frost and should not affect the tank

performance.

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3.5.1.2 Barometric Pressure

Atmospheric pressure between sea level and @ altitude of 12200m.

3.5.1.3 Temperature

Temperature range between ‐7C and + 65 C.

3.5.1.4 Transportability

The tanks shall be compatible with preflight environments as defined in Chapter 7 & 8 of this document.

3.5.2

Operating Conditions

The tank shall perform within specification during exposure to the following after having been filled with working medium as per

paragraph 3.3.2 and pressurized as per paragraph 3.3.1.

3.5.2.1

Temperature

a) First two years: 10 C to 35 C with daily variation of 10C temperature.

b) Remaining 16 years Life: 10 C to 45 C with daily variation of 8 C temperature.

c) During AMF, for gas temperature, refer paragraph 3.3.3

In addition, the tank shall be able to withstand a temperature gradient of 10 C between the gas port and the propellant port with the gas port hotter.

3.5.2.2 Ambient Pressure

1 bar to 1x10‐10 Torr.

3.5.2.3 Relative Humidity

Relative humidity’s of up to 100 per cent.

3.5.2.4 Random Vibration

The random vibration environment is shown in Table 3‐2. No flow is required from the tank under this environment.

3.5.2.5 Sine Vibration

The sine vibration level and duration is shown in Table 3‐3. No flow is required from the tank when under this environment.

3.5.2.6

Acceleration

a. Steady acceleration

Qualification quasi‐static accelerations at the C.G. of the tank are 18 g in longitudinal direction and 8 g in lateral directions

b. On orbit acceleration. (See Chapter 6)

3.5.2.7

Mathematical Models

Mathematical models / Finite element (FE) of the propellant tank, along with reports, shall be provided to ISRO for the following cases:

Finite element model supplied should be compatible for NASTRAN 2005 or later

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Craig‐Bampton Model: Mass and stiffness matrices (Craig‐Bampton Model) with 70%, 85% & 95% fill fractions with specific

gravity of 0.878 and 0.785 simulating slosh models.

Dry tank full FE model

FE model report shall contain the following

o The model should be in SI units with Length in meter, Mass in kilogram, Time in second and Angle in Radian

Requirement details in the report

o System of co‐ordinates, Details of Tank Idealisation, COG, Mass and inertia properties, Description of Craig‐Bampton Model,

interface description

o Mass and stiffness matrices (Craig‐Bampton Model) with 70%, 85% & 95% fill fractions with specific gravity of 0.878 and

0.785 simulating slosh models.

o Free Vibration characteristics, output transformation matrices for accelerations, output transformation matrices for COG

accelerations and resp. I/F forces, simplified restitution model for visualization, concordance tables of DOF’s and I/F grid co‐

ordinates, Dry tank full FE model

3.5.2.8

Shock

The shock test environment is shown in Table 3‐4. No flow is required from the tank under this environment. Compliance to shock

qualification can be provided by one of the below with supporting documents

a. by test

b. by analysis

c. test data from qualification model.

3.6 Physical Characteristics

3.6.1

Configuration

The tank shall consist of a pressure vessel and an internally mounted Propellant Management Device (PMD). The tank shall be filled

with propellant (or other compatible fluids) through the propellant port. During operation, propellant shall be expelled from the tank

through the propellant port. Helium gas pressure shall be supplied through the pressurant port.

The PMD will ensure the supply of gas free propellant at tank outlet interface under the conditions specified herein (including Chapter

6)

Tank shall be attached to the spacecraft structure through interface as per the table detailed in 3.1.1. The interior of the unit, including

the surface tension device, shall be designed and fabricated to facilitate cleaning and prevent the entrapment of contaminants. The

tank construction shall facilitate draining of fluid from the tank. Tanks shall be cleaned as per requirements of paragraph 3.6.8 and

shall contain no chips, slag, particulate matter, grease or other foreign material.

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Cleanliness requirements for parts, assemblies and the assembly/work area shall be established and maintained.

The shell of the tank shall be constructed of 6Al‐4V Titanium alloy. Tank shell forging shall be 100% ultrasonically inspected. The PMD

shall also be built out of Titanium to the extent possible with the use of corrosion resistant steel restricted to bare minimum. Use of

stainless steel / Titanium wire cloth of compatible composition is allowed. However no non‐metallic parts are allowed in propellant

exposed area.

3.6.2 Mass

The tank mass shall not be more than 16.5 kg.

3.6.3 Proof Pressure/Burst Pressure

Proof pressure: Minimum 1.25 x MEOP and Burst pressure: Minimum 1.5 x MEOP

3.6.4

Pressure Cycles

The number of pressure cycles shall be derived from Table 3‐1. The number shall be used for all the analysis and verification required

by the safety (fracture mechanics safe life, etc.) in accordance with MIL‐STD‐1522‐A. The tank shall be capable of withstanding 12

pressure cycles at proof pressure as specified in paragraph 3.6.3, 50 cycles from ambient to MEOP.

3.6.5

Collapse Pressure

Vendor to provide the differential pressure level to which the tank can be evacuated when the external pressure is at ambient. The

same may be supported with analysis reports.

3.6.6

Connections

The tank shall be designed with appropriate Titanium‐to‐Stainless Steel transition tubes for connection to SS 304L pipe work by

welding. The pipe work dimensions shall be:

Outer Diameter Wall Thickness

Pressurant inlet 6.0+0.1 / 0.0 mm 0.7 ± 0.07 mm

Propellant outlet 10.0+0.1 / 0.0 mm 0.7 ± 0.07 mm

3.6.7

Compatibility

Exposure of the tank to MMH [(as per applicable document 2(c) in Table 2‐1] liquid or vapour for a period of 18 years shall not degrade

its performance.

In addition the tank shall also be compatible with the following:

a. Helium [as per applicable document 2(g) in Table 2‐1] b. Nitrogen [as per applicable document 2(f) in Table 2‐1] c. Argon [as per applicable document 2(e) in Table 2‐1] d. Iso‐propyl alcohol [as per applicable document 2(h) in Table 2‐1]

e. De‐ionized water [as per applicable document 2(j) in Table 2‐1]

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3.6.8

Cleanliness

The particulate and chemical cleanliness of the unit shall be achieved, measured and maintained in accordance with the

manufacturer's specifications which are to be approved by ISRO.

The chemical cleanliness must be such that necessary to ensure compatibility with the specified propellants and referee fluids.

The level of particulate contamination shall be determined by a rinse test using a fluid approved by ISRO. The cleanliness check shall

be done both in normal and reverse flow directions and shall include the PMD. Samples shall be drawn from each port for particle

count analysis. The maximum allowable particle count distribution, when tested in accordance with ARP‐598 standard or equivalent,

shall be as per the following:

< 5 micron ‐ No limit, no silting

5‐15 micron ‐ 1200

15‐25 micron ‐ 100

25‐50 micron ‐ 30

> 50 micron ‐ None

Non volatile residue(NVR) ‐ < 1mg/100 ml

3.6.9 Maintainability

No field maintenance, servicing or adjustment shall be required within the specified lifetime.

3.6.10 Transportation

3.6.10.1

Before Integration to Spacecraft

The tanks shall be designed to be transported by common carrier (including air transport) with adequate protection. The

transportation environment shall be as per Chapter 7.

The tanks shall be provided with protection covering to prevent contamination during transportation outside clean areas and to

protect against damage in handling. Inlet and outlet ports shall be individually protected.

3.6.10.2

After Integration into Spacecraft

All integration accessories namely bearings, fasteners, flanges etc. along with required tool kit and integration procedure to be

supplied. After the tanks are integrated to spacecraft, the tanks are required to meet the transportation environment as per Chapter

8.

3.6.11 Interchangeability

Each tank shall be directly interchangeable in form, fit, and function.

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3.6.12

Surface Finish

The surface of the tank shall be adequately finished to prevent deterioration from exposure to the specified environments that might

affect specified performance. No plating shall be used on any component.

The tank mounting surfaces shall be unpainted and any protective coating used shall produce a conductive finish suitable for electrical

bonding.

3.6.13 Fungus Resistance

Materials, which are nutrients to fungi, shall not be used.

3.6.14

Corrosion of Materials

a. Corrosive Materials

Materials shall be corrosion resistant type or suitably treated to resist corrosive conditions likely to be met in storage and/or normal

service. It shall be ensured that metals used comply with tank life requirement specified under paragraph 3.4

b. Stress Corrosion Sensitivity

Metals and alloys, which are susceptible to stress corrosion cracking, shall not be used. Heat‐treating of alloys to obtain non‐stress

corrosion sensitive conditions is allowed.

3.6.15

Dissimilar Metals

The selection and use of dissimilar metals shall conform to the requirements of avoiding galvanic corrosion. Wherever it is

impracticable to avoid dissimilar metals in direct contact with each other or their exposure to electrolyte, suitable protection shall be

provided by coating, or otherwise protecting one or both surfaces.

3.6.16

Stiffness

In the mounting condition as specified in section 3.1.1, the tank shall have Axial natural frequency greater than or equal to 70Hz and

Lateral natural frequency greater than 50Hz under maximum filled condition. All these frequencies shall be met with the boundary

conditions applied at spacecraft interface locations as specified in figure 3.1.

3.6.17

Interface Loads

Details of all Mounting interface tolerances and the maximum tolerable interface loads (including the maximum displacements on

the inlet and outlet tubes) to be provided by the Contractor.

3.6.18

Identification and Marking

Each hardware shall have identification markings. The identification marking shall be upon the external visible surface of the

equipment by an adhesive bonded aluminium label and its location shall be noted on the interface control drawings for the tank. The

label and its fixation shall not degrade tank performance or hinder further operations of the tank with the spacecraft.

MARKING: Following particulars shall be marked.

a. Part name.

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b. ISRO Part number as per applicable document 2(a)

c. Specification number.

d. Item serial number.

e. Manufacturer's name.

f. Date of manufacture.

g. Contract number.

Where size limitations make it impractical to mark the complete identifying information on the tank, the information may be attached

to the shipping/storage container for the tank. As a minimum, the part number and serial number shall be marked on the tank.

3.6.19

Traceability

The contractor shall have written procedure for traceability of hardware linked with serial number allotted to the deliverable tanks.

The hardware includes basic raw materials like billets, forgings, machined parts, test coupons, and associated elements.

The programme to implement the traceability procedures including authorizations for deviations/waivers at different levels of

manufacturing stages shall be provided to ISRO.

3.6.20

Workmanship

Standards of workmanship shall meet or exceed the contractor's manufacturing process standards that are documented, controlled

and approved.

3.6.21

Reliability

Probability of success

Reliability of operation shall be considered of prime importance in the design and manufacture of the tank. FMECA based on

performance and stress analysis is required. Achievable reliability figures are to be provided by the contractor.

To verify the following requirements, an analysis using fracture methods shall be used to assure that the largest crack or any flaw

which could escape detection will not grow to failure of cause leakages exceeding the requirement of para 3.3.7 during the intended

life of the tank. The size of the potentially assumed crack or any other flaw to be considered shall be defined depending on the

inspection methods used.

Moreover, the influence of all the environmental parameters like temperatures, all sources of stress such as applied loads, thermal

and chemical effects including residual stresses shall be accounted for.

The inspections and investigations shall cover the base metal, parts after machining, weld materials and heat effected zones due to

welding activities.

A numerical approach using the stress/strength method shall make sure that the following reliability figures are achieved.

R ≥ 0.999

Reliability analysis to be a part of deliverables.

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3.6.22

Safety

The tanks shall be designed and fabricated with compatible materials in such a manner that all hazards associated with the tank are

eliminated or minimized and controlled. The tanks shall be designed to comply with the requirements of applicable document 2(n)

complying with Leak Before Burst criteria and a Fracture control plan for the tank, which shall be prepared by the contractor and

approved by ISRO.

The tanks shall be designed with positive margins of safety to meet the design and performance requirements of this specification

prior to exposure, during exposure and after exposure to the environments specified herein. Environments experienced during tank

fabrication, transportation and storage shall be controlled so as to be significantly less severe than the operational environments.

Any data required by launch vehicle agency as part of safety submission shall be provided by the contractor even after the delivery

of tanks, if required.

The tank shall be in accordance with the requirements of the MIL‐STD‐1522, section 5, Approach A, of the latest applicable issue

(design, analysis, tests, etc) and the latest applicable Launch Vehicle safety requirement documents of GSLV, Ariane 5, Proton, Land

Launch, Atlas, SEA Launch, Soyuz and Falcon.

3.6.23

Items subject to Wear out and Degradation

All parts, materials and processes subject to radiation, application stresses or inherent physical processes shall be designed,

fabricated, selected and used to attain performance life requirements. The design life of such items (except those meant for one time

operation in the initial period) shall be at least 18 years operation in orbit. Any item with less than the predicted 18 years orbital

performance life shall be clearly identified by the contractor and these shall need approval of ISRO.

Table 3‐1 Propellant Tank Expected load cycles (page 3‐13 , Page 3‐14 and Page 3‐15 of RFP Document)

Table 3.2 Random Vibration Levels

Qualification (All Three Orthogonal Axes)Frequency (Hz) Power Spectral Density (PSD)g2/Hz grms Duration per axis (sec)

20‐110 110‐700 700‐2000

+6dB/octave0.09

‐3 dB/octave 11.2 120

Proto‐flight (All Three Orthogonal Axes) Frequency (Hz) Power Spectral Density (PSD)g2/Hz grms Duration per axis (sec)

20‐110 110‐700

+6dB/octave0.09

11.2 60

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700‐2000 ‐3 dB/octave

Acceptance (All Three Orthogonal Axes) Frequency (Hz) Power Spectral Density (PSD) g2/Hz grms Duration per axis (sec)

20‐110 110‐700 700‐2000

+6 dB/Octave 0.04

‐3dB/octave 7.47 60

Note: Notching criteria shall be as in Chapter 9.Resonance Search:

A low level resonance search shall be conducted prior to performing the test specified. The transmissibility and cross‐talk of the test

fixture shall be determined for each of the three orthogonal axes.

Input:

Acceleration at amplitude : 0.2g

Frequency : 5 to 2000 Hz

Sweep Rate : 2 oct/min

Before and after the sinusoidal test and before and after the random vibration test a resonance search shall be carried out on the

tank in each axis at input level given above. The resonant frequencies before and after each test in each axis shall be identical to great

extent. Notching is allowed.

Table 3.3 Sine Vibration Levels

Qualification



5 ‐ 15 15 ‐ 60 60 – 80 80‐100

11 mm10 6 3.5

5 ‐ 16 16 ‐ 75 75 ‐100

4.9 mm 5 3.5

Sweep rate: 2 octaves/min ; No. of sweeps: 2 (one up and one down)

Proto‐flight

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5 ‐ 15 15 ‐ 60 60 – 80 80‐100

11 mm10 6 3.5

5 ‐ 16 16 ‐ 75 75 ‐100

4.9 mm 5 3.5

Sweep rate: 4 octaves/min; No of sweeps: One

Acceptance


Frequency (Hz) Amplitude (g) Frequency (Hz) Amplitude(g)

5 ‐ 15 15 ‐ 60 60 – 80 80‐100

7.4 mm6.66 4

2.33

5 ‐ 11 11 ‐ 75 75 ‐100

3.7mm 3.33 2.33

Sweep rate: 4 octaves/min ; No of sweeps : one


Table 3.4 Shock Test ‐ Qualification Levels (All Three Axes)

Frequency (Hz) SRS

100 – 600 15 dB / oct

600 – 4000 900 g

4000 – 10000 ‐ 6 dB / oct

Note:

The levels given are the qualification level.

Two shocks per axis.

The shock levels specified are with a Q=10.

4 QUALITY ASSURANCE PROVISIONS

4.1 The metric standard system shall be used for design, manufacturing and testing.

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The parts, materials, processes and workmanship shall be in accordance with manufacturing and process standards that are

documented, controlled and approved as specified in the PA plan.

Welding operations shall be performed according to vendor standards approved by the customers.

The personnel involved in the manufacturing, handling and testing shall have adequate qualification.

4.1.1

Test philosophy

Vendor shall clearly bring out the differences between the proposed flight model tank to the already qualified tank, if any, including

flight heritage.

Following test philosophy shall be adopted accordingly:

a. New design tank shall be subjected to all qualification tests.

Qualification Philosophy: One qualification model tank shall undergo qualification tests as mentioned in paragraph

4.2. All flight model tanks (4 nos) shall undergo acceptance tests to the requirements of paragraph 4.4.

b. Heritage tank with minor modifications shall be subjected to proto‐flight level tests.

Proto‐flight Philosophy: One flight model tank shall undergo Proto‐flight tests as mentioned in paragraph 4.3.

Remaining flight model tanks (3 nos) shall undergo acceptance tests to the requirements of paragraph 4.4.

c. Already qualified heritage tank with no changes shall be subjected to acceptance level tests.

4.1.2

Responsibility for Inspection and Tests

Unless otherwise stated in the statement of work or contract, the contractor is responsible to perform all inspection and tests as

specified in paragraphs 4.2 and 4.3 of this document.

ISRO reserves the right to witness, or review the tests or documentation of any of the inspections and tests set forth in the

specification where such witnessing is deemed necessary to assure that supplies and services conform to prescribed requirements.

4.1.3

Verification of Compliance

Compliance with requirements of section 3 shall be verified by any or combination of the following:

Design, Analysis, Inspection, Test and similarity as indicated in Table 4‐1.

The required inspection, Qualification, Proto‐flight and Acceptance Tests are listed in para 4.2, 4.3 and 4.4. The tank vendor shall

provide positive verification from analysis, trials or in‐service experience, of the MMH compatibility with the tank to the requirements

of paragraph 3.6.7.

4.1.4

Heritage

Vendor shall have adequate experience and space heritage in design and delivery of side mount type tanks.

Vendor shall provide the flight history of side mount type tanks delivered to other reputed international space agencies.

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4.2

Qualification

The vendor shall offer a qualified tank with flight heritage. The vendor shall propose qualification tests, if any, to meet the

qualification sequence shown in paragraph 4.2.2. However, the vendor may also propose qualification of the tank by similarity. For

this purpose, data from existing designs and tests of comparable hardware shall be compiled and analyzed to conclusively prove that

the proposed tank design complies with the test requirements set forth in paragraph 4.2.1 and the safety requirements set forth in

para 3.6.22. All the above documentation shall be submitted to ISRO for review and approval.

4.2.1

Test Requirements

The Qualification by similarity shall consider the tests as in para 4.2.2 and corresponding analysis to demonstrate adequacy of the

tank to meet specification. The qualification test matrix is shown in Table 4‐2. This is applicable only if the offered hardware is not

proved to be already qualified.

4.2.2

Test Sequence

If already qualified, complete qualification test data shall be provided. This report shall be reviewed by ISRO for acceptance. The test

sequence shall be as below.











11. Sustained Acceleration Para 4.7.10



14. Shock test Para 4.7.13





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19. Burst pressure test Para 4.7.14




4.2.3

Failure Criteria

Failure to meet any of the requirements under 4.2.1 by analysis shall be cause for rejection of qualification by similarity and will call

for demonstration of qualification status by tests.

4.2.4

Qualification Test Report

Following completion of qualification by Test/similarity and analysis, a report shall be prepared detailing the performance obtained

at each stage of analysis.

Also, Mathematical model of the propellant tank shall be provided to ISRO for following cases as detailed in section 3.5.2.7.


4.3

Proto‐flight TestsThe vendor shall propose Proto‐flight tests if there are with minor modifications with respect to already qualified tank and to meet

the qualification sequence shown in paragraph 4.3.1. However, the vendor may also propose qualification of the tank by similarity.

For this purpose, data from existing designs and tests of comparable hardware shall be compiled and analyzed to conclusively prove

that the proposed tank design complies with the test requirements set forth in paragraph 4.3.1 and the safety requirements set forth

in para 3.6.22. All the above documentation shall be submitted to ISRO for review and approval.

4.3.1

Test Requirements

One flight model tank shall undergo Proto‐flight tests as mentioned in paragraph 4.3.2. Remaining flight model tanks shall undergo

acceptance tests to the requirements of paragraph 4.4. This is applicable only if the offered hardware has minor modifications with

respect to already qualified.

4.3.2

Test Sequence

If already qualified, complete qualification test data shall be provided. This report shall be reviewed by ISRO for acceptance. The test

sequence shall be as below.







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4.3.3

Failure Criteria

Failure of test article subjected to acceptance tests listed in paragraph 4.4.2 and not meeting the performance requirements shall be

cause for rejection of tank.

4.3.4

Proto‐flight Test Report

Following completion of qualification by Proto‐flight tests/similarity and analysis, a report shall be prepared detailing the performance

obtained at each stage of analysis.

Also, Mathematical model of the propellant tank shall be provided to ISRO for cases as detailed in section 3.5.2.7.


4.4 Acceptance Tests

4.4.1

Test Sample

Every flight standard tank manufactured against this specification shall be acceptance tested to the requirements of paragraph 4.4.2

4.4.2 Test Requirement

An acceptance test shall be carried out on each flight tank as per the sequence specified in paragraph 4.4.3.

4.4.3

Test Sequence

Acceptance testing shall be carried out in the sequence specified as below.

1. Initial inspection Para 4.7.1

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2. Non‐Destructive Inspection Para 4.7.2





7. Sine Vibration test Para 4.7.12



10. Non‐destructive inspection Para 4.7.2



13. Final inspection Para 4.7.16

14. Preparation for data review & End item acceptance Para 4.7.17

4.4.4

Failure Criteria

Failure of test article subjected to acceptance tests listed in paragraph 4.4.2 and not meeting the performance requirements shall be

cause for rejection of flight tank.

4.4.5

Test Limitations

The acceptance Inspection and test shall not degrade the tank performance or expose it to test levels or conditions, which could induce

a subsequent failure.

4.4.6

Acceptance Test Report

Following completion of acceptance tests, a report shall be prepared by the vendor detailing the performance obtained at each stage

of testing. This report shall be reviewed by ISRO for acceptance. Delivery of tank(s) can be done only after the acceptance of test

results by ISRO.

4.5 Test Conditions

4.5.1

Environmental Conditions

Unless otherwise specified, the qualification and acceptance tests shall be carried out under closely controlled environment in order

to obtain reproducible results, with a reference temperature of 20C and a relative humidity of 50%, together with tolerances as

needed to obtain the desired precision of measurement.

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4.5.2

Measurement Tolerances

Unless otherwise stated, the maximum attainable tolerances of test conditions (exclusive of accuracy of instruments) shall be as

follows

Temperature ± 1 C Pressure + 2 %

Relative Humidity (RH) ± 5 %

Acceleration + 10 %

Sinusoidal Vibration Amplitude ± 10 %

Random Vibration:

Random Overall (g rms)

Power spectral density (g²/Hz)

± 10 %

± 1.5 dB for 20‐300 Hz

± 3 dB for 300‐2000 Hz

Force (static tests) + 5 %

The maximum allowable tolerances on data required for each tank are

Dry mass ±0.1%

Internal volume ±500 cm3

Flow rate ±10%

4.5.3

Calibration

Instruments and test equipment shall be calibrated by the contractor prior to tests. The date of calibration of the instrument or

equipment used for the inspection or test shall be indicated in the corresponding report.

4.5.4 Test Reports

Following completion of formal tests, test reports shall be prepared as defined in this document.

4.5.5

Test Data

The following data shall be supplied with each delivered tank. Items (b),(c),(d),(e) can be established by analysis. The mass of the inlet

and outlet tube caps and fittings used for testing and which do not form part of tank shall be deducted to obtain the net dry weight of

the tank in accordance with item (e) a. Acceptance Test Data b. Net internal volume at AMB, MEOP & PROOF. c. Residual liquid volume. d. Dry mass of tank e. Centre of gravity (CG) of dry tank.

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4.6

Test Fluids

All test fluids shall be as per applicable documents listed in section 2, Table 2‐1. Test fluids prior to entering the tank, shall be filtered

through suitable filters to meet the requirements of cleanliness as per 3.6.8.

4.7 Test Methods

4.7.1

Initial Inspection

The tank shall be inspected by contractor Quality Assurance for general compliance with requirements set forth in the inspection and

test procedures. General workmanship dimensions, and configuration with respect to applicable interface control drawings,

identification marking etc shall be reviewed.

4.7.2 Non‐destructive Inspections

4.7.2.1

For Tank and PMD

Propellant tank inspection has to be performed according to fracture mechanics analysis requirements. This is applicable to the tank

membrane and all load bearing joints. The contractor shall propose suitable method to verify the integrity of the PMD before and

after environmental tests, which shall be reviewed and approved by ISRO.

4.7.2.2

Penetrant Inspection

The entire external surface of each tank shall be inspected in accordance with applicable document 2 (l) listed in Table 2‐1 (Type I,

Method A, Sensitivity level 4) with halogen free solutions.

4.7.2.3

Other Methods

In the event of some part of the tank being inaccessible for the type of inspections specified under 4.7.2.1 and 4.7.2.2 or the sensitivities

offered by these methods are inadequate to screen the tank for flaws, the contractor shall propose alternate methods of inspection

for review and acceptance by ISRO.

4.7.3

Proof Pressure Test

The tank shall be subjected to an ambient temperature proof pressure test at minimum 1.25 times MEOP as per accepted test

procedures. The proof pressure shall be maintained for a minimum of 5 seconds. The tolerance on the test pressure shall be + 2 %.

The internal volume of the tank shall be recorded before, during and after pressurization. Volume measurements shall be normalized

to +20C temperature as per paragraph 4.6.4. The tank shall not exhibit permanent set greater than 0.2%. No failure, degradation or

evidence of physical damage shall be permitted. The strain measurement is to be included during proof pressure testing of Flight tank

deliverables.

4.7.4

Internal Volume

The net internal volume of the tank shall be determined to an accuracy of 500 cm3. The tank interior volume shall be normalized to

+20C.

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4.7.5

Physical Parameters of Tanks

a. Mass of empty, dry tank shall be measured to an accuracy of 0.1% or better.

b. Centre of gravity (C.G) of empty, dry tank shall be determined by analysis/ modeling to an accuracy of 0.5 mm or better in X, Y

and Z axis.

c. Mass moments of inertia of empty dry tank θx, θy and θz shall be determined by analysis/ modeling to an accuracy of ± 0.5%.

4.7.6

Pressure Cycling

Pressure cycling of tank shall be performed as follows. During qualification the pressure cycling test shall be performed in accordance

with MIL‐STD‐1522 A, Approach A.

4.7.6.1

Internal Pressure Cycling

The tank shall be capable of withstanding 12 pressure cycles at proof pressure as specified in paragraph 3.6.3, minimum 50 cycles

from ambient to MEOP for Qualification model tank. In case of Proto‐flight tests, the tank shall be capable of withstanding 3 proof

pressure cycles as specified in paragraph 3.6.3 and minimum 12 cycles from ambient to MEOP.

4.7.7 External Leakage Test

The dry tank shall be pressurized using Helium gas to MEOP and leakage measured for compliance with paragraph 3.3.7

4.7.8

Cleanliness

The tank shall be cleanliness checked with Iso‐propyl alcohol as per applicable document 2(h) or de‐ionized, distilled and filtered water

as per applicable document 2(j). Samples of the effluent shall be withdrawn from gas port for particle count analysis. The maximum

allowable number of particles per 100 ml of effluent fluid when tested in accordance with applicable document 2(m) shall meet

cleanliness requirement as indicated in paragraph 3.6.8.

After cleaning and drying, while the tank is still in a controlled clean room area the tank ports are to be capped off or enclosed using

anti‐static nylon material and clean room tape. The tank shall then be bagged in an anti‐static nylon inner bag, which is pre‐cleaned.

An outer bag of pre‐cleaned nylon/polythene material shall then be put over this as enclosure. The inner bag shall be evacuated and

heat sealed. A non‐shedding type identification tag displaying caution "OPEN IN A CONTAMINATION CONTROLLED AREA ONLY" shall

be placed between the inner and outer bags at a convenient location such that it is visible after opening the container. The outer bag

shall then be heat‐sealed closed.

After all cleaning procedures have been completed, the level of chemical contaminants retained in the tank will be such that correct

functioning of the tank shall not be impaired or compromised throughout the operation life time.

4.7.9 PMD Health Check

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4.7.9.1

Bubble Point Test

Each porous capillary element assembly in the Propellant Management Device (PMD) shall be bubble point tested to assure that gas

free propellant delivery will be achieved under all specified operating conditions. The bubble point reject criteria required for this test

shall be determined by analysis and incorporated in the appropriate test procedures. The tests shall be accomplished for each of

three levels as follows:

Level 1 PMD sub assembly level or individual welded screen detail part level.

Level 2 PMD assembly level prior to installation into the tank assembly.

Level 3 Tank assembly level.

4.7.9.2 Expulsion Efficiency

Where the tank and PMD designs permit fluid expulsion on ground, the expulsion efficiency shall be demonstrated by test.

4.7.10

Sustained Acceleration

The tank shall be filled to maximum liquid loading with simulated propellant, pressurized to MEOP and attached to a fixture in such a

manner simulating the actual mounting to the spacecraft structure. Reduction in internal pressure to satisfy the test facility safety

requirements, if any, shall be proposed by the contractor with analysis data for review and acceptance by ISRO. The mounting fixture

shall be attached to the centrifuge such that the tank experiences an acceleration of

18 g applied in the longitudinal direction and 8 g applied in the lateral direction. Note under Table 3‐2 & para 3.5.2.6 is applicable.

The differing acceleration levels imposed by the centrifuge across the tank being tested excluding inlet/outlet ports shall not vary from

the specified acceleration by more than + 10 %. The acceleration specified shall be at the location of the centre of gravity of the loaded

tank. The minimum duration of the test shall be one minute for each of two acceleration directions.

Note: This test is only to be made if levels are not covered by sine vibration qualification test.

4.7.11

Random Vibration Test

The tank shall be mounted simulating the mechanical interface with spacecraft. The test fixture shall be sufficiently stiff to be

considered rigid for the particular frequency ranges that are critical for the tank. Verification of the test fixture stiffness is required by

analysis or test.

The tank shall be subjected to a random vibration test when filled to the maximum or minimum levels given in paragraph 3.3.10

(whichever is the worst case), using fluids to simulate the propellants and pressurized to 6 bar differential using gaseous Helium or

Nitrogen.

The qualification and acceptance random vibration levels and test directions are given in Table 3‐2 and Notching philosophy is as per

Chapter‐9.

Specific relaxation requests, if any, have to be discussed and mutually agreed between the contractor and ISRO.

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4.7.12

Sine Vibration Test

The tank shall be filled to the worst case launch propellant load (that load which generates the most critical stresses in the tank

structure) with fluids to simulate the propellants and pressurized to 6 bar differential with gaseous helium or nitrogen. The tank shall

be mounted on a stiff mount (as per paragraph 4.7.11) and vibrated in accordance with levels shown in Table 3‐3 in each of the three

orthogonal axes.

For the purpose of controlling vibration applied to the tank, calibrated control accelerometers shall be attached rigidly on the fixture

near the tank‐mounting interface and trued with the axis of applied vibration. When more than one control accelerometer is used per

axis, an average reading shall be used.

Notching philosophy is as per Chapter‐10.

4.7.13

Shock Tests

The shock levels are given Table 3‐4. The levels specified are the qualification level. The shock levels are for Q = 10. The qualification

for shock can be shown through shock tests on a representative tank or through shock tests on critical elements and the rest by an

assessment. Two shocks per axis are to be used for the shock test. If qualification model tank is not proposed, compliance shall be

provided by analysis or similarity.

4.7.14

Burst Pressure Test

A burst pressure test shall be conducted on the qualification tank to demonstrate minimum 1.5 x MEOP. Burst shall not occur at a

pressure ≤ minimum 1.5 x MEOP. Medium: De‐ionized water.

4.7.15

Dryness Check

The tank interior shall be dried by a suitable method and the dryness established through measurement of dew point of the flush gas

nitrogen. The tank dryness requirement is a dew point of better than ‐60C.

4.7.16

Final Inspection

The tank shall be subjected to a final visual inspection to verify compliance with;

a. Mechanical interface requirements

b. No handling damages

The log book and records shall be verified to ensure that all specified tests have been gone through and no open ended action items

exist. The tank exterior shall be inspected for its cleanliness, and identification marking.

4.7.17

Preparation for Data Review & End Item Acceptance

The tank shall be inspected by contractor quality assurance for conformance with requirements specified. Data taken during the

inspections and tests shall be compiled and required analysis and computations shall be performed. All data shall be reviewed and

certified by contractor quality assurance. The data shall be submitted to ISRO for review as defined in this document. Accepted item

shall be appropriately sealed by the contractor’s QA and released for storage or shipment

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Table 4.1 Tank Requirement Verification*

Table 4.2 Tank Qualification/Proto‐flight Test Matrix

Table 4.3 Tank Acceptance Test Matrix

5 DELIVERY OF PROPELLANT TANKS

5.1

Preservation and Packaging

Preservation and packaging of the tank shall be accomplished in a manner, which will ensure protection against mechanical damage,

deterioration and contamination. Double bagged units shall be packaged within each shipping container with cellulose cushioning

material such as pads, fillers, or other acceptable packaging aids which will centralize and provide protection to tank ports and prevent

contact, shifting or rotation of the tank within the container.

The shipping container shall be designed and constructed to provide sufficient strength and protection of the tank during the handling

and environmental hazards which may be encountered when transported by common carrier. The inside dimensions of the container

shall permit a minimum of 50mm spacing between any surface of the tank and inside surface of the container which shall be filled

with cushioning materials

5.1.1

Retention and cleanliness

The units shall be sealed for retention of cleanliness using pre‐cleaned bags as port closures. The bags shall be retained by pressure

sensitive tape, applied over the bags. The tape shall not contact the fitting end.

The sealed tank shall be double bagged in anti‐static polyethylene or polymatic film (50 micron total thickness minimum) and shall

then be packed according to commercial practice in a manner which will provide adequate protection against hazards encountered

during shipping, handling and/or storage.

To provide constant cleanliness inside the tank, it must be kept permanent positive pressure during transport (approx. 2 bar)

5.1.2

Identification and Marking

The identification shall be visible when the unit is mounted and its location shall be also noted on ICD/ICS. The identification shall be

legible from 0.5m distance with unaided eye. The S/C axis shall be permanently identifiable on the tank skirt.

5.2

Marking for Shipment and Storage

All markings on containers shall be clearly legible from a distance of one meter and may be applied by stencil, rubber stamp, or lacquer

over coated gummed labels. Following caution shall be marked on the container:

ITEMS FOR SPACE FLIGHT USE

In addition all interior packages and exterior shipping containers shall be marked as follows.

a. Part Number

b. Quantity

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c. Serial number

d. Contract number

e. Gross weight of packaged tank (Marked on outside of package only)

f. Warning: “open only with QA supervision”

g. Contractor’s name or trade mark

5.3 Handling, Integration and utilization

5.3.1

Filling and Ground Operations

In the normal position (+X‐axis up, the tank “equator welds” in a plane Y‐Z) the tanks shall be capable to be filled to its nominal volume

and to emptied (axis definition shown in Fig 6‐1).

The tank, when loaded with propellant to 85% fill level min. or 95% maximum will be transported in vertical / horizontal condition

connected with the launcher up to the launch place. Possible de‐loading if necessary, down to mission fill level will be performed

thereafter in vertical position.

5.3.2

Handling/Handling provision

Vendor to specify/provide the following:

Tank handling procedure.

Tank handling and safety precautions, if any, during assembly to the spacecraft.

Handling interface on tanks.

Needed hardware for handling to be supplied.

5.4 List of reviews and deliverables

5.4.1

Milestones for reviews

The proposed milestone for the reviews is as per the Table 5‐1

Table 5‐1 Review Milestones

# Activity Schedule


2 Preliminary design review (PDR) / EQSR T0 + 2 months

3 Critical design review (CDR) T0 + 5 months

4 Test readiness review (TRR) T0 + 6 months

5 Delivery Review Board (DRB) clearance T0 + 10 months

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5.4.2

Vendor shall intimate ISRO the reviews dates 30 days in prior and submit the respective review documents to ISRO at least 15 days in

prior to the reviews.

List of Documents & Analysis reports The list of deliverable documents and analysis as part of procurement contract is listed in table 5.2. If any of the

document from the following list is not part of standard deliverable, bidder may quote for it separately. If any of the

documents cannot be offered, reason for the same shall be provided.

Table 5‐2 List of Deliverables & Analysis reports


1. Propellant Tank Specification finalization and award of contract T0

2. Tank ICD with clear dimensions and interfaces

Mathematical models of the propellant tank, along with reports, as per thesection 3.5.2.7

T0 + 1 month

3. Technical Design Description PDR/EQSR

4. Parts, Materials & Processes List PDR/EQSR

5. Equipment Qualification Status Review (EQSR) PDR/EQSR

6.

CG & MI of the dry tank and at various fill levels for propellants at followingconditions as equations

CG & MI of the dry tank.

CG & MI of tank with propellant from fill levels 95% to 5% in normalacceleration condition (in steps of 10%).

CG & MI of tank with propellant from fill levels 35% to 1% in lateralacceleration condition (in steps of 2%).

PDR/EQSR

7. Propellant Tank Design Verification Matrix PDR/EQSR

8. Reliability Prediction of the Propellant Tank PDR/EQSR

9. Manufacturing and Inspection Flow Chart of the Propellant Tank PDR/EQSR

10. Structural Mechanics Qualification Verification Data PDR/EQSR

11. Functional Performance Analysis of Propellant Tank PDR/EQSR

12. Stress & Stability Analysis of the Propellant Tank CDR

13. Fracture Analysis CDR

14. Qualification/ QBS (Qualification by Similarity) Report CDR

15. Shock qualification/assessment report CDR

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16. Slosh analysis results for various fill fractions covering AMF phase, Station keeping maneuvers at BOL, MOL & EOL cases

CDR

17. Failure Modes, Effects and Criticality Analysis CDR

18. Analytical Prediction for Vibration Acceptance Tests CDR

19. Random Vibration Acceptance Test Procedure TRR

20. Proof Pressure Test Procedure TRR

21. Functional Performance Test Procedure TRR

22. Handling procedure for the propellant tank PDR/EQSR

23. Forging and raw material details including source of supply document PDR/EQSR

24. Tank as built summary, CIDL TRR

25. Listing of all NCR’s, discussions and dispositions TRR

26. User Manual for the Propellant Tank

DRB

27. Report for: Mass, Volume, C.O.G and Moment of Inertia

28. NDI reports and dispositions

29. Proof Pressure Test Report with strain data

30. Test Report of Vibration Acceptance

31. Functional Acceptance Test Report

32. External Leak & Cleanliness test reports

Comprehensive Acceptance Data Package – e Copy+ 5 sets of hard Copy

5.4.3

Table 5‐3 Hardware Delivery Schedule

# Activity Schedule


2 First Two (2) nos of flight Tanks with

Mounting hardware (Struts, flex plate etc. as shown in figure 3.1)

Handling accessories for one tank.

EIDPs*.

T0 + 12months

3 Second Two (2) nos of flight Tanks with

Mounting hardware (Struts, flex plate etc. as shown in figure 3.1).

EIDPs*

T0+ 14 month

*EIDPs shall contain test report of all the tests conducted on the tank including NDT, Environmental test, functional test etc. as per applicable sections 4.2.1/4.3.1/4.4.2.

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6

ACCELERATIONS & PROPELLANT FLOW RATES APPLICABLE TO PMD

Following is a summary of Acceleration and propellant flow rates expected of fuel (MMH) tank during the various phases of the mission.

Appropriate design/safety margins shall be considered over these figures for PMD design.

Please ref to Fig.6‐1 for overall location of tanks on structure and for definition of reference axes.

Figure 6‐1 Tank Configuration and Spacecraft axes definition

6.1 Launch Phase

The situation at lift off is shown in the figure 6‐2 below. No flow is required from the tanks during this phase.

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Figure 6‐2 Launch Phase

6.2

Transfer Orbit 3‐Axis Stabilization

Spacecraft in the Sun‐pointing mode with 1/s rate about pitch axis (+Y axis) or in the earth acquisition mode with 3 ‐ axis control.

Three numbers of AOCS thrusters on East/West face and one of roll thruster (anti‐earth face) may be firing simultaneously for attitude

control.

Fill fraction 80 – 95%


Acceleration along ±Z axis 1.1 x 10‐3 g

Acceleration along Y axis 9.71 x 10‐4 g

Radial Acceleration along Y axis 2.17 x 10‐4 rad/sec2

Fuel flow rate per tank 16.95 g/s


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6.3

LAM Burn

The LAM burn situation as shown in the figure 6‐5 below. This maneuver consumes approximately 80% propellants with a 440 N

thruster burning continuously. Attitude maintained with 22 N thrusters with as many as six thrusters fired at a time for roll, pitch and

yaw attitude control.

Figure 6.3 LAM Burn

Initial acceleration along X axis 2.1 x 10‐2 g

Final acceleration along X axis 3.7 x 10‐2 g


6.4

Station Acquisition‐ East‐West Station Keeping

During station acquisition and station keeping maneuvers the spacecraft attitude is controlled in 3 axis using thrusters. The roll attitude

is controlled by either the south face thrusters (acceleration along Z axis) or thrusters on anti‐earth face (acceleration along X axis)

The pitch and yaw attitude is controlled in off‐ modulation mode by the respective thrusters on East/West face. These conditions are

depicted as shown in the figure 6‐6 below.

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Figure 6‐4 Acquisition & E‐W Station Keeping

The thruster duty cycle for East/West off‐modulation rate would be approximately 30 to 50 ms off and 150 to 200 ms on and for anti‐

earth / south face thrusters typically 150 to 200 ms off and 30 to 50 ms on.

Corrections performed with four East/West face thrusters in the off modulation mode. Station keeping maneuvers to be performed

periodically during spacecraft life.


Acceleration along X axis 2.2 X 10‐3 g


Fuel Consumption per tank 1 L

Duration between successive maneuvers 1 day

6.5 North‐South Station Keeping

Maneuver with two roll thrusters on the south face of the spacecraft in off modulation, as typically shown in Fig 6‐7.

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Attitude maintained with 2 x 22 N thrusters with as many as three from East/West face for pitch / Yaw control. The maneuver to be

performed periodically during the spacecraft life of 18 years.

Figure 6‐5 North South Station Keeping

Acceleration along ± Z axis 4.4 X 10‐3 g




Duration between successive

maneuvers 1 day

6.6

On Orbit Mode

Thrusters on East/ West face will be used for momentum dumping with pulse duration of 10 ms, and 10 to 20 pulses per day.


6.7

On‐ Orbit Attitude Loss/Recovery

During the attitude loss, the spacecraft may experience attitude rates up to 3° per second in roll/yaw and 10° per second in pitch axis

for a maximum period of 2 minutes before attitude recovery procedure starts. After the start of attitude recovery procedure,

spacecraft will be in the Sun‐pointing mode with 1° per second rate about roll axis (Y axis) or in the earth acquisition mode with 3‐axis

control. Three AOCS thrusters on East/West face and one of the roll thrusters (On the anti‐earth or south face) may be firing

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simultaneously in pulse mode for the attitude control. Propellant consumption from attitude loss to achieving Sun‐pointing mode

would be approximately 1 kg per tank.

Figure 6‐6 On‐Orbit Attitude Loss

Accelerations during attitude loss and the recovery

Radial acceleration along X‐ axis 3.85 x 10‐3 rad/s2

Radial acceleration along Y‐ axis 2.0 x 10‐3 rad/s2

Radial acceleration along Z‐ axis 2.0 x 10‐3 rad/s2



Fuel consumption per tank 1 kg

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7 MODES, CONDITIONS & ACCELERATIONS LEVELS FOR SPACECRAFT TRANSPORTATION

7.1

Steady state acceleration

Transportation containers and their method of transportation shall be such as to ensure that levels experienced by the tanks are less

severe than those specified in the table below.

Condition Acceleration (g)

Air transportation Vertical

Horizontal

1.50

1.00

Ground transportation Vertical

Horizontal

3.00

2.00

Rail transportation

(for Proton and Land launch case‐tanks filled with propellants‐

horizontal transportation)

Vertical

Horizontal

3.00

2.00

Ship transportation

(For sea launch case – tanks filled with propellants‐horizontal

transportation)

Horizontal 2.00

Note: The direct injection to GSO for Proton launch not considered. The minimum fill fraction for the tanks is 85%

7.2

Sine and Random vibration

Transportation containers shall be designed to ensure that the load levels on tanks are limited to the constant acceleration levels

defined in the Table above.

7.3

Shock

The transportation containers shall be designed to ensure that the flight tank contained within is protected from a drop of 100 mm

on to concrete.

7.4

Other Environments

The transportation container may experience extremes of temperature, pressure, etc during transportation and shall be designed to

withstand the environments as specified in paragraph 3.5.1 of the main part of this document.

8

TRANSPORTABILITY AFTER INTEGRATION WITH SPACECRAFT

(a) Attitude of tanks Vertical/ Horizontal

(b) Liquid Load:

MMH

224 kg simulant Fluid or 224 kg max. (for 95%) / 201

kg ( for 85%) of MMH

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(c) Internal Pressure 6 bar differential (with Simulant Fluids)

MEOP (with propellant)

4 bar differential (without propellant / simulant fluid)

(d) Transportation Loads:

i) Steady acceleration due to ground / air / ship / rail

transportation

Vertical:

Horizontal:

3 g

2 g

(ii) Sine and Random vibration levels limited to constant acceleration levels mentioned under (i)

9

NOTCHING CRITERIA FOR RANDOM VIBRATION TEST

The test input can be reduced in small frequency bands at major resonances to limit COG responses as per Table 9.1

Table 9‐1 Notching criteria for Random Vibration Test

Output Limitations:

Shell limit : 4.4 g2/Hz ± 3 dB (20 ‐ 2000 Hz)

At COG Qualification level aax. C.O.G. = 18 g alat. C.O.G. = 8 g

At COG Acceptance level aax. C.O.G. = 12 g alat. C.O.G. = 5.33 g

10 NOTCHING CRITERIA FOR SINE VIBRATION TEST

The input levels can be reduced if required in small frequency bands covering major resonances to limit COG response as per table 10‐1

Table 10‐1 Notching criteria for Sine Vibration Test Output Limitations:


alat. C.O.G. = 8 g


alat. C.O.G. = 5.33 g

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13 PROPELLANT TANK ICD

Figure 13‐1 265 L Propellant Tank ICD

TO BE PROVIDED BY CONTRACTOR

Figure 13‐2 Typical Propellant Tank ICD

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COMPLIANCE MATRIX FORMAT

CONTRACTUAL ANNEXURE ‐2

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1 INVITATION FOR BIDS

1.1 Vendors shall submit a Firm and Fixed Price quotation (inclusive of all taxes and duties) for propellant tanks.

2 BID SUBMISSION

2.1 The proposals shall be submitted in two parts: i) Techno‐commercial bid and ii) Price bid.

2.2 The bidder shall, at their own cost, submit the bid in response to this RFP and also participate in any negotiations that may be called

for. No obligations, financially or otherwise, in this regard shall be acceptable to ISAC.

3 REJECTION OF BID

3.1 ISAC reserves the right to accept or reject any offer in part or full without assigning any reason thereof.

3.2 Canvassing by the Bidder in any form, unsolicited letter and post‐tender correction may invoke summary rejection of Bids.

Conditional Tenders will be rejected.

4 Lower offer

4.1 The Lowest offer (L‐1) shall be decided based on the aggregate value of all deliverables and services put together for which quotation

have been called for, wherever necessary.

4.2 In case of advance payment, the bids are evaluated by suitably loading interest component @ 11% per annum on the advance amount

(or) applicable rate declared by the Government of India which are in force at the time of advancing.

5 TRANSPARENCY

5.1 Vendors are free to clarify with ISAC for the Bidding conditions, Process and/or Rejection of bids etc., during the procurement process.

6 PARTICIPATION OF INDIAN AGENTS

6.1 Either the Indian Agent on behalf of Principal/OEM or Principal/OEM itself can bid. But both cannot bid simultaneously. If an Agent

submit bid on behalf of Principal/OEM, the same Agent shall not submit a bid on behalf of another Principal/OEM.

7 AGENCY COMMISSION

7.1

The amount of Commission included in the price and payable to the Indian Agent of the Vendor shall be paid directly to the Indian

Agent[s] by ISAC in equivalent Indian Rupees on the basis of an Invoice from the Indian Agent by applying T.T. buying rate of exchange

ruling on the date of placement of the Purchase Order/Contract and within 30 days from the date of receipt and acceptance of the

hardware and services.

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7.2

The Vendor shall Invoice only for the net amount payable to him, after deducting the amount of Agency Commission included in the

Invoice which would be paid to the Indian Agent[s] directly by ISAC. However, the Vendor[s] quote should separately reflect the

amount of Commission payable to his Indian Agent.

7.3

As per the Compulsory Enlistment Scheme of the Department of Expenditure, Ministry of Finance, it is compulsory for Indian Agents

who desired to quote directly on behalf of their Foreign Principals to get themselves enlisted with the Central Purchase Organization

[Eg: DGS&D].

8 Payment terms

8.1 ISAC payment terms are; payment within 30 days after the completion of the delivery and acceptance by ISAC.

9 Bank Charges

9.1 While ISAC shall bear the Bank Charges payable within India, the vendor shall bear the Bank Charges payable outside India.

10 EARNEST MONEY DEPOSIT (EMD) / BID SECURITY

10.1

The Techno‐commercial Bid should be accompanied with an Earnest Money Deposit (Refundable) of Rs. 5.00 Lakhs [Indian Rupees

Five Lakhs Only] in a single instalment through Demand Draft/Banker’s Cheque/Fixed Deposit Receipts or Bank Guarantee from any of

the Nationalized/Scheduled Banks executed on non‐judicial stamp paper of appropriate value. In case of bank guarantee, it should be

valid for a period of 45 days beyond the final tender validity date. EMD in the form of Demand Draft/Bank Draft should be drawn in

favour of Accounts Officer, ISAC, Bengaluru. EMD in the form of Bank Guarantee shall be submitted while submitting the proposal.

10.2

The Earnest Money Deposit in respect of the Bidders who do not qualify the Technical Bid [First Stage] / Financial Bid [Second

Competitive Stage] shall be returned to them without any interest. However, the EMD in respect of the successful Bidder shall be

adjusted towards the Security Deposit.

10.3

EMD of a Bidder shall be forfeited if the Bidder withdraws or amends his tender or deviates from the tender in any respect within the

period of validity of the tender. Failure to furnish security deposit/performance bond by the successful Bidder within the specified

period shall also result in forfeiture of EMD.

10.4 Foreign vendors, registered vendors or vendors who have already applied for renewal of registration, Central PSUs/PSEs/Autonomous

Bodies, Micro and Small Enterprises, National Small Industries Corporation, etc., are exempted from the payment of EMD.

10.5 Any tender not accompanied with EMD shall be treated as invalid tender and rejected.

10.6 Bidders seeking exemption from payment of EMD, under the above mentioned Category shall submit necessary proof for claiming

such exemption.

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10.7

EMD shall be refunded to all the unsuccessful Bidders within thirty days after entering into Contract with successful Bidder. EMD shall

be refunded to the successful Bidder/Vendor after receipt of the Security Deposit or may be adjusted against the Security Deposit.

EMD shall be refunded to all the participants in cases where the tender is cancelled or withdrawn by ISAC, within thirty days from the

date of such cancellation or withdrawal.

11 SECURITY DEPOSIT

11.1

The Successful vendor shall execute Security Deposit for 10% of the value of the Purchase Order/Contract towards satisfactory

execution of the Purchase Order/Contract. The Security Deposit shall be executed through Demand Draft/Bankers Cheque/Fixed

Deposit Receipts or Bank Guarantee issued by a Nationalized Bank/Scheduled Bank valid till the Purchase Order/Contract is completely

executed.

11.2

In case the vendor fails to furnish the Security Deposit within 20 days after the receipt of PO or on signing of the Contract or any

extension thereof, the Purchase Order/ Contract shall be cancelled or terminated. The Earnest Money Deposit if any executed shall

be forfeited and appropriate penal action shall be initiated.

11.3 The Security Deposit will not carry any interest and shall be returned after completion of all the obligations of the Contract.

12 TAXES AND DUTIES

12.1 Applicable taxes and duties shall be specified in the bid. The percentage of Taxes, Duties, etc., where legally leviable and intended to

be claimed shall be calculated and indicated.

13 PERFORMANCE BANK GUARANTEE

13.1

The Vendor shall guarantee for satisfactory performance of the delivered product and services as per the terms and conditions of

the Purchase Order/Contract. Towards this, the Vendor shall furnish Performance Bank Guarantee (PBG) for 10% of the deliverables

on a non‐judicial stamp paper of Rs.200/‐ issued by Nationalized/Scheduled Bank which shall cover the following:

i. The satisfactory performance of product covered under this Purchase Order, under the conditions and for the

services specified.

ii. Guarantee the product as represented and specified.

iii. Guarantees against any and all defects in material and workmanship. Upon written notice by ISAC, undertakes to

replace or fully remedy free of expenses to ISAC such defects as developed under normal operation of the propellant

tanks for a period of 12 months from the date of receipt and acceptance by ISAC or until the launch of the satellite

where it is integrated, whichever is later.

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iv. The PBG shall be issued preferably by State Bank of India, ISRO Branch, Airport Road, Bengaluru – 560 017, India or

by an internationally reputed bank or any bank approved by Reserve Bank of India and made payable to ISAC for due

performance and completion of contract in all respects. PBG shall be returned to the Vendor after successful

completion of all contractual obligations without any interest.

14 VENDOR'S DEFAULT LIABILITY

14.1

ISAC may upon written notice of default to the Vendor, may terminate the Contract by giving 30 days prior notice in whole or in part

in circumstances detailed hereunder:

i. If in the judgment of ISAC, the Vendor fails to fulfil their contractual obligations within the time specified in the

Contract/agreement or within the period for which extension has been granted by ISAC to the Vendor.

ii. If in the judgment of ISAC, the Vendor fails to comply with any of the other provisions of this Contract.

14.2

In the event ISAC terminates the Contract in whole or in part as provided in the Contract, ISAC reserves the right to get the services,

upon such terms and in such a manner as ISAC may deem appropriate, services similar to that terminated and the Vendor shall be

liable to ISAC for any additional costs for such similar services and/or for liquidated damages for delay as defined in the Contract until

such reasonable time as may be required for the final Service.

14.3

If this Contract is terminated as provided in the Contract, ISAC in addition to any other rights provided in this Clause, may require the

Vendor to transfer title and provide service under any of the following clauses in the manner and as directed by ISAC:

i. Any completed service.

ii. Such partially completed services, information and Contract rights as the Vendor has specifically acquired for the

performance of the Contract was terminated. ISAC shall pay to the Vendor the Contract price for the completed

services provided to and accepted, by ISAC.

14.4 In the event ISAC does not terminate the Contract as provided above, the Vendor shall continue the performance of the Contract in

which case he shall be liable to ISAC for liquidated damages as set out in the Contract until the services are accepted.

15 REPLACEMENT

15.1

If the delivered hardware or any portion thereof, is damaged or lost during the transit, the vendor shall give notice to ISAC setting

forth particulars of such hardware damaged or lost during transit. The replacement of such hardware shall be effected by the vendor

within a reasonable time to avoid unnecessary delay in the intended usage of the hardware. The payment for the replacement of

hardware shall be in accordance with the responsibilities as per INCOTERMS 2010.

15.2 In case of damage or malfunctioning of any supplied item during assembly, integration and testing process or during launch base

operations due to the vendor, replacements shall be made by the Vendor at no additional cost.

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16 SUBLETTING CONTRACT

16.1

The Contract shall not be sublet, transferred or assigned to any other firm/agencies/person, etc., without the prior written permission

of ISAC. In case of violation of this clause, the Service Provider/Vendor shall be solely responsible for any legal action besides

termination of Contract.

17 TERMS OF CANCELLATION

17.1

Under the normal circumstances, Termination/Short Closing of the PO/Contract is not foreseen. However, in case of repeated non‐

performance of the PO/Contract, ISAC reserves the right to terminate the Contract in whole or in part by giving 30 days prior notice

under the following circumstances

i. For repeated non‐performance in the execution of P.O/Contract.

ii. If the Vendor fails to deliver the final Product within the stipulated delivery schedule or any extension thereof,

granted by the Purchaser.

iii. If the final Product does not pass inspection and quality requirements of P.O/Contract.

iv. If the Vendor fails to perform any other obligations under P.O/Contract.

v. If the Vendor becomes bankrupt or otherwise insolvent.

vi. Owing to deficiency of service, breach of Contract.

vii. For inefficiency, indiscipline, irregularity, insincerity, indifference in work, disobedience, doubtful

credentials/integrity, etc., at any point of time during the Contract period.

viii. To terminate the PO/Contract at any time by giving 30 days’ prior notice.

18 LIQUIDATED DAMAGES

18.1 If the vendor fails to deliver the hardware as per the delivery schedule specified in this RFP, ISAC shall recover from the vendors

Liquidated Damages a sum of one‐half of one percent (0.5%) on the cost of undelivered part for delay of each calendar week or part

of the calendar week. The total liquidated damages shall not exceed 10% of the relevant cost.

18.2 The hardware will be deemed to have been delivered only when all its relevant deliverables are delivered in full.

18.3 Liquidated Damages (LD) is proposed to be levied after contracted delivery period. However, this shall exclude any Force Majeure

reasons or valid technical reasons beyond the control of the Vendor. The Vendor may foresee any of the Force Majeure / technical

reasons and submit the offer with due explanations to remove any uncertainty in the future.

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18.4 In case of delay in delivery of the hardware beyond the delivery date stipulated in the Purchase Order/Contract or any extension

thereof, such hardware shall be received under protest. The hardware shall be accepted without prejudice to the terms and conditions

of the Purchase Order/Contract.

19 APPROVALS, GOVERNMENT & REGULATORY CLEARANCES

19.1

It shall be the responsibility of the vendor to obtain all the necessary clearances from its government for submission of technical data

related to the proposal and for supplying the propellant tanks. The vendor shall submit a declaration of acceptance in this regard along

with the bid and shall obtain the necessary governmental clearances before signing of the contract in the event of being chosen as the

successful bidder.

19.2 Any other contractual / statutory requirements either governmental or procedural issues which influence the contract implementation

by the vendor may be explicitly brought out. The vendor shall obtain all the necessary governmental licenses that are required to

provide for supply of the tanks. In case any undertaking / statement is required for submitting the bid, ISAC shall provide the same.

19.3 All costs pertaining to custom clearance and other incidentals shall be borne by the Vendor while transporting subsystems,

components, etc., to India. ISAC will provide end user certificate and all possible document support in obtaining custom clearance.

20 FORCE MAJEURE

20.1

Neither party shall bear responsibility complete or partial non‐performance of any of his obligations [except for failure to pay any sum

which has become due on account of receipt of goods under the provisions of the Purchase Order/Contract] if the non‐performance

results from such force majeure circumstances such as, but not restricted to, flood, fire, earthquake, civil commotion, sabotage,

explosion, epidemic, quarantine restriction, strike, lock out, freight embargo, acts of the Government either in its sovereign or its

contractual capacity, hostility, acts of public enemy and other acts of God as well as war or revolution, military operation, blockade,

acts or actions of state authorities or any other circumstances beyond the control of the parties that have arisen after the conclusion

of Purchase Order/Contract. In such circumstances, the time stipulated for the performance of an obligation under the Purchase

Order/Contract may be proportionately extended.

20.2

The party for whom it has become impossible to meet the obligation under this contract due to force majeure condition will notify the

other party in writing not later than 21 days from the date of commencement of unforeseeable event. Unless agreed by both the

parties, in writing, the Vendor shall continue to perform his obligations under the Purchase Order/Contract as far as is practical and

shall seek all reasonable alternative means for performance not prevented by the force majeure event.

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20.3

Any Certificate issued by the Chamber of Commerce or any other competent authority or organization of the respective country shall

be sufficient proof of commencement and cessation of the above circumstances. In case of failure to carryout complete or partial

performance of an obligation for more than 60 days, either party shall reserve the right to terminate the Contract totally or partially.

A prior written notice of 30 days to the other party will be given informing of the intention to terminate without any liability.

21 COUNTERTERMS AND CONDITIONS OF BIDDER /VENDOR

21.1 Where counter terms and conditions / printed or cyclostyled conditions have been offered by the Bidder, the same shall not be deemed

to have been accepted by ISAC, unless specific written acceptance thereof is obtained.

22 ARBITRATION

22.1

In the event of any dispute/s, difference/s or claim/s arising out of or relating to the interpretation and application of the Contract,

such dispute/s or difference/s or claim/s shall be settled amicably by mutual consultations of the good Offices of the respective Parties

and recognizing their mutual interests attempt to reach a solution satisfactory to both the parties. If such a resolution is not possible,

within 30 days from the date of receipt of written notice of the existence of such dispute/s, then the unresolved dispute/s or

difference/s or claim/s shall be referred to the Sole Arbitrator appointed by President of the International Chamber of Commerce in

accordance with the rules and procedures of Arbitration and Conciliation Act 1996 together with amendments thereto or any

modification thereof. The expenses for the Arbitration shall be paid as may be determined by the Arbitrator. The considered and

written decision of the Arbitrator shall be final and binding between the Parties. The Seat for Arbitration shall be “Bengaluru” and the

Arbitration proceedings shall be conducted in “English” Language only.

22.2 Work under the contract shall be continued by the Contractor during the pendency of Arbitration proceedings, without prejudice to a

final adjustment in accordance with the decision of the Arbitrator unless otherwise directed in writing by the Purchaser or unless the

matter is such that the work cannot be possibly continued until the decision (whether final or interim) of the Arbitrator is obtained.

23 APPLICABLE LAW

23.1 The vendor shall be interpreted, construed and governed by the Laws of India

24

PLACE OF DELIVERY:

Hardware shall be delivered to ISRO at its campus at the address mentioned below.

STORES OFFICER,

ISRO SATELLITE CENTRE,

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VIMANAPURA POST,

HAL AIRPORT ROAD,

BENGALURU 560017, INDIA.

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