KU BAND WAVEGUIDE CIRCULATORS and TERMINATIONS

REQUEST FOR PROPOSAL

OF

KU BAND WAVEGUIDE CIRCULATORS and TERMINATIONS

(SAC-GCP-XI -RFP-12-09)

(JULY 2012)

GOVERNMENT OF INDIA

SPACE APPLICATIONS CENTRE

INDIAN SPACE RESEARCH ORGANISATION

AHMEDABAD – 380 015

INDIA

CONTENTS

INTRODUCTION

EXHIBIT-A

BACKGROUND

EXHIBIT-B

1.0 INTRODUCTION

2.0 GUIDELINES FOR PREPARING TECHNICAL DETAILS

3.0 GUIDELINES FOR PREPARING QUOTATIONS

EXHIBIT-C

1.0 RELIABILITY

1.1. LIFE

1.2 RELIABILITY

2.0 ENVIRONMENTAL CONDITIONS

2.1 NON-OPERATING ENVIRONMENT

2.2 OPERATING ENVIRONMENT

2.3 VIBRATION/SHOCK

2.4 EMI/EMC SHIELDING

3.0 PARTS AND MATERIALS

4.0 PROCESSES

5.0 MARKING AND IDENTIFICATION

6.0 TRANSPORTATION

7.0 SCREENING AND LOT ACCEPTANCE TEST (LAT)

7.1 SCREENING

7.2 LOT ACCEPTANCE TESTING

7.3 FAILURE CRITERIA

8.0 TOLERANCES

8.1 PARAMETERS TO BE MEASURED AFTER ENVIRONMENTAL TEST

8.2 PARAMETER TOLERANCE OVER OP. TEMP.

8.3 TOLERANCE ON TEST CONDITIONS

9.0 TEST DETAILS

9.1 VISUAL INSPECTION

9.2 PHYSICAL MEASUREMENT

9.3 INITIAL PERFORMANCE TEST

9.4 EMI/EMC TEST

9.5 THERMAL SHOCK

9.6 TEMPERATURE STORAGE

9.7 TEMPERATURE OPERATIONAL TEST

9.8 VIBRATION

9.8.1 SINE VIBRATION

9.8.2 RANDOM

9.9 THERMAL VACUUM TEST

9.10 POWER HANDLING TEST

9.11 MULTIPACTOR TEST

9.12 FINAL PERFORMANCE TEST

9.13 RESISTANCE TO SOLVENTS

10.0 LIST OF DOCUMENTS

11.0 GENERAL

EXHIBIT-D

TECHNICAL SPECIFICATIONS

EXHIBIT-E

QUANTITIES & SCHEDULES

1.0 QUANTITY

2.0 DELIVERY SCHEDULE

3.0 WARRANTY

REQUEST FOR PROPOSAL (RFP) – KU-BAND HIGH POWER WAVEGUIDE

CIRCULATORS AND TERMINATIONSS

INTRODUCTION

The Indian Space Research Organisation (ISRO) requests your company to submit

quotation for space qualified KU-BAND HIGH POWER WAVEGUIDE CIRCULATORS

AND TERMINATIONSS, as detailed in this document. These will be used in the Flight

Models of the Communication /Broadcast Satellite Service Pay TERMINATIONSs of

INSAT & GSAT series Operational Spacecrafts. This document consists of five sections:

EXHIBIT-A: Gives the general background of the Project for which the units are required.

EXHIBIT-B: Gives the details which vendor shall follow for preparing the response

against this RFP.

EXHIBIT-C: Gives the Reliability and Quality Assurance requirements.

EXHIBIT-D: Gives the Electrical Specifications.

EXHIBIT-E: Gives the details on quantity, delivery schedules and warranty.

EXHIBIT-A

BACKGROUND

1.0 The Indian National Satellite System (INSAT) is a domestic multipurpose system,

using satellites in geo-stationary orbit, for long distance telecommunications, Radio

and TV programme distribution, meteorological earth-observation, data relay,

search and rescue. The Department of Space of the Government of India, which has

the responsibility for establishing and maintaining the INSAT space segment, has

embarked on development and fabrication of INSAT and GSAT series Spacecrafts.

2.0 The GSAT satellite series is designed to be compatible with most of the commercially

available launchers and also the Indian Geosynchronous Launch Vehicle (GSLV),

which is under development. The items under procurement are to be used for the

development / fabrication of GSAT satellites.

3.0 For fabrication of these GSAT Spacecrafts, the Department of Space of the

Government of India, through its Indian Space Research Organisation (ISRO), is

planning to purchase certain spacecraft components and related services. Since

your company is a supplier of components for our / other satellite projects, we are

requesting, proposals from you for similar products and services for the GSAT

project.

4.0 It is very important for our evaluation of offer that your proposal also includes

sufficient technical data on form, fit and function. If this technical data is not in public

domain, we request that you apply in advance to your Department of State for a

license to export this technical data in your proposals.

EXHIBIT - B

GUIDELINES TO VENDORS

1.0 INTRODUCTION

The total program has been divided in two phases:

PHASE-1 - DESIGN VERIFICATION MODEL:

Requirement of DVM unit shall be decided based on qualification status and space

heritage. Vendor shall provide details regarding Space flight Heritage, overall as well as

specific to the quoted part, Qualification status, Qualification report summary along with

the quote. If DVM unit is required, then one Circulator & TERMINATIONS shall be

supplied as per the agreed delivery schedule.

These units are required for design verification only and need not under go the complete

testing. These should meet all electrical and mechanical specifications and should be

identical to the flight hardware in all respect.

PHASE-2 - FLIGHT MODEL:

Delivery of flight hardware fully tested as per Exhibit-C requirements and Lot Acceptance

tests carried out (as per Figure-1) on samples.

Go-ahead for phase-2 will be given subject to successful completion of phase-1

(Wherever applicable).

2.0 GUIDELINES FOR PREPARING TECHNICAL DETAILS

2.1 These are very special hardware and ONLY THOSE VENDORS who have

adequate experience in

a) Design, development and fabrication of Hi-Rel systems

b) Qualification of such hardware for onboard communication, satellites should

respond and quote against this RFP.

2.2 The vendor is requested to examine the RFP thoroughly and offer

compliance/non-compliance point by point. In case of non-compliance, the

deviation from the specified parameter shall be furnished and for complied

parameters the vendor specification (better or same) shall be provided.

2.3 The vendor should also submit compliance statement consisting of compliance /

non compliance with test philosophy, test plans and other requirements as detailed

in Exhibit-C under "Reliability & Quality Assurance Requirements". The vendor

may submit the Screening /Lot Acceptance testing programme which might have

been used for supplying similar hardware for other space missions. If compliance

statement is not supplied along with the quote, the offer will not be considered.

2.4 It is necessary for the vendor to furnish complete information as required in various

exhibits (-B to -E) of this RFP for proper evaluation and assessment of his proposal.

2.5 The vendor can attach additional information, if any, which may provide more

information on these products.

2.7 The vendor may seek clarifications, if any, in advance before submitting the

quotations. However, any clarification thus sent to the vendor will also be sent to all

other vendors.

2.8 The vendor shall give complete qualification status, flight history, space programme

details and failure data etc. along with the response.

3.0 GUIDELINES FOR PREPARING QUOTATIONS

3.1 The quotation shall include, in addition to unit cost, all the prices towards screening,

qualification, acceptance and lot-acceptance testing etc. The cost break up should

include charges for each test to enable SAC in deciding to include/exclude any test

depending on the cost and schedule constraints. The break up of overall cost in

terms of Phase-1 and 2 (as defined in para 1.0) also needs to be indicated.

3.2 This requirement is for flight hardware but the order may also include one (1) unit of

design verification units which are required to confirm the electrical, mechanical

specifications, quality assurance etc. The each type of flight hardware shall be

subjected to proto / qualification testing on the representative basis.

3.4 The vendor is requested to acknowledge the receipt of this RFP and his

willingness/inability to respond and quote against this RFP.

3.5 The vendor must ensure that his quotation along with all the details reaches

SAC/ISRO before the due date.

3.6 The quotation shall consist of two parts:

a) PART-1 : `Detailed Technical Proposal'

giving all details as required in Exhibit -C & -D.

b) PART-2 : `Cost & Management Proposal'

giving cost, payment terms and other financial details.

3.7 The supplier shall give preliminary thermal design analysis along with the offer,

particularly for the KU BAND CIRCULATORS and TERMINATIONS. The

detailed analysis shall be provided later.

Note: Part-2 shall be submitted in a separate sealed envelop. This requirement shall be

strictly adhered to. However, both parts shall be submitted together in a sealed

envelop.

EXHIBIT-C

RELIABILITY AND QUALITY ASSURANCE (R & QA)

INTRODUCTION

Reliability and Quality are important prerequisites of any Space programme hardware. It is

therefore very essential for the vendor to understand and implement the R & QA

requirements judiciously. This section provides the details on R & QA requirements, which

shall be assured for this programme for Ku band HIGH POWER WAVEGUIDE

CIRCULATOR and TERMINATIONS (referred as „unit‟ in this Exhibit).

1.0 RELIABILITY :

1.1. LIFE :

a) The unit shall meet all the design requirements for use onboard spacecraft with a

minimum life for 15 years.

b) The unit shall be capable of meeting all the functional requirements at various stages

of spacecraft assembly and storage as follows;

- 3 years storage and life at various levels of spacecraft assembly

- 5 years in controlled environmental conditions. The vendor shall specify the

exact method of storage and retest criteria in case of longer storage.

1.2. RELIABILITY ANALYSIS :

The CIRCULATOR / ISOLATOR shall be designed and fabricated to achieve a failure rate

of better than 0.06 x 10-06 per Hour.

2.0 ENVIRONMENTAL CONDITIONS :

2.1. NON-OPERATING ENVIRONMENT :

The units shall be capable of withstanding following environmental conditions:

a) TEMPERATURE RANGE : -55oC to +85oC

b) PRESSURE : Ambient to 10-10 torr

c) RELATIVE HUMIDITY : Upto 95% without condensation of water at +40oC

2.2. OPERATING ENVIRONMENT :

a) Temperature Range :

i) Screening : -20oC to +70oC

ii) Lot Acceptance : -25oC to +75 oC

b) Pressure : Ambient to 10-10 torr

c) Relative Humidity : Up to 95% without condensation of water at 40oC

(Applicable for ground testing only)

The temperatures specified are base plate temperature. Thermal conductance of 1000

W/m2-degC shall be considered. Temperature rise due self heating of unit during operating

conditions with full power under thermo-vacuum conditions at this base plate temperature

shall be specified by vendor and unit shall be designed to operate in these conditions for

15 years on-board communication satellite. There shall not be any non-linearity in unit

performance over the specified operating temperature range wherein the higher

temperature limit shall include temperature rise due to self heating. Vendor shall comply

and demonstrate performance linearity over the temperature.

Unit shall be designed with adequate venting to allow quick depressurization during launch

ascent. Vendor shall demonstrate the same by analysis.

2.3. VIBRATION / SHOCK :

The unit shall be designed and fabricated to meet the vibration (Sine and Random) and

mechanical shock requirements as per the qualification tests mentioned in paragraph 9.0.

2.4. EMI / EMC SHIELDING :

The unit shall be designed for both MAGNETIC and EMI shielding as per MIL-STD-461E.

No RF leakage (Electromagnetic) shall be allowed from the unit. The RF leakage/RF

shielding specification as given in Electrical Specifications shall be complied with.

3.0 PARTS AND MATERIALS :

Parts and materials proposed to be used in Units shall be selected from qualified parts

and materials list and through a qualified sub-vendor normally associated with long life

communication satellite hardware.

The epoxy for coating and adhesion shall not degrade / soften with use of isopropyl

alcohol (electronic grade), normally used for cleaning.

Ferrous and non-ferrous materials used shall be corrosion resistant type or suitably

treated to resist corrosion caused by atmospheric conditions existent in storage or normal

operational conditions. Non-magnetic materials shall be used for all parts except where

magnetic materials are essential. Materials, which are nutrient for fungus, shall not be

used unless they are in the hermetically sealed containers.

Organic and inorganic materials shall be stable under atmospheric and high vacuum

conditions. These materials shall have Total Mass Loss (TML) less than 1% and collected

volatile condensable material (CVCM) of less than 0.1 % when subjected to test conditions

of 125oC and 10-6 torr pressure for 24 hours. Only space qualified epoxies, potting

materials, etc. shall be used. Their use shall be restricted and failures due to these shall

be recorded as and when they are detected.

The selection and use of dissimilar materials shall be avoided, where it is impractical to

avoid dissimilar metals in direct contact with each other, suitable protection shall be

provided by space proven coating-plating etc.

4.0 PROCESSES :

The unit shall be built to the standards normally associated with long life communication

satellite hardware. Particular attention shall be paid, as a minimum, in respect to the

following :

- Eliminate bubble entrapment in coatings/epoxies wherever used,

- The marking and plating etc. shall be permanent and should not get damaged during

normal cleaning process using Isopropyl Alcohol / Freon and other cleaning solvents

approved for the fabrication of electronic hardware. Further, a list of recommended

solvents may be provided to ISRO.

- Interface dimensions.

- Surface flatness, finish, and plating quality

- Cleanliness and handling of plated / painted surfaces, particularly of the venting holes

All tolerances not specified shall be consistent with the best engineering practices. Units

shall be uniform in quality and free from blemishes and defects.

5.0 MARKING AND IDENTIFICATION :

The unit shall be identified by assigning unique serial number on the exterior surface by a

suitable process applicable for space use. Marking shall not degrade the performance of

the unit. In addition to functional markings like input/output, frequency etc. following

marking shall appear on each unit:

a) Part name b) Part Number

c) Serial Number d) Port marking (Input / Output marking)

e) Name of the Manufacturer f) Date of Manufacture

h) LAT unit (Applicable to Lot Acceptance Test unit only)

Following part No. shall be applicable for these devices :

P XXXXX-YYYYY-WRZZZ-WWW-NN-RFP

Where , P = C for Circulator, T for TERMINATIONS

XXXXX = Start frequency in MHz (e.g. 10700 for 10.7 GHz)

YYYYY = Stop frequency in MHz (e.g. 11700 for 11.7 GHz)

ZZZ = waveguide interface (e.g. 75 for WR-75) of forward path

WWW = Forward Power handling capability in watts (e.g 150 for 150W)

NN = 1 for TERMINATIONS, 3 for Circulator

The permanency of the marking shall be sufficient to withstand the specified

environmental conditions and normal cleaning operations using Isopropyl alcohol and

other cleaning solvents. The test method to demonstrate the same shall be specified by

the vendor.

6.0 TRANSPORTATION :

Waveguide windows shall be suitably protected to prevent contamination entering the

waveguide cavities, during handling and transportation. The unit shall be packaged in

separate containers to protect against electrical, mechanical and environmental damage.

Each individual container shall have a moisture absorbing material inside. Devices

subjected to Lot Acceptance Test shall be clearly marked as “LAT unit” and “NOT FOR

FM”.

The individual unit package shall be fixed within the shipping package in such a way that

they will be resistant to mechanical shock, humidity and dust. The shipping package shall

contain all the necessary technical documents as specified and the necessary commercial

documents.

In addition to other mandatory shipping markings, the following additional marking shall

appear on the shipping packages in bold letters:

"handle with Care'/HIGH-RELIABILITY COMPONENTS"

"To be opened under clean environment with ESD protection only"

"Store in a cool and dry place"

7.0 SCREENING AND LOT ACCEPTANCE TEST (LAT) :

All the units shall undergo Screening and Lot Acceptance Test (LAT) specified in flow

chart before they are acceptable to ISRO (Figure – 1).

The manufacturer shall submit the test plan for the functional and environmental tests to

be conducted on the units during the Screening (ATP) and LAT (QTP) test programme.

The test plan shall include but not limited to the tests and specification in the sequence

indicated in the Table-1. The test plan shall also include the procedure for conducting each

test, the test equipment used and their calibration, total uncertainty for each test set-up

and parameter tolerance / limits for the unit under test. Suitable buffer connections shall be

provided during testing.

7.1. SCREENING :

All the units shall undergo Screening Test as per table-1. Units exceeding the specified

limits shall be removed from the lot.

7.2. LOT ACCEPTANCE TESTING :

On successful completion of Screening Test as per section 7.1, the Lot Acceptance Test

(LAT) shall be carried out on 3% (minimum one) samples, randomly selected from

screened lot of each type as per Table-1. No failure is allowed during LAT.

7.3. FAILURE CRITERIA :

The details of the unit fall-out during Screening Test shall be informed to ISRO. Failure at

any stage shall be reported to ISRO immediately. This shall be followed by detailed failure

analysis. Maximum 5% failures are allowed during screening and No failure is allowed

during LAT. In case of number of failures exceeding this criterion, entire lot shall be

rejected. However, based on failure analysis, ISRO may decide for the acceptance of lot

after necessary corrective actions and retest of units. This shall be decided based on

failure analysis report and implemented by vendor.

8.0 Tolerances :

8.1. Parameters to be measured after environmental test :

- Insertion loss

- Isolation

- Return loss

8.2. Parameter tolerance over operating temperature range with reference to ambient,

(Absolute values shall comply to the specifications) :

- Insertion loss : + 0.05 dB

- Isolation : + 2.0 dB

- Return loss : + 2.0 dB

8.3. Tolerance on Test Conditions :

Maximum allowed tolerances on test conditions are as given below :

Temperature : +1oC

Atmospheric Pressure

Greater than 0.1 torr : + 5%

Less than 0.1 torr : + 50%

Relative Humidity : +0%, -5%

Acceleration : + 10%

Vibration

Frequency : + 2% above 20 Hz, 0.5 Hz below 20 Hz

Sinusoidal Amplitude : + 10%

Random (g-rms) : + 10%

Power Spectral Density

20-300 Hz : + 1.5 dB

300-2000 Hz : + 3.0 dB

Yes

LOT ACCEPTANCE TEST AS PER

TABLE-1 ON 3 % RANDOMLY

SELECTED SAMPLE OF EACH TYPE

Failures

observed?

SCREENING TESTS AS

PER TABLE-1

No. of failures

< 5% of lot?

DELIVERABLES

FABRICATION OF EACH

TYPE OF UNIT IN A

SINGLE LOT

No

Yes No

Yes

FIGURE 1.0: FLOW CHART FOR SCREENING AND LOT ACCEPTANCE

PROGRAMME

TABLE-1 TEST MATRIX for SCREENING and LAT

Sr. No. TEST SCREENING LAT

1. VISUAL INSPECTION X X

2. PHYSICAL MEASUREMENTS X X

3. INITIAL PERFORMANCE TEST X X

4. THERMAL SHOCK X X

5. TEMPERATURE OPERATIONAL X X

6.

VIBRATION

- Sine

- Random

-

X

X

X

7. MECHANICAL / PYRO SHOCK - X

8. EMI / EMC TEST - X

9. THERMO-VACUUM - X

10. POWER HANDLING TEST X X

11. MULTIPACTOR TEST - X

12. FINAL PERFORMANCE TEST X X

13. RESISTANCE TO SOLVENTS - X

Note-1 : At the end or during each environmental test Electrical Performance checks as

per section 8.1 and visual inspection as per Para 9.1 shall be carried out.

Note-2 : "X" Mark against the test denotes applicability of test. Test details and

conditions are described in Para 9.0.

9.0 TEST DETAILS :

9.1. VISUAL INSPECTION :

Visual inspection shall be carried out at 10X (min) magnification. Devices shall be

inspected for material, finish, surface, workmanship related defects. Further details shall

be specified by the vendor giving accept / reject criteria.

9.2. PHYSICAL MEASUREMENT :

Mechanical dimensions of the unit with respect to the ICD shall be measured. ICD shall

specify the surface finish also, and the same shall be verified on sample basis. Test details

to be specified by the manufacturer.

9.3. INITIAL PERFORMANCE TEST :

Full RF characterization shall be carried out as per electrical specification given.

9.4. THERMAL SHOCK :

The test shall be carried out as per MIL-STD-202, Method 107, Condition 'A'. The number

of cycles shall be as given below .Test shall be conducted with cold cycle first.

Screening : 10 cycles

Lot Acceptance : 25 cycles

9.5. TEMPERATURE STORAGE :

High and Low temperature storage test shall be performed as per the sequence given

below :

Step-1 : Stabilize at ambient and perform Functional Test.

Step-2 : Store all units at -55oC for 6 hours.

Step-3 : At the end of 6 hrs. stabilize the unit at ambient for 1 hour and perform functional

Test.

Step-4 : Store all units at +85oC for 6 hours.

Step-5 : At the end of 6 hours stabilize the unit at ambient for 1 hour and perform

functional Test.

9.6. TEMPERATURE OPERATIONAL TEST :

The temperature operational tests shall be performed both during the Screening and Lot

Acceptance testing programs by verifying the electrical performances at the specified High

and Low operating temperature limits. Vendor shall demonstrate linear performance of the

unit over the specified temperature during the test. Unit with non-linearity shall be rejected.

The units shall be placed in a suitable thermal chamber, and connected with the external

test set-up through an interconnecting plate carrying suitable connectors. The test shall be

conducted according to the following sequence and conditions:

Step-1 : Decrease the chamber temperature down to the specified minimum operating

temperature and maintain this condition for 1 hour after stabilisation;

Step-2 : While in the above conditions perform a functional verification as per Para 8.3

according to the applicable Test Procedure.

Step-3 : At the end, increase the chamber temperature up to the maximum operating

temperature and maintain this condition for 1 hour after stabilization.

Step-4 : While in the above conditions perform a functional verification as per Para 8.3

according to the applicable Test Procedure.

Step-5 : At the end, decrease the chamber temperature at ambient conditions and after

1 hour for stabilization performs a functional verification as per Para 8.3 in

accordance with the applicable Test Procedure.

At the end of the above a visual inspection shall be carried out to verify any possible

physical degradation of materials and processes deterioration after the exposure to the

high and low temperature conditions.

9.7. VIBRATION :

The units shall be subjected to vibration test as specified in following paragraphs. The

natural resonant frequency of the units shall be higher than 100 Hz.

9.7.1. SINE VIBRATION :

Sine Vibration test shall be carried out as per MIL-STD-202, Method 204, condition „E‟,

except the following test levels shall be applicable for all 3 axes :

10 to 2000 Hz, 30 g peak.

Sweep Rate: 2 Octave/Min.

No. of sweeps : 4 per axis

9.7.2 RANDOM :

The test shall be carried out as per MIL-STD-202, Method 214, following conditions shall

apply :

Frequency (Hz) Screening LAT

20-50 + 6 dB/Octave + 6 dB/Octave

50-1200 0.20 g2/Hz 0.45 g2/Hz

1200-2000 - 6 dB/Octave - 6 dB/Octave

Overall Level 18.2 g rms 27.2 g rms

Duration 1 minute/axis 2 minute/axis

9.8. MECHANICAL / PYRO SHOCK TEST :

The units design shall be capable to withstand the mechanical / pyro shock test conditions

given below. Requirement of the compliance demonstration by test shall be decided based

on the Qualification status, Shock test level during qualification and Space flight heritage.

Frequency (Hz) SRS Normal to mounting plane SRS Parallel to mounting plane

100 – 600 15 dB/oct 15 dB/oct

600 – 5000 700 g 400 g

5000 – 10000 - 6 dB/oct - 6 dB/oct

Number of shocks 2 2 per axis

9.9. EMI/ EMC TEST :

The units shall be subjected to RE102 test as per MIL-STD-461E over its operational

frequency band at rated power. Alternatively vendor may perform RF shielding

measurements to demonstrate compliance to electrical specifications of RF shielding. In

case of RF shielding measurements, vendor shall give detailed measurement procedure

with the calculations to derive shielding effectiveness. The radiated emissions shall not

exceed the MIL-STD-461E requirements.

9.10. THERMAL VACUUM TEST :

Thermo-vacuum test shall be carried out only on LAT samples. The test shall be carried

out as per the profile given in fig. 2.0. The test shall consist of five cycles. Dwell time shall

be two (2) hours for all the cycles. The duration of cycle may be extended for completion

of performance measurement tests. Temperature limits shall be storage temperature limit

for first cycle & operating temperature limit (LAT) for remaining four cycles. The insertion

loss and isolation of each unit under test, during transition from each temperature extreme

shall also be monitored and recorded.

9.11. POWER HANDLING TEST :

During screening, Power handling test shall be carried out on 100% units. However,

applicability of power handling test on 100% of lot OR on sample basis shall be decided

based on heritage, qualification status and design capability (design margins). Hence,

vendor shall quote for power handling in quantity slabs. The test shall be conducted under

thermo-vacuum conditions at maximum operating temperature at rated power level. All the

RF paths (where ever applicable) shall be energized at rated power. The test duration

shall be six hours at maximum rated power after temperature stabilization. During the test

body temperature, I/p power, O/p power and reflected power of the unit shall be monitored

and recorded.

9.12. MULTIPACTOR TEST :

Multipactor testing shall be conducted on all the LAT units at the power level specified in

the electrical specifications (Multipactor Threshold – peak power). The test shall be

conducted to demonstrate the multipactor free performance at input power as stated in

“peak power handling capacity ” of electrical specifications, with 25% duty cycle.

9.13. FINAL PERFORMANCE TEST :

This shall be carried out as per electrical specification given in Exhibit-B.

9.14. RESISTANCE TO SOLVENTS

Resistance to solvents shall be carried out as per MIL-STD-202, method 215. The test may

be carried out on electrically rejected samples.

10.0 LIST OF DOCUMENTS

a) The following documents shall accompany the quotes :

Space History / Space Programme to which similar items have been supplied with

frequency of operation and RF power level.

Qualification report summary giving details regarding the list of tests and test

conditions of similar design units.

Mechanical / pyro shock test levels

Qualification power level for the proposed design and multipactor margin

Estimated / measured body temperature of unit at rated power level for the proposed

design (this shall be supplied for all the types).

Generic failure rate

Screening / Qualification Plans

b) Apart from above the documents/reports as given below, but not limited to, shall

be supplied later after the award of contract. These have to be full reports (not the

summary reports) :

List of parts, materials, their quality levels, derating criterion followed, traceability data,

purchase history etc.

Documents containing test procedures (ATP & QTP with test set up details)

Non conformance parts and material test reports

Multipactor analysis

Thermal Analysis at maximum operating temperature and rated power level.

Mechanical / Structural Analysis

Venting Analysis

Non conformance parts and material test reports

Documents containing test procedures, test and calibration facilities, environmental

facilities and relevant operation details.

Failure reports (for catastrophic failures), mechanical or handling failures,

malfunctioning or operative deviations from the specifications along with corrective

actions. In absence of failure report, the entire lot shall be rejected in case of failure.

c) Test data reports of Screening / LAT and certificate of compliance along with the

deliverable units (1 hard copy + 2 soft copies in CD/DVD form) shall be provided.

11.0 GENERAL

11.1 The parts supplied by the manufacturer shall be from a single date code. In case of

the off-the-shelf parts, it should not be older than 2 years from the date of shipment

to SAC.

11.2 The cost of each test is to be indicated separately in the proposal. Based on the

quality, previous qualification and space flight history details from the supplier in the

proposal, SAC may delete any test or group of tests.

11.3 All the data/drawings should be provided on a CD/DVD with a hardcopy. The

drawings / ICD, preferably, should be in AUTOCAD compatible format and test data

in Microsoft Office.

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EXHIBIT-D

Type-1 WAVEGUIDE CIRCULATOR 12.20– 12.45 GHz

1.0 ELECTRICAL SPECIFICATIONS: Compliance/

Noncompliance

1.1 Operating Frequency Band 12.20 – 12.45 GHz

1.2 Insertion Loss 0.15 dB (max.), 0.1 dB Typical

1.3 Return loss at all ports 23 dB (min)

1.4 Insertion loss slope 0.001 dB/MHz (max)

1.5 Insertion loss change over

any 40 MHz Band

0.02 dB (max)

1.6 Group delay variation over

any 40 MHz Band

0.5 nSec (max)

1.7 Isolation 23.0 dB (min)

1.8 Average Power handling

capacity

150 W minimum in forward

direction

150 W minimum in reverse

direction

(i.e circulator should operate in

fully short circuited

TERMINATIONS condition)

1.9 Radiated Interference < -75 dBi

1.10 Peak Power handling

capacity (multipaction)

600 watts , pulse in forward

direction

1.11 Input/Output ports (W/G) WR-75 ,flange drawing provided

2.0 TEMPERATURE RANGE

Over which electrical

Specifications to be met

-25°C to +75°C (LOT

ACCEPTANCE)

-20°C to +70°C (Screening)

3.0 MECHANICAL SPECIFICATIONS

3.1 Mountings As per given drawing

3.2 Overall Weight 75 gms (approx.)

3.3

Outside Finish of the Flanges

Black Thermal Painted (Except

mating surfaces)

TYPE-2 WAVEGUIDE TERMINATION 10.95 – 12.75 GHz

1.0 ELECTRICAL SPECIFICATIONS: Compliance/

Noncompliance

1.1 Operating Frequency Band

: 10.95 – 12.75 GHz

1.2 Return loss : 23 dB (min)

1.3 Average Power handling Capacity

: 150 W (min)

1.4 Peak Power handling

capacity (multipaction)

600 watts , pulse in

forward direction

1.5 Radiated Interference : < -75 dBi

1.6 Input/Output Ports (w/g) : WR-75 , flange

drawing provided

2.0 TEMPERATURE RANGE:

( Over which electrical

Specifications to be met )

: -25°C to +75°C

(LOT ACCEPTANCE)

: -20°C to +70°C

(Screening)

3.0 MECHANICAL SPECIFICATIONS:

3.1 Mountings : As per given drawing

3.2 Overall Weight : 60 gms. Max

3.3 Outside Finish : Black Thermal

Painted (Except mating

surfaces of the Flanges)

3.4 Inside Finish : Silver plated

3.5 Heat Dissipation : Heat dissipation

through Conduction to

the mounting panel

EXHIBIT-E

QUANTITIES, SCHEDULE AND WARRANTIES

1.0 QUANTITIES

The vendor shall quote in step quantities for KU BAND CIRCULATORS and

TERMINATIONS. As clarified earlier that the requirement is primarily for Flight

hardware however one unit of each may be required to be supplied by the vendor for

design verification (Electrical/Mechanical/Quality etc.) in Phase-1 as per schedules

given below (refer Para 2.0 below).

STEPS OF QUANTITIES

1.1 DESIGN VERIFICATION MODEL

Circulator : 1 No.

Termination : 1 No.

1.2 FLIGHT UNITS

Please quote in quantity slabs of

10-15,16-29,30-50

for KU BAND CIRCULATORS and TERMINATIONS

1.3 LAT Units : Qty. to be decided depending upon the FM quantity

selected. Hence this will be as per para 7.2 of EXIBIT-C.

PLEASE QUOTE IN FOLLOWING FORMAT ONLY

SR NO

ITEM/ TEST CHARGES QTY (SLABS) EACH COST

TOTAL COST

1 DVM 1 XXXXXX XXXXXXXX

2 FM INCLUDING SCREENING (FROM TOTAL FM ORDERED , 5% WILL BE USED AS LAT )

10-15,

16-29,

30-50

XXX XXXXX XXXXXXX

XXXXX XXXXXXX XXXXXXXXX

3 LOT ACCEPTANCE TEST CHARGES ON 5% UNITS /OR AS SUGGESTED BY SAC QA TO ROUNDED UP QUANTITY(EXCLUDING LAT UNITS HARDWARE)

-------- XXXXXXX

4 OTHER CHARGES IF ANY WITH BREAKUP

XXXX XXXXXX

2.0 ORDERING

The order will be placed for total requirement including Deign verification, Lot

Acceptance and Flight models.

3.0 DELIVERY SCHEDULES

Design Verification Model along with

Design Review : WITHIN 2 Months after L/I

Flight Model : WITHIN 6 Months after L/I

LAT Units : WITHIN 8 Months after L/I

4.0 WARRANTY

(a) The vendor shall provide warranty as given below:

“The units supplied here upon shall be free from any defects in material or

workmanship and in accordance with the applicable specifications and drawings”.

(b) This warranty shall run for period of Four years from the date of final acceptance by

SAC/ISRO and shall be in addition to any other rights available to SAC/ISRO. This

warranty shall continue to be valid for corrected or replaced units until four years

after the date of final acceptance by SAC/ISRO of the corrected or replaced parts.