ISRO Ka-Band High Throughput Communication Satellite [India]

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GOVERNMENT OF INDIA

DEPARTMENT OF SPACE

ISRO SATELLITE CENTRE [ISAC]

AIRPORT ROAD, VIMANAPURA POST

BANGALORE – 560 017

Ref. No. ISGE 2012-0-24300 05.11.2012

INVITATION FOR “EXPRESSION OF INTEREST”

ISRO KA-BAND HIGH THROUGHPUT COMMUNICATION

SATELLITE

In India ISRO has played a big role in establishing a strong communication infrastructure thus

partnering the increasingly vibrant entrepreneurial spirit of India’s business, industrial and

entertainment sectors. In order to enhance and upgrade this infrastructure, ISRO is planning to

implement a new generation of payloads and satellite buses.

In this regard, ISRO is looking for design, development, fabrication and operationalization of a next

generation State of the art high throughput Ka-band communication satellite into the geostationary

orbit.

This expression of interest is sought from bidders to provide their proposals which will aid to firm up

the procurement specifications prior to release of a formal RFP later.

Interested Vendors, Manufacturers having sufficient knowhow, experience and financial background

are invited to express their interest.

Along with “Expression of Interest” please furnish the following information also in detail:

1. Registered address with Phone, Fax, Email etc.

2. Status [Proprietary/Partnership/Private Ltd. Etc] with names and addresses of Proprietor,

Partners, Board of Directors etc.

3. Associates : [a] Indian [b] Foreign

4. List of Major Customers with full address and their Contact Persons.

5. Details of other Contracts, if any now in hand.

6. Details of Infrastructure facilities owned/available.

7. A brief of the designing and developing various types of spacecraft for LEO and GEO for

different types of applications.

8. Capital and Turnover for last three years with copy of latest Annual Report.9. Financial Capacity/Credit facilities available.

10. Name and address of Bankers.

11. Trade Association to which you belong to.

12. Any other information you consider relevant.

Details are available on ISRO website www.isro.gov.in Interested Vendors may at their option,

download the details from website and submit the application with all the above information shall

reach the undersigned, quoting Ref. No. on or before 1600 Hrs on 20.12.2012. ISAC reserves the right

to accept or reject all or any such “Expression of Interest” without assigning any reasons what so ever.

Sd/-

HEAD, PURCHASE & STORES

ISRO SATELLITE CENTRE



ISRO-ISAC-GEO-HTS-EOI-001

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EXPRESSION OF INTEREST

FOR

ISRO KA-BAND HIGH THROUGHPUT COMMUNICATION SATELLITE

REQUIREMENTS SPECIFICATION

OCTOBER 2012

ISRO SATELLITE CENTREDEPARTMENT OF SPACE, GOVT. OF INDIA

BANGALORE




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ISRO SATELLITE CENTRE, BANGALORE ISGE2012-0-24300-01

TABLE OF CONTENTS

1. SCOPE.................................................................................................................................................. 3

2. INTRODUCTION ................................................................................................................................... 4

2.1 SPACECRAFT................................................................................................................................................. 4

2.2 ASSOCIATED HARDWARE ................................................................................................................................ 4

2.3 SPACECRAFT HARDWARE TRANSPORTATION AND HANDLING ................................................................................. 5

2.4 LAUNCH PREPARATION................................................................................................................................... 5

2.5 GROUND CONTROL SYSTEM ...................................................... ............................................................... 5

3. ISRO SPACECRAFT GENERAL REQUIREMENTS ...................................................................................... 7

3.1 MISSION...................................................................................................................................................... 7

3.2 SPACECRAFT LIFE AND MASS ........................................................................................................................... 7

3.3 LAUNCH VEHICLE COMPATIBILITY ..................................................................................................................... 7

3.4 PRODUCT ASSURANCE.................................................................................................................................... 8

3.4.1 Part, Material, Process and System Development ................................................................................... 8

3.4.2 Product Assurance Plan ............................................................................................ .............................. 10

3.4.3 Model philosophy ................................................................................................................................... 11

3.4.4 Reviews .......................................................... ............................................................... .......................... 12

3.4.5 Test plans and procedures .................................................................... .................................................. 12

4. COMMUNICATION PAYLOAD REQUIREMENTS .................................................................................. 14

4.1 INTRODUCTION ...................................................................................................................................... 14

4.2 SYSTEM REQUIREMENTS .................................................................................................. ...................... 14

4.2.1 LOCATION .................................................... ................................................................ ........................... 14

4.2.2 COVERAGE REQUIREMENTS ............................................................................................... .................... 15

4.2.3 SERVICE ARCHITECTURE ......................................................................................................................... 15

4.2.4 THROUGHPUT REQUIREMENTS ...................................................................... ........................................ 16

4.2.5 SERVICE REQUIREMENTS .................................................................... .................................................... 16

4.2.6 SPECTRUM AVAILABILITY ....................................................................................................................... 16

4.2.7 PAYLOAD SYSTEM CONFIGURATION ......................................................................... ............................. 17

4.2.8 PAYLOAD PERFORMANCE....................................................................................................................... 18

4.3 PRODUCT ASSURANCE............................................................................................................................ 19

4.3.1 MODEL PHILOSOPHY ............................................................................................................. ................. 19 4.3.2 SINGLE POINT FAILURES ........................................................................................................ ................. 19

4.3.3 SUBSYSTEM REDUNDANCY..................................................................................................................... 19

4.3.4 TEST & EVALUATION .............................................................................................................................. 20

4.4 PAYLOAD MASS & POWER BUDGET .................................................... .................................................... 20

4.5 THROUGHPUT ESTIMATION ................................................................................................................... 20

4.6 ADDITIONAL DESIRED FEATURES ............................................................................................................... 20

4.6.1 ON-BOARD FLEXIBILITY ........................................................................................................................... 20

4.6.2 FADE MITIGATION .................................................................................................... .............................. 21

4.6.3 BEAM STEERING CAPABILITY .............................................................................................................. .... 21

4.6.4 MESH CONNECTIVITY ............................................................................................................................. 21

4.7 GROUND SEGMENT ........................................................... ................................................................ ..... 21




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4.7.1 USER TERMINALS ..................................................................... ............................................................... 21

4.7.2 HUB STATIONS ........................................................... ............................................................... .............. 21

4.7.3 ACCESS SCHEMES ................................................................... ............................................................... . 22

4.7.4 GROUND BEACON STATIONS.................................................................................................................. 22

4.7.5 FLUX DENSITY LIMITS ............................................................................................................................. 22

4.7.6 FADE MITIGATION .................................................................................................... .............................. 22

5. REALIZATION PLAN ............................................................................................................................ 23

5.1 SCHEDULE AND ISRO’S PARTICIPATION ..................................................................... .................................. 23

5.2 SPACECRAFT TEST PLAN................................................................................................................................ 23

5.2.1 Subsystem Level Test Plan .................................................................... .................................................. 23

5.2.2 System Level Test Plan ............................................................. ............................................................... 24

5.3 SUPPORT FOR ON-ORBIT OPERATIONS.............................................................................................................. 24 5.4 MANUAL/TECHNICAL DOCUMENTATION.......................................................................................................... 24




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1. SCOPE

In India ISRO has played a big role in establishing a strong communication infrastructure

thus partnering the increasingly vibrant entrepreneurial spirit of India’s business, industrial

and entertainment sectors. In order to enhance and upgrade this infrastructure, ISRO is

planning to implement a new generation of payloads and satellite buses.

In this regard, ISRO is looking for design, development, fabrication and operationalization of

a next generation State of the art high throughput Ka-band communication satellite into the

geostationary orbit.

This expression of interest is sought from bidders to provide their proposals which will aid tofirm up the procurement specifications prior to release of a formal RFP later.

Bidders may note that, all information given by the bidders to ISRO will be kept confidential.

The spacecraft readiness for shipment is required to be a maximum of 36 months from the

date of signing of contract. However bidders may indicate their capability for less than 36

months shipment schedule.

This Expression of Interest defines the work to be performed by bidder and also the required

deliverable hardware, software, documentation and services.

All program, technical documentation and meetings related to this program are required to be

written and held in English.




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2. INTRODUCTION

a. This requirements specifications document is to invite suitable technical proposal

from the interested prospective bidders for the realization of spacecraft and to provide

launch support, and the means of construction of space system, which shall include:

i. A space segment consisting of the satellite;

ii. Technical consultancy for augmentation /up-gradation of ISRO control centre to

meet the operational requirements of proposed spacecraft under procurement.

All project specific hardware and software to be provided by the bidder.

iii. All necessary hardware, software simulators and documentation.

iv. All requirements for the space system for entire term of satellite mission lifewith margin after its acceptance in orbit.

v. All requirements for the space system, which are not dependent on position of

the satellite in the orbit, must be fulfilled regardless of the satellite position in

geostationary orbit.

vi. Considering these requirements, the space system includes all necessary

equipment and software of the space segment and the ground segment.

2.1 SPACECRAFTa. Bidder shall be fully responsible for all the tasks related to development, design,

construction, integration, testing and storage of the spacecraft (as per requirement).

b. The bidder is also responsible for shipment of spacecraft to the launch site, testing at

launch preparation site, all work required in conjunction with the customer selected

Launch Services for launch vehicle compatibility and installation of spacecraft on the

launcher, launch support, orbit raising activities and In Orbit Testing of spacecraft.

c. The bidder is also expected to provide support during subsequent period of on orbit

maintenance of spacecraft. (Duration TBD)

2.2 ASSOCIATED HARDWARE

a. Bidder shall provide all consumables (fluids, propellant etc.) required to build, test,

launch and operationalize the Spacecraft. Sufficient consumables shall be provided to

load the tanks to the maximum allowed tank capacity.

b. Bidder shall ensure that a sufficient amount of spare flight equipment is available to

support the timely Spacecraft realisation and Launch. Bidder shall have a replacement

plan to support unit failures, starting with full system test of the Spacecraft at the




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bidder’s facility, and culminating at the launch. Under no circumstances shall the

bidder be permitted to claim an excusable delay because of the lack of replacementunits.

c. Bidder shall provide Spacecraft handling Ground Support Equipment (GSE) fixtures

and implement operating procedures to ensure that the Spacecraft hardware is not

overstressed during ground handling operations. Customer shall have technical

visibility into the GSE and operating procedures but shall not take delivery of the

GSE. Bidder shall also make available Spacecraft GSE to be used during the pre-

launch phases of the mission and ensure that a sufficient amount of spare GSE

equipment is available at the launch site. In particular, spares need to be available for

all critical equipment required during countdown phase.

2.3 SPACECRAFT HARDWARE TRANSPORTATION AND HANDLING

Bidder shall be responsible for the safe handling and transportation of Spacecraft /

sub-assemblies and equipment within the manufacturer premises and across different

work centers.

2.4 LAUNCH PREPARATION

a. Bidder is responsible for shipping the Spacecraft to customer selected launch base, the

associated launch preparation site equipment, the Spacecraft propellants and

pressurants, the technicians required to perform the work at the launch preparation

site, the required equipment to interface with the launch vehicle and all the required

spacecraft GSE. The Spacecraft shall be shipped to the launch base, with the satellite

fully integrated in a single container.

b. Bidder is responsible for the loading/unloading operations enroute until the spacecraft

preparations facility at launch base.

c. Unloading, loading devices (cranes etc) from the tarmac to the Launch Preparation

Facility and transportation means (trucks, train etc) shall be provided by the Launch

Services Contractor as per agreement with the Customer. Bidder is also responsible

for performing all works at launch site and support the Launch Services Contractor

for all interface requirements to achieve Successful Injection and Spacecraft

separation.

2.5 GROUND CONTROL SYSTEM

a. The Spacecraft In-orbit GSO operations will be controlled from satellite operations

facilities at one of ISRO’s ground stations in India.




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b. Bidder will be responsible for development and installation of the Real-time Software

(RTS) at the customer control center. This RTS will be used for the operationalcontrol of the Spacecraft. The bidder shall provide all technical support to make the

software operational.

c. Bidder shall provide RTS including (but not limited to) the following:

i. Ground to Spacecraft Interface definition

ii. TM/TC Database interpretation and conversion

iii. Spacecraft memory map and adaptation of the RTS on-board processor support

iv. Spacecraft-specific Derived Parameters

v. Interface of the Spacecraft Manufacturer’s Off-line Spacecraft Control Software

to the RTS (if applicable)vi. Interface of the RTS (TM, Ranging and Spacecraft Procedures) with the orbit

operations specifications

vii. Procedures conversion into the RTS Commanding Language

viii. Procedure validation on the RTS hardware

d. Bidder shall be responsible for the design, development, on-site integration, test and

documentation of software and hardware components including (but not limited to)

the following:

i. Any off-line Spacecraft-specific Software not explicitly mentioned, but required

to properly operate the Spacecraft. This includes but not limited to any tools

developed by the manufacturer which would aid in the on-orbit operation of the

satellite such as excel spreadsheet calculations and the like.

ii. Dynamic Satellite Simulator (DSS) software;

iii. Validated TM/TC database

iv. Validated Spacecraft Procedures

v. Specific Orbital Operations software (Orbops) specification.

vi. Transponder Management Software

vii. Set point determination tool

e. The ground related interface specifications of the TT&C and ranging shall be defined

in the appropriate format with the selected bidder.




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3. ISRO SPACECRAFT GENERAL REQUIREMENTS

3.1 MISSION

a. The mission requirement is for one firm ISRO Ka Band High Throughput

Communication Satellite and upon exercise of the relevant option, a repeat satellite,

named ISRO Ka Band High Throughput Communication Satellite (R) for use in a

Geostationary Satellite Orbit (GSO).

b. The Spacecraft has to meet all requirements when operated at an orbital location 55

deg E (To be confirmed) over Indian Ocean Region. The final GEO slot will be

indicated at the time of tendering a formal RFP. However manufacture shall explore

the possibility of operating the same satellite from any GEO slot from 48 deg E to93.5 deg E.

c. The Spacecraft shall be designed to operate with up to eight other collocated

communications satellites within the Customer fleet over the Indian Ocean region.

The Spacecraft design shall incorporate all required filtering in its uplink and

downlink to preclude interference to and from adjacent satellites and other ITU

coordinated RF transmissions. Frequency co-ordination will be carried out by ISRO.

3.2 SPACECRAFT LIFE AND MASS

a. The spacecraft operational life shall be a minimum of 15 years with an additional oneyear margin. The bidder shall also take into account additional life margins across

systems, which are required to meet the spacecraft insurer’s requirements.

b. The Spacecraft design shall be qualified to carry and consume the full capability of its

propellant and pressurant, even if it is not required to meet the spacecraft Life

requirements. Upon request by Customer, Bidder shall provide such propellant and

pressurant up to the maximum capacity of the tanks at no extra cost, even if the

spacecraft Life requirements can be met with less than full tanks.

c. The spacecraft shall be a typical of 6 tones class. The bidder is expected to propose anoptimal dry mass of the spacecraft which meets all functional requirements and

mission life with 3σ performance. The mass estimate shall be justified with proper

explanations. The bidder shall also keep in view the constraint posed by commercially

available launch vehicles.

3.3 LAUNCH VEHICLE COMPATIBILITY

The Spacecraft shall be compatible with the constraints, restrictions, and limitations

imposed by the commercially available launch vehicles. If there are any issues related

to restriction with respect to any launch vehicle, the same shall be brought out. The




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baseline reference for the compatibility requirements with the launch vehicle shall be

the current version of Launch Vehicle Users Manual.

3.4 PRODUCT ASSURANCE

a. ISRO requires that the bidder along with subcontractors establish, implement and

maintain a product assurance program. The program shall include detailed

requirements, policies, objectives, plans and methods of implementation related to (

but not limited to) the following:

i. Reliability assurance

ii. Quality assurance

iii. Parts, materials and processes controliv. Software

v. Testing

vi. Non-conformance control with respect to materials, configuration and tests

vii. Contamination and cleanliness control

viii. Data management, and

ix. Safety.

b. The bidder has to ensure that all hardware and software are designed, manufactured,

tested, stored and delivered to meet the requirements of this program. This shall bedocumented in a product assurance plan.

c. The bidder shall provide details of the product assurance organization and

management proposed for implementation of the product assurance plan.

3.4.1 Part, Material, Process and System Development

a. The bidder shall provide details of the proposed Electrical, Electronic and Electro-

mechanical (EEE) Parts Control program. The part selection, qualification testing,

screening, radiation approach, critical EEE part identification, handling, storage etc.

need to be addressed in the EEE components control plan.

b. Declared Component list shall be prepared which shall include as a minimum

i. Generic designation

ii. Part type, package and value range

iii. Manufacturer (name, country)

iv. Specification reference (generic/detailed)

v. Equipment name(s)

vi. PAD sheet references

vii. Quality level

viii. PAD status




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ix. Radiation test status

c. The bidder’s shall provide details of Radiation Hardness Philosophy proposed. The

following effects shall be taken into account:

i. Total dose

ii. Displacement damage

iii. Single Event Effect (SEU, Latch-up, Burn-out, Gate Rupture and SET)

iv. Enhanced Low Dose Rate Sensitivity (ELDRS) effects

d. The bidder shall provide details of the Materials, Mechanical Parts and processes

Control program proposed. The bidder's program shall be described in the Product

Assurance Plan and will define the requirements for selection, application,

specification, qualification, control and traceability of materials and processes to be

used in satellite equipment. This program shall:

i. Ensure rigorous selection of materials, mechanical parts and processes which can

fulfill the functional requirements during a lifetime compatible with the mission

duration and the specific environmental conditions

ii. Rely on available space proven technologies whenever possible

iii. Identify and control all new products, critical materials, and mechanical parts andprocesses.

e. Bidder shall prepare a declared material list (DML) and declared process list (DPL)

for implementation.

f. The bidder shall provide details of the review process proposed and shall have regular

reviews during the contract phase.

i. Non-conformance Review Boards

ii. Mandatory Inspection Points

iii. Test Readiness reviews/Test Review Boards (TRRs/TRBs)iv. Hardware Delivery Review Board

v. Non-conformances

vi. Parts

vii. Critical Items

viii. Materials and Processes

ix. Software

g. The bidder shall provide details of critical item identification, listing and control

policy proposed.




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h. The bidder shall provide details of the reliability assurance program proposed and listthe reliability analyses, tests and other activities carried out to ensure required

reliability. The reliability analyses shall include (but not be limited to) the following:

i. Failure Modes Effects Analysis

ii. Derating analysis

iii. Hardware software interaction analysis

iv. Reliability apportionment/ reliability prediction

v. Fault tree analysis

vi. Worst case circuit analysis

vii. Availability analysis

viii. Radiation and Single Event Transient (SET) analysis

3.4.2 Product Assurance Plan

a. The bidder shall provide details of the redundancy management philosophy proposed

at component, card, equipment and system level and handling of single point failures

shall be detailed in the product assurance plan.

b. The bidder shall provide details of the quality assurance program for hardware and

software proposed to ensure that adequate quality requirements are established and

achieved and verified throughout all phases of the program. The program shall

describe the detailed requirements and procedures for controlling workmanship

standards during design, quality control during procurement, fabrication, assembly

and integration of hardware, test of hardware and software, reporting and corrective

action for non-conforming items, packing, storing, transportation and launch site

activities. The bidder’s quality assurance program shall be described in the Product

Assurance Plan.

c. The bidder shall provide details of the software product assurance program proposed.

The software product assurance program shall address management issues, life cycleactivities and processes and the product quality aspects. The software product

assurance program shall be compatible with the software engineering approach to be

defined for the project by the bidder.

d. The bidder shall provide details of the configuration and information/documentation

management program proposed. The system shall provide for the control,

identification and verification of all hardware and software related documentation,

and changes there to and accounting for all items of hardware and software within the

program.




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e. The bidder shall provide ISRO with the right to participate in or execute surveys,

audits, reviews, source inspection, test observation, mandatory inspections and any

other activity during the contract, or have resident or itinerant personnel at the plants

of the bidder, Subcontractors, Suppliers and Manufacturers. The participation shall be

during the following phases

i. System Engineering Phase

ii. Design and Development

iii. Manufacture, Assembly, Integration and Test

iv. Preparation for Launch

f. The bidder shall provide details of the development, qualification and acceptance planproposed for flight equipment, subsystems and satellites. The plan shall include ( but

not be limited to ) the following:

i. Qualification Status List

ii. Design and Development Plan

iii. Assembly, Integration and Test Plan

iv. Specification of Environmental Conditions

v. Acceptance Matrix

3.4.3 Model philosophya. The bidder shall provide a heritage matrix for all the equipment proposed for the

project. The model philosophy followed for different equipment shall be in

conformance with the categories listed below.

Category 1: Production equipment requiring no modification which has been

subjected to a qualification test program for space applications at least as severe as

that expected for the project. Further qualification testing is not required.

Category 2: Production equipment requiring no modifications that have already been

tested and qualified but subjected to a different qualification program or to a different

environment. A delta qualification test program shall be decided by ISRO andperformed case by case.

Category 3: Production equipment requiring minor design modifications or has had a

change in components, materials, processes or manufacturing or control procedures.

A delta or full qualification test program shall be decided by ISRO on a case-by-case

basis depending on the impact of the required modification.

Category 4: Newly designed and developed equipment or existing equipment

requiring major re-design. A full qualification test program shall be performed.

Note: The bidder shall include the heritage matrix of the proposed equipment in their

proposal.




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3.4.4 Reviews

a. The bidder shall provide details of the reviews proposed during the development andqualification phase. These reviews shall include (but not be limited to) the following:

i. Equipment Qualification status Review

ii. Baseline Design Review

iii. Critical Design review

b. The bidder shall provide details of the reviews proposed during the manufacturing,

assembly, integration and test phase. These reviews shall include (but not be limited

to) the following:

i. Test readiness reviews prior to equipment, subsystem and spacecraft tests

ii. Test Review board/Hardware Delivery Reviews for Flight Model equipment

iii. Test Review board for subsystem and spacecraft tests

iv. Flight Readiness Reviews for satellite.

c. The bidder may propose a list of reviews, which can be held during the execution of

program.

3.4.5 Test plans and procedures

a. The bidder shall provide details on the functional and environmental tests proposed onequipment, subsystem and spacecraft. The environmental tests shall include (but not

be limited to) the following:

i. Mechanical load test (e.g. static load, acceleration, vibration, acoustic

noise, shock as applicable)

ii. Thermal vacuum tests including temperature cycling

iii. Electric field exposure tests (e.g. EMC, EMI, ESD testing as applicable)

iv. Magnetic field exposure tests as applicable

b. The bidder shall provide the environmental standards to which the equipment,

subsystem and spacecraft are to be tested and provide the compliance in the TRBs.

The environmental standards shall encompass the following:

i. On-ground phase, including manufacture, handling, assembly and integration,

testing, storage and transportation prior to launch

ii. Launch phase, including parking orbit

iii. In-orbit phase, including transfer orbit and drift orbit




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c. The bidder shall provide the test plan and test matrix at equipment, subsystem and

spacecraft level. The bidder shall provide details of the life test proposed for lifelimited equipment. All life limited equipment shall be subjected to life tests to

demonstrate 1.5 times the proposed mission duration.

d. Depressurization and thermal vacuum tests shall be carried out wherever applicable.

Absence of corona or multipaction in RF systems shall also be demonstrated.

e. At the subsystem level, the bidder shall include (but not limited to) the following

tests:

i. Static test for structure subsystem

ii. Bus/Subsystem testsiii. Propulsion system integrated checks

iv. ADCS in loop simulation checks

v. Payload repeater system and antenna system checks

vi. Thermo-elastic distortion tests on antenna subsystem

vii. Harness tests prior to installation

viii. Deployment tests on deployable appendages

f. At the spacecraft level, the bidder shall include the following tests, verification and

measurements (but not limited to):

i. Disassembled mode IST

ii. Spacecraft integrated mode tests

iii. Spacecraft thermovacuum tests

iv. Thermal balance test /Thermal design validation test

v. Appendages Assembly and testing

vi. Spacecraft dynamic tests – sine, random and acoustic noise

vii. CG, MI and alignment tests

viii. Spacecraft EMI/EMC test for launcher compatibility

ix. Polarity tests

x. CATF Tests including Spacecraft level antenna radiation pattern measurements

xi. Spacecraft mass properties measurement

xii. Spacecraft alignment verification

xiii. Deployment checks at spacecraft level

xiv. Pre shipment tests

xv. Pre launch tests




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4. COMMUNICATION PAYLOAD REQUIREMENTS

4.1 INTRODUCTION

a. The objective is to provide a single high throughput platform to support a large

subscriber base for Broadband services. Since the terminals to be supported are

typically USATs, the on-board platform should have coverage performances to

support high data rate services, which calls for a multi-beam architecture with spot

beams covering the desired region. This also allows frequency reuse across the beams

enhancing the overall system throughput within a given spectrum.

b. The proposed system consists of

i. Space Segment: Advanced Multiple-beam High Power Satellite Platform

ii. Ground Segment: Hub Stations, which can perform the functions beyond

switching like Adaptive Coding and Modulation (ACM).

iii. User Segment: New generation user terminals which can be commanded to

adapt.

c. Section 4.2 provides the details regarding the overall communication system

requirements. As a part of proposal, bidder shall address all the aspects related to the

payload under the headings given in section 4.6.

d. Bidder shall also provide the trade-off studies among the technology elements, which

can finally culminate in the proposed system configuration such as optimum number

of spot beams & size to suit frequency re-use color scheme within the allocated

frequency spectrum, minimize gain loss at coverage edge of the antenna beam to close

the user links and maximize throughput generation & capacity, optimum pointing

error budget that loads the spacecraft system, establishing the right balance of the use

of the bandwidth and power in the satellite channel etc.

e. In addition to the advanced on-board technologies that are considered, bidder shall

address the critical issues related to compatibility with the ground system

technologies like applicability of signal structures utilizing advanced modcod, sitediversity for Ka band Hub stations & sizing for fade mitigation along with rain fade

statistics considering Indian tropical rain zones etc.

4.2 SYSTEM REQUIREMENTS

4.2.1 LOCATION

The satellite shall be located at a longitude of 55 degree E (TBD).




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4.2.2 COVERAGE REQUIREMENTS

a. The payload configured shall provide coverage over Indian mainland along with theIslands (Andaman & Nicobar Islands as well as Lakshadweep Islands (as shown in

Figure 4.1).

Figure 4.1: Indian Mainland Plus Island Coverage

b. Bidder may also suggest possibility of providing coverage over Middle East Asia /

Africa / South East Asia to provide connectivity with these regions from Indian

mainland.

c. Additional redundancy/back-up option to be provided for key location (Maximum

four) on Indian land mass having high density traffic.

4.2.3 SERVICE ARCHITECTURE

a. The payload configured shall provide FSS services to multiple users utilizing a Star

based communication network with Forward links (from Hub to user terminals) and

Return links (from User terminals to Hubs) via Satellite.

b. Bidder may suggest possibility of providing direct user-to-user Mesh connectivity via

satellite for delay sensitive applications.




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4.2.4 THROUGHPUT REQUIREMENTS

a. The payload configured shall provide communication to Ultra Small Apertureterminals.

b. The overall throughput shall be of the order of ~50 Gbps. Bidder may suggest the

feasibility of achieving greater than 50 Gbps in their proposal.

4.2.5 SERVICE REQUIREMENTS

a. The satellite shall provide mainly broad band internet services as well as multimedia

services to a number of users. Bidder may also explore the possibility of providing

DTH/HDTV broadcast services over Indian region.

b. The user terminals to be supported by the payload shall have following typical

parameters.

• Terminal Size : 0.45 to 0.8 meters

• Terminal EIRP : < 50 dBW

• Polarization : Circular/Linear

• Data rate support

Uplink : Upto 4 Mbps

Downlink : Upto 10 Mbps

• ModCod support : Multiple modcod structures for ACM support

c. Bidder may propose the feasibility of providing higher data rates based on

technologies likely to be available in future.

d. Mobile user terminal in addition to fixed terminals is a desirable feature. Bidder shall

include this in their proposal.

4.2.6 SPECTRUM AVAILABILITY

4.2.6.1 HUB LINK SPECTRUM

Spectrum available for Hub link operation is 1 GHz (in both polarizations) in the

following band: The spectrum may not be in a continuous band (TBD).

• Uplink Spectrum : 27.00 - 31.00 GHz

• Downlink Spectrum : 17.70 - 21.20 GHz




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4.2.6.2 USER LINK SPECTRUM

Spectrum available for User link operation is 500 MHz × 2 (including bothpolarizations) in the following band (TBD):

• Uplink Spectrum : 29.50 - 30.00 GHz

• Downlink Spectrum : 19.70 - 20.20 GHz

4.2.7 PAYLOAD SYSTEM CONFIGURATION

Bidder shall provide the configuration details required for catering the service

requirements mentioned in the previous section (Section 4.2.5) in addition tofollowing.

4.2.7.1 NUMBER OF USER BEAMS

Bidder shall propose the number of user beams covering the region specified in

Section 4.2.2 catering to the service links as specified in Section 4.2.5.

4.2.7.2 NUMBER OF HUB BEAMS

Bidder shall propose the number of hub beams, their locations as well as their

connectivity requirements which will cater to star based communication to the user

beams as specified in Section 4.2.5.

4.2.7.3 COMMUNICATION ARCHITECTURE

Bidder shall define the communication architecture describing the forward and return

links between hub and users for Star and mesh connectivity.

4.2.7.4 SPECTRUM PER USER BEAM

Bidder shall specify usable bandwidth per user beam for both forward and return

links.

4.2.7.5 SPECTRUM PER HUB BEAM

Bidder shall specify usable bandwidth per Hub beam for both forward and return

links.

4.2.7.6 SPECTRUM RE-USE

Bidder shall specify frequency as well as polarization reuse factor as per spectrum

allocation per beam as specified in Section 4.2.6.




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4.2.7.7 PAYLOAD CONFIGURATION

Bidder shall provide detailed block diagram illustrating the configuration for thetransponders indicating all the individual subsystems.

4.2.7.8 ANTENNA CONFIGURATION

Bidder shall provide details of the proposed antenna system configuration and the

proposed on-board RF sensing /tracking scheme needed to achieve the required beam

stability.

4.2.7.9 POINTING ERROR

All coverage performance requirements shall be met under worst case pointing error

conditions, including eclipse and maneuver transients. Bidder shall also provide thedetailed pointing error budget.

4.2.7.10 RF SUBSYSTEMS

Bidder shall provide details of the RF subsystems such as technology, major

specifications, packaging, heritage etc for major RF elements as per the performance

requirement.

4.2.8 PAYLOAD PERFORMANCEBidder shall specify major parameters to define the payload performance as defined

below in Table 4.1.

Table 4.1: Payload Performance Parameters

S.N. Performance Parameter Remarks

1 EIRP per transponder

• To be specified for Forward & Return link

transponders.

• Flux density levels over the specified coverage

should not exceed the limits recommended byITU.

2 G/T per beam

• To be specified for User as well as Hub beams

• A uniform brightness temperature value of 290

K shall be assumed for the calculation of

antenna G/T performance

3 Saturation Flux Density

• The nominal SFD shall be adjustable over a

dynamic range of 20 dB minimum in the step

of one dB. The accuracy of SFD shall be

defined by the bidder.




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4 Receiver performance

• Frequency Stability over operating temperature

range, over a month and over mission lifetimemeeting the technical requirements of services.

• Phase noise at different frequency offsets

meeting the technical requirement of services.

5 Frequency Response

• For forward and return link transponders with

the applicable bandwidths.

• Near-band and Wideband Transmit & Receive

rejection requirements.

6 Noise Power Ratio• Bidder to specify NPR levels for operation

under multicarrier conditions.

7 Performance stability• EIRP Stability

• Gain Stability

4.3 PRODUCT ASSURANCE

Bidder shall provide probability of survival of the Payload system to ensure reliable

satellite operation for a minimum period of 15 years with one year margin. Whenever

non-recurring hardware needs to be used in order to meet the performance

requirements, priority should be given to redundancy and to maintain high stress

margins between the utilization of the hardware and its capability.

4.3.1 MODEL PHILOSOPHY

Bidder shall propose the model philosophy for hardware subsystems based on the

heritage and bring out the qualification requirements, if any.

4.3.2 SINGLE POINT FAILURES

a. All active components shall have on board redundancy.

b. The Spacecraft shall have no electrical and electronic component with single point

failure. This requirement applies to parts, harness, printed circuit boards, connectors

and all other electrical paths in the design of the Payload. The Payload design shall

provide sufficient redundancy for all electrical and electronic components to meet the

reliability goal.

4.3.3 SUBSYSTEM REDUNDANCY

Bidder shall propose the redundancy configuration of the following active subsystems

and any other systems deemed necessary by bidder:




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i. LNAs : [to be provided by Bidder]

ii. Down-converters : [to be provided by Bidder]

iii. HPAs : [to be provided by Bidder]

4.3.4 TEST & EVALUATION

Bidder shall provide the test methodology to be followed at system as well as

subsystem level to ensure the reliable operation of the communication payload over

mission lifetime.

4.4 PAYLOAD MASS & POWER BUDGET

a. Bidder shall provide estimate of payload mass & power budget giving breakup for

different subsystems.

b. Also bidder shall specify the estimated thermal dissipation for the payload.

4.5 THROUGHPUT ESTIMATION

a. Bidder shall provide estimation for total throughput along with supporting link

analysis considering the terminals parameter as in section 4.2.5, as applicable to the

Indian Tropical climatic conditions for rain fade. Hub link and user link availability to

be maintained at a minimum of 99.9 % and 99.6 % respectively.

b. The throughput of 50 Gbps projected in Section 4.2.7 is the minimum requirement.

However bidder may propose payload configuration options providing higher

throughput.

4.6 ADDITIONAL DESIRED FEATURES

4.6.1 ON-BOARD FLEXIBILITY

Bidder may suggest on-board re-configurability of the payload for providing

flexibility as per dynamic service requirements, e.g.:

a. Demand based beam-wise bandwidth assignment flexibility for users in High/low

traffic density.




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b. Demand based beam-wise power assignment to get higher throughput in high traffic

region by appropriate power sharing between beams.

c. Dynamic allocation of higher power to higher rain/higher traffic regions.

d. Addition capacity/redundancy to serve/protect the high traffic metro beams

(maximum four)

4.6.2 FADE MITIGATION

Bidder may suggest fade mitigation techniques to cater to the tropical fade conditions

over Indian region to maintain the specified user and hub availability. The suggested

fade mitigation techniques should cater to fade impairments for user as well as hub

links. Bidder may also propose possible modification in payload/ground hardware to

support certain fade mitigation techniques.

4.6.3 BEAM STEERING CAPABILITY

Bidder may suggest possibility of steering some of the spot beams to provide

flexibility in coverage over certain regions.

4.6.4 MESH CONNECTIVITY

Bidder may suggest provision of providing mesh connectivity among user beams

using transparent/regenerative processor.

4.7 GROUND SEGMENT

Bidder shall suggest the supporting ground segment options to meet the throughput as

well as availability requirements as mentioned in the previous sections. Bidder shall

provide options as under in the following subsections:

4.7.1 USER TERMINALS

Bidder shall suggest various user terminal options in terms of terminal sizes, HPAsize, data rate supported, modcod supported, and services (i.e. voice, data, fax, video

etc) which can be supported by the communication payload. Bidder will also include

provision for a mobile terminal in their proposal.

4.7.2 HUB STATIONS

Bidder shall suggest the configuration of Hub stations in terms of number of hubs,

station sizes, HPA size, data rate and modcod to be supported etc. Bidder may also

suggest Inter-hub connectivity requirements for a unified star network over the region.




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4.7.3 ACCESS SCHEMES

Bidder shall suggest signal multiplexing schemes as well as transponder multipleaccess schemes and suitable network protocols for both forward and return links.

4.7.4 GROUND BEACON STATIONS

Bidder may propose the requirement of uplink beacon stations, if required, for on-

board antenna pointing system.

4.7.5 FLUX DENSITY LIMITS

Bidder shall provide the flux density calculations and their compliance with the ITU-

recommended limits for Transmission as well as reception

4.7.6 FADE MITIGATION

Bidder may suggest possible fade mitigation techniques like ULPC, ACM, Site

diversity etc. applicable to Hub/User terminals to cater to the tropical fade conditions

over Indian region to maintain the specified availability in Section 4.5.




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5. REALIZATION PLAN

5.1 SCHEDULE AND ISRO’S PARTICIPATION

a. Bidder must fabricate the above satellite and execute the whole cycle of all testing

leading to the stage of launching the satellite within a maximum of 36 months from

the date of signing of contract. However bidders may indicate their capability for less

than 36 months shipment schedule.

b. Period for satellite acceptance is the flight acceptance test by the Manufacturer after

the satellite launch and in orbit successful performance demonstration.

c. Manufacturer shall specify the time line of the contract execution cycle e.g.translation of mission requirements to system/subsystem requirements/specifications,

PDR, CDR, Integrated Test Plan etc. Customer’s participation and approval is

mandatory during major milestones.

d. ISRO shall get fully involved during the System Engineering, configuration

finalization, design, development, fabrication and AIT stages of spacecraft. This

means an active interaction and participation of manpower from ISRO during various

phases of spacecraft building. The activities like overall configuration finalization ,

design drivers, system level definitions and configuration ,build plan and process shall

be well coordinated , and understood by ISRO team . This may also include somediscussions and knowledge sharing on latest technology domains. It is foreseen that a

full time participation of a few engineers from ISRO is required during the entire

spacecraft realization period. ISRO engineers will be stationed at selected

manufacturer’s premises and should have access to ongoing activities. The bidder

shall clearly express their approach on the subject and also propose a mechanism for

execution of the same.

5.2 SPACECRAFT TEST PLAN

The bidder shall submit Spacecraft subsystem and system level test plan/test

procedure for customer approval.

5.2.1 Subsystem Level Test Plan

a. A typical subsystem level test sequence shall minimally include all the tests as

detailed in section 3.4.5.

b. All primary and redundant functions shall be tested, even in the case of redundancy

internal to the Unit. These tests shall be done to ensure proper subsystem to

subsystem interfaces to ensure appropriate performance of each bus subsystem at the

earliest possible level.




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5.2.2 System Level Test Plan

The Spacecraft shall be subjected to a system Level test program that includes all thetests required to assess the performance of the Spacecraft and its subsystems .The

details are provided in section 3.4.5.

5.3 SUPPORT FOR ON-ORBIT OPERATIONS

Before the launch of spacecraft, the manufacturer must carry out all necessary cycle of

training of personnel of the Customer for correct operation of ISRO spacecraft. The

bidder is also expected to provide support during subsequent period of on orbit

maintenance of spacecraft. (Duration TBD)

5.4 MANUAL/TECHNICAL DOCUMENTATION

Before the start of the ground testing of ISRO I6K spacecraft the bidder should

provide the Customer with all necessary technical documentation in English.

Customer reserves the right to clarify the content and composition of manual technical

documentation after its delivery.




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DEFINITIONS AND ABBREVIATIONS

ADCS

ALCAttitude Determination Control System Automatic Level Control

AM/FM Amplitude Modulation/Frequency Modulation

C/I

CATF

CDR Carrier-to-interference ratio

Compact Antenna Tests Facility

Critical Design Review

CSM

DSS

Communication System MonitoringDynamic Satellite Simulator

DVB-RCS DVB Return Channel over SatelliteDVB-S/S2ELDRS

Digital Video Broadcasting SatelliteEnhanced Low Dose Rate Sensitivity

EIRPEOI

Effective Isotropically Radiated PowerExpression of Interest

FGM Fixed Gain Mode

G/T Gain-to-noise-Temperature

HDTV High Definition TV

HPA High-Power Amplifier

IBO Input Backoff

MCPC Multi Channel Per CarrierNPR Noise-Power Ratio

OFR Orbital Frequency Resource

OOS

RFP

RTS

PAD

PDR

Off-Optimum Situations

Request for Proposal

Real Time Software

Part Approved Document

Preliminary Design Review

RTCC Reserve Terrestrial Control Center

SCPC

SETSEU

Single Channel Per Carrier

Single Event TransientSingle Event Upset

SFD Saturation Flux DensitySS

TBD

Space System

To Be Decided

TDM Time-Division Multiplexing

TDMA Time-Division Multiple Access

TCC Terrestrial Control Center

VSAT Very Small Aperture Terminal



GUIDELINES FOR BIDDERS

CONFIDENTIAL – ISRO Proprietary

GENERAL INSTRUCTIONS TO BIDDERS

1. Structure of the Response

These Guidelines have been prepared to assist Bidders in generating the proposals in

response to the ISRO Expression of Interest (EOI). ISRO reserves the right to revise the

requirements as may evolve based on interaction with bidder during evaluation of EOI. The

bidders should have extensive experience in the industry in building various spacecraft

platforms, State of Art Communication Payloads and operational experience in High

Throughput Ka Band Communication Satellites.

The cost of preparing proposals in response to this EOI shall be borne solely by the bidders

and the release of this EOI does not bind any financial or other obligation on the part of ISRO.

ISRO reserves the right to consider the bidder in the RFP Process for the whole or any part of

the work defined in the EOI, ISRO also reserves the right not to float the RFP.

2. Notice of Intention to Submit Proposals

All Bidders intending to submit proposals are requested to notify ISRO apriori by fax, letter

or e-mail to the following address:

Head, Purchase and StoresISRO Satellite Centre, Old Airport Road

Bangalore – 560017, India

Ph No. : +918025084004/+918025084369

Fax : +918025205283/+918025205284

E-mail : [email protected]

Notifications must also include the name of the point of contact, together with the appropriate

fax number and e-mail address.

3. Clarifications Concerning the EOI

Clarifications concerning the EOI may be submitted by fax or e-mail to the ISRO contact

point indicated below.

Head, Purchase and Stores

ISRO Satellite Centre, Old Airport Road


Ph No. : +918025084004/+918025084369

Fax : +918025205283/+918025205284


Bidders are requested not to contact ISRO for information on the progress or possibleoutcome of the evaluation.



4. Submission of Proposals

Complete proposals must be received by the ISRO at the address given below, not later than

the date specified in the EOI cover letter.

Head, Purchase and StoresISRO Satellite Centre, Old Airport Road


Ph No. : +918025084004/+918025084369

Fax : +918025205283/+918025205284


5. Proposed Calendar of Events

SL No. Event Target Date

1 Release of EOI 06t November, 20122 Last date to submit the Proposal 20

tDecember, 2012

6. Presentation of Proposals

Proposals in response to this EOI shall be submitted in electronic form along with two sets of

Hard copy.

Bidders are also requested to provide a transmittal letter, signed by an authorised company

official, with respect to the technical commitments made in the proposal.

All parts of the proposal and communications relating thereto shall be in English.

All parts of the proposal shall adopt the metric system for unit of measurements, e.g. meter

(m), kilogram (kg), second (s) etc.

7. Evaluation Criteria

The evaluation criteria used by ISRO to determine the acceptability of proposals at any stage

and eventual technical discussion with one or more selected bidders will include but notlimited to the following:

• Compliance of proposal with requirements set forth in this EOI.

• Previous experience including major sub-contractors and equipment suppliers with

equivalent contracts/deliveries having demonstrated substantial heritage in-orbit.

• Design margins in each and every subsystem

• Typical Delivery schedule

• Satellite operational lifetime,

• Compatibility with all suitable commercially available launch vehicles

• Any other points of relevance to this EOI



8. Validity Period of Proposals

The proposals shall remain valid for a period of 6 months from the closing date of submission

of proposals.

9. Retention of Proposals/Proprietary Information/Confidentiality

All documents submitted in response to the EOI shall become the property of ISRO. Any

information in such documents, which is proprietary to the bidder, should be specifically

identified as such. Proprietary information shall not be deemed to include information that is

obtainable from another source or is or becomes available in the public domain.

Notwithstanding the foregoing, ISRO may disclose proposals, including proprietary

information, to appropriate personnel selected by ISRO for evaluation purposes.

All information contained in this EOI is proprietary information of ISRO and is protectedunder Indian law.

All the information contained in this EOI is confidential and cannot be disseminated to third

parties or used by any recipient of this EOI for any purpose other than answering to this EOI.

No public statement or press release shall be issued by the recipient regarding this EOI, the

information contained within, or the EOI process without the prior written authorization of

ISRO.

10. GENERAL INSTRUCTIONS FOR THE TECHNICAL PROPOSAL

The Bidder is free to select any specific structure of the Technical Proposal that is suitable to

present information in the clearest possible manner. However, to ensure a minimum level of

details and to facilitate the task of proposal evaluation, several self contained sections or

appendices should be produced to address the following topics as a minimum for which the

requirements are given below.

1. Satellite Design

2. System Budgets and Analyses

3. Payload Design and Communication Analyses

4. Launcher compatibility5. Hardware Status

6. Realisation Schedule

7. Satellite Operations

8. LEOP

9. Product Assurance

10. Applicable Standards

11. Compliance to EOI

12. Alternative proposals

Documents

ISRO Ka-Band High Throughput Communication Satellite [India]