Fine Sun Sensor Requirements Specificationemits.sso.esa.int/emits-doc/ASTRIUMLIM/GAIA_FSS/GAIA.ASU.SP.ES… · Gaia GAIA.ASU.SP.ESM.00016 Issue 1 Page 5 of 53 Astrium Ltd owns the

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Document Autogenerated from DOORS Module : /GAIA Prime/Level 4/4_15 Sun Sensor RS/FSS Fine Sun Sensor Requirements Specification.doc

Fine Sun Sensor Requirements Specification

CI CODE: 13210 DRL Refs : EN-3

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Rated By :

Prepared by: Date:

Checked by: Date:

Approved by: Date:

Authorised by: Date:

This document is produced under ESA contract, ESA export exemptions may therefore apply. These Technologies may require an export licence if exported from the EU

© Astrium Limited 2006

Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated

to any person without written permission from the owner.

Astrium Limited, Registered in England and Wales No. 2449259 Registered Office: Gunnels Wood Road, Stevenage, Hertfordshire, SG1 2AS, England

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Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.

Fine Sun Sensor Requirements Specification.doc

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CONTENTS 1 Introduction and Scope ..............................................................................................................................5

1.1 Introduction..........................................................................................................................................5 1.2 Scope ..................................................................................................................................................5 1.3 Summary Description..........................................................................................................................5

2 DOCUMENTS ............................................................................................................................................7 2.1 Applicable Documents ........................................................................................................................7 2.2 Reference Documents ........................................................................................................................7

3 Functional and Performance Requirements...............................................................................................8 3.1 Reference frames definition ................................................................................................................8

3.1.1 FSS Alignment reference frame definition ...................................................................................8 3.1.2 FSS Measurement reference frame definition.............................................................................8

3.2 FSS FoV..............................................................................................................................................8 3.3 Performance........................................................................................................................................9

3.3.1 Performance Requirement Conditions.........................................................................................9 3.3.2 Output ........................................................................................................................................10 3.3.3 Measurement Errors ..................................................................................................................11

3.4 FDIR ..................................................................................................................................................12 4 Unit Specific Design and Interface Requirements ...................................................................................14

4.1 Mechanical Design and Interface Requirements ..............................................................................14 4.1.1 Mass...........................................................................................................................................14 4.1.2 Finite Element Model .................................................................................................................14

4.2 Thermal Design and Interface...........................................................................................................14 4.3 Electrical Design and Interface .........................................................................................................14

4.3.1 Power Interface..........................................................................................................................14 4.3.2 Power Consumption...................................................................................................................14 4.3.3 Interface to Satellite Data Handling ...........................................................................................14 4.3.4 Analogue Interface.....................................................................................................................15 4.3.5 Harness......................................................................................................................................15 4.3.6 Test Equipment..........................................................................................................................15

5 General Design and interface Requirements ...........................................................................................17 5.1 General Design Requirements..........................................................................................................17

5.1.1 Lifetime ......................................................................................................................................17 5.1.2 Reliability....................................................................................................................................17 5.1.3 GDIR Applicability ......................................................................................................................17

5.2 Mechanical ........................................................................................................................................17 5.3 Thermal .............................................................................................................................................17 5.4 Electrical............................................................................................................................................17 5.5 Identification and Marking .................................................................................................................17

6 Verification Requirements ........................................................................................................................18 7 Product Assurance Requirements ...........................................................................................................19 8 Acronyms..................................................................................................................................................20 9 GDIR Applicability Matrix..........................................................................................................................21

FIGURES Figure 3.1-1: Unit Axis Systems ........................................................................................................................8 Figure 3.2-1: Definition of Sun Angles...............................................................................................................9

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1 INTRODUCTION AND SCOPE

1.1 Introduction

This document establishes the design, performance, interface and verification requirements of the Fine Sun Sensor (FSS) for the Attitude & Orbit Control Subsystem on board the Gaia spacecraft.

The Gaia mission (global astrometric interferometer for astrophysics) is one of the cornerstone projects in the ESA scientific program.

The prime objective of Gaia is to provide Astrometric measurements of all (approx 1 billion) objects to 20 mag, with multi-colour multi-epoch photometry and radial velocities for objects brighter than 16-17 mag. Accuracies are better than 10 micro-arcsecond at 15 mag. The envisaged experiment operations principle is a continuous scanning of the sky on great-circles with constant inclination to the Sun. Mainly because of the high thermal stability requirements, the current orbit baseline, a Lissajous orbit around the L2 Libration point in the Earth-sun system has been selected.

1.2 Scope

The document in hand comprises the requirements and constraints for the Gaia Fine Sun Sensor. This includes:

• the performance as well as design and interface requirements of subject hardware;

• the product assurance requirements;

• the testing and verification requirements.

Requirements within this document are shown in an italic font. Each requirement is proceeded by a summary line that contains the following fields, delimited by "/".

• <Doors Requirement Number> FSS-xyz. This is a unique number, assigned consecutively

• <Created From> Shows parent requirement

• <Test Method> T= Test, A = Analysis, I = Inspection, R = Review of Design, D = Definition (if more than one Test Methods is specified, this means that a combination of them is required).

Requirement Text - If tables are considered as part of requirement they are referenced clearly in the text and inserted after and separated from the requirement.

Upper Links - The trace to the upper level requirements shall be managed with the following format:

AAA-NNNN where AAA is a label associated to the upper document and NNNN the requirement identifier of this upper level.

Or CREATED key word if the requirement has no link with upper level

All document elements, which are not presented in the format explained above are not requirements and will not be verified or tracked.

In references to GDIR requirements the section number is provided for information only. If there is any conflict between the GDIR requirement number and the section number then the requirement number takes precedence

1.3 Summary Description

The FSS will be used in the AOCS for attitude measurement in Sun Acquisition Mode (SAM), and as an Attitude Anomaly Detector for all phases of the mission.

Gaia will have 3 electrically independent 2-axis sun sensors operated in hot redundancy using a Triple-Majority Voting (TMV) approach in s/w to achieve a combined 'failure free' sun direction measurement. This specification recognises that both single string and internally redundant configurations are available and either configuration (e.g. 3 off single string Sun sensors or 2 off internally redundant Sun sensors) is acceptable for Gaia as long as the electrical independence and continuous simultaneous operation requirements are respected.

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One Fine Sun Sensor is understood here as the FSS detector assembly, optical components and mechanical field of view baffles plus the potentially necessary electronics, interfacing to the EIU.

If not otherwise specified, the performance and characteristics given hereafter are applicable for the whole life time, including ground and flight periods, for every bus voltage in the specified range and after the unit have been subjected to any specified combination of environmental and local conditions.

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2 DOCUMENTS

2.1 Applicable Documents

The following publications form a part of this document to the extent specified herein. Unless an issue is quoted for a document, the current issue is deemed to apply. When an issue is quoted, that issue and no other must be used.

AD-1 Gaia General Design & Interface Requirements

Gaia.ASF.SP.SAT.00002

AD-2 Gaia Finite Element Modelling Requirements

Gaia.ASD.SP.SAT.00007

AD-3 Gaia Thermal Modelling Specification


AD-4 Gaia Product Assurance Requirements For Subcontractors


AD-5 CAD Data Exchange Requirement Specification


2.2 Reference Documents

The following publications do not form part of this specification but were used during its preparation.

RD-1 Hypotheses for AOCS Analysis

Gaia.ASF.TCN.SAT.00009

RD-2 Gaia FSS Usage and Performance Requirements TN

Gaia.ASU.TCN.ESM.00009

RD-3 Gaia E-SVM Requirements Specification


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3 FUNCTIONAL AND PERFORMANCE REQUIREMENTS

3.1 Reference frames definition

3.1.1 FSS Alignment reference frame definition

FSS-38/GDI-176/I,R

Each FSS box that houses the FSS Optical Head shall include an optical reference cube for the purpose of aligning the FSS onto the spacecraft. The location of the optical reference cube mounting shall be agreed with EADS Astrium.

FSS-327/GDI-188/R

The normals to three of the optical cube faces shall be used to form a right handed Cartesian reference frame, the Alignment Reference Frame (OXYZ_unit_aP) as shown in Figure 3.1-1

+X_unit_mP

+Z_unit_aP

O_unit_aP

+X_unit_aP

+Y_unit_aP

O_unit_mP

+Y_unit_mP

+Z_unit_mP

Figure 3.1-1: Unit Axis Systems

3.1.2 FSS Measurement reference frame definition

FSS-328/CREATED/R

The FSS Optical Head shall employ a right handed Cartesian reference frame that shall be able to provide measurement range for the sun angles such that the FSS FoV requirements are satisfied. This shall be designated as the FSS Measurement Reference Frame.

FSS-41/CREATED/R

The FSS supplier shall deliver all transfer matrix data necessary for converting from the FSS Alignment reference frame to the FSS Measurement reference frame.

FSS-316/CREATED/R

The delivered transfer matrix referred cited in the requirement above shall be measured after all the environmental tests performed during the acceptance phase.

Measurement uncertainties affecting the transfer matrix must be delivered with the transfer matrix.

FSS-3154/CREATED/T,A

The alignment error between the measurement reference frame and the alignment reference frame shall be smaller than 0.25° (TBC) in each axis including all launch, 0g, outgassing and thermo-elastic effects.

3.2 FSS FoV

FSS-548/CREATED/R

The FSS shall determine the angle of the incoming parallel light (sun light) in two orthogonal directions, α and β (see Figure 3.2-1 in which OXYZ_unit_mP is the FSS measurement reference frame as defined in FSS-328 for an example of how α and β might be defined). The FSS supplier shall propose a clear definition for α and β in the FSS measurement reference frame.

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The operational FoV is understood as the α by β rectangular range in which the FSS outputs allow the determination of the sun direction w.r.t. the measurement reference frame to the accuracy required by this specification.

α

β

+X_unit_mP O_unit_mP

+Y_unit_mP

+Z_unit_mP

Figure 3.2-1: Definition of Sun Angles

FSS-3116/RD-2/T,A

The operational FoV of an FSS unit shall be at least ±62° on each orthogonal measurement axis.

3.3 Performance

3.3.1 Performance Requirement Conditions

The performance requirements relate to the angular measurement of sun direction that can be recovered by the appropriate processing of the raw FSS outputs by the S/C Central SoftWare (CSW). For sensors providing an analogue output, the performance requirements shall apply assuming A to D conversion of the sensor raw outputs over 12-bits will have the characteristics specified in section 3.5.5.6.2, AD-1 with the exception that 'noise' shall be assumed to be <2mV rms (rather than <8mV rms).

3.3.1.1 General


The performance requirements of the unit or units shall be met under worst case BOL and EOL conditions, in the presence of all known effects influencing the performance except Earth Albedo below an altitude of 20000km from the Earth. Such effects include (where appropriate), but are not restricted to, environmental, launch loads, spacecraft dynamic conditions, orientation in the celestial sphere, ageing, nominal radiation environment, sensor bias, sensor noise, quantisation, temperature effects, unit conversion factor errors, 1g to 0g effects and SEU's

The constraints on the FSS behaviour of Earth Albedo below an altitude of 20000km are addressed in section 3.3.3.3.

3.3.1.2 Dynamic conditions

FSS-3152/RD-2/T,A

The FSS shall meet the performance requirements with S/C rates of up to 1.5°/s around any axis in the FSS measurement reference frame.

FSS-3232/RD-2/T,A

Sun direction measurements with degraded performance w.r.t. the requirements shall be provided for S/C rates up to 4.5°/s around any axis in the FSS measurement reference frame.

The supplier shall provide an initial analysis of the sensor performance under the stated dynamic condition in their proposal submission.

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3.3.1.3 Operating environments

FSS-3153/RD-1/T,A

The FSS shall offer nominal performance (not including Earth Albedo effects) over sun intensity range from Earth Altitude of 2900Km to 1.8 million Km towards the Earth-Sun system L2 Lagrange Point.

FSS-3129/RD-3/T,A

The accuracy requirements shall be met in the presence of the Sun intensity variation due to a 20% lunar eclipse at L2 Lagrange point.


The accuracy requirements shall be met assuming all spacecraft structural elements are at least 69° (TBC) away from the FSS line of sight.

3.3.1.4 Calibration


No in flight calibration shall be required, but accuracy can be met after on-board processing with ground-measured calibration data. The calibration data shall be provided by the supplier for each unit.

FSS-3130/CREATED/R

If the FSS does not directly output the Sun angles, the supplier shall provide a clear algorithm description of the on-board processing necessary to recover the Sun direction angles from only the raw FSS output in the proposal.

3.3.2 Output


The measurement performance requirements shall include any effect due to conversion from raw output to final angle measurements.


The FSS shall provide a Sun Presence (SP) signal (either as an explicit SP signal, or data such that the CDMU can generate an SP) when the sun is in the FoV as specified above.

For an explicit SP signal, either Bi-level or analogue signal interfaces are acceptable.

FSS-3209/CREATED/R

The FSS shall output such signals as are necessary to determine the general health of the unit independently of the sun direction related outputs.

FSS-3219/CREATED/R

The FSS shall output a temperature measurement.

FSS-3210/CREATED/T,R

The temperature measurement output shall be in accordance with AD-1 (Both thermister terminals isolated).

FSS-3211/RD-2/T

The FSS shall provide measurement output within 5 seconds after the necessary secondary voltages are applied.


If the sensor incorporates an externally controlled multiplexer, a valid signal shall be available on the analogue output line within 2ms (TBC) of the MUX address being selected by appropriate voltage application on the MUX control lines.

In this context "valid" shall be understood as the MUX output signal being equal to the selected input signal to within the steady-state performance of the MUX. If the proposed equipment is able to achieve full read-

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out accuracy faster than 2ms, the supplier shall identify the minimum achievable read-out delay in their proposal.


The measurement signal latency between the application of solar illumination from a given angle and the corresponding signal voltage availability at the input to the output multiplexer shall be less than 2ms (TBC).

3.3.3 Measurement Errors

3.3.3.1 Bias

FSS-1583/RD-2/T

The total bias (including alignment knowledge but excluding Earth Albedo) between the actual and measured sun angles shall not be greater than 0.17°(3σ) in each axis of the FSS measurement reference frame across the entire operational FoV.

3.3.3.2 Noise error

FSS-3118/RD-2/T,A

The Noise Equivalent Angle (NEA) error (excluding Earth Albedo) in each axis shall not be greater than 0.08°(3σ) across the entire operational FoV.

FSS-3237/CREATED/T

The supplier shall supply representative measurement data sets of the sensor output noise behaviour by measuring direct outputs from sensor electronics as a function of time at a number of fixed sun positions across the FoV. The locations in the FSS FoV to be tested, and hence the number of necessary test cases, shall be agreed with Astrium however it is anticipated that no more than 15 cases will be sufficient to adequately characterise any variation in noise properties across the sensor FoV.

Each measurement data set shall span at least 2000 sec with a fixed sample time who's value shall be no greater than 0.025 sec, using test equipment which introduces acceptably small additional filtering and noise. The data sets shall be supplied to Astrium in an electronically readable format to be agreed with Astrium.

The objective of this requirement is to gain a clear and detailed understanding of the FSS output signal noise characteristics in order to be able to determine what additional filtering (in either H/W or S/W) might be appropriate to further improve the quality of the Sun angle measurement recovered from the FSS. The FSS supplier is welcome to propose alternative test scenarios that will better characterise the noise behaviour of their product.

3.3.3.3 Albedo

FSS-3120/RD-2/T,A,R

Under no circumstances at an Earth altitude greater than 2900km shall it be possible for the FSS to deliver a false positive Sun Presence signal (as defined by FSS-3123) due to Earth Albedo.

FSS-4200/RD-2/T,A,R

The impact of the Earth Albedo on the accuracy of the sun direction determination shall not be greater than 5°(TBC)(3σ) in all axes above altitude of 2900km and below altitude of 20000km.

FSS-4201/RD-2/R

Earth and Moon Albedo contribution to FSS measurement accuracy at Earth (and Moon) altitudes of 20000km and above shall be included in the errors considered when assessing compliance to the performance requirements given in sections 3.3.3.1 and 3.3.3.2.

FSS-3233/RD-2/T,A

The FSS supplier shall characterise the Earth Albedo effect over the Earth altitude range given in FSS-3153.

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First issue of this analysis shall be provided in proposal submission.

FSS-4202/RD-2/T,A

The FSS supplier shall characterise the Moon Albedo effect over the moon altitude range of 2900km to 20000km.

First issue of this analysis shall be provided in proposal submission.

3.3.3.4 Linearity

FSS-3119/RD-2/T,A

The local slope of the actual (input) angle to the measured angle shall not vary by more than 1.5% from unity over the whole FoV, as defined by the following equations:

| dα (measured ) / dα (actual ) -1 | < 0.015

and

| dβ (measured ) / dβ (actual ) -1 | < 0.015

FSS-3234/RD-2/T,A

The cross-coupling between the orthogonal sensor measurement angles shall be less than 1.5 % over the whole FoV, as defined by the following equations:

| dα (measured ) / dβ (actual ) | < 0.015

and

| dβ (measured ) / dα (actual ) | < 0.015

The actual sun angle changes (dα (actual ) and dβ (actual )) for calculating the linearity and cross-coupling as described above shall not be greater than 0.1° (TBC).

3.3.3.5 Quantisation

FSS-3121/RD-2/T,A

The FSS angle measurement quantisation in each axis shall be better than 0.02° (TBC, equivalent to 1 bit change) when considering the digitisation performance described in section 3.3.1.

3.4 FDIR

FSS-639/ERS-165/T,A,R

For the configuration that the main and redundant FSS are assembled in one box, there shall be no possibility of failure propagation between the main and redundant electronic units. The operations of the two FSS shall be completely independent.

FSS-3225/CREATED/T,A,R

If the main and redundant FSS are assembled in one box, it shall be possible to operate both main and redundant FSS continuously for the entire mission whilst still meeting the reliability figure in FSS-3078 for each main and redundant FSS.

FSS-641/CREATED/R

Health status telemetry provision in the unit shall be clearly described at the time of the proposal.

FSS-1410/CREATED/R

The precise failure coverage and reliability of the health status telemetry shall be fully described.

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4 UNIT SPECIFIC DESIGN AND INTERFACE REQUIREMENTS

4.1 Mechanical Design and Interface Requirements

4.1.1 Mass

FSS-173/CREATED/T

For an internally redundant configuration, the complete FSS mass per redundant head in flight configuration shall be less than 0.7 kg (TBC). For a single string FSS, the complete FSS mass per unit shall be less than 0.4 kg (TBC). This shall be verified by mass measurement on the fully assembled unit.

4.1.2 Finite Element Model

A finite element model of the FSS shall be provided by the supplier to sufficient detail to allow assessment of the thermo-elastic distortion effects between the FSS and the mounting fixtures. The FEM shall be sufficiently detailed to allow prime to assess the impact from the thermo-elastic distortion in relation to the measurement performance requirements cited in Section 3.3.

FSS-1947/CREATED/R

The FEM requirements in section 9 and AD-2 and AD-3 shall apply to the FEM provided.

4.2 Thermal Design and Interface

FSS-181/CREATED/T,A

The maximum thermal dissipation of one active FSS shall not exceed TBD W.

FSS-635/CREATED/R

The actual thermal dissipation characteristics exhibited by each FSS element shall be provided by the supplier for use in the thermal budget. The first issue of this information shall be provided in the proposal.

FSS-1923/CREATED/R

The thermal control of the FSS shall be feasible through mainly passive radiative dissipation and limited conductive dissipation.


The thermal environment cited in section 4.3.2 (TBC) of AD-1 shall be assumed for analysis of the performance requirements in section 3.3. The supplier shall quantify the contribution of the worst case thermal elastic distortion to the total bias and characterise its temperature dependence.

4.3 Electrical Design and Interface

4.3.1 Power Interface

FSS-651/CREATED/T,A

The FSS shall operate with DC voltages (TBD V) conditioned in the EIU.

4.3.2 Power Consumption

FSS-3136/CREATED/R

The average power consumption of each FSS while in "on" state shall be less than 0.3W (TBC) at normal operation.

4.3.3 Interface to Satellite Data Handling

FSS-3144/AD-1/R

If the unit is Off-The-Shelf product, the supplier shall give a detailed description of the data interface(s).

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4.3.4 Analogue Interface

FSS-3146/AD-1/R

If the unit uses analogue interface(s), it shall comply with the standard requirements specified in section 9.

4.3.5 Harness

All power and signal interfaces between the FSS and other units and subsystems will be made via the harness subsystem.

FSS-573/CREATED/R

The FSS shall interface with other units and subsystems via connectors only (in accordance with the GDIR requirements as identified in section 9).

FSS-4205/CREATED/R

Power and signal connectors shall be separate.

FSS-4213/CREATED/R

If the unit has an internally redundant configuration, the redundant functions shall use independent power and signal connectors.

4.3.6 Test Equipment


In order to support closed loop testing, the unit shall have provisions to be electrically stimulated through a separate connector which bypasses the detector(s). The supplier shall delineate the stimulus interface and describe the stimulation signal characteristics. The stimuli input shall be DC coupled.

The supplier is asked to identify in their proposal what interface standards they are able to support.

FSS-3176/CREATED/R

The blanking caps for the simulation interface connector shall be removable.

FSS-3177/CREATED/R

The FSS shall meet all of the requirements specified herein with a test harness, 5m in length, connected to the FSS test connector.

This harness will be connected to the spacecraft skin connector.


The presence of the stimulation interface when no stimulation is applied shall not affect the performance of the FSS.


At spacecraft level, the test harness cited in requirement FSS-3177 will be connected to the FSS electronics stimulation interface and routed to the spacecraft skin connector. This harness, which may be up to 5m long, may be left in situ for flight and therefore the FSS shall meet the requirements of this specification with this harness in situ.

FSS-3181/CREATED/R

Requirements for termination of the in situ test harness shall be defined by the supplier.


The stimulation signal shall be independent of the sensor signal so that no compensation will be required for ground test.

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The FSS shall survive fault voltages on test stimulus inputs (28V TBC) and also during S/C AIV on any test pin.

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5 GENERAL DESIGN AND INTERFACE REQUIREMENTS

5.1 General Design Requirements

5.1.1 Lifetime

FSS-1671/ERS-32/ERS-643/T,A

The unit shall perform without degradation,

• On ground = 4 years

• During Transfer + operational lifetime = 5.5 years

5.1.2 Reliability

FSS-3078/CREATED/A,R

The reliability of an individual FSS shall be higher than 0.9967 over 5 years in flight.

5.1.3 GDIR Applicability

The FSS shall be designed to withstand the environmental requirements specified in AD-1. See details in GDIR Applicability matrix Section 9.

The FSS shall comply with the general design requirement of AD-1. See details in GDIR Applicability Matrix Section 9.

5.2 Mechanical

The FSS shall comply with the mechanical design requirements of AD-1. See details in GDIR Applicability Matrix Section 9.

5.3 Thermal

The FSS shall comply with the thermal design requirements of AD-1. See details in GDIR Applicability Matrix Section 9.

5.4 Electrical

The FSS shall comply with the electrical design requirements of AD-1. See details in GDIR Applicability Matrix Section 9.


The unit shall not show any malfunction or deviation from the specified performance when irradiated with the following E-fields:

X band Transmitter 8450 - 8500 MHz : 45 V/m

5.5 Identification and Marking

FSS-2001/CREATED/I,R

A nameplate shall mark the unit hardware in order to achieve configuration traceability. The identification shall be made in accordance with the requirements of AD-1.

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6 VERIFICATION REQUIREMENTS

FSS-2004/CREATED/T

Equipment verification shall be performed in accordance with the detailed requirements contained within the specification and AD-1 and AD-4.

FSS-4210/CREATED/R

Open loop polarity checks will be performed during spacecraft AIV using a standard AIT light source.

The supplier shall define any operational constraints that must be considered for this approach.

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7 PRODUCT ASSURANCE REQUIREMENTS

FSS-2006/CREATED/R

The FSS shall be designed, manufactured and tested in accordance with the PA requirements specified in AD-4.

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8 ACRONYMS

Acronyms for Gaia project are defined in TBC.

Additional acronyms are as follows:

AOCS Attitude and Orbit Control System

BOL Beginning Of Life

CDMU Control and Data Management Unit

CSW Central SoftWare

CoG Centre of Gravity

EIU Electrical Interface Unit

EOL End Of Life

EU Electronic Unit

FDIR Failure Detection, Isolation and Recovery

FoV Field of View

FSS Fine Sun Sensor

NEA Noise equivalent angle

PAA Phased Array Antenna

SEU Single Event Upset

SP Sun Presence

TBC To Be Confirmed

TBD To Be Decided

TC Telecommand

TMV Triple Majority Voting

TV Thermal vacuum

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9 GDIR APPLICABILITY MATRIX

The following table lists the applicable requirements of the GDIR.

It contains, in the first column, the Local ID for each applicable GDIR requirement number.

The second column contains the GDIR Requirement number and the opening text of the requirement.

The third column defines the Applicability Y/N

The final column shows the intended verification method

Where no specific verification method is shown, this means method is TBD at this time. It shall be assumed that an appropriate verification method will be applied.

Req No. Reference Applicability Verif. Method

3 General Design and interface Requirements 3.1 General Design Requirements 3.1.1 Lifetime FSS-3243 GDI-31:

The on-ground lifetime of flight hardware is defin ... Y R

FSS-3244 GDI-32: The Unit shall meet the requirements of this speci ...

Y A,R

FSS-3245 GDI-33: The in-orbit lifetime of the satellite is defined ...

Y R

FSS-3246 GDI-34: The unit shall be designed with positive margins o ...

Y A,R

FSS-3247 GDI-2700: The units shall be compatible with a storage perio ...

Y

FSS-3248 GDI-35: Maintenance during storage shall be as limited as ...

Y R

3.1.2 Design Safety FSS-3250 GDI-37:

The unit shall be designed and fabricated with com ... Y A

FSS-3251 GDI-38: General safety requirements for units are as follo ...

Y A

3.1.3 Venting FSS-3253 GDI-41:

The unit shall be able to operate within a pressur ... Y A,R

FSS-3254 GDI-42: For all relevant thermal hardware, explicitly MLI, ...

Y R

FSS-3255 GDI-43: Unless a cavity is hermetically sealed adequate me ...

Y R

FSS-3256 GDI-44: Structural members (honeycomb panels, in particula ...

Y T,A

3.1.4 Interchangeability FSS-3258 GDI-46:

All spacecraft units of the same part or configura ... Y R

3.1.5 Identification & Marking FSS-3260 GDI-50:

The unit hardware shall be identified with a namep ... Y I

FSS-3261 GDI-2253: The unit identification nameplate shall be mounted ...

Y

FSS-3262 GDI-2254: For the particular case of connector identificatio ...

Y

3.1.6 Accessibility/Maintainability FSS-3264 GDI-52:

The design of the unit, the position of the connec ... Y R

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FSS-3265 GDI-53: The equipment shall be designed to require a minim ...

Y R

FSS-3266 GDI-54: No field maintenance, servicing or adjustment shal ...

Y R

3.1.7 Transportation, Handling and Storage 3.1.7.1 Transport FSS-3269 GDI-2272:

The unit containers, covers (for optics and expose ... Y

FSS-3270 GDI-2273: The transport container shall ensure that the envi ...

Y

FSS-3271 GDI-2274: The storage container shall be designed to protect ...

Y

3.1.7.2 Unit packing FSS-3273 GDI-2275:

Where applicable blanking caps shall be fitted to ... Y

FSS-3274 GDI-2276: All units shall be packaged to ensure that it is s ...

Y

3.1.7.3 Container identification FSS-3276 GDI-2277:

Each container shall be labelled, tagged or marked ... Y

FSS-3277 GDI-2278: In addition to the above, the container shall also ...

Y

3.1.7.4 Handling FSS-3279 GDI-2271:

Units weighing more than 10 kg shall be equipped w ... Y

3.1.7.5 Thermally Conductive Materials FSS-3281 GDI-70:

Unless justified and agreed beforehand, any therma ... Y I,R

3.1.7.6 Magnetic Materials 3.1.7.7 Seals FSS-3284 GDI-75:

Any seals used shall comply with all the applicabl ... Y R

FSS-3285 GDI-76: Any seals requiring periodic replacement during gr ...

Y R

3.1.7.8 Lubricants and Sealants FSS-3287 GDI-78:

No lubricants shall be used without the prior writ ... Y R

3.1.7.9 Screw Locking FSS-3289 GDI-80:

All fasteners used on the unit shall be locked by ... Y I,R

FSS-3290 GDI-2270: All screw type hardware used on the unit shall be ...

Y

3.2 Mechanical Design and Interface Requirements FSS-3292 GDI-82:

All drawings, specifications and engineering data ... Y R

FSS-3293 GDI-83: Units shall be compliant with ECSS-E30 Part 2A, an ...

Y R

FSS-3294 GDI-84: Following testing the unit shall be inspected to c ...

Y I

FSS-3295 GDI-87: No unit shall generate microvibration loads at its ...

Y A,R

3.2.1 Structural Design 3.2.1.1 General Requirements

Gaia


Page 22 of 53




FSS-3298 GDI-91: The following failure modes, for units at all leve ...

Y A

FSS-3299 GDI-92: The unit shall be designed to withstand the enviro ...

Y A,R

FSS-3300 GDI-2282: The design of the units handling and transportatio ...

Y

FSS-3301 GDI-94: Wherever practical a fail safe design based on red ...

Y A

FSS-3302 GDI-95: In cases where a failsafe design cannot be impleme ...

Y A

FSS-3303 GDI-2045: All potential fracture critical items shall be sub ...

Y A

3.2.1.2 Mass properties FSS-3305 GDI-2284:

A mass justification shall be provided indicating ... Y

FSS-3306 GDI-98: All mass estimations shall be accompanied by the d ...

Y T

FSS-3307 GDI-100: The mass of an item must be measured with the foll ...

Y T

3.2.1.3 Centre of Gravity and Moment of Inertia FSS-3309 GDI-102:

All COG and MOI estimates shall be accompanied by ... Y A

FSS-3310 GDI-104: The unit centre of gravity shall be determined wit ...

Y T,A

FSS-3311 GDI-105: The unit moment of inertia shall be determined wit ...

Y A

3.2.1.4 Stiffness requirement 3.2.1.4.1 Definitions and General Requirements FSS-3314 GDI-2288:

Units fixed on a rigid interface shall have their ... Y

FSS-3315 GDI-2289: The stiffness requirements shall be demonstrated t ...

Y

3.2.1.4.2 Mechanical Analysis FSS-3317 GDI-2539:

Finite Elements Models (FEM) shall be prepared to ... Y

FSS-3318 GDI-2540: The adequacy of the FEM to predict thermo-elastic ...

Y

FSS-3319 GDI-2541: The FEM of the represented item in its launch conf ...

Y

FSS-3320 GDI-2542: The FEM of the equipment shall be verified and cor ...

Y

FSS-3321 GDI-2544: Reduced FEM mathematical models to be employed in ...

Y

FSS-3322 GDI-2546: Adequate models to calculate Centre of Mass and Mo ...

Y

3.2.1.5 Strength Requirements 3.2.1.5.1 Definitions and General Requirements FSS-3325 GDI-2354:

The design load factor philosophy of the GAIA spac ... Y

FSS-3326 GDI-2366: GAIA equipment mechanical testing shall take into ...

Y

FSS-3327 GDI-2367: GAIA equipment mechanical testing shall take into ...

Y

Gaia


Page 23 of 53




FSS-3328 GDI-2368: An additional Protoflight Factor of Safety, FOSPF ...

Y

3.2.1.5.2 Margin Of Safety & Safety Factors FSS-3330 GDI-2370:

For all Gaia elements the design factor, FOSD = 1. ... Y

FSS-3331 GDI-2371: Where design loads are generated using FE analyses ...

Y

FSS-3332 GDI-2372: The GAIA hardware shall be able to withstand, with ...

Y

FSS-3333 GDI-2375: All mechanical elements shall demonstrate positive ...

Y

FSS-3334 GDI-2380: The margins of safety for all elements of the unit ...

Y

FSS-3335 GDI-2381: All bolts shall be sized to prevent sliding under ...

Y

FSS-3336 GDI-2502: Initially conservative friction coefficients regar ...

Y

FSS-3337 GDI-2382: Wherever applicable, rules for general design of b ...

Y

FSS-3338 GDI-2383: In addition, in case of combined loads due to ther ...

Y

FSS-3339 GDI-2385: where T, S and M are applied values including safe ...

Y

FSS-3340 GDI-2386: Method for evaluation of dimensioning loads/stress ...

Y

FSS-3341 GDI-129: The units shall be designed with positive margins ...

Y A

FSS-3342 GDI-130: The design loads for the structure elements are to ...

Y A

FSS-3343 GDI-131: The internal loads (thermo elastic, pre-stressed m ...

Y A

FSS-3344 GDI-132: For the computation of the design loads the maximu ...

Y A

FSS-3345 GDI-2297: For sine and random vibrations, the mechanical siz ...

Y

3.2.1.6 Alignment and Stability FSS-3347 GDI-2550:

The stability of the equipment shall comply with r ... Y

FSS-3348 GDI-2548: The following causes of misalignment shall be anal ...

Y

3.2.2 Design Requirements 3.2.2.1 Attachment Requirements FSS-3351 GDI-160:

For the preliminary determination of the requested ... Y A

FSS-3352 GDI-161: The attachment points shall provide a controlled s ...

Y I,R

FSS-3353 GDI-162: The interface plane flatness of a unit shall be be ...

Y I

FSS-3354 GDI-163: The mechanical mounting interface shall be consist ...

Y R

FSS-3355 GDI-164: The unit bolts type and number shall be defined to ...

Y R

FSS-3356 GDI-165: Unless otherwise specified all units shall be thro ...

Y I,R

Gaia


Page 24 of 53




FSS-3357 GDI-2132: To minimise CoG uncertainty of the unit when mount ...

Y I,R

FSS-3358 GDI-168: Unless special conditions override, the thickness ...

Y I,R

FSS-3359 GDI-169: For the unit mounting, provision shall be made for ...

Y I,R

FSS-3360 GDI-2123: Unit Lug/Hole Design Requirements: Unit mounting h ...

Y I,R

FSS-3361 GDI-170: Sufficient clearance shall be allowed between mech ...

Y I,R

FSS-3362 GDI-171: Requirement deleted ...

Y A

FSS-3363 GDI-173: Fasteners shall be procured and tested according t ...

Y I

FSS-3364 GDI-2599: Fasteners shall comply with the requirements of EC ...

Y

FSS-3365 GDI-2600: Fasteners smaller than diameter 5 mm shall not be ...

Y

FSS-3366 GDI-2598: Titanium alloy fasteners shall not be used in safe ...

Y

FSS-3367 GDI-174: The Flight equipment shall be able to survive:- - ...

Y A

3.2.2.2 Alignment Requirements FSS-3369 GDI-176:

Units requiring alignment with an accuracy better ... Y R

FSS-3370 GDI-177: Optical references are required to withstand all t ...

Y R

FSS-3371 GDI-178: Location of optical references for units shall be ...

Y R

FSS-3372 GDI-179: The alignment errors shall be included in pointing ...

Y R

FSS-3373 GDI-180: Units which require alignment accuracy of ±0.25° o ...

Y R

3.2.2.3 Electrical connectors FSS-3375 GDI-2302:

All electrical connectors shall be located at a mi ... Y

FSS-3376 GDI-2303: Connectors shall be arranged in such a way that th ...

Y

FSS-3377 GDI-2304: Unit shall offer means to mechanically lock male a ...

Y

3.2.3 Mechanical / Optical Interface Control Documents FSS-3379 GDI-183:

The mechanical and optical configuration and its i ... Y A

FSS-3380 GDI-184: Interfaces will be subjected to a formal inspectio ...

Y T,I

FSS-3381 GDI-185: The issues of ICDs have to be released as defined ...

Y A

FSS-3382 GDI-186: One of the attachment holes on a unit shall be spe ...

Y R

FSS-3383 GDI-187: The unit reference frame shall have its origin at ...

Y R

Gaia


Page 25 of 53




FSS-3384 GDI-188: The unit alignment reference frame shall have its ...

Y R

FSS-3385 GDI-190: The dimensioning of the attachment hole pattern sh ...

Y A

FSS-3386 GDI-191: Interface Control Drawings shall be provided to th ...

Y R

3.2.4 Mechanical Mathematical Model Requirements 3.3 Thermal Design and Interface Requirements 3.3.1 Definition of Temperatures and Terms 3.3.1.1 Radiatively Controlled Unit FSS-3391 GDI-239:

In the frame of GAIA, all units shall be radiativ ... Y R

3.3.1.2 Conductively Controlled Unit FSS-3393 GDI-241:

All units which were conductively controlled in pr ... Y R

3.3.1.3 Isothermal Unit FSS-3395 GDI-244:

For radiative units the temperature difference bet ... Y R

FSS-3396 GDI-245: For conductive units the temperature difference be ...

Y R

FSS-3397 GDI-246: For units not fulfilling GDI-244/245 additional th ...

Y R

3.3.1.4 Temperature Reference Point (TRP) FSS-3399 GDI-248:

The temperature reference point (TRP) shall be sel ... Y R

3.3.2 Thermal Interface Requirements 3.3.2.1 Conductive Interface FSS-3402 GDI-252:

The mounting interface shall comply with the mecha ... Y A

FSS-3403 GDI-253: Unit mounting areas shall not be painted or anodis ...

Y R

FSS-3404 GDI-254: All units dissipating significantly through their ...

Y R

FSS-3405 GDI-255: Local heat flux shall not be greater than 1.5x spe ...

Y A

3.3.2.2 Radiative Interface FSS-3407 GDI-258:

Units shall be designed with an emittance > 0.8 (b ... Y R

FSS-3408 GDI-2582: Units shall demonstrate compliance to their design ...

Y

3.3.2.3 Internal Temperature Monitoring FSS-3410 GDI-260:

Temperature monitoring of selected points within a ... Y R

FSS-3411 GDI-261: The location, type and electrical interface of all ...

Y R

3.3.3 Thermal Design Requirements FSS-3413 GDI-2657:

The units shall take into account the following de ... Y

FSS-3414 GDI-263: The units shall be designed such that all internal ...

Y A

FSS-3415 GDI-264: Hot spots on the external surface of the unit are ...

Y A,R

FSS-3416 GDI-2656: In the absence of any uncertainty analysis an init ...

Y

Gaia


Page 26 of 53




FSS-3417 GDI-2079: For units located outside of the Focal Plane Assem ...

Y A,R

3.3.4 Thermal Control 3.3.4.1 General FSS-3420 GDI-2555:

The equipment thermal control shall comply with EC ... Y

FSS-3421 GDI-2556: The equipment thermal control shall be achieved pr ...

Y

FSS-3422 GDI-2557: The equipment thermal control design shall permit ...

Y

FSS-3423 GDI-2558: The equipment thermal control must be testable on ...

Y

FSS-3424 GDI-2559: If special equipment is required to evacuate the h ...

Y

FSS-3425 GDI-2560: No thermal control item shall prevent the spacecra ...

Y

FSS-3426 GDI-2561: Deviations and temporal degradations from the nomi ...

Y

FSS-3427 GDI-2562: A Thermal Reference Point (TRP) shall be defined a ...

Y

FSS-3428 GDI-2563: The TRP temperature also called "interface tempera ...

Y

FSS-3429 GDI-2564: In addition, the TRP temperature shall be monitore ...

Y

FSS-3430 GDI-2565: The equipment thermal control shall include and mo ...

Y

FSS-3431 GDI-2566: The design limits of units are equal to the qualif ...

Y

FSS-3432 GDI-2567: The design limits of units are equal to the accept ...

Y

3.3.4.2 Thermal Analysis FSS-3434 GDI-2552:

Mathematical models in ESARAD and ESATAN shall be ... Y

FSS-3435 GDI-2553: The Geometrical and Thermal Mathematical Models (G ...

Y

3.3.5 Thermal Interface Control Documents FSS-3437 GDI-267:

All thermal hardware mounted on the unit shall be ... Y R

FSS-3438 GDI-269: All unit thermal interfaces shall be described wit ...

Y R

3.3.6 Thermal Mathematical Model Requirements 3.3.6.1 Thermal Interface Modeling FSS-3441 GDI-2091:

The use of the ESARAD and ESATAN software packages ... Y A,R

FSS-3442 GDI-272: The Thermal mathematical model shall be provided f ...

Y A

FSS-3443 GDI-273: Units: All units used in thermal models (geometric ...

Y A

3.3.6.2 Thermal Model Correlation FSS-3445 GDI-275:

The detailed thermal model of a unit shall be veri ... Y T,A

3.3.6.3 Reduced Thermal Model

Gaia


Page 27 of 53




FSS-3447 GDI-277: The consistency between reduced and detailed therm ...

Y A

FSS-3448 GDI-278: The convergence of the thermal models shall be dem ...

Y A

3.4 Optical Design and Interface Requirements 3.4.1 Optical Design Requirements 3.4.1.1 General Optical Design FSS-3452 GDI-282:

For each optical surface, the physical dimension s ... Y R

3.4.1.2 Materials FSS-3454 GDI-284:

Glass types and material quality shall be selected ... Y R

FSS-3455 GDI-285: The use of stain sensitive glasses shall be avoide ...

Y R

FSS-3456 GDI-286: The use of optical cements shall be avoided as far ...

Y R

3.4.1.3 Coatings FSS-3458 GDI-289:

Metallic layers of the coatings, if any, shall be ... Y R

FSS-3459 GDI-290: Thermo-optical properties of the coatings shall be ...

Y R

FSS-3460 GDI-292: High efficiency anti-reflective coatings shall be ...

Y R

FSS-3461 GDI-293: Sensitivity of coatings to polarisation effects as ...

Y T,R

3.4.1.4 Performances FSS-3463 GDI-295:

The optical performance of the unit shall be verif ... Y T

FSS-3464 GDI-296: Alignment and interface with regard to other optic ...

Y T

3.4.2 Optical Interface Requirements FSS-3466 GDI-298:

The unit supplier shall provide the optical interf ... Y R

FSS-3467 GDI-299: The free mechanical aperture of optical surfaces s ...

Y R

FSS-3468 GDI-300: In addition to specific requirements mentioned in ...

Y R

3.4.3 Optical Mathematical Model Requirements FSS-3470 GDI-302:

The unit supplier shall use an optical model for n ... Y A

FSS-3471 GDI-303: The numerical model shall be developed preferably ...

Y A

3.5 Electrical Design and Interface Requirements 3.5.1 General Requirements FSS-3474 GDI-308:

All electrical performances are specified under Wo ... Y R

FSS-3475 GDI-309: Beginning-Of-Life criteria shall be derived by the ...

Y R

3.5.2 Power Interface Requirements (LC & FC) FSS-3477 GDI-2046:

The design of the FCLs and of all essential loads ... Y T,A

3.5.2.1 Regulated Power Requirements FSS-3479 GDI-338:

All units connected to the fully regulated bus sha ... Y T,A

Gaia


Page 28 of 53




FSS-3480 GDI-2104: The spacecraft fully regulated bus shall have a no ...

Y T,R

FSS-3481 GDI-2103: For load changes of up to 50% of the nominal load ...

Y T,R

FSS-3482 GDI-2133: The bus voltage shall remain within 5% of its nomi ...

Y T,R

FSS-3483 GDI-339: If undervoltage protection is implemented by the l ...

Y T

FSS-3484 GDI-340: In case of an inductive load, when considering the ...

Y T,A

FSS-3485 GDI-341: The load shall not be irreversibly degraded for an ...

Y R

FSS-3486 GDI-342: No fuse protection shall be implemented. ...

Y R

FSS-3487 GDI-343: Primary current protection shall not be implemente ...

Y R

FSS-3488 GDI-344: The contractor shall design the load side of the L ...

Y T,R

FSS-3489 GDI-346: All power converters shall be designed to allow op ...

Y T

FSS-3490 GDI-347: The free-running frequency shall be limited to ±10 ...

Y T

FSS-3491 GDI-348: The as designed free-running frequency and frequen ...

Y T

FSS-3492 GDI-349: Units connected to LCL's or FCL's shall be designe ...

Y T,A

FSS-3493 GDI-1273: At the point of regulation, the impedance of the v ...

Y T,R

FSS-3494 GDI-352: The contractor shall design his side of the Regula ...

Y T,R

FSS-3495 GDI-354: Following switch-ON, and during input filter charg ...

Y T,R

3.5.2.2 Power Consumption Requirements FSS-3497 GDI-361:

The compliance versus the power allocations shall ... Y T,A

FSS-3498 GDI-362: For each power interface circuit, the following co ...

Y T,A

FSS-3499 GDI-363: A power consumption test shall be required at temp ...

Y T,R

3.5.2.3 Tolerance to Power Bus Failures FSS-3501 GDI-365:

When a unit is internally redundant, and the suppl ... Y T,A

3.5.2.4 Initial Electrical Status FSS-3503 GDI-367:

Upon application of power in nominal conditions al ... Y T

3.5.2.5 Special Case: Secondary Power Supplied Units FSS-3505 GDI-370:

It shall be possible to switch on the source unit ... Y T

FSS-3506 GDI-371: The source unit shall be protected against short-c ...

Y T

FSS-3507 GDI-372: The supplied unit and Electrical I/F shall withsta ...

Y T,A

3.5.3 Standard Signals 3.5.3.1 General Conventions

Gaia


Page 29 of 53




FSS-3510 GDI-378: Specified driver (or source) characteristics shall ...

Y R

FSS-3511 GDI-379: All data and signal interface drivers shall surviv ...

Y T,A

FSS-3512 GDI-380: The unit shall tolerate active signal I/Fs when un ...

Y T,A

FSS-3513 GDI-381: In case the electrical architecture does foresee c ...

Y T,R

FSS-3514 GDI-382: In case no load is specified, the characteristics ...

Y R

3.5.3.2 Harness Capacitance FSS-3516 GDI-391:

Interface signal drivers shall consider the capaci ... Y A

3.5.4 Connectors General Design Requirements 3.5.4.1 Harness FSS-3519 GDI-395:

Cables falling into different EMC classifications ... Y I,R

FSS-3520 GDI-396: All cable bundles shall be routed as close as poss ...

Y I,R

FSS-3521 GDI-397: In wiring through connectors all leads shall be ke ...

Y I,R

FSS-3522 GDI-398: The DC resistance between the single cable shield ...

Y T

FSS-3523 GDI-399: The structure termination of shields shall be made ...

Y I,R

3.5.4.2 Connector Types FSS-3525 GDI-401:

All connectors mounted on units shall be D*MA** co ... Y R

FSS-3526 GDI-402: All flight connectors shall be designed to withsta ...

Y I,R

FSS-3527 GDI-2158: Individual mate/demates shall be recorded in a mat ...

Y R

FSS-3528 GDI-2157: The number of times flight connectors are mated / ...

Y R

FSS-3529 GDI-2156: If by prior agreement with S/C Prime the number of ...

Y I,R

FSS-3530 GDI-403: Different connector classes shall be implemented i ...

Y R

3.5.4.3 Connector Characteristics FSS-3532 GDI-405:

Connectors at interfaces shall be clearly identifi ... Y R

FSS-3533 GDI-406: Connectors shall not be a source of single point f ...

Y R

FSS-3534 GDI-407: Equipment or structure-mounted connectors shall be ...

Y R

FSS-3535 GDI-408: Male and female connectors shall be mechanically l ...

Y R

FSS-3536 GDI-409: Active lines together with their return shall be o ...

Y I

FSS-3537 GDI-410: Connectors shall be made of Non magnetic material ...

Y R

FSS-3538 GDI-411: For any unit connector which contains a number of ...

Y T,R

Gaia


Page 30 of 53




FSS-3539 GDI-412: Nominal and redundant lines shall have separated c ...

Y R

3.5.4.4 Connector Mounting FSS-3541 GDI-414:

All electrical connectors shall be located at a mi ... Y R

FSS-3542 GDI-415: Connectors shall be arranged in such a way that th ...

Y R

FSS-3543 GDI-416: Mechanical methods in conjunction with identificat ...

Y I,R

FSS-3544 GDI-417: Connector savers shall be utilized on all flight s ...

Y R

FSS-3545 GDI-418: The connection shield ground pin to case shall be ...

Y R

3.5.4.5 Test Connectors FSS-3547 GDI-420:

Test connectors shall have sufficient protection t ... Y R

FSS-3548 GDI-421: Test connectors shall be protected by EMC metal co ...

Y I,R

FSS-3549 GDI-422: The metallic protection cover shall be capable of ...

Y R

3.5.5 Standard Interfaces 3.5.5.2 MIL-STD-1553 Bus Interfaces (MIL) FSS-3552 GDI-426:

Each data bus subscriber equipment shall comply wi ... Y R

FSS-3553 GDI-427: All units (BC or RT) shall be configured in long s ...

Y R

FSS-3554 GDI-2177: The maximum length of the long stub shall be 6 met ...

Y I,R

FSS-3555 GDI-2176: Only one RT shall be connected to a stub cable. ...

Y I,R

FSS-3556 GDI-428: Each BC and RT (N&R) shall be connected to both 15 ...

Y I,R

FSS-3557 GDI-429: Each stub shall be grounded inside each RT or BC d ...

Y R

FSS-3558 GDI-430: The RT address shall be programmable on an externa ...

Y R

FSS-3559 GDI-431: The 1553-bus shall be connected on separate connec ...

Y R

FSS-3560 GDI-2139: The 1553-bus shall be connected on separate connec ...

Y R

FSS-3561 GDI-1198: Unless otherwise agreed with the Prime Contractor, ...

Y R

FSS-3562 GDI-432: The 1553-Bus Protocol shall be compliant to the Ga ...

Y R

FSS-3563 GDI-434: The unit shall be compatible with the setup as def ...

Y R

3.5.5.2.1 BC/RT Test Requirements 3.5.5.2.1.1 Qualification Test FSS-3566 GDI-2460:

For each part assessed as already qualified, the s ... Y

FSS-3567 GDI-2462: These tests shall be performed only in ambient con ...

Y

FSS-3568 GDI-2463: ...

Y

Gaia


Page 31 of 53




FSS-3569 GDI-2464: ...

Y

FSS-3570 GDI-2465: ...

Y

FSS-3571 GDI-2466: ...

Y

FSS-3572 GDI-2467: ...

Y

FSS-3573 GDI-2468: ...

Y

FSS-3574 GDI-2469: ...

Y

FSS-3575 GDI-2470: ...

Y

FSS-3576 GDI-2471: ...

Y

FSS-3577 GDI-2472: ...

Y

FSS-3578 GDI-2473: ...

Y

FSS-3579 GDI-2474: ...

Y

FSS-3580 GDI-2475: ...

Y

FSS-3581 GDI-2476: ...

Y

FSS-3582 GDI-2477: ...

Y

FSS-3583 GDI-2478: ...

Y

FSS-3584 GDI-2479: ...

Y

FSS-3585 GDI-2480: Note 1: Functional test through 1553B interface ...

Y

FSS-3586 GDI-2481: ...

Y

3.5.5.2.1.2 Acceptance Test FSS-3588 GDI-2485:

... Y

FSS-3589 GDI-2486: ...

Y

FSS-3590 GDI-2487: ...

Y

FSS-3591 GDI-2488: ...

Y

FSS-3592 GDI-2489: ...

Y

FSS-3593 GDI-2490: ...

Y

FSS-3594 GDI-2491: ...

Y

FSS-3595 GDI-2492: ...

Y

Gaia


Page 32 of 53




FSS-3596 GDI-2493: ...

Y

FSS-3597 GDI-2494: Note 1: Functional test through 1553B interface ...

Y

3.5.5.3 Standard Balanced Digital link (SBDL) FSS-3599 GDI-438:

The SBDL link interface is dedicated to serial dig ... Y T,R

FSS-3600 GDI-1201: The contractor shall design his side of the Standa ...

Y T,R

3.5.5.4 UART Serial Link (USL) FSS-3602 GDI-450:

The UART RS-422 serial link shall be composed of t ... Y R

FSS-3603 GDI-451: The UART RS-422 Serial Link Interface shall be imp ...

Y R

FSS-3604 GDI-452: The contractor shall design his part of the UART R ...

Y R

FSS-3605 GDI-453: Figure GDI-456 shows an example for data transmiss ...

Y R

FSS-3606 GDI-1274: The OBC shall be able to send commands on the Tran ...

Y T

FSS-3607 GDI-1275: No data repetition mechanism in both directions sh ...

Y T

FSS-3608 GDI-1276: Command messsages sent by the OBC to the user and ...

Y T

3.5.5.5 Timing Pulses 3.5.5.5.1 Synchronisation or Datation Pulses (PPS) FSS-3611 GDI-460:

The Pulse Per Second (PPS) Interface shall be impl ... Y R

3.5.5.6 Housekeeping Analog Acquisitions FSS-3613 GDI-471:

The interface shall consist of a differential link ... Y R

3.5.5.6.1 Analogue Telemetry Aquisition (AN1) FSS-3615 GDI-1205:

Analogue Telemetry Acquisition -5V to +5V Interfac ... Y T,R


Analogue Telemetry Acquisition 0V to +5V Interface ... Y T,R


Analogue Telemetry Acquisition -10V to +10V Interf ... Y T,R

3.5.5.7 Temperature Acquisitions (ANY, ANP, ANF, ANT) FSS-3621 GDI-482:

The signal shall be transmitted via twisted shield ... Y R

FSS-3622 GDI-483: The temperature aquisition interface circuitry, as ...

Y R

3.5.5.7.1 Thermistor Type1: YSI-44907/-44908 (ANY) FSS-3624 GDI-1215:

Temperature Acquisition Type 1: YSI 44907/YSI-4490 ... Y T,R

3.5.5.8 Relay Commands (SHP, EHP, SLP) FSS-3626 GDI-493:

The High Power On/Off Command source shall be refe ... Y R

FSS-3627 GDI-494: The High Power On/Off Command receiver shall be is ...

Y R

Gaia


Page 33 of 53




FSS-3628 GDI-495: The High Power On/Off Command receiver shall be eq ...

Y R

FSS-3629 GDI-496: The High Power On/Off Command source shall be shor ...

Y R

FSS-3630 GDI-1220: The Standard High Power On/Off Command interface s ...

Y R

3.5.5.8.1 Standard High Power On/Off Command (SHP) FSS-3632 GDI-497:

Standard High Power On/Off Command: The contractor ...

Y T,R

3.5.5.8.3 Standard Low Power On/Off Commands (SLP) FSS-3634 GDI-509:

The Low Power On/Off Command source shall be refer ... Y R

FSS-3635 GDI-510: The Low Power On/Off Command receiver shall be iso ...

Y R

FSS-3636 GDI-511: The Low Power On/Off Command receiver shall be equ ...

Y R

FSS-3637 GDI-512: The Low Power On/Off Command source shall be short ...

Y R

FSS-3638 GDI-1252: Standard Low Power On/Off Command: The contractor ...

Y T,R

3.5.5.9 Relay Status Acquisitions (RSA) FSS-3640 GDI-1229:

The open/closed status of a relay/switch contact ( ... Y R

FSS-3641 GDI-516: Relay Status Acquisition The contractor shall desi ...

Y T,R

3.5.5.12 Digital Bi-Level TM Acquisitions (BLD) FSS-3643 GDI-523:

Each bi-level digital channel shall be used to acq ... Y R

FSS-3644 GDI-1232: The OBC shall acquire via the Bi-Level Digital Acq ...

Y R

FSS-3645 GDI-1233: Each channel shall be allocated to a specific bit ...

Y R

FSS-3646 GDI-524: Bi-level Digital Interface The contractor shall de ...

Y T,R

3.5.6 Electrical Interface Control Document FSS-3648 GDI-558:

Interfaces will be formally controlled within the ... Y R

3.5.7 EMC Requirements FSS-3650 GDI-2154:

In order to achieve compliance with the requiremen ... Y A,R

3.5.7.1 Bonding FSS-3652 GDI-562:

The bond shall be resistant against corrosion and ... Y R

FSS-3653 GDI-563: Metallic parts of each electrical equipment chassi ...

Y T

FSS-3654 GDI-564: Joint faces shall be flat and clean before assembl ...

Y I,R

FSS-3655 GDI-565: All non-electrical equipment shall be bonded to th ...

Y T

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FSS-3656 GDI-566: Each electrical equipment chassis (case) shall be ...

Y T,R

FSS-3657 GDI-567: Metallic receptacles of connectors shall be electr ...

Y T

3.5.7.1.1 Ground Reference Rail FSS-3659 GDI-569:

Electrical bonding throughout CFRP structure shall ... Y R

FSS-3660 GDI-570: The resistance between any adjacent parts of the G ...

Y T,R

FSS-3661 GDI-571: The resistance between any two points of the GRR s ...

Y T,R

3.5.7.1.2 Cable and Harness Shields FSS-3663 GDI-573:

Where shielded wires are used, the shield shall be ... Y R

FSS-3664 GDI-574: The maximum unshielded length of any shielded wire ...

Y R

FSS-3665 GDI-575: Daisy chaining of shield terminations shall be avo ...

Y R

FSS-3666 GDI-576: Shields shall not be used as an intentional curren ...

Y R

3.5.7.1.3 Structure Parts FSS-3668 GDI-578:

Conductive structure components shall be electrica ... Y I,R

FSS-3669 GDI-1990: The DC resistance between two mating metal strutur ...

Y T,R

FSS-3670 GDI-1991: Across moveable parts, a bond strap shall be appli ...

Y T,R

FSS-3671 GDI-1992: For CFRP structure without shielding function, the ...

Y T,R

FSS-3672 GDI-2093: This Requirement has been Deleted. ...

Y

FSS-3673 GDI-2092: For CFRP structure used for electromagnetic shield ...

Y T,R

FSS-3674 GDI-1989: Metal fittings shall be bonded to the structure wi ...

Y T,R

FSS-3675 GDI-579: Metal fittings shall be bonded to CFRP with a DC r ...

Y T,R

FSS-3676 GDI-2105: The DC resistance from any metal structure part an ...

Y T,R

FSS-3677 GDI-2094: The DC resistance between any other conductive com ...

Y T,R

FSS-3678 GDI-1993: The GRR shall be attached at less than or equal to ...

Y T,R

3.5.7.1.4 Mechanical Parts FSS-3680 GDI-581:

Mechanical Parts without electrical nor shielding ... Y T,R

FSS-3681 GDI-582: Mechanical Parts used for electromagnetic shieldin ...

Y T,R

3.5.7.2 Grounding and Isolation 3.5.7.2.1 General FSS-3684 GDI-585:

Each unit shall provide a grounding point, which i ... Y I

FSS-3685 GDI-586: CFRP and SiC shall not be used as an electrical bo ...

Y R

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3.5.7.2.2 Electrical and Electronic Unit Requirement FSS-3687 GDI-588:

The structure of electrical and electronic unit sh ... Y T

FSS-3688 GDI-589: Openings for drainage, ventilation, etc... shall n ...

Y I

FSS-3689 GDI-590: All units shall have a M4 bonding stud ...

Y I

FSS-3690 GDI-591: The design of this bonding stud shall allow the co ...

Y I

3.5.7.2.3 Insulating materials FSS-3692 GDI-593:

Space exposed insulating material having a bulk re ... Y R

3.5.7.2.4 Thermal parts FSS-3694 GDI-595:

MLI: MLI shall carry at least 1 conductive layer ...

Y I

FSS-3695 GDI-596: MLI: The grounding points shall be in a minimum of ...

Y I,R

FSS-3696 GDI-597: MLI: The resistance between each bonding point an ...

Y T

FSS-3697 GDI-598: MLI: The resistance between each bonding point an ...

Y T

FSS-3698 GDI-599: PAINTS: Refer to Section GDI-592 above. ...

Y R

FSS-3699 GDI-600: HEATERS & THERMISTORS: Heaters, thermistors and o ...

Y T,R

3.5.7.3 Primary and Secondary Power Lines 3.5.7.3.1 Primary Power Lines FSS-3702 GDI-605:

Isolation: Within all units the primary power buse ... Y R

FSS-3703 GDI-606: Isolation: All units (except PCDU) shall maintain ...

Y T,R

3.5.7.3.2 Secondary Power Lines FSS-3705 GDI-609:

Grounding: All secondary supplies, inside a unit, ... Y I,R

FSS-3706 GDI-1988: Equipment with its own dedicated DC - DC converter ...

Y T

FSS-3707 GDI-610: Isolation: prior to connection of the unit interna ...

Y T,R

FSS-3708 GDI-2106: After grounding, the impedance between the unit se ...

Y T,R

FSS-3709 GDI-611: Secondaries distributed between units (1 supplier; ...

Y R

FSS-3710 GDI-612: Secondaries distributed between units (1 supplier; ...

Y R

FSS-3711 GDI-614: Grounding diagram including zero volts interconnec ...

Y I

FSS-3712 GDI-615: The symbols in Figure GDI-2107 below shall be used ...

Y R

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3.5.7.3.3 Signal Interfaces FSS-3714 GDI-617:

Signal circuits interfacing between Satellite equi ... Y R

FSS-3715 GDI-618: Where single-ended signal transmitters are used, i ...

Y R

FSS-3716 GDI-619: The use of common signal return paths is only perm ...

Y R

3.5.7.3.4 EGSE Grounding and Isolation FSS-3718 GDI-621:

EGSE signal and power circuits interfacing with fl ... Y R

3.5.7.4 Magnetic Moment FSS-3720 GDI-1997:

Each equipment shall be designed and fabricated to ... Y T,R

FSS-3721 GDI-1998: Deleted. ...

Y T

3.6 Operations Design and Interface Requirements 3.6.1 Bit / Byte Numbering Convention FSS-3724 GDI-632:

In all project specific documentation including co ... Y T,R

FSS-3725 GDI-634: During file transfer, within any data type structu ...

Y T,R

3.6.2 Operational Functions 3.6.2.1 Handling of Operational Configuration, Modes and

States

FSS-3728 GDI-638: Mode/State transitions: Transitions from one mode/ ...

Y R

FSS-3729 GDI-639: The unit supplier shall identify appropriate modes ...

Y R

FSS-3730 GDI-640: At all times, equipment and units shall be in a cl ...

Y T,R

FSS-3731 GDI-641: In addition, modes and the mode transitions manage ...

Y T,R

FSS-3732 GDI-642: The unit supplier shall identify all internal and ...

Y R

FSS-3733 GDI-643: The unit supplier shall identify all transition ti ...

Y R

FSS-3734 GDI-644: Mode/State transitions with duration longer than 1 ...

Y R

FSS-3735 GDI-645: It shall be possible to command the unit into each ...

Y T,R

3.6.2.2 Commandability 3.6.2.2.1 General FSS-3738 GDI-648:

Commandability is characterised by the set of comm ... Y T

FSS-3739 GDI-649: In operating states of the unit, it shall be possi ...

Y T

FSS-3740 GDI-650: In addition, in non-operating states of the unit, ...

Y T

FSS-3741 GDI-651: Individual switching of switchable elements (e.g. ...

Y T

FSS-3742 GDI-652: The on-board reception, processing and execution o ...

Y T,R

FSS-3743 GDI-653: The function of a command shall not change through ...

Y T,R

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FSS-3744 GDI-654: A single command may be used to initialise a chang ...

Y T,R

FSS-3745 GDI-655: Commands with variable bit-fields meaning shall no ...

Y R

FSS-3746 GDI-656: Nominal and the redundant functions or equipments ...

Y T

FSS-3747 GDI-657: The unit design shall avoid any conflict between a ...

Y T

3.6.2.3 Observability 3.6.2.3.1 General FSS-3750 GDI-660:

Observability is characterised by the set of telem ... Y R

FSS-3751 GDI-661: The unit shall provide in its housekeeping telemet ...

Y T,R

FSS-3752 GDI-662: The unit shall provide the necessary instrumentati ...

Y T,R

FSS-3753 GDI-663: Telemetry measurement sensors shall be designed su ...

Y T

FSS-3754 GDI-664: It shall be possible to determine the status of th ...

Y T

FSS-3755 GDI-665: Essential (high-priority) telemetry data enabling ...

Y T,R

FSS-3756 GDI-666: Telemetry shall always be provided to identify una ...

Y T,R

FSS-3757 GDI-667: Status information in telemetry shall be provided ...

Y T,R

FSS-3758 GDI-668: Any TM processing required at a higher operational ...

Y R

FSS-3759 GDI-669: Telemetry shall always be available to determine t ...

Y R

FSS-3760 GDI-670: When a key parameter is derived on-board from seve ...

Y T,R

3.6.2.3.2 Telemetry Acquisition FSS-3762 GDI-672:

The TM acquisition process by the data bus shall n ... Y T

FSS-3763 GDI-673: The unit design shall avoid any conflict between t ...

Y T

FSS-3764 GDI-674: TM acquisitions with conditional meaning shall not ...

Y R

FSS-3765 GDI-675: The value of a telemetry parameter shall be transm ...

Y R

FSS-3766 GDI-676: Analog TM Acquisition: Analog TM acquisitions sha ...

Y T,R

FSS-3767 GDI-677: Acquisition of safety critical analog parameters o ...

Y R

FSS-3768 GDI-678: The values of currents or voltages readings shall ...

Y R

FSS-3769 GDI-679: The calibration curve of an analog parameter shall ...

Y R

3.6.2.3.3 Observability of Hardware Configuration FSS-3771 GDI-681:

At switch on, the configuration of the unit at ele ... Y T

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FSS-3772 GDI-682: In case a unit includes several elementary functio ...

Y R

FSS-3773 GDI-683: The configuration of any on-board device and any s ...

Y T,R

FSS-3774 GDI-684: Any configuration command register shall be observ ...

Y R

FSS-3775 GDI-685: The acquisition of the unit configuration/state sh ...

Y R

FSS-3776 GDI-686: The acquisition of an ON/OFF status for a relay sh ...

Y R

FSS-3777 GDI-687: If the unit controls the redundancy configuration ...

Y T

FSS-3778 GDI-688: Nominal and redundant functions shall be observabl ...

Y R

3.6.2.3.4 Observability of Commands FSS-3780 GDI-690:

Commands to the unit shall be acknowledged in an u ... Y R

FSS-3781 GDI-691: Acknowledgement of commands shall be direct (i.e. ...

Y T,R

FSS-3782 GDI-692: The association between command acknowledgement ac ...

Y I

FSS-3783 GDI-693: Successful execution of a command to the unit shal ...

Y T,R

FSS-3784 GDI-694: Failures in the acceptance and /or the execution o ...

Y T,R

3.6.2.3.5 Converters Observability FSS-3786 GDI-696:

Sufficient data to monitor the converters shall be ... Y T

3.6.2.4 Safety Critical and Hazardous Functions FSS-3788 GDI-700:

All critical commands shall be identified at equip ... Y A

FSS-3789 GDI-701: The execution of any unit command or command seque ...

Y A

FSS-3790 GDI-702: Commanding of critical commands shall be implement ...

Y A,R

FSS-3791 GDI-703: The status of inhibition of safety critical functi ...

Y T

FSS-3792 GDI-704: Units shall provide an unambiguous health status o ...

Y T

3.6.2.5 Handling of Memories FSS-3794 GDI-706:

Any part of installed RAM’s shall be readable by m ... Y T

FSS-3795 GDI-707: Any part of installed RAM’s shall be overwriteable ...

Y T

FSS-3796 GDI-708: Any part of installed ROM’s shall be readable by m ...

Y T

FSS-3797 GDI-709: For failure investigation, it shall be possible to ...

Y T

3.6.2.6 Autonomy FSS-3799 GDI-711:

Apart from failure situations, the unit shall oper ... Y T

FSS-3800 GDI-712: All parameters used for autonomous operations and ...

Y T

3.6.2.7 Automatic Functions

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FSS-3802 GDI-714: It shall be possible to inhibit and to override al ...

Y T

FSS-3803 GDI-715: All actions generated by automatic on-board logic ...

Y T

FSS-3804 GDI-716: The automatic function design shall be such that n ...

Y A,R

FSS-3805 GDI-717: Telemetry shall be associated to all automatic fun ...

Y T

FSS-3806 GDI-718: For all the automatic logic using several criteria ...

Y T

FSS-3807 GDI-719: The capability to change all on board logic (hardw ...

Y T,R

3.6.2.8 Time Synchronisation FSS-3809 GDI-721:

If the unit has operationally not been synchronise ... Y R

FSS-3810 GDI-722: If the unit has the function, all information on h ...

Y R

FSS-3811 GDI-723: Timing information provided in Housekeeping teleme ...

Y T,R

3.6.2.9 Fault Management / FDIR 3.6.2.9.1 Unit Fault Protection FSS-3814 GDI-726:

Any unit shall be able to withstand (i.e. remain i ... Y T,R

FSS-3815 GDI-727: Any unit shall be able to withstand (i.e. remain i ...

Y T,R

FSS-3816 GDI-728: It shall be possible to repeat any command several ...

Y T,R

3.6.2.9.2 Unit Self Tests FSS-3818 GDI-730:

All units that perform regular self-tests shall re ... Y R

3.6.2.9.3 Failure Detection, Isolation and Recovery (FDIR) Functions

FSS-3820 GDI-733: FDIR functions shall be implemented in a hierarchi ...

Y A,R

FSS-3821 GDI-734: The unit shall automatically detect any failure, w ...

Y T,R

FSS-3822 GDI-735: At unit level failures shall be detectable by adeq ...

Y A

FSS-3823 GDI-736: Failure detection algorithms shall report in event ...

Y A,R

FSS-3824 GDI-737: Failures which require a reaction time less than 1 ...

Y T,A

FSS-3825 GDI-738: Failure which requires a reaction time between 10s ...

Y A,R

FSS-3826 GDI-739: Failure isolation shall be performed at switchable ...

Y T,A

FSS-3827 GDI-740: Any FDIR actions on unit level shall be reported t ...

Y T,R

FSS-3828 GDI-741: The need for intervention of higher levels to reac ...

Y T,A,R

3.6.3 Other Requirements 3.6.3.1 Inputs to Design Justification File FSS-3831 GDI-744:

The unit supplier shall provide a design justifica ... Y R

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3.6.3.2 Inputs to Operational Database FSS-3833 GDI-746:

The unit supplier shall provide inputs to the Oper ... Y R

FSS-3834 GDI-747: Data to be provided (the list is not exhaustive): ...

Y R

3.6.3.3 Operation Manual FSS-3836 GDI-749:

The unit supplier shall provide an Operations Manu ... Y R

FSS-3837 GDI-750: The following standardization (Table GDI-751) shal ...

Y R

3.7 Software Design & Interface Requirements 3.7.1 General FSS-3840 GDI-2181:

All sotfware production and test shall follow the ... Y R

FSS-3841 GDI-2182: All on-board software running in sub-systems shall ...

Y R

FSS-3842 GDI-2183: The on-board software shall be developed using a h ...

Y R

FSS-3843 GDI-2184: The use of a non high-level language code (e.g., a ...

Y A

FSS-3844 GDI-2185: The on-board sotware shall be implemented with a l ...

Y R

3.7.2 Flight Processor Resource Sizing FSS-3846 GDI-2192:

During development, flight processors providing co ... Y T,A

FSS-3847 GDI-2193: Any on-board software shall provide the capability ...

Y T,R

FSS-3848 GDI-2194: The resource utilisation monitor shall be availabl ...

Y T,R

FSS-3849 GDI-2196: Sizing of the software resources shall be done in ...

Y T,A

3.7.3 Robustness 3.7.3.1 Infinite Loops FSS-3852 GDI-2197:

The on-board software shall protect itself against ... Y

FSS-3853 GDI-2218: Whenever possibility of Warm Restart is implemente ...

Y

3.7.3.2 Overload FSS-3855 GDI-2198:

Any on-board software product shall provide a tabl ... Y T,A

FSS-3856 GDI-2199: If and only if the overload situation cannot be ab ...

Y T

3.7.4 Events FSS-3858 GDI-2214:

The on-board software shall provide a means to fil ... Y T

FSS-3859 GDI-2215: The on-board software shall maintain counters for: ...

Y T

3.7.5 Initialisation FSS-3861 GDI-2226:

Any on-board unit embedding software shall provide ... Y T,R

FSS-3862 GDI-2228: The Cold Restart shall start execution from a hard ...

Y T

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FSS-3863 GDI-2229: The Warm Restart shall start from a software comma ...

Y T

FSS-3864 GDI-2230: The Warm Restart shall perform a processor reset a ...

Y T

FSS-3865 GDI-2227: The Cold Restart and the Warm Restart initialisati ...

Y T

FSS-3866 GDI-2234: At a predictible stage of the initialisation, the ...

Y

3.7.6 Testability FSS-3868 GDI-2205:

Any on-board unit embedding software shall provide ... Y T,R

3.7.7 SW Maintainability 3.7.7.1 Version Number FSS-3871 GDI-2209:

All software products shall store their version nu ... Y T

FSS-3872 GDI-2212: The flight software version number shall be retrie ...

Y T

FSS-3873 GDI-2208: The flight software version number shall be modifi ...

Y T

3.7.7.2 In Flight SW Modification FSS-3875 GDI-2186:

Any on-board unit embedding software shall support ... Y T

FSS-3876 GDI-2187: The on-board software shall be structured such tha ...

Y R

FSS-3877 GDI-2231: Any on-board unit embedding software shall support ...

Y T

FSS-3878 GDI-2232: Any on-board unit embedding software shall support ...

Y T

FSS-3879 GDI-2201: Any on-board unit embedding software shall be repr ...

Y T

3.7.7.3 Ease of SW Operations & Modifications FSS-3881 GDI-2206:

Wherever possible, the software shall be table-dri ... Y R

FSS-3882 GDI-2210: All on-board software data that are anticipated to ...

Y R

FSS-3883 GDI-2211: The on-board software shall have knowledge of the ...

Y T

FSS-3884 GDI-2207: Software-implemented limits and triggers for anoma ...

Y T,R

3.7.8 SafeGuard Memory (SGM) Maintainability FSS-3886 GDI-2223:

In case of Cold Restart, any on-board unit embeddi ... Y R

FSS-3887 GDI-2224: The on-board software shall implement SGM data str ...

Y T

3.7.9 Independent SW Validation (ISV) FSS-3889 GDI-2188:

The software components that are critical for the ... Y R

3.7.10 SW Maintenance Products FSS-3891 GDI-2189:

All on-board software, including new and reused SW ... Y T

FSS-3892 GDI-2190: All on-board software resident in ASIC, FPGA, or o ...

Y T

FSS-3893 GDI-2233: The SW maintenance environment shall provide the m ...

Y T

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FSS-3894 GDI-2235: All software licenses for any software used to dev ...

Y T

FSS-3895 GDI-2236: For any on-board unit embedding software, a softwa ...

Y T

FSS-3896 GDI-2237: The software development and maintenance facility ...

Y T

4 Environment Design Requirements FSS-3898 GDI-2315:

All component of the spacecraft shall be designed ... Y

4.1 Ground operation phase FSS-3900 GDI-2318:

To allow validation and integration operations, al ... Y

4.1.1 Thermal and climatic environment FSS-3902 GDI-2320:

For AIV and storage, the climatic conditions shall ... Y

FSS-3903 GDI-2321: Assembly, integration and verification of flight h ...

Y

FSS-3904 GDI-2322: During transport prior to integration on the space ...

Y

FSS-3905 GDI-2323: The flight hardware transportation containers shal ...

Y

4.1.2 Mechanical environment FSS-3907 GDI-790:

The equipment/assembly and associated transport co ... Y T,A

FSS-3908 GDI-793: During ground transportation the equipments shall ...

Y T,A

FSS-3909 GDI-2327: All MGSE, containers, transportation and handling ...

Y

FSS-3910 GDI-2328: Sine and random vibrations: the unit transport con ...

Y

FSS-3911 GDI-2329: For containers, the shock requirement is a drop of ...

Y

FSS-3912 GDI-2663: Fatigue loads : in case of a launch from Baikonur, ...

Y A

4.2 Launch and Early Operation phase 4.2.1 Pressure Environment FSS-3915 GDI-780:

Units mounted on the S/C shall be designed to with ... Y T

4.2.2 Contamination FSS-3917 GDI-782:

Cleanliness requirements are as defined in the PA ... Y T,R

4.2.3 Mechanical environment 4.2.3.1 Quasi static and low frequency loads FSS-3920 GDI-799:

The quasi-static and low frequency flight limit ac ... Y T,A

4.2.3.2 Dynamic Environment 4.2.3.2.1 Sinusoidal Environment FSS-3923 GDI-808:

All units mounted on the SCM structure shall be de ... Y T,A

4.2.3.2.2 Random Environment FSS-3925 GDI-812:

Units shall be designed and tested to withstand, ... Y T,A

4.2.3.2.3 Acoustic environment

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FSS-3927 GDI-2338: Units shall be designed and tested to withstand, ...

Y

4.2.3.2.4 Shock Environment FSS-3929 GDI-818:

Units mounted on the S/C Structure shall be design ... Y A,R

4.2.4 Thermal environment FSS-3931 GDI-2602:

For units having a view factor to external space, ... Y

4.2.5 Electromagnetic and radio frequency environment 4.3 In orbit Environment 4.3.1 In orbit mechanical loads 4.3.1.1 Quasi-static & Thermo-elastic Loads FSS-3936 GDI-823:

During orbit and attitude correction manoeuvres, u ... Y T,A,R

FSS-3937 GDI-2131: The unit shall be compatible with internal loads g ...

Y A

4.3.1.2 Micro-vibrations FSS-3939 GDI-825:

Equipment generating micro-vibrations shall not be ... Y T,R

4.3.1.3 Dynamical distrurbances FSS-3941 GDI-2677:

In equipment operating mode, any potential equipme ... Y

FSS-3942 GDI-2678: Once the equipment operational conditions have bee ...

Y

4.3.2 In orbit thermal FSS-3944 GDI-841:

During the In Orbit phase, the spacecraft units TR ... Y A,R

FSS-3945 GDI-2583: During the In Orbit phase, the spacecraft units wi ...

Y

FSS-3946 GDI-2603: For units having a view factor to external space, ...

Y

4.4 Radiation Environment 4.4.1 Introduction FSS-3949 GDI-847:

The radiation environment for the mission is shown ... Y A,R

4.4.2 GAIA Radiation Environment 4.4.2.1 Galactic Cosmic Ray (GCR) and Solar Energetic

Particle Environment

FSS-3952 GDI-1946: The integral LET spectra generated using CREME96 ( ...

Y R

4.4.2.2 Trapped Proton Environment during transfer 4.4.2.3 Solar Proton Environment on station 4.4.2.4 Trapped Electron Environment 4.4.3 Long Term Effect Considerations 4.4.3.1 Ionizing Dose Depth Curve FSS-3958 GDI-1966:

The radiation environment for the mission shall be ... Y A,R

4.4.3.2 Displacement Damage 4.4.4 Rules for Design and Performance FSS-3961 GDI-876:

No protective shielding by the outer panels of the ... Y R

FSS-3962 GDI-877: Unit shall take into account the shielding provide ...

Y A,R

4.4.5 Radiation Sensitive Components

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FSS-3964 GDI-1969: The Subcontractor shall implement a Radiation Hard ...

Y R

FSS-3965 GDI-1970: All parts shall be reviewed by the Subcontractor t ...

Y R

FSS-3966 GDI-1971: The Subcontractor shall issue a Radiation Assessme ...

Y R

4.4.5.1 Total Dose FSS-3968 GDI-1975:

The total dose to be taken into account is defined ... Y A,R

4.4.5.2 Single Event Effects (SEE) FSS-3970 GDI-1977:

Parts are considered SEE immune when the LETth is ... Y R

FSS-3971 GDI-1978: The component shall be designed to tolerate GCR, p ...

Y T,A,R

4.4.5.3 Single Event Latch-up FSS-3973 GDI-1980:

Devices which are known to be susceptible to latch ... Y A,R

4.4.5.4 Non Destructive Single Event (Single Event Upset, Single Event Transient...)

FSS-3975 GDI-1982: Part types shall be acceptable according to the ac ...

Y A,R

FSS-3976 GDI-2681: Memory circuits shall have sufficient error det ...

Y

4.4.5.5 Single Event Burnout (SEB) and Single Event Gate Rupture (SEGR)

FSS-3978 GDI-1984: For SEB and SEGR, error rate prediction techniques ...

Y A,R

4.4.5.6 Displacement Damage FSS-3980 GDI-1986:

Parametric and functional sensitivity of an EEE pa ... Y R

FSS-3981 GDI-1987: The reset or data corruption occurrence rate due t ...

Y A,R

4.5 EMC Environment 4.5.1 EMC Performance Requirements 4.5.1.1 Inrush Current FSS-3985 GDI-895:

Inrush current at unit switch on shall not exceed ... Y T,R

4.5.1.2 Voltage Transients FSS-3987 GDI-897:

The transient on the primary power bus distributio ... Y T

FSS-3988 GDI-899: Conducted voltage transients on the primary power ...

Y T

4.5.1.3 Conducted Emissions on Regulated Power Bus 4.5.1.3.1 Conducted Emissions on Power Leads,

Frequency Domain

FSS-3991 GDI-902: Conducted narrow band current emissions (different ...

Y T

FSS-3992 GDI-904: Conducted narrow band current emissions (common mo ...

Y T

FSS-3993 GDI-2716: In case of internal redundancy, conducted emission ...

Y T

4.5.1.3.2 Conducted Emissions on Power Leads, Time Domain

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FSS-3995 GDI-907: Time domain conducted differential mode voltage ri ...

Y T

FSS-3996 GDI-908: For Primary Power users, time domain conducted emi ...

Y T

FSS-3997 GDI-2709: Time domain current emissions shall be < 10% of th ...

Y

FSS-3998 GDI-2717: In case of internal redundancy, time domain emissi ...

Y T

4.5.1.4 Conducted Emissions on Secondary Power Lines 4.5.1.4.1 CE for Secondary Power Supply Units, Frequency

Domain

FSS-4001 GDI-918: The maximum voltage emission levels for secondary ...

Y T

4.5.1.4.2 CE for Secondary Power Supply Units, Time Domain

FSS-4003 GDI-920: The voltage ripple and spikes on secondary power s ...

Y T

4.5.1.5 Conducted Emissions Signal lines Common Mode FSS-4005 GDI-2711:

Conducted Narrow band conducted emissions (common ... Y T

FSS-4006 GDI-2712: : Conducted Emission on Signal Bundle ...

Y T

4.5.2 Radiated Emissions - E field FSS-4008 GDI-922:

The unit shall not exceed the specified limits in ... Y T

FSS-4009 GDI-2704: On board Receiver Notch: 20 dBµV/M between 7190 an ...

Y T

4.5.3 Radiated Emissions - H field FSS-4011 GDI-926:

The radiated H field generated by Units, shall be ... Y T

4.5.4 Radiated Emissions Fluctuations - E Field FSS-4013 GDI-2013:

Any specific requirements on E-field will be detai ... Y R

4.5.5 Radiated Emissions Fluctuations - H Field FSS-4015 GDI-2022:

Any specific requirements on H-field will be detai ... Y R

4.5.6 Radiated Susceptibility - E field FSS-4017 GDI-928:

The unit shall not show any malfunction or deviati ... Y T

FSS-4019 GDI-929: No unit that is powered On at launch shall show an ...

Y T

4.5.7 Radiated Susceptibility - H field FSS-4021 GDI-932:

Units shall not be susceptible when submitted to t ... Y T

4.5.8 Units linked by Secondary Power Lines FSS-4023 GDI-934:

When secondary lines power a unit, the unit shall ... Y T

FSS-4024 GDI-935: When a unit delivers secondary lines, the unit sha ...

Y T

4.5.9 Conducted Susceptibility Power Lines

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4.5.9.1 Conducted Susceptibility Sine Wave - Differential Mode

FSS-4027 GDI-938: Primary power bus powered units shall not exhibit ...

Y T

4.5.9.2 Conducted Susceptibility Sine Wave - Common Mode

FSS-4029 GDI-2000: Primary power bus powered units shall not exhibt a ...

Y T

4.5.9.3 Conducted Susceptibility - Transient FSS-4031 GDI-2007:

The unit shall not exhibit any malfunctions, degra ... Y T

FSS-4032 GDI-2009: Transient Type 1 With reference to (figure GDI-941 ...

Y T

FSS-4033 GDI-2010: Transient Type 2 With reference to (figure GDI-941 ...

Y T

4.5.9.4 CE / CS on Interface signal lines FSS-4035 GDI-944:

No unit shall exhibit any malfunction, degradation ... Y T

FSS-4036 GDI-2089: The unit shall not exhibit any malfunction, degrad ...

Y T

4.5.10 Secondary Power Lines Susceptibility 4.5.10.1 CS Sinewave injection for secondary power

supply units

FSS-4039 GDI-949: The conducted susceptibility specification for sec ...

Y T,R

4.5.10.2 Requirement at subsystem or system level FSS-4041 GDI-951:

In addition, a margin of at least +6dB shall be de ... Y T,R

4.5.11 DC Magnetic Requirements FSS-4043 GDI-958:

The use of relays shall be limited to the most cri ... Y R

4.5.12 ESD Susceptibility FSS-4045 GDI-962:

The unit shall not be susceptible when submitted t ... Y T

FSS-4046 GDI-2693: Equipments and sub-systems shall be free from gas ...

Y

FSS-4047 GDI-2694: Adequate venting shall be provided to ensure that ...

Y

FSS-4048 GDI-2695: If the above requirements GDI-2693 and GDI-2694 ca ...

Y

4.5.14 Micrometeoroid environement FSS-4050 GDI-2683:

The micrometeoroid environment for the mission sha ... Y

FSS-4051 GDI-2686: A damage assessment based on the micrometeoroid en ...

Y

5 Unit Level Test Requirements 5.1 General 5.1.1 Test Definition 5.1.1.1 Qualification tests FSS-4056 GDI-967:

Qualification of the design shall be accomplished ... Y T,A

5.1.1.2 Acceptance Tests

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FSS-4058 GDI-969: Environmental acceptance testing shall be performe ...

Y T,A,R

5.1.1.3 Functional Performance Tests FSS-4060 GDI-971:

The objective of the test item functional performa ... Y T,A

5.1.2 Test Facilities RequirementsY FSS-4062 GDI-973:

Any test facility to be used within the instrument ... Y A,R

5.1.2.1 Accuracy of Test Instrumentation FSS-4064 GDI-975:

The accuracy of instrument and test equipment used ... Y A,R

5.1.2.2 Tolerances of Test Parameters FSS-4066 GDI-977:

The allowed test condition tolerances shall be app ... Y A,I,R

5.1.2.3 Facility Ambient Condition FSS-4068 GDI-981:

Unless otherwise specified herein, all measurement ... Y A,I,R

5.1.3 Test Execution FSS-4070 GDI-983:

Test execution shall be started only if all starti ... Y A,I,R

5.1.4 Success Criteria FSS-4072 GDI-985:

The test is successfully performed if all measurem ... Y T,A

5.2 Unit Tests 5.2.1 Mechanical Environment Tests 5.2.1.1 Vibration Test Set Up FSS-4076 GDI-989:

The unit under test shall be mounted (to a rigid f ... Y T

FSS-4077 GDI-990: At least one triaxial sensor shall be mounted on t ...

Y T

FSS-4078 GDI-991: At least two axis aligned sensors shall be mounted ...

Y T

FSS-4079 GDI-992: All units powered on during launch shall be powere ...

Y T

5.2.1.2 Test Fixture FSS-4081 GDI-995:

The test item shall be attached to the vibration e ... Y T

FSS-4082 GDI-996: The variation of transmissibility between test ite ...

Y T

FSS-4083 GDI-997: Adequate fixture design and specimen installation ...

Y T

FSS-4084 GDI-998: A pre-test of the empty fixture shall be performed ...

Y T

5.2.1.3 Frequency Search FSS-4086 GDI-1000:

Frequency search tests shall be conducted in order ... Y T

FSS-4087 GDI-1002: Frequency search tests shall be conducted along ea ...

Y T

5.2.1.4 Vibration Tests Level FSS-4089 GDI-1005:

For units the vibration test levels that are appli ... Y A,R

5.2.1.5 Sine And Random Vibration Test FSS-4091 GDI-1011:

Sine and random vibration tests shall be performed ... Y T

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FSS-4092 GDI-1012: Prior and after sine and random vibration qualific ...

Y T

FSS-4093 GDI-1013: Before applying full levels, a test at intermediat ...

Y T

FSS-4094 GDI-1015: The vibration facility shall include a shock free ...

Y T

5.2.1.6 Shock Tests FSS-4096 GDI-1017:

Units shall demonstrate by test their ability to w ... Y T

FSS-4097 GDI-1018: Prior and after shock tests a low level sine frequ ...

Y T

5.2.1.7 Static tests FSS-4099 GDI-1020:

Static tests shall be performed by applying the sp ... Y T

5.2.2 Units Thermal Environment Tests 5.2.2.1 Thermal Test Setup FSS-4102 GDI-1024:

The temperatures shall be selected and controlled ... Y R

FSS-4103 GDI-1025: The test arrangement shall be as shown in Figure G ...

Y R

FSS-4104 GDI-1026: The unit shall be bolted to a thermally controlled ...

Y R

FSS-4105 GDI-1027: On all external surfaces flight representative the ...

Y R

FSS-4106 GDI-1028: The heat sink (HS) plates shall be black painted ( ...

Y R

FSS-4107 GDI-1029: The conductive heat sink temperature and the chamb ...

Y R

FSS-4108 GDI-1030: For vacuum tests the pressure inside the chamber s ...

Y R

5.2.2.2 Thermal Test Sequences 5.2.2.2.1 Qualification Thermal Vacuum FSS-4111 GDI-1034:

Unit’s suppliers shall perform Thermal Vacuum (TV) ... Y T

FSS-4112 GDI-1036: The TV test on unit level shall be performed as in ...

Y R

FSS-4113 GDI-1037: The qualification temperatures for the different u ...

Y R

FSS-4114 GDI-1038: The units shall be tested following the thermal va ...

Y T,R

5.2.2.2.2 Acceptance Thermal Vacuum FSS-4116 GDI-1044:

Unit suppliers shall perform thermal vacuum (TV) a ... Y T

FSS-4117 GDI-1045: The thermal vacuum acceptance test shall be perfor ...

Y T,R

5.2.2.2.3 Protoflight Thermal Vacuum FSS-4119 GDI-1049:

Unit suppliers shall perform thermal vacuum (TV) p ... Y T

FSS-4120 GDI-1050: The thermal vacuum protoflight test shall be perfo ...

Y T,R

5.2.3 Electromagnetic Compatibility Tests 5.2.3.1 General EMC Test Requirements 5.2.3.1.1 EMC Development Test

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FSS-4124 GDI-1057: Development tests may be performed to evaluate the ...

Y T,R

5.2.3.1.2 EMC Qualification Test FSS-4126 GDI-1059:

Qualification tests for PFM shall be performed as ... Y T,R

5.2.3.1.3 EMC Acceptance Test FSS-4128 GDI-1061:

Acceptance tests for FM shall be performed as spec ... Y T,R

5.2.3.1.4 EMC Integration Test FSS-4130 GDI-1063:

In order to ensure the proper grounding of the sec ... Y T,R

5.2.3.1.5 Retest Criteria FSS-4132 GDI-1065:

A retest may be required in case a test result is ... Y R

5.2.3.1.6 Pre and Post Test Inspection FSS-4134 GDI-1067:

The pre- and post-test inspection is specified in ... Y R

5.2.3.1.7 Test Sequence FSS-4136 GDI-2155:

The actual EMC test sequence shall be agreed with ... Y R

5.2.3.2 Test Facility 5.2.3.2.1 EMC Test Environment FSS-4139 GDI-1072:

All EMC tests shall be conducted at standard ambie ... Y R

5.2.3.2.2 Capabilities FSS-4141 GDI-1074:

The test facilities used for the EMC test program ... Y R

5.2.3.3 Test Instrumentation 5.2.3.3.1 General Tolerances and Test Parameters FSS-4144 GDI-1077:

The maximum allowable tolerance for the test param ... Y R

5.2.3.3.2 Accuracy of the Test Measurement Equipment FSS-4146 GDI-1079:

The accuracy of measurement equipment and test equ ... Y R

5.2.3.3.3 Special Requirements on the Test Equipment FSS-4148 GDI-1081:

Grounding of Test Equipment: Measurement equipment ...

Y R

FSS-4149 GDI-1082: Antenna Placement: For radiated emission measureme ...

Y R

FSS-4150 GDI-1083: Receiver Bandwidth: The following receiver bandwid ...

Y R

FSS-4151 GDI-1085: Power Adjustment: The primary power for unit level ...

Y R

5.2.3.3.5 Test Conditions FSS-4153 GDI-1095:

The equipment under test shall be switched on in t ... Y R

FSS-4154 GDI-1096: For emission testing the unit shall operate within ...

Y R

FSS-4155 GDI-1097: For susceptibility testing the suitable operationa ...

Y R

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FSS-4156 GDI-1098: After testing the equipment shall be switched off ...

Y R

FSS-4157 GDI-1099: Both operational modes shall provide operational c ...

Y R

FSS-4158 GDI-1100: The particular test set-up shall represent the fli ...

Y R

5.2.3.3.6 Susceptibility Testing FSS-4160 GDI-2142:

The applicable pass/fail criteria for susceptibili ... Y R

FSS-4161 GDI-1103: Data Acquisition: The item under test shall be mon ...

Y T

5.2.3.4 Specific EMC Test Requirement 5.2.3.4.1 Electrical Bonding FSS-4164 GDI-1107:

The bonding test shall be performed with the unit ... Y R

FSS-4165 GDI-1108: The bonding test shall be performed without any ha ...

Y R

5.2.3.4.2 Isolation FSS-4167 GDI-1111:

The isolation test shall be performed with the UUT ... Y R

5.2.3.4.3.2 CE on Secondary Power Lines FSS-4169 GDI-1123:

UUT operation shall be selected in order to maximi ... Y R

FSS-4170 GDI-1124: When the secondary power provider and user need to ...

Y R

5.2.3.4.4 Conducted Susceptibility, Signal Harnesses, Bulk Current Injection

FSS-4172 GDI-2090: The mode selection for susceptibility testing shal ...

Y T,R

5.2.3.4.6 Conducted Susceptibility on Secondary Power Lines

FSS-4174 GDI-1140: The mode selection for susceptibility testing shal ...

Y R

FSS-4175 GDI-1141: The test set-ups are shown in Figure GDI-1142 (CS0 ...

Y T

5.2.3.4.7 Radiated Emission, Electric Field FSS-4177 GDI-1151:


5.2.3.4.8 Radiated Emissions, E-Field Fluctuations 5.2.3.4.9 Radiated Emission, Magnetic Field FSS-4180 GDI-1155:


5.2.3.4.10 Radiated Emissions, Magnetic Field Fluctuations

5.2.3.4.11 Radiated Susceptibility, Electric Field FSS-4183 GDI-1159:


5.2.3.4.12 Radiated Susceptibility, Magnetic Field FSS-4185 GDI-1163:


5.2.3.4.13 Electrostatic Discharge (ESD) FSS-4187 GDI-1167:


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5.2.3.4.14 Magnetic Moment FSS-4189 GDI-1173:

Verification by similarity may be applied to equip ... Y A,R

5.2.4 Life Test FSS-4191 GDI-1185:

A life test shall be required for all the assembli ... Y T,R

5.2.5 Space Conditioning FSS-4193 GDI-1187:

Space conditioning shall be performed whenever des ... Y T,R

FSS-4194 GDI-1188: The contractors shall propose the corresponding te ...

Y R

FSS-4195 GDI-1189: For example, but without limitation to, materials ...

Y T

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Requirement/Section Cross Reference Page numbers are the pages where the sections start

FSS-38 ...............3.1.1 ................8 FSS-41 ...............3.1.2 ................8 FSS-173 .............4.1.1 ................14 FSS-181 .............4.2 ...................14 FSS-316 .............3.1.2 ................8 FSS-327 .............3.1.1 ................8 FSS-328 .............3.1.2 ................8 FSS-548 .............3.2 ...................8 FSS-573 .............4.3.5 ................15 FSS-635 .............4.2 ...................14 FSS-639 .............3.4 ...................12 FSS-641 .............3.4 ...................12 FSS-651 .............4.3.1 ................14 FSS-1410 ...........3.4 ...................12 FSS-1583 ...........3.3.3.1 .............11 FSS-1671 ...........5.1.1 ................17 FSS-1923 ...........4.2 ...................14 FSS-1947 ...........4.1.2 ................14 FSS-2001 ...........5.5 ...................17 FSS-2004 ...........6 ......................18 FSS-2006 ...........7 ......................19 FSS-3078 ...........5.1.2 ................17 FSS-3116 ...........3.2 ...................8 FSS-3118 ...........3.3.3.2 .............11 FSS-3119 ...........3.3.3.4 .............12 FSS-3120 ...........3.3.3.3 .............11 FSS-3121 ...........3.3.3.5 .............12 FSS-3123 ...........3.3.2 ................10 FSS-3126 ...........4.3.6 ................15 FSS-3127 ...........3.3.1.4 .............10 FSS-3128 ...........3.3.1.1 .............9 FSS-3129 ...........3.3.1.3 .............10 FSS-3130 ...........3.3.1.4 .............10 FSS-3135 ...........4.2 ...................14 FSS-3136 ...........4.3.2 ................14 FSS-3144 ...........4.3.3 ................14 FSS-3146 ...........4.3.4 ................15 FSS-3152 ...........3.3.1.2 .............9 FSS-3153 ...........3.3.1.3 .............10 FSS-3154 ...........3.1.2 ................8 FSS-3171 ...........3.3.1.3 .............10 FSS-3176 ...........4.3.6 ................15 FSS-3177 ...........4.3.6 ................15 FSS-3179 ...........4.3.6 ................15 FSS-3180 ...........4.3.6 ................15 FSS-3181 ...........4.3.6 ................15 FSS-3183 ...........4.3.6 ................15 FSS-3208 ...........3.3.2 ................10 FSS-3209 ...........3.3.2 ................10 FSS-3210 ...........3.3.2 ................10 FSS-3211 ...........3.3.2 ................10 FSS-3219 ...........3.3.2 ................10 FSS-3220 ...........3.3.2 ................10 FSS-3221 ...........3.3.2 ................10 FSS-3225 ...........3.4 ...................12 FSS-3232 ...........3.3.1.2 .............9 FSS-3233 ...........3.3.3.3 .............11

FSS-3234 ........... 3.3.3.4 ............. 12 FSS-3237 ........... 3.3.3.2 ............. 11 FSS-4200 ........... 3.3.3.3 ............. 11 FSS-4201 ........... 3.3.3.3 ............. 11 FSS-4202 ........... 3.3.3.3 ............. 11 FSS-4203 ........... 5.4 ................... 17 FSS-4205 ........... 4.3.5 ................ 15 FSS-4206 ........... 4.3.6 ................ 15 FSS-4210 ........... 6 ...................... 18 FSS-4213 ........... 4.3.5 ................ 15

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EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.


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