GAIA.ASU.SP.ESM.00023 1.0...

Gaia

GAIA.ASU.SP.ESM.00023 Issue 1

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Document Autogenerated from DOORS Module : /GAIA Prime/Level 4/4_14 GYRO RS/GYRO GAIA.ASU.SP.ESM.00023 1.0 (GYRO).doc

Gyro Requirements Specification

CI CODE: 13230 DRL Refs : EN-3

UK EXPORT CONTROL RATING : 7E001

Rated By : T. Colegrove

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

© EADS Astrium Limited 2006

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.

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

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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.

GAIA.ASU.SP.ESM.00023 1.0 (GYRO).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 Gyro Alignment Reference Frame Definition...............................................................................8 3.1.2 Transformations and Alignment...................................................................................................8

3.2 Functional and Performance Requirements .......................................................................................8 3.2.1 Operating Modes .........................................................................................................................8 3.2.2 Performance Requirement Conditions.........................................................................................9 3.2.3 Output ........................................................................................................................................10 3.2.4 Measurement Errors ..................................................................................................................11

3.3 Gyro Configuration ............................................................................................................................13 3.4 FDIR ..................................................................................................................................................14

4 Unit Specific Design and Interface Requirements ...................................................................................15 4.1 Mechanical Design and Interface Requirements ..............................................................................15

4.1.1 Mass...........................................................................................................................................15 4.1.2 Micro Vibration ...........................................................................................................................15 4.1.3 On/Off Command.......................................................................................................................15

4.2 Thermal Design and Interface...........................................................................................................15 4.3 Electrical Design and Interface .........................................................................................................16

4.3.1 Power Interface..........................................................................................................................16 4.3.2 Power Consumption...................................................................................................................16 4.3.3 Interface to Satellite Data Handling ...........................................................................................16 4.3.4 Harness......................................................................................................................................16 4.3.5 Test Equipment..........................................................................................................................17

5 General Design and interface Requirements ...........................................................................................18 5.1 General Design Requirements..........................................................................................................18

5.1.1 Lifetime ......................................................................................................................................18 5.1.2 Reliability....................................................................................................................................18 5.1.3 Maintainability ............................................................................................................................18 5.1.4 GDIR Applicability ......................................................................................................................18

5.2 Mechanical ........................................................................................................................................18 5.3 Thermal .............................................................................................................................................18 5.4 Electrical............................................................................................................................................18 5.5 Identification and Marking .................................................................................................................18

6 Verification Requirements ........................................................................................................................19 7 Product Assurance Requirements ...........................................................................................................20 8 Acronyms..................................................................................................................................................21 9 GDIR Applicability Matrix..........................................................................................................................22

FIGURES Figure 3.1-1: Unit Axis Systems ........................................................................................................................8 Figure 3.2-1: Gyro Modes..................................................................................................................................9

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1 INTRODUCTION AND SCOPE

1.1 Introduction

This document establishes the design, performance, interface and verification requirements of Gyro (the inertial measurement unit) 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 Gyro. 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> Gyro-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 Gyro will be used for angular rate measurement during Sun Acquisition Mode (SAM) and as part of a gyro-stellar attitude filter in Inertial Guidance Mode (IGM), Orbit Control Mode (OCM) and TranSition Mode (TSM), and as a Rate Anomaly Detector for all phases of the mission.

The baseline Gyro configuration assumed for Gaia is that there will be a ‘nominal’ set of Gyros giving rate measurement in three orthogonal axes, and a co-aligned ‘redundant’ set of Gyros as (typically) cold-redundant backup. This specification recognises that products of various internal configurations exist that can satisfy this arrangement (e.g. 3 off internally redundant 1-axis units, 2 off non-redundant 3-axis units). Any such configuration is acceptable to Gaia as long as the electrical independence and continuous simultaneous operation requirements are respected.

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Gyro product solutions that do not allow operation as fully independent ‘nominal’ and ‘redundant’ 3-axis measurement systems (e.g. 4 or 5 mutually skewed heads) will only be acceptable if unambiguous, 100% accurate, internal failure detection and isolation at Gyro system level can be clearly demonstrated.

One single channel is understood here as the single angular rate sensor for rate measurement in single axis, and one Gyro is understood here as the assembly of angular rate sensor(s), mechanical parts housing and supporting the angular rate sensor(s) and electronic unit(s) for data processing, data compensation, output drive and power converter(s) for rate measurements in three orthogonal axes, and finally the Gyro system refers to the entire rate measurement system with provision of redundancies. Therefore, the three orthogonal channels form one Gyro, and two Gyros form a Gyro system. This specification also recognises that sensor head and electronic unit can be assembled in separate boxes.

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 has been subjected to any specified combinations 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 MIL-STD-1553B Bus Protocol Specification


AD-3 GAIA Software Product Assurance Requirements


AD-4 Gaia Product Assurance Requirements For Subcontractors


2.2 Reference Documents

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

RD-1 Gaia E-SVM Requirements Specification


RD-2 Gaia AOCS Gyro Performance and Configuration Justification

Gaia.ASU.TCN.ESM.00005

RD-3 IEEE Standard Specification Format Guide and Test Procedure for

Single Axis Interferometric Fibre Optic Gyros

IEEE-STD-952-1997(R2003)

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3 FUNCTIONAL AND PERFORMANCE REQUIREMENTS

3.1 Reference Frames Definition

3.1.1 Gyro Alignment Reference Frame Definition

Gyro-36/GDI-188/I,R

Each Gyro box that houses the Gyro angular rate sensor shall include an optical reference cube for the purpose of aligning the Gyro onto the spacecraft. The location of the optical reference cube mounting shall be agreed with EADS Astrium.

Gyro-37/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 Transformations and Alignment

Gyro-40/CREATED/R

A transformation matrix shall be provided which transforms from the sensitive axis/axes of each Gyro unit to the alignment reference frame.

Gyro-42/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.

Gyro-44/RD-2/T,A

The misalignment of the sensitive axis/axes in the alignment reference frame shall be smaller than 0.1°(3σ) including all measurement uncertainties from launch, 0g, outgassing and thermo-elastic effects.

Gyro-1225/RD-2/T,A

The absolute alignment thermal stability for each sensitive axis shall not exceed 5.0arcsecond/°C for a temperature variation at the temperature reference point.

3.2 Functional and Performance Requirements

3.2.1 Operating Modes

The mode names cited in this document are for clarification with regard to the requirement. It is not a requirement that these mode names are used, and additional modes are allowed.

Gyro-1228/CREATED/R

The Gyro shall have its own drive circuitry, signal conditioning and interface electronics.

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Gyro-1229/RD-2/T,R

The Gyro shall provide a Start-up Mode which shall last for no more than 5 seconds.

Gyro-1230/CREATED/T,R

The Gyro shall provide a Ready Mode, which shall provide angular rate data and/or incremental attitude data, health status and data validity.

Note: It is acceptable for the initial measurement outputs (i.e. for a limited time span after the transition from Start Up Mode to Ready Mode) to be of reduced accuracy with respect to the performance requirements defined in section 3.2.4 (with the exception of the maximum rate bias, for which no relaxation can be tolerated). If the proposed unit cannot meet all the performance requirements defined in section 3.2.4 within 5 seconds of switch on, the supplier shall state in their proposal what the achievable performance with respect to each parameter in section 3.2.4 is at initial entry to Ready Mode, and shall state how long after entry to Ready Mode full performance is achieved.


There shall be an unambiguous identification that the Gyro has switched from Start-Up Mode to Ready Mode available in the telemetry data provided by the unit.


The Gyro shall provide an Error Mode which shall be identical to the Ready Mode with the exception of reporting and identifying sensor errors and errors in the conditioning electronics.


When in Error Mode, measurement channels unaffected by the error shall be full accuracy, i.e. shall perform as defined for Ready Mode.

The Gyro mode diagram is shown below:

S t a r t - U p M o d e

R e a d y M o d e E r r o r M o d e M o d e

A u t o n o m o u s T r a n s i t i o n

A u t o n o m o u s T r a n s i t io n

C o m m a n d e d T r a n s i t i o n

Figure 3.2-1: Gyro Modes

This Mode Diagram and the mode transitions shown should be considered indicative of the anticipated Gyro functionality only. Alternative Mode sets that achieve the functionality set out by these requirements are also acceptable.

3.2.2 Performance Requirement Conditions

3.2.2.1 General

Gyro-54/CREATED/T,A

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. Such effects include (where appropriate), but are not restricted to, environmental, launch loads, spacecraft dynamic

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conditions, ageing, nominal radiation environment, sensor bias, sensor noise, quantisation, power line variations, temperature effects, unit conversion factor errors, 1g to 0g effects and SEU's

3.2.2.2 Dynamic Conditions

Gyro-57/RD-2/T,A

The Gyro shall meet the performance requirements with input rates of up to 6°/s around any sensitive axis.

Gyro-1235/RD-2/T,A

For input rate above 6°/s, the sign of the output measurements from the Gyro shall be valid even if the output measurement is saturated up to at least 10°/s.

The maximum measurable rate (even if non-linear) is to be identified in the first instance in the technical proposal.

Gyro-58/CREATED/T,A

The Gyro shall be capable of withstanding rates of at least 10°/s about each input axis, without sustaining damage or impairing performance over the nominal input rate range.

3.2.3 Output

Gyro-68/CREATED/T,A

The measurement performance requirements shall include any effect due to conversion from raw output to final incremental angle and/or angular rate measurements.

Gyro-69/RD-2/T,A

The Gyro shall have a bandwidth of 4 Hz. If the bandwidth is implemented using an anti-aliasing filter which can be disabled, performance shall be evaluated with and without the filter. The supplier shall be responsible for the performance of the anti-aliasing filter so that both raw and filtered incremental angle and/or angular rate outputs satisfy the performance requirements given in section 3.2.4.

Gyro-71/RD-2/T,R

The Gyro shall provide measurements at an update rate of 8 Hz such that the incremental attitude and angular rate can be derived.

Gyro-75/CREATED/T

The data of all each Gyro channel shall be frozen (synchronisation data) upon receipt of a command via either MIL STD 1553 or PPS.

Gyro-76/CREATED/T,A

The data output of each Gyro channel shall have its own time tag. This time tag shall have a maximum error of 1 ms.

Gyro-77/RD-2/T,A

The latency of the data (from the measurement to output on data bus if there isn't an anti-aliasing filter, or to the anti-aliasing filter if there is one) shall be a maximum of 20 ms. The data latency due to anti-aliasing filter shall be less than 40 ms (TBC).

The supplier shall characterise the data latency due to anti-aliasing filter if such a filter is implemented in their Gyro.

Gyro-1240/CREATED/R

In the event that the Gyro uses the PPS signal for its time stamp function, the PPS requirements shall be compliant with AD-1, and section 9.

Preference will be given to the solutions using PPS for synchronisation rather than over MIL STD 1553.

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Gyro-1241/CREATED/R

The usage of a PPS signal shall be defined by the supplier at the time of the proposal.

Gyro-72/CREATED/R

The Gyro shall output a temperature measurement for health monitoring.

Gyro-73/CREATED/T,R

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

Gyro-1283/CREATED/T,A

If post-processing of the outputs shall be implemented in the Central SW to meet the performance requirement (compensation for temperature or anything else), the supplier:

- shall provide a detailed definition of the post-processing

- shall make sure that all outputs required for this post-processing are outputs delivered by the gyro

- shall provide any calibration coefficient (for each unit) required for the post-processing

- shall take into account the compensation residual error in the performance budgets

Any such on-board post processing shall be defined in detail as part of the proposal submission.


The time tag quantisation shall be better than 0.1ms (TBC).


The angular rate quantisation shall be better than 0.1mas/s (TBC).


The incremental angle quantisation shall be better than 0.01mas (TBC).

3.2.4 Measurement Errors

3.2.4.1 General

Gyro-1243/CREATED/R

All performance requirements cited in section 3.2.4 shall be understood as being applicable to each measurement channel of the Gyro.

Gyro-1244/CREATED/R

All performance requirements apply in the presence of all error sources. This shall include, but not limited to:

1).The Gyro self-heating effects.

2).Power line variation.

3).Environmental temperature excursions over the full operating temperature range for these units.

4).Operations from switch-on to switch-on.

5).Radiation effects from the environment specified in AD-1.

6).Other sources identified by the supplier.


For input rate below 6°/s, the supplier shall provide performance data for the requirements specified in this section for each channel of the Gyro. This rate range is defined as the nominal input rate range.

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

Gyro-1245/CREATED/R

The subcontractor shall provide a detailed error budget for alignment, bias, scale factor and noise, for agreement with Astrium Ltd, to demonstrate compliance with the requirements.

The error budget is to be provided in the first instance in the technical proposal.

Gyro-1247/CREATED/R

If an internally redundant unit is proposed, the subcontractor shall assume that all sensors are on for calibration and for assessing the self-heating effects, i.e. the sensors can be operated in hot-redundancy during some phases of the mission.

3.2.4.2 Rate Bias

Gyro-80/CREATED/T,A

The rate bias and its stability cited in this section shall take into account the following maximum environment variations:

1).Magnetic field variation: ±6.10-5T (TBC).

2).Temperature range: -20°C to +60°C.

3).Temperature variation rate: up to 0.035°C/minute.

4).Linear acceleration: up to 0.05 m/s2.

5).Angular accelerations of up to 0.6°/s2 around any sensitive axis in the Gyro configuration.

Gyro-1251/RD-2/T,A

The maximum rate bias over life shall be better than 17.5°/hr (3σ) in each sensitive axis of the Gyro.

This requirement applies immediately from the time that measurements are available after the Start Up Mode.

Gyro-3014/RD-2/T,A

The bias stability over 6 hours shall be better than 0.015°/hr (3σ) in each sensitive axis of the Gyro subject to the temperature range listed in point 2) of Gyro-80.


The bias repeatability from switch-on to switch-on effect only shall be better than 0.04°/hr (3σ).

3.2.4.3 Noise error

Gyro-82/RD-2/T,A

The Gyro noise error shall take into account at least the following contributions:

1).Angle white noise (including quantisation noise).

2).Angle random walk.

3).Rate flicker.

4).Rate random walk.


The value of the parameters characterising the above (Gyro-82) error contributions shall be provided in the first instance in the technical proposal.

Gyro-1288/RD-2/T,A

The rate flicker noise model coefficient shall satisfy:

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B < 0.01°/hr (1σ)

where B is defined in Appendix C of RD-3.

Gyro-1293/RD-2/T,A

The angle random walk noise model coefficient shall satisfy:

N < 0.005°/root hr (1σ)

where N is defined in Appendix C of RD-3.

Gyro-1252/RD-2/T,A

The maximum integrated Gyro noise error computed as the RSS of all contributors shall not be greater than 0.1°(1σ) on each Gyro channel over a 6 hours 40 minutes duration assuming that the integration starts with a calibrated bias.

Gyro-83/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 input rate conditions. 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 nominal measurement range of Gyro.

Each measurement data set shall span at least 24000 sec with a fixed sample time whose value shall be no greater than 0.125 sec, using test equipment which introduces acceptably small additional filtering and noise. The data sets shall be supplied to Astrium Ltd in an electronically readable format to be agreed with Astrium Ltd.

The objective of this requirement is to gain a clear and detailed understanding of the Gyro 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 angular rate measurement. The Gyro supplier is welcome to propose alternative test scenarios that will better characterise the noise behaviour of their product.

3.2.4.4 Scale Factor

Gyro-86/CREATED/R

The scale factor for the digital output, relating input angular rate to the measurement output of the associated Gyro channel, shall be fixed, i.e. not changeable by external command.

Gyro-87/CREATED/T

The Scale factor shall be measured on-ground to an accuracy of 100ppm.

Gyro-88/RD-2/R

The maximum overall error on scale factor shall not exceed 9985ppm (3σ) in all conditions during lifetime.

Gyro-3008/RD-2/R

The scale factor stability over 6 hours shall be better than 500ppm (3σ) including ±2°C (TBC) temperature variation at the temperature reference point.

3.3 Gyro Configuration

The Gyro channel configuration shall meet the following requirements.


The Gyro configuration shall provide sufficient channels to allow full performance measurement in 3 orthogonal axes to be derived.


If 2 off 3-axis units are provided each 3-axis unit shall contain a set of 3 orthogonal axes.

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Gyro-1261/CREATED/R

The channel alignment configuration shall be subject to approval by Astrium Ltd.

3.4 FDIR


Taking into account the overall Gyro System redundancy, no single failure shall reduce the number of working channels below 3, thus allowing the Gyro to still provide a measurement in 3 orthogonal axes.

Gyro-102/CREATED/R

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

Gyro-103/CREATED/R

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


The probability of a false alarm in any health status telemetry provided shall be less than 0.01%.

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4 UNIT SPECIFIC DESIGN AND INTERFACE REQUIREMENTS

4.1 Mechanical Design and Interface Requirements

4.1.1 Mass

Gyro-107/CREATED/T

The total mass of the Gyro system, including the provision of redundancy, shall be less than 12.6 kg for all 2 or 3 units together (harness included in case of separate electronic and sensor head). This shall be verified by mass measurement on the fully assembled unit.

4.1.2 Micro Vibration

Gyro-1286/ERS-53/R

The Gyro shall not contain any purposefully or functionally moving elements that generate any vibration.

4.1.3 On/Off Command

Gyro-1266/CREATED/R

There shall be an ON/OFF command (SHP) per power supply that allows the Gyro or gyro channel power consumption to be removed from the Power Bus. This function shall be latched and shall provide telemetry status independent of the Gyro powered status.

This internal On/Off relay is primarily intended to be able to isolate the unit from the spacecraft power subsystem following a unit failure. Nominal power switching may be performed by either the satellite power subsystem under LCL control or the ON/OFF command.

Gyro-3015/CREATED/R

The Gyro shall automatically initialise and begin rate measurement as soon as external power is applied.

Gyro-3007/CREATED/R

This internal on/off switch shall be activated by the specific pulse from CDMU whose characteristics are defined in Section 3.5.5.8 in AD-1.

4.2 Thermal Design and Interface


The maximum thermal dissipation of one active Gyro shall not exceed 30W.

Gyro-113/CREATED/R

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

Gyro-114/ERS-701, ERS-702/R

The thermal control of the Gyro shall be feasible through mainly passive radiative dissipation to a heat sink all around the unit (on 4 PI steradian) with temperature range defined in the AD-1 in requirement GDI-2583 and limited conductive dissipation of 0.015 W/K at each unit fixation foot .

Gyro-1990/ERS-705, ERS-706/R

The supplier shall identify whether or not an additional radiator panel is needed in order for their Gyro product to provide full performance measurements in the thermal environments defined in section 4.3.2 of AD-1. The conclusion shall be provided in the first instance in the technical proposal.


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.

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For an internally redundant configuration, it shall be possible to power and operate both the main and redundant functions simultaneouly.

4.3 Electrical Design and Interface

4.3.1 Power Interface

Gyro-118/CREATED/T

The Gyro shall draw power from the current limited, externally switched power bus (LCL) as defined in section 9.

A total of 6 individual class A (1A) LCLs are available for use. Alternative configurations not exceeding this total current rating can be proposed

Gyro-1269/CREATED/R

In the case of a separate electronics and sensor head, only the electronics shall interface to the power bus.

4.3.2 Power Consumption

Gyro-120/CREATED/R

The average power consumption of one active Gyro shall be less than 30W at normal operation. For proposed Gyro solutions comprising two non-redundant units, this requirement shall be met with both units powered simultaneously.

Gyro-3017/CREATED/R

When switched OFF, the gyro shall take nominally zero current.

4.3.3 Interface to Satellite Data Handling

Gyro-122/AD-1/R

The Gyro shall provide redundant digital interfaces to the Spacecraft Data Handling system that are compliant to MIL-STD-1553B. The MIL STD 1553B interface shall comply with the standard requirements specified in section 9, and with AD-2.

Gyro-3018/CREATED/R

Up to 6 RTs may be used to interface the Gyros with the spacecraft. Each RT shall comprise both Nominal and Redundant Mil Bus interfaces. Full communication shall be possible from either Nominal or Redundant Interface.

4.3.4 Harness

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

Gyro-127/CREATED/R

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

Gyro-1276/CREATED/R

In the case that the Gyro comprises separate electronics and sensor head, then they shall interface with one another via connectors only.

Gyro-1277/CREATED/R

In the case that the Gyro comprises separate electronics and sensor head, then the harness connecting the head to the electronics, up to a maximum length of 2m, shall be provided by the Gyro supplier (in accordance with the GDIR requirements as identified in section 9).

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Gyro-1278/CREATED/R

In the case that the Gyro comprises separate electronics and sensor head, then both the head and the electronics shall be compatible with a harness up to 2m in length.

Gyro-128/CREATED/R

Power and signal connectors shall be separate.

Gyro-129/CREATED/R

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

4.3.5 Test Equipment


In order to support closed loop testing at both subsystem and spacecraft level, the Gyro shall have provisions to be electrically stimulated through a separate connector which bypasses the sensor(s). The supplier shall delineate the stimulus interface and describe the required stimulation signal characteristics at the time of proposal in sufficient detail that a third-party ESGE supplier can produce a ‘gyro stimulation function’ that will allow performance-representative closed-loop testing to be performed.

Gyro-132/CREATED/R

The Gyro stimulation interface shall be digital and the details of this interface shall be provided in the first instance within the technical proposal.

Gyro-133/CREATED/R

The blanking caps for the Gyro stimulation interface connector shall be removable.

Gyro-134/CREATED/R

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

This harness will be connected to the spacecraft skin connector.


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


At spacecraft level, the test harness cited in requirement Gyro-134 will be connected to the Gyro 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 Gyro shall meet the requirements of this specification with this harness in situ.

Gyro-138/CREATED/R

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

Gyro-1279/CREATED/R

The Gyro stimulation interface circuits shall be compatible with a test harness of 40m, length between the test equipment and the skin connector.


The stimulation signal shall be independent of the sensor signal. It shall bypass the sensor head and interface the sensor electronics directly.


The Gyro shall accept stimulation signal at a frequency of up to 64Hz.

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5 GENERAL DESIGN AND INTERFACE REQUIREMENTS

5.1 General Design Requirements

5.1.1 Lifetime

Gyro-144/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

Gyro-146/CREATED/A,R

The reliability of the complete Gyro System (i.e. both nominal and redundant elements together) shall be higher than 0.9983 over 5 years in flight. The supplier shall show how they have calculated this figure from individual equipment reliability figures in their proposal. Any temperature dependence shall be included.

In calculating the Gyro System reliability, the supplier shall assume that no mix of prime and redundant elements shall be allowed.

5.1.3 Maintainability

Gyro-3022/CREATED/A,R

If periodic maintenance is necessary for the gyro it shall be feasible while integrated on the spacecraft without the need to dismount the unit.

5.1.4 GDIR Applicability

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

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

5.2 Mechanical

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

5.3 Thermal

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

5.4 Electrical

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

5.5 Identification and Marking

Gyro-158/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

Gyro-160/CREATED/T

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

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7 PRODUCT ASSURANCE REQUIREMENTS

Gyro-163/CREATED/R

The Gyro shall be designed, manufactured and tested in accordance with the PA requirements specified in AD-3 and 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

IGM Initial Guidance Mode

NEA Noise Equivalent Angle

OCM Orbital Control Mode

RSS Root Squared Sum

SAM Sun Acquisition Mode

SEU Single Event Upset

SHP Standard High Power

TBC To Be Confirmed

TBD To Be Decided

TC TeleCommand

TSM TranSition Mode

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 given it shall be assumed verification is required and method shall be considered TBD at this time.

Req No. Reference Applicability Verif. Method

3 General Design and interface Requirements 3.1 General Design Requirements 3.1.1 Lifetime Gyro-2047 GDI-31:

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

Gyro-2048 GDI-32: The Unit shall meet the requirements of this speci ...

Y A,R

Gyro-2049 GDI-33: The in-orbit lifetime of the satellite is defined ...

Y R

Gyro-2050 GDI-34: The unit shall be designed with positive margins o ...

Y A,R

Gyro-2051 GDI-2700: The units shall be compatible with a storage perio ...

Y

Gyro-2052 GDI-35: Maintenance during storage shall be as limited as ...

Y R

3.1.2 Design Safety Gyro-2054 GDI-37:

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

Gyro-2055 GDI-38: General safety requirements for units are as follo ...

Y A

3.1.3 Venting Gyro-2057 GDI-41:

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

Gyro-2058 GDI-42: For all relevant thermal hardware, explicitly MLI, ...

Y R

Gyro-2059 GDI-43: Unless a cavity is hermetically sealed adequate me ...

Y R

Gyro-2060 GDI-44: Structural members (honeycomb panels, in particula ...

Y T,A

3.1.4 Interchangeability Gyro-2062 GDI-46:

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

3.1.5 Identification & Marking Gyro-2064 GDI-50:

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

Gyro-2065 GDI-2253: The unit identification nameplate shall be mounted ...

Y

Gyro-2066 GDI-2254: For the particular case of connector identificatio ...

Y

3.1.6 Accessibility/Maintainability Gyro-2068 GDI-52:

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

Gyro-2069 GDI-53: The equipment shall be designed to require a minim ...

Y R

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Gyro-2070 GDI-54: No field maintenance, servicing or adjustment shal ...

Y R

3.1.7 Transportation, Handling and Storage 3.1.7.1 Transport Gyro-2073 GDI-2272:

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

Gyro-2074 GDI-2273: The transport container shall ensure that the envi ...

Y

Gyro-2075 GDI-2274: The storage container shall be designed to protect ...

Y

3.1.7.2 Unit packing Gyro-2077 GDI-2275:

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

Gyro-2078 GDI-2276: All units shall be packaged to ensure that it is s ...

Y

3.1.7.3 Container identification Gyro-2080 GDI-2277:

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

Gyro-2081 GDI-2278: In addition to the above, the container shall also ...

Y

3.1.7.4 Handling Gyro-2083 GDI-2271:

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

3.1.7.5 Thermally Conductive Materials Gyro-2085 GDI-70:

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

3.1.7.7 Seals Gyro-2087 GDI-75:

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

Gyro-2088 GDI-76: Any seals requiring periodic replacement during gr ...

Y R

3.1.7.8 Lubricants and Sealants Gyro-2090 GDI-78:

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

3.1.7.9 Screw Locking Gyro-2092 GDI-80:

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

Gyro-2093 GDI-2270: All screw type hardware used on the unit shall be ...

Y

3.2 Mechanical Design and Interface Requirements Gyro-2095 GDI-82:

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

Gyro-2096 GDI-83: Units shall be compliant with ECSS-E30 Part 2A, an ...

Y R

Gyro-2097 GDI-84: Following testing the unit shall be inspected to c ...

Y I

Gyro-2098 GDI-87: No unit shall generate microvibration loads at its ...

Y A,R

3.2.1 Structural Design 3.2.1.1 General Requirements Gyro-2101 GDI-91:

The following failure modes, for units at all leve ... Y A

Gyro-2102 GDI-92: The unit shall be designed to withstand the enviro ...

Y A,R

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Gyro-2103 GDI-2282: The design of the units handling and transportatio ...

Y A

Gyro-2104 GDI-93: Requirement deleted, see GDI-2297 ...

Y A

Gyro-2105 GDI-94: Wherever practical a fail safe design based on red ...

Y A

Gyro-2106 GDI-95: In cases where a failsafe design cannot be impleme ...

Y A

Gyro-2107 GDI-2045: All potential fracture critical items shall be sub ...

Y A

3.2.1.2 Mass properties Gyro-2109 GDI-2284:

A mass justification shall be provided indicating ... Y R

Gyro-2110 GDI-98: All mass estimations shall be accompanied by the d ...

Y T

Gyro-2111 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 Gyro-2113 GDI-102:

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

Gyro-2114 GDI-104: The unit centre of gravity shall be determined wit ...

Y T,A

Gyro-2115 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 Gyro-2118 GDI-2288:

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

Gyro-2119 GDI-2289: The stiffness requirements shall be demonstrated t ...

Y A

3.2.1.4.2 Mechanical Analysis Gyro-2121 GDI-2539:

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

Gyro-2122 GDI-2540: The adequacy of the FEM to predict thermo-elastic ...

Y A

Gyro-2123 GDI-2541: The FEM of the represented item in its launch conf ...

Y A

Gyro-2124 GDI-2542: The FEM of the equipment shall be verified and cor ...

Y A

Gyro-2125 GDI-2544: Reduced FEM mathematical models to be employed in ...

Y A

Gyro-2126 GDI-2546: Adequate models to calculate Centre of Mass and Mo ...

Y A

3.2.1.5 Strength Requirements 3.2.1.5.1 Definitions and General Requirements Gyro-2129 GDI-2354:

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

Gyro-2130 GDI-2366: GAIA equipment mechanical testing shall take into ...

Y T

Gyro-2131 GDI-2367: GAIA equipment mechanical testing shall take into ...

Y T

Gyro-2132 GDI-2368: An additional Protoflight Factor of Safety, FOSPF ...

Y T

3.2.1.5.2 Margin Of Safety & Safety Factors

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Gyro-2134 GDI-2370: For all Gaia elements the design factor, FOSD = 1. ...

Y A

Gyro-2135 GDI-2371: Where design loads are generated using FE analyses ...

Y A

Gyro-2136 GDI-2372: The GAIA hardware shall be able to withstand, with ...

Y T,A

Gyro-2137 GDI-2375: All mechanical elements shall demonstrate positive ...

Y A

Gyro-2138 GDI-2380: The margins of safety for all elements of the unit ...

Y A

Gyro-2139 GDI-2381: All bolts shall be sized to prevent sliding under ...

Y A

Gyro-2140 GDI-2502: Initially conservative friction coefficients regar ...

Y A

Gyro-2141 GDI-2382: Wherever applicable, rules for general design of b ...

Y A

Gyro-2142 GDI-2383: In addition, in case of combined loads due to ther ...

Y A

Gyro-2143 GDI-2385: where T, S and M are applied values including safe ...

Y

Gyro-2144 GDI-2386: Method for evaluation of dimensioning loads/stress ...

Y A

Gyro-2145 GDI-129: The units shall be designed with positive margins ...

Y A

Gyro-2146 GDI-130: The design loads for the structure elements are to ...

Y A

Gyro-2147 GDI-131: The internal loads (thermo elastic, pre-stressed m ...

Y A

Gyro-2148 GDI-132: For the computation of the design loads the maximu ...

Y A

Gyro-2149 GDI-2297: For sine and random vibrations, the mechanical siz ...

Y A

3.2.1.6 Alignment and Stability Gyro-2151 GDI-2550:

The stability of the equipment shall comply with r ... Y T,A

Gyro-2152 GDI-2548: The following causes of misalignment shall be anal ...

Y T,A

3.2.2 Design Requirements 3.2.2.1 Attachment Requirements Gyro-2155 GDI-160:

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

Gyro-2156 GDI-161: The attachment points shall provide a controlled s ...

Y I,R

Gyro-2157 GDI-162: The interface plane flatness of a unit shall be be ...

Y I

Gyro-2158 GDI-163: The mechanical mounting interface shall be consist ...

Y R

Gyro-2159 GDI-164: The unit bolts type and number shall be defined to ...

Y R

Gyro-2160 GDI-165: Unless otherwise specified all units shall be thro ...

Y I,R

Gyro-2161 GDI-2132: To minimise CoG uncertainty of the unit when mount ...

Y I,R

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Gyro-2162 GDI-168: Unless special conditions override, the thickness ...

Y I,R

Gyro-2163 GDI-169: For the unit mounting, provision shall be made for ...

Y I,R

Gyro-2164 GDI-2123: Unit Lug/Hole Design Requirements: Unit mounting h ...

Y I,R

Gyro-2165 GDI-170: Sufficient clearance shall be allowed between mech ...

Y I,R

Gyro-2166 GDI-173: Fasteners shall be procured and tested according t ...

Y I

Gyro-2167 GDI-2599: Fasteners shall comply with the requirements of EC ...

Y T,A

Gyro-2168 GDI-2600: Fasteners smaller than diameter 5 mm shall not be ...

Y R

Gyro-2169 GDI-2598: Titanium alloy fasteners shall not be used in safe ...

Y R

Gyro-2170 GDI-174: The Flight equipment shall be able to survive:- - ...

Y A

Gyro-2171 GDI-176: Units requiring alignment with an accuracy better ...

Y R

Gyro-2172 GDI-177: Optical references are required to withstand all t ...

Y R

Gyro-2173 GDI-178: Location of optical references for units shall be ...

Y R

Gyro-2174 GDI-179: The alignment errors shall be included in pointing ...

Y R

Gyro-2175 GDI-180: Units which require alignment accuracy of ±0.25° o ...

Y R

3.2.2.3 Electrical connectors Gyro-2177 GDI-2302:

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

Gyro-2178 GDI-2303: Connectors shall be arranged in such a way that th ...

Y I,R

Gyro-2179 GDI-2304: Unit shall offer means to mechanically lock male a ...

Y I,R

3.2.3 Mechanical / Optical Interface Control Documents Gyro-2181 GDI-183:

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

Gyro-2182 GDI-184: Interfaces will be subjected to a formal inspectio ...

Y T,I

Gyro-2183 GDI-185: The issues of ICDs have to be released as defined ...

Y A

Gyro-2184 GDI-186: One of the attachment holes on a unit shall be spe ...

Y R

Gyro-2185 GDI-187: The unit reference frame shall have its origin at ...

Y R

Gyro-2186 GDI-188: The unit alignment reference frame shall have its ...

Y R

Gyro-2187 GDI-190: The dimensioning of the attachment hole pattern sh ...

Y A

Gyro-2188 GDI-191: Interface Control Drawings shall be provided to th ...

Y R

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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 Gyro-2193 GDI-239:

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

3.3.1.2 Conductively Controlled Unit Gyro-2195 GDI-241:

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

3.3.1.3 Isothermal Unit Gyro-2197 GDI-244:

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

Gyro-2198 GDI-245: For conductive units the temperature difference be ...

Y R

Gyro-2199 GDI-246: For units not fulfilling GDI-244/245 additional th ...

Y R

3.3.1.4 Temperature Reference Point (TRP) Gyro-2201 GDI-248:

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

3.3.2 Thermal Interface Requirements 3.3.2.1 Conductive Interface Gyro-2204 GDI-252:

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

Gyro-2205 GDI-253: Unit mounting areas shall not be painted or anodis ...

Y R

Gyro-2206 GDI-254: All units dissipating significantly through their ...

Y R

Gyro-2207 GDI-255: Local heat flux shall not be greater than 1.5x spe ...

Y A

3.3.2.2 Radiative Interface Gyro-2209 GDI-258:

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

Gyro-2210 GDI-2582: Units shall demonstrate compliance to their design ...

Y T,A

3.3.2.3 Internal Temperature Monitoring Gyro-2212 GDI-260:

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

Gyro-2213 GDI-261: The location, type and electrical interface of all ...

Y R

3.3.3 Thermal Design Requirements Gyro-2215 GDI-2657:

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

Gyro-2216 GDI-263: The units shall be designed such that all internal ...

Y A

Gyro-2217 GDI-264: Hot spots on the external surface of the unit are ...

Y A,R

Gyro-2218 GDI-2656: In the absence of any uncertainty analysis an init ...

Y A

Gyro-2219 GDI-2079: For units located outside of the Focal Plane Assem ...

Y A,R

3.3.4 Thermal Control 3.3.4.1 General Gyro-2222 GDI-2555:

The equipment thermal control shall comply with EC ... Y T,A,R

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Gyro-2223 GDI-2556: The equipment thermal control shall be achieved pr ...

Y R

Gyro-2224 GDI-2557: The equipment thermal control design shall permit ...

Y A

Gyro-2225 GDI-2558: The equipment thermal control must be testable on ...

Y T,A

Gyro-2226 GDI-2559: If special equipment is required to evacuate the h ...

Y T,I

Gyro-2227 GDI-2560: No thermal control item shall prevent the spacecra ...

Y R

Gyro-2228 GDI-2561: Deviations and temporal degradations from the nomi ...

Y A

Gyro-2229 GDI-2562: A Thermal Reference Point (TRP) shall be defined a ...

Y A

Gyro-2230 GDI-2563: The TRP temperature also called "interface tempera ...

Y A

Gyro-2231 GDI-2564: In addition, the TRP temperature shall be monitore ...

Y T

Gyro-2232 GDI-2565: The equipment thermal control shall include and mo ...

Y A,R

Gyro-2233 GDI-2566: The design limits of units are equal to the qualif ...

Y T,A

Gyro-2234 GDI-2567: The design limits of units are equal to the accept ...

Y T,A

3.3.4.2 Thermal Analysis Gyro-2236 GDI-2552:

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

Gyro-2237 GDI-2553: The Geometrical and Thermal Mathematical Models (G ...

Y T,A

3.3.5 Thermal Interface Control Documents Gyro-2239 GDI-267:

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

Gyro-2240 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 Gyro-2243 GDI-2091:

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

Gyro-2244 GDI-272: The Thermal mathematical model shall be provided f ...

Y A

Gyro-2245 GDI-273: Units: All units used in thermal models (geometric ...

Y A

3.3.6.2 Thermal Model Correlation Gyro-2247 GDI-275:

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

3.3.6.3 Reduced Thermal Model Gyro-2249 GDI-277:

The consistency between reduced and detailed therm ... Y A

Gyro-2250 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

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Gyro-2254 GDI-282: For each optical surface, the physical dimension s ...

Y R

3.4.1.2 Materials Gyro-2256 GDI-284:

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

Gyro-2257 GDI-285: The use of stain sensitive glasses shall be avoide ...

Y R

Gyro-2258 GDI-286: The use of optical cements shall be avoided as far ...

Y R

3.4.1.3 Coatings Gyro-2260 GDI-289:

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

Gyro-2261 GDI-290: Thermo-optical properties of the coatings shall be ...

Y R

Gyro-2262 GDI-292: High efficiency anti-reflective coatings shall be ...

Y R

Gyro-2263 GDI-293: Sensitivity of coatings to polarisation effects as ...

Y T,R

3.5 Electrical Design and Interface Requirements 3.5.1 General Requirements Gyro-2266 GDI-308:

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

Gyro-2267 GDI-309: Beginning-Of-Life criteria shall be derived by the ...

Y R

3.5.2 Power Interface Requirements (LC & FC) Gyro-2269 GDI-2046:

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

3.5.2.1 Regulated Power Requirements Gyro-2271 GDI-338:

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

Gyro-2272 GDI-2696: During all mission phases the spacecraft power bus ...

Y T

Gyro-2273 GDI-2104: The spacecraft fully regulated bus shall have a no ...

Y T,R

Gyro-2274 GDI-2103: For load changes of up to 50% of the nominal load ...

Y T,R

Gyro-2275 GDI-2133: The bus voltage shall remain within 5% of its nomi ...

Y T,R

Gyro-2276 GDI-339: If undervoltage protection is implemented by the l ...

Y T

Gyro-2277 GDI-340: In case of an inductive load, when considering the ...

Y T,A

Gyro-2278 GDI-341: The load shall not be irreversibly degraded for an ...

Y R

Gyro-2279 GDI-342: No fuse protection shall be implemented. ...

Y R

Gyro-2280 GDI-343: Primary current protection shall not be implemente ...

Y R

Gyro-2281 GDI-344: The contractor shall design the load side of the L ...

Y T,R

Gyro-2282 GDI-346: All power converters shall be designed to allow op ...

Y T

Gyro-2283 GDI-347: The free-running frequency shall be limited to ±10 ...

Y T

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Gyro-2284 GDI-348: The as designed free-running frequency and frequen ...

Y T

Gyro-2285 GDI-349: Units connected to LCL's or FCL's shall be designe ...

Y T,A

Gyro-2286 GDI-1273: At the point of regulation, the impedance of the v ...

Y T,R

3.5.2.2 Power Consumption Requirements Gyro-2288 GDI-361:

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

Gyro-2289 GDI-362: For each power interface circuit, the following co ...

Y T,A

Gyro-2290 GDI-363: A power consumption test shall be required at temp ...

Y T,R

3.5.2.3 Tolerance to Power Bus Failures Gyro-2292 GDI-365:

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

3.5.2.4 Initial Electrical Status Gyro-2294 GDI-367:

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

3.5.2.5 Special Case: Secondary Power Supplied Units Gyro-2296 GDI-370:

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

Gyro-2297 GDI-371: The source unit shall be protected against short-c ...

Y T

Gyro-2298 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 Gyro-2301 GDI-378:

Specified driver (or source) characteristics shall ... Y R

Gyro-2302 GDI-379: All data and signal interface drivers shall surviv ...

Y T,A

Gyro-2303 GDI-380: The unit shall tolerate active signal I/Fs when un ...

Y T,A

Gyro-2304 GDI-381: In case the electrical architecture does foresee c ...

Y T,R

Gyro-2305 GDI-382: In case no load is specified, the characteristics ...

Y R

3.5.3.2 Harness Capacitance Gyro-2307 GDI-391:

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

3.5.4 Connectors General Design Requirements 3.5.4.1 Harness Gyro-2310 GDI-395:

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

Gyro-2311 GDI-396: All cable bundles shall be routed as close as poss ...

Y I,R

Gyro-2312 GDI-397: In wiring through connectors all leads shall be ke ...

Y I,R

Gyro-2313 GDI-398: The DC resistance between the single cable shield ...

Y T

Gyro-2314 GDI-399: The structure termination of shields shall be made ...

Y I,R

3.5.4.2 Connector Types

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Gyro-2316 GDI-401: All connectors mounted on units shall be D*MA** co ...

Y R

Gyro-2317 GDI-402: All flight connectors shall be designed to withsta ...

Y I,R

Gyro-2318 GDI-2158: Individual mate/demates shall be recorded in a mat ...

Y R

Gyro-2319 GDI-2157: The number of times flight connectors are mated / ...

Y R

Gyro-2320 GDI-2156: If by prior agreement with S/C Prime the number of ...

Y I,R

Gyro-2321 GDI-403: Different connector classes shall be implemented i ...

Y R

3.5.4.3 Connector Characteristics Gyro-2323 GDI-405:

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

Gyro-2324 GDI-406: Connectors shall not be a source of single point f ...

Y R

Gyro-2325 GDI-407: Equipment or structure-mounted connectors shall be ...

Y R

Gyro-2326 GDI-408: Male and female connectors shall be mechanically l ...

Y R

Gyro-2327 GDI-409: Active lines together with their return shall be o ...

Y I

Gyro-2328 GDI-410: Connectors shall be made of Non magnetic material ...

Y R

Gyro-2329 GDI-411: For any unit connector which contains a number of ...

Y T,R

Gyro-2330 GDI-412: Nominal and redundant lines shall have separated c ...

Y R

3.5.4.4 Connector Mounting Gyro-2332 GDI-414:

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

Gyro-2333 GDI-415: Connectors shall be arranged in such a way that th ...

Y R

Gyro-2334 GDI-416: Mechanical methods in conjunction with identificat ...

Y I,R

Gyro-2335 GDI-417: Connector savers shall be utilized on all flight s ...

Y R

Gyro-2336 GDI-418: The connection shield ground pin to case shall be ...

Y R

3.5.4.5 Test Connectors Gyro-2338 GDI-420:

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

Gyro-2339 GDI-421: Test connectors shall be protected by EMC metal co ...

Y I,R

Gyro-2340 GDI-422: The metallic protection cover shall be capable of ...

Y R

3.5.5 Standard Interfaces 3.5.5.1.3.1 Low Voltage Differential Signaling (LVDS) Gyro-2343 GDI-2406:

All the SpaceWire links shall use Low-Voltage Diff ... Y I,R

Gyro-2344 GDI-2407: The LVDS driver and receiver interfaces shall be d ...

Y T

3.5.5.1.3.2 Failsafe Operation of LVDS

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Gyro-2346 GDI-2410: The LVDS failsafe operation requirements of the EC ...

Y T,I,R

Gyro-2347 GDI-2408: No LVDS configuration involving more than one (1) ...

Y T,I,R

3.5.5.2 MIL-STD-1553 Bus Interfaces (MIL) Gyro-2349 GDI-426:

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

Gyro-2350 GDI-427: All units (BC or RT) shall be configured in long s ...

Y R

Gyro-2970 GDI-2177: The maximum length of the long stub shall be 6 met ...

Y I,R

Gyro-2971 GDI-2176: Only one RT shall be connected to a stub cable. ...

Y I,R

Gyro-2351 GDI-428: Each BC and RT (N&R) shall be connected to both 15 ...

Y I,R

Gyro-2352 GDI-429: Each stub shall be grounded inside each RT or BC d ...

Y R

Gyro-2353 GDI-430: The RT address shall be programmable on an externa ...

Y R

Gyro-2354 GDI-431: The 1553-bus shall be connected on separate connec ...

Y R

Gyro-2355 GDI-2139: The 1553-bus shall be connected on separate connec ...

Y R

Gyro-2356 GDI-1198: Unless otherwise agreed with the Prime Contractor, ...

Y R

Gyro-2357 GDI-432: The 1553-Bus Protocol shall be compliant to the Ga ...

Y R

Gyro-2358 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 Gyro-2974 GDI-2460:

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

Gyro-2975 GDI-2462: These tests shall be performed only in ambient con ...

Y

Gyro-2976 GDI-2463: ...

Y T

Gyro-2977 GDI-2464: ...

Y T

Gyro-2978 GDI-2465: ...

Y T

Gyro-2979 GDI-2466: ...

Y T

Gyro-2980 GDI-2467: ...

Y T

Gyro-2981 GDI-2468: ...

Y T

Gyro-2982 GDI-2469: ...

Y T

Gyro-2983 GDI-2470: ...

Y T

Gyro-2984 GDI-2471: ...

Y T

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Gyro-2985 GDI-2472: ...

Y T

Gyro-2986 GDI-2473: ...

Y T

Gyro-2987 GDI-2474: ...

Y T

Gyro-2988 GDI-2475: ...

Y T

Gyro-2989 GDI-2476: ...

Y T

Gyro-2990 GDI-2477: ...

Y T

Gyro-2991 GDI-2478: ...

Y T

Gyro-2992 GDI-2479: ...

Y T

Gyro-2993 GDI-2480: Note 1: Functional test through 1553B interface ...

Y T

Gyro-2994 GDI-2481: ...

Y T

3.5.5.2.1.2 Acceptance Test Gyro-2996 GDI-2485:

... Y T

Gyro-2997 GDI-2486: ...

Y T

Gyro-2998 GDI-2487: ...

Y T

Gyro-2999 GDI-2488: ...

Y T

Gyro-3000 GDI-2489: ...

Y T

Gyro-3001 GDI-2490: ...

Y T

Gyro-3002 GDI-2491: ...

Y T

Gyro-3003 GDI-2492: ...

Y T

Gyro-3004 GDI-2493: ...

Y T

Gyro-3005 GDI-2494: Note 1: Functional test through 1553B interface ...

Y T

3.5.5.3 Standard Balanced Digital link (SBDL) Gyro-2360 GDI-438:

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

Gyro-2361 GDI-1201: The contractor shall design his side of the Standa ...

Y T,R

3.5.5.4 UART Serial Link (USL) Gyro-2363 GDI-450:

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

Gyro-2364 GDI-451: The UART RS-422 Serial Link Interface shall be imp ...

Y R

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Gyro-2365 GDI-452: The contractor shall design his part of the UART R ...

Y R

Gyro-2366 GDI-453: Figure GDI-456 shows an example for data transmiss ...

Y R

Gyro-2367 GDI-1274: The OBC shall be able to send commands on the Tran ...

Y T

Gyro-2368 GDI-1275: No data repetition mechanism in both directions sh ...

Y T

Gyro-2369 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) Gyro-2372 GDI-460:

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

Gyro-2373 GDI-462: The active level shall be High level ...

Y R

Gyro-2374 GDI-463: The synchronisation edge shall be the rising edge ...

Y R

Gyro-2375 GDI-464: The pulse width shall be ³ 900 ns ...

Y T

3.5.5.5.2 Synchronization Clock Interface (TBC) 3.5.5.6 Housekeeping Analog Acquisitions Gyro-2378 GDI-471:

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

3.5.5.6.1 Analogue Telemetry Aquisition (AN1) Gyro-2379 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) Gyro-2385 GDI-482:

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

Gyro-2386 GDI-483: The temperature aquisition interface circuitry, as ...

Y R

3.5.5.7.1 Thermistor Type1: YSI-44907/-44908 (ANY) Gyro-2388 GDI-1215:

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

3.5.5.7.2 Thermistor Type2: PT-1000 (ANP) Gyro-2390 GDI-487:

Temperature Acquisition Type 2: PT-1000 (ANP) Inte ... Y T,R

3.5.5.7.3 Thermistor Type3: Fenwell (ANF) Gyro-2392 GDI-1216:

Temperature Acquisition Type 3: Fenwall (ANF) Inte ... Y T,R

3.5.5.7.4 Thermistor Type4: PT-200 (ANT) Gyro-2394 GDI-2136:

Temperature Acquisition Type 4: PT-200 (ANT) Inter ... Y T,R

3.5.5.8 Relay Commands (SHP, EHP, SLP) Gyro-2396 GDI-493:

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

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Gyro-2397 GDI-494: The High Power On/Off Command receiver shall be is ...

Y R

Gyro-2398 GDI-495: The High Power On/Off Command receiver shall be eq ...

Y R

Gyro-2399 GDI-496: The High Power On/Off Command source shall be shor ...

Y R

Gyro-2400 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) Gyro-2402 GDI-497:

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

Y T,R

3.5.5.9 Relay Status Acquisitions (RSA) Gyro-2404 GDI-1229:

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

Gyro-2405 GDI-516: Relay Status Acquisition The contractor shall desi ...

Y T,R

3.5.5.12 Digital Bi-Level TM Acquisitions (BLD) Gyro-2407 GDI-523:

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

Gyro-2408 GDI-1232: The OBC shall acquire via the Bi-Level Digital Acq ...

Y R

Gyro-2409 GDI-1233: Each channel shall be allocated to a specific bit ...

Y R

Gyro-2410 GDI-524: Bi-level Digital Interface The contractor shall de ...

Y T,R

3.5.6 Electrical Interface Control Document Gyro-2412 GDI-558:

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

3.5.7 EMC Requirements Gyro-2414 GDI-2154:

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

3.5.7.1 Bonding Gyro-2416 GDI-562:

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

Gyro-2417 GDI-563: Metallic parts of each electrical equipment chassi ...

Y T

Gyro-2418 GDI-564: Joint faces shall be flat and clean before assembl ...

Y I,R

Gyro-2419 GDI-565: All non-electrical equipment shall be bonded to th ...

Y T

Gyro-2420 GDI-566: Each electrical equipment chassis (case) shall be ...

Y T,R

Gyro-2421 GDI-567: Metallic receptacles of connectors shall be electr ...

Y T

3.5.7.1.1 Ground Reference Rail Gyro-2423 GDI-569:

Electrical bonding throughout CFRP structure shall ... Y R

Gyro-2424 GDI-2715: the GRR shall be attahced at less than or equal to ...

Y R

Gyro-2425 GDI-570: The resistance between any adjacent parts of the G ...

Y T,R

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Gyro-2426 GDI-571: The resistance between any two points of the GRR s ...

Y T,R

3.5.7.1.2 Cable and Harness Shields Gyro-2428 GDI-573:

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

Gyro-2429 GDI-574: The maximum unshielded length of any shielded wire ...

Y R

Gyro-2430 GDI-575: Daisy chaining of shield terminations shall be avo ...

Y R

Gyro-2431 GDI-576: Shields shall not be used as an intentional curren ...

Y R

3.5.7.1.3 Structure Parts Gyro-2433 GDI-578:

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

Gyro-2434 GDI-1990: The DC resistance between two mating metal strutur ...

Y T,R

Gyro-2435 GDI-1991: Across moveable parts, a bond strap shall be appli ...

Y T,R

Gyro-2436 GDI-1992: For CFRP structure without shielding function, the ...

Y T,R

Gyro-2437 GDI-2093: This Requirement has been Deleted. ...

Y

Gyro-2438 GDI-2092: For CFRP structure used for electromagnetic shield ...

Y T,R

Gyro-2439 GDI-1989: Metal fittings shall be bonded to the structure wi ...

Y T,R

Gyro-2440 GDI-579: Metal fittings shall be bonded to CFRP with a DC r ...

Y T,R

Gyro-2441 GDI-2105: The DC resistance from any metal structure part an ...

Y T,R

Gyro-2442 GDI-2094: The DC resistance between any other conductive com ...

Y T,R

Gyro-2443 GDI-1993: The GRR shall be attached at less than or equal to ...

Y T,R

3.5.7.1.4 Mechanical Parts Gyro-2445 GDI-581:

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

Gyro-2446 GDI-582: Mechanical Parts used for electromagnetic shieldin ...

Y T,R

3.5.7.2 Grounding and Isolation 3.5.7.2.1 General Gyro-2449 GDI-585:

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

Gyro-2450 GDI-586: CFRP and SiC shall not be used as an electrical bo ...

Y R

3.5.7.2.2 Electrical and Electronic Unit Requirement Gyro-2452 GDI-588:

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

Gyro-2453 GDI-589: Openings for drainage, ventilation, etc... shall n ...

Y I

Gyro-2454 GDI-590: All units shall have a M4 bonding stud ...

Y I

Gyro-2455 GDI-591: The design of this bonding stud shall allow the co ...

Y I

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3.5.7.2.3 Insulating materials Gyro-2457 GDI-593:

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

Gyro-2458 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 Gyro-2461 GDI-605:

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

Gyro-2462 GDI-606: Isolation: All units (except PCDU) shall maintain ...

Y T,R

3.5.7.3.2 Secondary Power Lines Gyro-2464 GDI-609:

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

Gyro-2465 GDI-1988: Equipment with its own dedicated DC - DC converter ...

Y T

Gyro-2466 GDI-610: Isolation: prior to connection of the unit interna ...

Y T,R

Gyro-2467 GDI-2106: After grounding, the impedance between the unit se ...

Y T,R

Gyro-2468 GDI-611: Secondaries distributed between units (1 supplier; ...

Y R

Gyro-2469 GDI-612: Secondaries distributed between units (1 supplier; ...

Y R

Gyro-2470 GDI-614: Grounding diagram including zero volts interconnec ...

Y I

Gyro-2471 GDI-615: The symbols in Figure GDI-2107 below shall be used ...

Y R

3.5.7.3.3 Signal Interfaces Gyro-2473 GDI-617:

Signal circuits interfacing between Satellite equi ... Y R

Gyro-2474 GDI-618: Where single-ended signal transmitters are used, i ...

Y R

Gyro-2475 GDI-619: The use of common signal return paths is only perm ...

Y R

3.5.7.3.4 EGSE Grounding and Isolation Gyro-2477 GDI-621:

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

3.5.7.4 Magnetic Moment Gyro-2479 GDI-1997:

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

Gyro-2480 GDI-1998: Deleted. ...

Y T

3.6 Operations Design and Interface Requirements 3.6.1 Bit / Byte Numbering Convention Gyro-2483 GDI-632:

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

Gyro-2484 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

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Gyro-2487 GDI-638: Mode/State transitions: Transitions from one mode/ ...

Y R

Gyro-2488 GDI-639: The unit supplier shall identify appropriate modes ...

Y R

Gyro-2489 GDI-640: At all times, equipment and units shall be in a cl ...

Y T,R

Gyro-2490 GDI-641: In addition, modes and the mode transitions manage ...

Y T,R

Gyro-2491 GDI-642: The unit supplier shall identify all internal and ...

Y R

Gyro-2492 GDI-643: The unit supplier shall identify all transition ti ...

Y R

Gyro-2493 GDI-644: Mode/State transitions with duration longer than 1 ...

Y R

Gyro-2494 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 Gyro-2497 GDI-648:

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

Gyro-2498 GDI-649: In operating states of the unit, it shall be possi ...

Y T

Gyro-2499 GDI-650: In addition, in non-operating states of the unit, ...

Y T

Gyro-2500 GDI-651: Individual switching of switchable elements (e.g. ...

Y T

Gyro-2501 GDI-652: The on-board reception, processing and execution o ...

Y T,R

Gyro-2502 GDI-653: The function of a command shall not change through ...

Y T,R

Gyro-2503 GDI-654: A single command may be used to initialise a chang ...

Y T,R

Gyro-2504 GDI-655: Commands with variable bit-fields meaning shall no ...

Y R

Gyro-2505 GDI-656: Nominal and the redundant functions or equipments ...

Y T

Gyro-2506 GDI-657: The unit design shall avoid any conflict between a ...

Y T

3.6.2.3 Observability 3.6.2.3.1 General Gyro-2509 GDI-660:

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

Gyro-2510 GDI-661: The unit shall provide in its housekeeping telemet ...

Y T,R

Gyro-2511 GDI-662: The unit shall provide the necessary instrumentati ...

Y T,R

Gyro-2512 GDI-663: Telemetry measurement sensors shall be designed su ...

Y T

Gyro-2513 GDI-664: It shall be possible to determine the status of th ...

Y T

Gyro-2514 GDI-665: Essential (high-priority) telemetry data enabling ...

Y T,R

Gyro-2515 GDI-666: Telemetry shall always be provided to identify una ...

Y T,R

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Gyro-2516 GDI-667: Status information in telemetry shall be provided ...

Y T,R

Gyro-2517 GDI-668: Any TM processing required at a higher operational ...

Y R

Gyro-2518 GDI-669: Telemetry shall always be available to determine t ...

Y R

Gyro-2519 GDI-670: When a key parameter is derived on-board from seve ...

Y T,R

3.6.2.3.2 Telemetry Acquisition Gyro-2521 GDI-672:

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

Gyro-2522 GDI-673: The unit design shall avoid any conflict between t ...

Y T

Gyro-2523 GDI-674: TM acquisitions with conditional meaning shall not ...

Y R

Gyro-2524 GDI-675: The value of a telemetry parameter shall be transm ...

Y R

Gyro-2525 GDI-676: Analog TM Acquisition: Analog TM acquisitions sha ...

Y T,R

Gyro-2526 GDI-677: Acquisition of safety critical analog parameters o ...

Y R

Gyro-2527 GDI-678: The values of currents or voltages readings shall ...

Y R

Gyro-2528 GDI-679: The calibration curve of an analog parameter shall ...

Y R

3.6.2.3.3 Observability of Hardware Configuration Gyro-2530 GDI-681:

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

Gyro-2531 GDI-682: In case a unit includes several elementary functio ...

Y R

Gyro-2532 GDI-683: The configuration of any on-board device and any s ...

Y T,R

Gyro-2533 GDI-684: Any configuration command register shall be observ ...

Y R

Gyro-2534 GDI-685: The acquisition of the unit configuration/state sh ...

Y R

Gyro-2535 GDI-686: The acquisition of an ON/OFF status for a relay sh ...

Y R

Gyro-2536 GDI-687: If the unit controls the redundancy configuration ...

Y T

Gyro-2537 GDI-688: Nominal and redundant functions shall be observabl ...

Y R

3.6.2.3.4 Observability of Commands Gyro-2539 GDI-690:

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

Gyro-2540 GDI-691: Acknowledgement of commands shall be direct (i.e. ...

Y T,R

Gyro-2541 GDI-692: The association between command acknowledgement ac ...

Y I

Gyro-2542 GDI-693: Successful execution of a command to the unit shal ...

Y T,R

Gyro-2543 GDI-694: Failures in the acceptance and /or the execution o ...

Y T,R

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3.6.2.3.5 Converters Observability Gyro-2545 GDI-696:

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

3.6.2.4 Safety Critical and Hazardous Functions Gyro-2547 GDI-700:

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

Gyro-2548 GDI-701: The execution of any unit command or command seque ...

Y A

Gyro-2549 GDI-702: Commanding of critical commands shall be implement ...

Y A,R

Gyro-2550 GDI-703: The status of inhibition of safety critical functi ...

Y T

Gyro-2551 GDI-704: Units shall provide an unambiguous health status o ...

Y T

3.6.2.5 Handling of Memories Gyro-2553 GDI-706:

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

Gyro-2554 GDI-707: Any part of installed RAM’s shall be overwriteable ...

Y T

Gyro-2555 GDI-708: Any part of installed ROM’s shall be readable by m ...

Y T

Gyro-2556 GDI-709: For failure investigation, it shall be possible to ...

Y T

3.6.2.6 Autonomy Gyro-2558 GDI-711:

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

Gyro-2559 GDI-712: All parameters used for autonomous operations and ...

Y T

3.6.2.7 Automatic Functions Gyro-2561 GDI-714:

It shall be possible to inhibit and to override al ... Y T

Gyro-2562 GDI-715: All actions generated by automatic on-board logic ...

Y T

Gyro-2563 GDI-716: The automatic function design shall be such that n ...

Y A,R

Gyro-2564 GDI-717: Telemetry shall be associated to all automatic fun ...

Y T

Gyro-2565 GDI-718: For all the automatic logic using several criteria ...

Y T

Gyro-2566 GDI-719: The capability to change all on board logic (hardw ...

Y T,R

3.6.2.8 Time Synchronisation Gyro-2568 GDI-721:

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

Gyro-2569 GDI-722: If the unit has the function, all information on h ...

Y R

Gyro-2570 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 Gyro-2573 GDI-726:

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

Gyro-2574 GDI-727: Any unit shall be able to withstand (i.e. remain i ...

Y T,R

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Gyro-2575 GDI-728: It shall be possible to repeat any command several ...

Y T,R

3.6.2.9.2 Unit Self Tests Gyro-2577 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

Gyro-2579 GDI-733: FDIR functions shall be implemented in a hierarchi ...

Y A,R

Gyro-2580 GDI-734: The unit shall automatically detect any failure, w ...

Y T,R

Gyro-2581 GDI-735: At unit level failures shall be detectable by adeq ...

Y A

Gyro-2582 GDI-736: Failure detection algorithms shall report in event ...

Y A,R

Gyro-2583 GDI-737: Failures which require a reaction time less than 1 ...

Y T,A

Gyro-2584 GDI-738: Failure which requires a reaction time between 10s ...

Y A,R

Gyro-2585 GDI-739: Failure isolation shall be performed at switchable ...

Y T,A

Gyro-2586 GDI-740: Any FDIR actions on unit level shall be reported t ...

Y T,R

Gyro-2587 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 Gyro-2590 GDI-744:

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

3.6.3.2 Inputs to Operational Database Gyro-2592 GDI-746:

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

Gyro-2593 GDI-747: Data to be provided (the list is not exhaustive): ...

Y R

3.6.3.3 Operation Manual Gyro-2595 GDI-749:

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

Gyro-2596 GDI-750: The following standardization (Table GDI-751) shal ...

Y R

3.7 Software Design & Interface Requirements 3.7.1 General Gyro-2599 GDI-2181:

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

Gyro-2600 GDI-2182: All on-board software running in sub-systems shall ...

Y R

Gyro-2601 GDI-2183: The on-board software shall be developed using a h ...

Y R

Gyro-2602 GDI-2184: The use of a non high-level language code (e.g., a ...

Y A

Gyro-2603 GDI-2185: The on-board sotware shall be implemented with a l ...

Y R

3.7.2 Flight Processor Resource Sizing

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Gyro-2605 GDI-2192: During development, flight processors providing co ...

Y T,A

Gyro-2606 GDI-2193: Any on-board software shall provide the capability ...

Y T,R

Gyro-2607 GDI-2194: The resource utilisation monitor shall be availabl ...

Y T,R

Gyro-2608 GDI-2196: Sizing of the software resources shall be done in ...

Y T,A

3.7.3 Robustness 3.7.3.1 Infinite Loops Gyro-2611 GDI-2197:

The on-board software shall protect itself against ... Y T,I

Gyro-2612 GDI-2218: Whenever possibility of Warm Restart is implemente ...

Y T,I

3.7.3.2 Overload Gyro-2614 GDI-2198:

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

Gyro-2615 GDI-2199: If and only if the overload situation cannot be ab ...

Y T,I

3.7.4 Events Gyro-2617 GDI-2214:

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

Gyro-2618 GDI-2215: The on-board software shall maintain counters for: ...

Y T,I

3.7.5 Initialisation Gyro-2620 GDI-2226:

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

Gyro-2621 GDI-2228: The Cold Restart shall start execution from a hard ...

Y T

Gyro-2622 GDI-2229: The Warm Restart shall start from a software comma ...

Y T

Gyro-2623 GDI-2230: The Warm Restart shall perform a processor reset a ...

Y T,I

Gyro-2624 GDI-2227: The Cold Restart and the Warm Restart initialisati ...

Y T

Gyro-2625 GDI-2234: At a predictible stage of the initialisation, the ...

Y

3.7.6 Testability Gyro-2627 GDI-2205:

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

3.7.7 SW Maintainability 3.7.7.1 Version Number Gyro-2630 GDI-2209:

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

Gyro-2631 GDI-2212: The flight software version number shall be retrie ...

Y T

Gyro-2632 GDI-2208: The flight software version number shall be modifi ...

Y T

3.7.7.2 In Flight SW Modification Gyro-2634 GDI-2186:

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

Gyro-2635 GDI-2187: The on-board software shall be structured such tha ...

Y I

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Gyro-2636 GDI-2231: Any on-board unit embedding software shall support ...

Y T

Gyro-2637 GDI-2232: Any on-board unit embedding software shall support ...

Y T

Gyro-2638 GDI-2201: Any on-board unit embedding software shall be repr ...

Y T

3.7.7.3 Ease of SW Operations & Modifications Gyro-2640 GDI-2206:

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

Gyro-2641 GDI-2210: All on-board software data that are anticipated to ...

Y I

Gyro-2642 GDI-2211: The on-board software shall have knowledge of the ...

Y T

Gyro-2643 GDI-2207: Software-implemented limits and triggers for anoma ...

Y T,I

3.7.8 SafeGuard Memory (SGM) Maintainability Gyro-2645 GDI-2223:

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

Gyro-2646 GDI-2224: The on-board software shall implement SGM data str ...

Y T,I

3.7.9 Independent SW Verification & Validation (ISVV) Gyro-2648 GDI-2188:

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

3.7.10 SW Maintenance Products Gyro-2650 GDI-2189:

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

Gyro-2651 GDI-2190: All on-board software executed in ASIC, FPGA, or o ...

Y T,I

Gyro-2652 GDI-2233: The SW maintenance environment shall provide the m ...

Y T,I

Gyro-2653 GDI-2235: All software licenses for any software used to dev ...

Y I

Gyro-2654 GDI-2236: For any on-board unit embedding software, a softwa ...

Y T,I

Gyro-2655 GDI-2237: The software development and maintenance facility ...

Y T,I

4 Environment Design Requirements Gyro-2657 GDI-2315:

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

4.1 Ground operation phase Gyro-2659 GDI-2318:

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

4.1.1 Thermal and climatic environment Gyro-2661 GDI-2320:

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

Gyro-2662 GDI-2321: Assembly, integration and verification of flight h ...

Y I

Gyro-2663 GDI-2322: During transport prior to integration on the space ...

Y I

Gyro-2664 GDI-2323: The flight hardware transportation containers shal ...

Y T,A

4.1.2 Mechanical environment Gyro-2666 GDI-790:

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

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Gyro-2667 GDI-793: During ground transportation the equipments shall ...

Y T,A

Gyro-2668 GDI-2327: All MGSE, containers, transportation and handling ...

Y T,A

Gyro-2669 GDI-2328: Sine and random vibrations: the unit transport con ...

Y T,A

Gyro-2670 GDI-2329: For containers, the shock requirement is a drop of ...

Y T

Gyro-2671 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 Gyro-2674 GDI-780:

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

4.2.2 Contamination Gyro-2676 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 Gyro-2679 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 Gyro-2682 GDI-808:

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

4.2.3.2.2 Random Environment Gyro-2684 GDI-812:

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

4.2.3.2.3 Acoustic environment Gyro-2686 GDI-2338:

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

4.2.3.2.4 Shock Environment Gyro-2688 GDI-818:

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

4.2.4 Thermal environment Gyro-2690 GDI-2602:

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

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 Gyro-2695 GDI-823:

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

Gyro-2696 GDI-2131: The unit shall be compatible with internal loads g ...

Y A

4.3.1.2 Micro-vibrations Gyro-2698 GDI-825:

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

4.3.1.3 Dynamical distrurbances Gyro-2700 GDI-2677:

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

Gyro-2701 GDI-2678: Once the equipment operational conditions have bee ...

Y I,R

4.3.2 In orbit thermal

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Gyro-2703 GDI-841: During the In Orbit phase, the spacecraft units TR ...

Y A,R

Gyro-2704 GDI-2583: During the In Orbit phase, the spacecraft units wi ...

Y T,A

Gyro-2705 GDI-2878: The units listed in the above table shall consider ...

Y T,A

4.4 Radiation Environment 4.4.1 Introduction Gyro-2708 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

Gyro-2711 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 Gyro-2717 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 Gyro-2720 GDI-876:

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

Gyro-2721 GDI-877: Unit shall take into account the shielding provide ...

Y A,R

4.4.5 Radiation Sensitive Components Gyro-2723 GDI-1969:

The Subcontractor shall implement a Radiation Hard ... Y R

Gyro-2724 GDI-1970: All parts shall be reviewed by the Subcontractor t ...

Y R

Gyro-2725 GDI-1971: The Subcontractor shall issue a Radiation Assessme ...

Y R

4.4.5.1 Total Dose Gyro-2727 GDI-1975:

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

4.4.5.2 Single Event Effects (SEE) Gyro-2729 GDI-1977:

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

Gyro-2730 GDI-1978: The component shall be designed to tolerate GCR, p ...

Y T,A,R

4.4.5.3 Single Event Latch-up Gyro-2732 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...)

Gyro-2734 GDI-1982: Part types shall be acceptable according to the ac ...

Y A,R

Gyro-2735 GDI-2681: Memory circuits shall have sufficient error det ...

Y A,R

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

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Gyro-2737 GDI-1984: For SEB and SEGR, error rate prediction techniques ...

Y A,R

4.4.5.6 Displacement Damage Gyro-2739 GDI-1986:

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

Gyro-2740 GDI-1987: The reset or data corruption occurrence rate due t ...

Y T,A,R

4.5 EMC Environment 4.5.1 EMC Performance Requirements 4.5.1.1 Inrush Current Gyro-2744 GDI-895:

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

4.5.1.2 Voltage Transients Gyro-2746 GDI-897:

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

Gyro-2747 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

Gyro-2750 GDI-902: Conducted narrow band current emissions (different ...

Y T,R

Gyro-2751 GDI-904: Conducted narrow band current emissions (common mo ...

Y T,R

Gyro-2752 GDI-2716: In case of internal redundancy, conducted emission ...

Y T

4.5.1.3.2 Conducted Emissions on Power Leads, Time Domain

Gyro-2754 GDI-907: Time domain conducted differential mode voltage ri ...

Y T,R

Gyro-2755 GDI-908: For Primary Power users, time domain conducted emi ...

Y T,R

Gyro-2756 GDI-2709: Time domain current emissions shall be < 10% of th ...

Y T

Gyro-2757 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

Gyro-2760 GDI-918: The maximum voltage emission levels for secondary ...

Y T,R

4.5.1.4.2 CE for Secondary Power Supply Units, Time Domain

Gyro-2762 GDI-920: The voltage ripple and spikes on secondary power s ...

Y T,R

4.5.1.5 Conducted Emissions Signal lines Common Mode Gyro-2764 GDI-2711:

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

4.5.2 Radiated Emissions - E field Gyro-2767 GDI-922:

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

Gyro-2768 GDI-2704: On board Receiver Notch: 20 dBµV/M between 7190 an ...

Y T,R

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4.5.3 Radiated Emissions - H field Gyro-2770 GDI-926:

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

4.5.4 Radiated Emissions Fluctuations - E Field Gyro-2772 GDI-2013:

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

4.5.5 Radiated Emissions Fluctuations - H Field Gyro-2774 GDI-2022:

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

4.5.6 Radiated Susceptibility - E field Gyro-2776 GDI-928:

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

Gyro-2777 GDI-2705: The unit shall not show any malfunction or deviati ...

Y T

Gyro-2778 GDI-929: No unit that is powered On at launch shall show an ...

Y T,R

4.5.7 Radiated Susceptibility - H field Gyro-2780 GDI-932:

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

4.5.8 Units linked by Secondary Power Lines Gyro-2782 GDI-934:

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

Gyro-2783 GDI-935: When a unit delivers secondary lines, the unit sha ...

Y T

4.5.9 Conducted Susceptibility Power Lines 4.5.9.1 Conducted Susceptibility Sine Wave - Differential

Mode

Gyro-2786 GDI-938: Primary power bus powered units shall not exhibit ...

Y T,R

4.5.9.2 Conducted Susceptibility Sine Wave - Common Mode

Gyro-2788 GDI-2000: Primary power bus powered units shall not exhibt a ...

Y T,R

4.5.9.3 Conducted Susceptibility - Transient Gyro-2790 GDI-2007:

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

Gyro-2791 GDI-2009: Transient Type 1 With reference to (figure GDI-941 ...

Y T

Gyro-2792 GDI-2010: Transient Type 2 With reference to (figure GDI-941 ...

Y T

4.5.9.4 CE / CS on Interface signal lines Gyro-2794 GDI-944:

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

Gyro-2795 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

Gyro-2798 GDI-949: The conducted susceptibility specification for sec ...

Y T,R

4.5.10.2 Requirement at subsystem or system level

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Gyro-2800 GDI-951: In addition, a margin of at least +6dB shall be de ...

Y T,R

4.5.11 DC Magnetic Requirements Gyro-2802 GDI-958:

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

Gyro-2803 GDI-959: Deleted. ...

Y

4.5.12 ESD Susceptibility Gyro-2805 GDI-962:

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

4.5.13.2 Corona Gas Discharge Gyro-2807 GDI-2693:

Equipments and sub-systems shall be free from gas ... Y A

Gyro-2808 GDI-2694: Adequate venting shall be provided to ensure that ...

Y A,I

Gyro-2809 GDI-2695: If the above requirements GDI-2693 and GDI-2694 ca ...

Y T,A

4.5.14 Micrometeoroid environement Gyro-2811 GDI-2683:

The micrometeoroid environment for the mission sha ... Y R

Gyro-2812 GDI-2686: A damage assessment based on the micrometeoroid en ...

Y A,R

5 Unit Level Test Requirements 5.1 General 5.1.1 Test Definition 5.1.1.1 Qualification tests Gyro-2817 GDI-967:

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

5.1.1.2 Acceptance Tests Gyro-2819 GDI-969:

Environmental acceptance testing shall be performe ... Y T,A,R

5.1.1.3 Functional Performance Tests Gyro-2821 GDI-971:

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

5.1.2 Test Facilities RequirementsY Gyro-2823 GDI-973:

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

5.1.2.1 Accuracy of Test Instrumentation Gyro-2825 GDI-975:

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

5.1.2.2 Tolerances of Test Parameters Gyro-2827 GDI-977:

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

5.1.2.3 Facility Ambient Condition Gyro-2829 GDI-981:

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

5.1.3 Test Execution Gyro-2831 GDI-983:

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

5.1.4 Success Criteria Gyro-2833 GDI-985:

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

5.2 Unit Tests

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Gyro-2835 GDI-2679: The qualification and acceptance tests to be perfo ...

Y T,A

5.2.1 Mechanical Environment Tests 5.2.1.1 Vibration Test Set Up Gyro-2838 GDI-989:

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

Gyro-2839 GDI-990: At least one triaxial sensor shall be mounted on t ...

Y T

Gyro-2840 GDI-991: At least two axis aligned sensors shall be mounted ...

Y T

Gyro-2841 GDI-992: All units powered on during launch shall be powere ...

Y T

5.2.1.2 Test Fixture Gyro-2843 GDI-995:

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

Gyro-2844 GDI-996: The variation of transmissibility between test ite ...

Y T

Gyro-2845 GDI-997: Adequate fixture design and specimen installation ...

Y T

Gyro-2846 GDI-998: A pre-test of the empty fixture shall be performed ...

Y T

5.2.1.3 Frequency Search Gyro-2848 GDI-1000:

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

Gyro-2849 GDI-1002: Frequency search tests shall be conducted along ea ...

Y T

5.2.1.4 Vibration Tests Level Gyro-2851 GDI-1005:

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

5.2.1.5 Sine And Random Vibration Test Gyro-2853 GDI-1011:

Sine and random vibration tests shall be performed ... Y T

Gyro-2854 GDI-1012: Prior and after sine and random vibration qualific ...

Y T

Gyro-2855 GDI-1013: Before applying full levels, a test at intermediat ...

Y T

Gyro-2856 GDI-1014: This Requirement has been Deleted. ...

Y

Gyro-2857 GDI-1015: The vibration facility shall include a shock free ...

Y T

5.2.1.6 Shock Tests Gyro-2859 GDI-1017:

Units shall demonstrate by test their ability to w ... Y T

Gyro-2860 GDI-1018: Prior and after shock tests a low level sine frequ ...

Y T

5.2.1.7 Static tests Gyro-2862 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 Gyro-2865 GDI-1024:

The temperatures shall be selected and controlled ... Y R

Gyro-2866 GDI-1025: The test arrangement shall be as shown in Figure G ...

Y R

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Gyro-2867 GDI-1026: The unit shall be bolted to a thermally controlled ...

Y R

Gyro-2868 GDI-1027: On all external surfaces flight representative the ...

Y R

Gyro-2869 GDI-1028: The heat sink (HS) plates shall be black painted ( ...

Y R

Gyro-2870 GDI-1029: The conductive heat sink temperature and the chamb ...

Y R

Gyro-2871 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 Gyro-2874 GDI-1034:

Unit’s suppliers shall perform Thermal Vacuum (TV) ... Y T

Gyro-2875 GDI-1036: The TV test on unit level shall be performed as in ...

Y R

Gyro-2876 GDI-1037: The qualification temperatures for the different u ...

Y R

Gyro-2877 GDI-1038: The units shall be tested following the thermal va ...

Y T,R

5.2.2.2.2 Acceptance Thermal Vacuum Gyro-2879 GDI-1044:

Unit suppliers shall perform thermal vacuum (TV) a ... Y T

Gyro-2880 GDI-1045: The thermal vacuum acceptance test shall be perfor ...

Y T,R

5.2.2.2.3 Protoflight Thermal Vacuum Gyro-2882 GDI-1049:

Unit suppliers shall perform thermal vacuum (TV) p ... Y T

Gyro-2883 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 Gyro-2887 GDI-1057:

Development tests may be performed to evaluate the ... Y T,R

5.2.3.1.2 EMC Qualification Test Gyro-2889 GDI-1059:

Qualification tests for PFM shall be performed as ... Y T,R

5.2.3.1.3 EMC Acceptance Test Gyro-2891 GDI-1061:

Acceptance tests for FM shall be performed as spec ... Y T,R

5.2.3.1.4 EMC Integration Test Gyro-2893 GDI-1063:

In order to ensure the proper grounding of the sec ... Y T,R

5.2.3.1.5 Retest Criteria Gyro-2895 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 Gyro-2897 GDI-1067:

The pre- and post-test inspection is specified in ... Y R

5.2.3.1.7 Test Sequence Gyro-2899 GDI-2155:

The actual EMC test sequence shall be agreed with ... Y R

5.2.3.2 Test Facility

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5.2.3.2.1 EMC Test Environment Gyro-2902 GDI-1072:

All EMC tests shall be conducted at standard ambie ... Y R

5.2.3.2.2 Capabilities Gyro-2904 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 Gyro-2907 GDI-1077:

The maximum allowable tolerance for the test param ... Y R

5.2.3.3.2 Accuracy of the Test Measurement Equipment Gyro-2909 GDI-1079:

The accuracy of measurement equipment and test equ ... Y R

5.2.3.3.3 Special Requirements on the Test Equipment Gyro-2911 GDI-1081:

Grounding of Test Equipment: Measurement equipment ...

Y R

Gyro-2912 GDI-1082: Antenna Placement: For radiated emission measureme ...

Y R

Gyro-2913 GDI-1083: Receiver Bandwidth: The following receiver bandwid ...

Y R

Gyro-2914 GDI-1085: Power Adjustment: The primary power for unit level ...

Y R

5.2.3.3.4 Line Impedance Stabilisation Network (LISN): Gyro-2916 GDI-1087:

For the conducted emission and susceptibility test ... Y R

Gyro-2917 GDI-1090: The LISN has to be designed and provided by the co ...

Y T

Gyro-2918 GDI-2116: Derivation of the bus impedance shall be performae ...

Y T

5.2.3.3.5 Test Conditions Gyro-2920 GDI-1095:

The equipment under test shall be switched on in t ... Y R

Gyro-2921 GDI-1096: For emission testing the unit shall operate within ...

Y R

Gyro-2922 GDI-1097: For susceptibility testing the suitable operationa ...

Y R

Gyro-2923 GDI-1098: After testing the equipment shall be switched off ...

Y R

Gyro-2924 GDI-1099: Both operational modes shall provide operational c ...

Y R

Gyro-2925 GDI-1100: The particular test set-up shall represent the fli ...

Y R

5.2.3.3.6 Susceptibility Testing Gyro-2927 GDI-2142:

The applicable pass/fail criteria for susceptibili ... Y R

Gyro-2928 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

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Gyro-2931 GDI-1107: The bonding test shall be performed with the unit ...

Y R

Gyro-2932 GDI-1108: The bonding test shall be performed without any ha ...

Y R

5.2.3.4.2 Isolation Gyro-2934 GDI-1111:

The isolation test shall be performed with the UUT ... Y R

5.2.3.4.3 Conducted Emissions on Power Lines 5.2.3.4.3.1 CE on Primary Power Lines Gyro-2937 GDI-1116:

UUT operation shall be selected in order to maximi ... Y R

Gyro-2938 GDI-1118: Ripple and transient interference tests on the pow ...

Y R

5.2.3.4.3.2 CE on Secondary Power Lines Gyro-2940 GDI-1123:


Gyro-2941 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

Gyro-2943 GDI-2090: The mode selection for susceptibility testing shal ...

Y T,R

5.2.3.4.5 Conducted Susceptibility on Power Lines Gyro-2945 GDI-1133:

The mode selection for susceptibility testing shal ... Y R

Gyro-2946 GDI-1134: The test set-ups are shown in Figure GDI-1135 (CS0 ...

Y T

5.2.3.4.6 Conducted Susceptibility on Secondary Power Lines

Gyro-2948 GDI-1140: The mode selection for susceptibility testing shal ...

Y R

Gyro-2949 GDI-1141: The test set-ups are shown in Figure GDI-1142 (CS0 ...

Y T

5.2.3.4.7 Radiated Emission, Electric Field Gyro-2951 GDI-1151:


5.2.3.4.8 Radiated Emissions, E-Field Fluctuations 5.2.3.4.9 Radiated Emission, Magnetic Field Gyro-2954 GDI-1155:


5.2.3.4.10 Radiated Emissions, Magnetic Field Fluctuations

5.2.3.4.11 Radiated Susceptibility, Electric Field Gyro-2957 GDI-1159:


5.2.3.4.12 Radiated Susceptibility, Magnetic Field Gyro-2959 GDI-1163:


5.2.3.4.13 Electrostatic Discharge (ESD) Gyro-2961 GDI-1167:


5.2.3.4.14 Magnetic Moment Gyro-2963 GDI-1173:

Verification by similarity may be applied to equip ... Y A,R

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5.2.4 Life Test Gyro-2965 GDI-1185:

A life test shall be required for all the assembli ... Y T,R

5.2.5 Space Conditioning Gyro-2967 GDI-1187:

Space conditioning shall be performed whenever des ... Y T,R

Gyro-2968 GDI-1188: The contractors shall propose the corresponding te ...

Y R

Gyro-2969 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

Gyro-36 ..............3.1.1 ................8 Gyro-37 ..............3.1.1 ................8 Gyro-40 ..............3.1.2 ................8 Gyro-42 ..............3.1.2 ................8 Gyro-44 ..............3.1.2 ................8 Gyro-54 ..............3.2.2.1 .............9 Gyro-57 ..............3.2.2.2 .............10 Gyro-58 ..............3.2.2.2 .............10 Gyro-68 ..............3.2.3 ................10 Gyro-69 ..............3.2.3 ................10 Gyro-71 ..............3.2.3 ................10 Gyro-72 ..............3.2.3 ................10 Gyro-73 ..............3.2.3 ................10 Gyro-75 ..............3.2.3 ................10 Gyro-76 ..............3.2.3 ................10 Gyro-77 ..............3.2.3 ................10 Gyro-80 ..............3.2.4.2 .............12 Gyro-82 ..............3.2.4.3 .............12 Gyro-83 ..............3.2.4.3 .............12 Gyro-86 ..............3.2.4.4 .............13 Gyro-87 ..............3.2.4.4 .............13 Gyro-88 ..............3.2.4.4 .............13 Gyro-100.............3.4 ...................14 Gyro-102.............3.4 ...................14 Gyro-103.............3.4 ...................14 Gyro-107.............4.1.1 ................15 Gyro-112.............4.2 ...................15 Gyro-113.............4.2 ...................15 Gyro-114.............4.2 ...................15 Gyro-115.............4.2 ...................15 Gyro-118.............4.3.1 ................16 Gyro-120.............4.3.2 ................16 Gyro-122.............4.3.3 ................16 Gyro-127.............4.3.4 ................16 Gyro-128.............4.3.4 ................16 Gyro-129.............4.3.4 ................16 Gyro-131.............4.3.5 ................17 Gyro-132.............4.3.5 ................17 Gyro-133.............4.3.5 ................17 Gyro-134.............4.3.5 ................17 Gyro-136.............4.3.5 ................17 Gyro-137.............4.3.5 ................17 Gyro-138.............4.3.5 ................17 Gyro-139.............4.3.5 ................17 Gyro-144.............5.1.1 ................18 Gyro-146.............5.1.2 ................18 Gyro-158.............5.5 ...................18 Gyro-160.............6 ......................19 Gyro-163.............7 ......................20 Gyro-1225...........3.1.2 ................8 Gyro-1228...........3.2.1 ................8 Gyro-1229...........3.2.1 ................8 Gyro-1230...........3.2.1 ................8 Gyro-1231...........3.2.1 ................8 Gyro-1232...........3.2.1 ................8 Gyro-1235...........3.2.2.2 .............10 Gyro-1237...........3.2.4.1 .............11

Gyro-1240 .......... 3.2.3 ................ 10 Gyro-1241 .......... 3.2.3 ................ 10 Gyro-1243 .......... 3.2.4.1 ............. 11 Gyro-1244 .......... 3.2.4.1 ............. 11 Gyro-1245 .......... 3.2.4.1 ............. 11 Gyro-1247 .......... 3.2.4.1 ............. 11 Gyro-1249 .......... 3.2.4.2 ............. 12 Gyro-1251 .......... 3.2.4.2 ............. 12 Gyro-1252 .......... 3.2.4.3 ............. 12 Gyro-1253 .......... 3.2.4.3 ............. 12 Gyro-1256 .......... 3.3 ................... 13 Gyro-1258 .......... 3.3 ................... 13 Gyro-1261 .......... 3.3 ................... 13 Gyro-1264 .......... 3.4 ................... 14 Gyro-1266 .......... 4.1.3 ................ 15 Gyro-1268 .......... 4.2 ................... 15 Gyro-1269 .......... 4.3.1 ................ 16 Gyro-1276 .......... 4.3.4 ................ 16 Gyro-1277 .......... 4.3.4 ................ 16 Gyro-1278 .......... 4.3.4 ................ 16 Gyro-1279 .......... 4.3.5 ................ 17 Gyro-1281 .......... 3.2.1 ................ 8 Gyro-1283 .......... 3.2.3 ................ 10 Gyro-1284 .......... 4.3.5 ................ 17 Gyro-1286 .......... 4.1.2 ................ 15 Gyro-1288 .......... 3.2.4.3 ............. 12 Gyro-1293 .......... 3.2.4.3 ............. 12 Gyro-1990 .......... 4.2 ................... 15 Gyro-3007 .......... 4.1.3 ................ 15 Gyro-3008 .......... 3.2.4.4 ............. 13 Gyro-3012 .......... 3.2.3 ................ 10 Gyro-3014 .......... 3.2.4.2 ............. 12 Gyro-3015 .......... 4.1.3 ................ 15 Gyro-3017 .......... 4.3.2 ................ 16 Gyro-3018 .......... 4.3.3 ................ 16 Gyro-3022 .......... 5.1.3 ................ 18 Gyro-3024 .......... 3.2.3 ................ 10 Gyro-3025 .......... 3.2.3 ................ 10

Gaia


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