GAIA.ASU.SP.ESM.00010 Gaia Issue 1emits.sso.esa.int/.../GAIA.ASU.SP.ESM.00010.pdf · GAIA.ASU.SP.ESM.00010 Issue 1 Page 6 of 68 EADS Astrium Ltd owns the copyright of this document

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Document Autogenerated from DOORS Module : /GAIA Prime/Level 4/4_13 STR RS/AST Autonomous Star Tracker Requirements Specification.doc

Autonomous Star Tracker Requirements Specification

CI CODE: 13220 DRL Refs : EN-3

UK EXPORT CONTROL RATING : Not Listed

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.

Autonomous Star Tracker Requirements Specification.doc

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CONTENTS 1 Introduction and Scope ............................................................................................................................. 6

1.1 Introduction ........................................................................................................................................ 6 1.2 Scope ................................................................................................................................................. 6 1.3 Summary Description......................................................................................................................... 6

2 DOCUMENTS ........................................................................................................................................... 8 2.1 Applicable Documents ....................................................................................................................... 8 2.2 Reference Documents ....................................................................................................................... 8

3 Functional and Performance Requirements.............................................................................................. 9 3.1 Reference frames definition ............................................................................................................... 9

3.1.1 STR Mechanical reference frame definition................................................................................ 9 3.1.2 STR Alignment reference frame definition.................................................................................. 9 3.1.3 STR Measurement reference frame definition............................................................................ 9 3.1.4 STR Inertial Reference Frame Definition.................................................................................. 10 3.1.5 Quaternion Format.................................................................................................................... 10

3.2 STR operating modes ...................................................................................................................... 10 3.3 Input Data......................................................................................................................................... 12 3.4 Output data ...................................................................................................................................... 12 3.5 Conditions for performance requirements........................................................................................ 14

3.5.1 General ..................................................................................................................................... 14 3.5.2 Dynamics conditions ................................................................................................................. 15 3.5.3 Optical environment .................................................................................................................. 15 3.5.4 Orbital Environment .................................................................................................................. 16

3.6 PERFORMANCE ............................................................................................................................. 16 3.6.1 Measurement Acquisition and Availability ................................................................................ 17 3.6.2 Measurement Errors ................................................................................................................. 17

3.7 FDIR................................................................................................................................................. 20 4 Unit Specific Design and Interface Requirements................................................................................... 22

4.1 Implementation Requirements ......................................................................................................... 22 4.2 Mechanical Design and Interface Requirements ............................................................................. 22

4.2.1 Mass.......................................................................................................................................... 22 4.2.2 Centre of Gravity....................................................................................................................... 22 4.2.3 Finite Element Model ................................................................................................................ 22 4.2.4 Mounting Location & Alignment ................................................................................................ 22

4.3 Thermal Design and Interface.......................................................................................................... 23 4.4 Electrical Design and Interface ........................................................................................................ 25

4.4.1 Power Consumption.................................................................................................................. 25 4.4.2 Power Interface......................................................................................................................... 25 4.4.3 Harness..................................................................................................................................... 26 4.4.4 Interface to Satellite Data Handling .......................................................................................... 26 4.4.5 Test Equipment......................................................................................................................... 26

5 General Design and interface Requirements .......................................................................................... 30 5.1 General Design Requirements......................................................................................................... 30

5.1.1 Lifetime ..................................................................................................................................... 30 5.1.2 Reliability................................................................................................................................... 30 5.1.3 GDIR Applicability ..................................................................................................................... 30

5.2 Mechanical ....................................................................................................................................... 30 5.3 Thermal ............................................................................................................................................ 30 5.4 Electrical........................................................................................................................................... 30 5.5 Identification and Marking ................................................................................................................ 30

6 Verification Requirements ....................................................................................................................... 31 7 Product Assurance Requirements........................................................................................................... 32 8 Acronyms................................................................................................................................................. 33 9 GDIR Applicability Matrix......................................................................................................................... 34

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FIGURES Figure 3.1-1: Unit Axis Systems ....................................................................................................................... 9 Figure 3.2-1: STR Modes ............................................................................................................................... 11 Figure 3.5-1: Earth-Spacecraft-Sun geometry during Scientific Observations .............................................. 16 Figure 3.6-1: PSD requirement illustrated with Science phase low frequency requirement values for X and Y

STR axes................................................................................................................................................. 20 Figure 4.2-1: Location of the Autonomous Star Trackers on the GAIA Spacecraft ....................................... 23 Figure 4.3-1: Geometry for Thermal Analysis (viewing along Spacecraft X axis).......................................... 24 Figure 4.3-2: Geometry for Thermal Analysis (Viewing perpendicularly to STR radiator plane) ................... 25

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1 INTRODUCTION AND SCOPE

1.1 Introduction

This document establishes the design, performance, interface and verification requirements of the Autonomous Star Tracker for the Attitude & Orbit Control Subsystem onboard 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 microarcsec 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 Autonomous Star Tracker. 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> STR-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 are specified, that means all of them are 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 STRs will be used in the AOCS for attitude measurement in all phases of the mission after the sun shield is deployed. GAIA will have two co-aligned star trackers, nominally operate in cold redundancy. This specification recognises that several different equipment configurations for a star track are possible, such as a monolithic concept where the Optical Head (OH) and Electronics Unit (EU) are fully integrated, or a disparate concept where the OH and EU are physically separated, and that for the separate OH and EU case, the functionally separate EU channels might be implemented within a single box. In order to account for the various possible implementation solutions, this specification refers OH and EU when such distinctions are relevant, to a 'star tracker' when referring to an individual star tracker functional chain, and a

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'star tracker system' when referring to the total combined hardware necessary to provide the Prime and Redundant star tracker functionality needed for GAIA.

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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

Doc Ref: GAIA-ASF-SP-SAT-00002

AD-2 GAIA MIL-STD-1553B Bus Protocol Specification

Doc Ref: GAIA.ASF.SP.SAT.00059

AD-3 GAIA EGSE GDIR


AD-4 GAIA Finite Element Modelling Requirements

Doc Ref: GAIA.ASD.SP.SAT.00007

AD-5 GAIA Product Assurance Requirements For Subcontractors

Doc Ref: GAIA-ASF-SP-SAT-00004

AD-6 GAIA Software Product Assurance Requirements


AD-7 GAIA Thermal Modelling Specification

Doc Ref: GAIA.ASD.SP.SAT.00008

AD-8 GAIA Packet Utilisation Standard,

SGICD Vol. 2

AD-9 GAIA SW PA Requirements for EGSE Software


AD-10 GAIA Non-Volatile Memory Protection (System Requirements for GAIA EEPROM use)

GAIA.ASF.TCN.CSW.00019

2.2 Reference Documents

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

RD-1 Hypotheses for AOCS Analysis

GAIA.ASF.TCN.SAT.00009

RD-2 GAIA Environmental Specification

TEC-EES-05011/JS

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3 FUNCTIONAL AND PERFORMANCE REQUIREMENTS

3.1 Reference frames definition

3.1.1 STR Mechanical reference frame definition

STR-36/CREATED/I,R

The STR (Optical Head (OH) and Electronics Unit (EU)) shall employ a right handed Cartesian reference frame with its origin at the reference point of the STR, and the orientation of the axes as defined below.

The Z_STR_mP axis is aligned with the STR line of sight and oriented from the platform to space.

The X_STR_mP axis shall be in the mounting plate plane and shall be clearly identified on the STR hardware.

The Y_STR_mP axis is defined in order to have a right-hand orthogonal reference frame.

The definition of this reference frame shall be defined in the STR Mechanical Interface Control Document.

Note : Should the STR have a modular architecture (Optical Head + Electronics Unit), this requirement is applicable to the optical unit.

3.1.2 STR Alignment reference frame definition

STR-38/CREATED/I,R

Each STR optical head shall include an optical reference cube for the purpose of aligning the STR optical head onto the spacecraft. The location of the optical reference cube mounting shall be agreed with EADS Astrium.

STR-327/GDI-188/R

The normals to three of the optical cube faces shall be used to form a right handed Cartesian reference frame, the Alignment Reference Frame (O_STR_aP, X_STR_aP, Y_STR_aP, Z_STR_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

3.1.3 STR Measurement reference frame definition

STR-328/CREATED/R

The STR shall employ a right handed Cartesian reference frame that has one of its axes perpendicular to the detector (e.g. CCD, APS) and pointing away from the detector towards Space. This shall be designated the STR Measurement Reference Frame.

The supplier may propose an alternative definition for the Measurement reference frame in his proposal for the benefit of better managing the error budget.

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STR-41/CREATED/R

The STR supplier shall deliver the 3x3-transfer matrix from the STR Alignment reference frame to the STR Measurement reference frame.

STR-316/CREATED/T,A,R

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

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

3.1.4 STR Inertial Reference Frame Definition

STR-40/CREATED/T,R

The STR shall deliver attitude quaternions defined as the orientation of the STR Measurement reference frame in the Earth Centred Inertial J2000 (true of date) reference frame:

· The positive X axis is in the direction of the first point of Aries on 01/01/2000 at 12 noon;

· The Z axis is in the direction of the Earth’s North Pole on 01/01/2000 at 12 noon;

· The Y axis is constructed such that it is orthogonal to both the X and Z axes, thereby completing right handed reference frame.

3.1.5 Quaternion Format

STR-402/CREATED/T,R

The supplier shall unambiguously define the format and sense of rotation of the output quarternion.

3.2 STR operating modes

The STR modes to be used in flight are shown in Figure 3.2-1 and detailed below. The mode names are for information and clarity with regard to the requirements below. A variation in mode names, distribution of functions between modes is permitted but all functions must remain.

STR-44/CREATED/T,R

The STR shall be able to operate in a STAND BY mode such that only health data is delivered in the telemetry packet.

STR-330/CREATED/T,R

The STANDBY mode shall always be entered upon the STR being powered ON.

STR-51/CREATED/T

The STR shall be available in STAND BY mode and ready to enter ACQUISITION & TRACKING mode in less than 60 sec after being powered.

STR-45/CREATED/T,R

The STR shall be able to operate in an ACQUISITION & TRACKING mode such that it automatically acquires the 3-axis attitude from “lost in space” conditions, and thereafter delivers updated quaternions at the required frequency.

STR-46/CREATED/T,R

The STR shall be able to operate in an AIDED ACQUISITION & TRACKING mode such that the STR will accept a prediction of Attitude (and Rate, if required) from the spacecraft which it then uses to rapidly acquire the 3 axis attitude, and thereafter deliver the updated quaternions as in the ACQUISITION & TRACKING mode.

Note that the purpose of this ‘aided tracking’ mode is to allow the star tracker to determine the three axis attitude, after a temporary outage, or during severe space weather conditions, significantly more quickly than it would do from a ‘lost in space’ situation.

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STR-47/CREATED/T,R

The STR shall be able to operate an IMAGE mode such that any portion of the complete detector image, prior to any correction being applied on the video, is made available, upon request, via one or more telemetry packets.

Note that requirement above does not require the detector image to be taken, stored and transmitted in one operation. If need be this can be done in stages and spread over several telemetry packets.

STR-333/CREATED/T,R

It shall be possible to define, via command, the portion of the detector, cited in the Image Mode requirement above, by specifying it in terms of the range of abscissa and ordinates of the pixels contained within it (i.e. a window) where the range can extend from one pixel to the complete detector image.

STR-48/CREATED/T,R

The STR shall be able to operate in a DOWNLOAD/UPLOAD modes such that it is possible to:

• Download all of the STR application software and parameter settings.

• Modify any part of the STR application software code.

• Modify STR parameter settings, including the on-board star catalogue, using explicit telecommands (i.e. not reliant on memory address patching).

• Reset the STR software and data memory.

The STR mode diagram is shown below:

Stand by mode

Image mode Download/Upload

Mode

Acquisition & trackingMode

Aided Acquisition & Tracking mode

Figure 3.2-1: STR Modes

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

STR-646/CREATED/R

Transitions between Stand-by Mode and any other mode identified in Figure 3.2-1 (and also the reverse transitions) shall each have a dedicated telecommand associated with them. Autonomous transitions between modes (e.g between Stand-by and Acquisition & Tracking, or between Aided Acquisition & Tracking and Acquisition & Tracking) shall be implemented as necessary to provide the overall functional behaviour specified.

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3.3 Input Data

STR-54/CREATED/T,R

When operating in the Aided Acquisition & Tracking Mode the STR shall accept:

• a quaternion representing the three-axis attitude of the STR Measurement Reference Frame in the J2000 inertial frame and/or

• the spacecraft body rates expressed in the STR Measurement Reference Frame.

Alternative information required for this function shall be indicated by the suppliers in their proposal

STR-56/ERS-1044/T,R

The STR shall be able to apply corrections for all relativistic effects due to the motion of the spacecraft. The supplier shall derive the worst case remaining error following relativistic correlation and include this in the STR performance budgets.

Supplier is expected to advise on information required from the spacecraft to fulfil STR-56. Spacecraft velocity knowledge error is described in section 3.5.4.

STR-335/CREATED/T,R

It shall be possible to enable/disable the internal correction function for relativistic effects cited in STR-56 via telecommand.


Internal correction shall be applied to all relavent available STR outputs.

STR-649/CREATED/R

The supplier shall quantify the degradation in performance if relativistic effects are not applied.

STR-57/CREATED/T,R

It is desired that the performance requirements set out in this specification shall be met without the need for in orbit calibration. Should any in-orbit calibration be considered necessary in order to meet the identified performance requirements, the supplier shall provide full details, including a procedure. The number and duration of any calibration events shall be minimised and clearly defined.


The supplier shall quantify the effect of each the calibrations cited in STR-57 above upon the quaternion output by the STR.

STR-338/CREATED/T,R

It shall be possible to enable/disable via telecommand all high level compensation functions including abberation correction and those that correct for the errors determined via any in-flight calibration processes.


For Aided Acquisition and Tracking mode, the accuracy of the attitude quaternion and rates, or other parameters provided to the STR in order to meet the acquisition time requirements shall be defined by the supplier.

3.4 Output data

STR-59/CREATED/R

The STR shall provide a cyclic telemetry output at a frequency of at least 2Hz.

It is intended to sample the output of the star tracker at a frequency of 2Hz. The internal measurement rate may be greater than 2Hz, but the actual output frequency considered for noise calculation shall be limited to 2Hz, considering under-sampling by the user.

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STR-60/ERS-168/T,R

In all modes, the STR shall always provide the following basic telemetry packet as part of its cyclic telemetry output:

• The STR current mode identification

• The STR health data including at least critical STR temperatures information

STR-1411/ERS-168/R

In addition to identification of the modes defined in section 3.2 the current mode identification shall indicate if the unit is in the Acquisition or Tracking phase of the Acquisition and Tracking or Aided Acquisition and Tracking mode.

STR-61/ERS-168/ERS-763/T,R

Whilst operating in either Acquisition and Tracking Mode or Aided Acquisition and Tracking Mode the STR shall, in addition to the basic telemetry packet cited in the requirement above (STR-60), provide the following as part of its telemetry output:

• the attitude measurement packet as defined below,

• the raw data telemetry packet as defined below (enabled or disabled by TC)

STR-62/ERS-763/T,R

The attitude measurement packet shall contain:

• The quaternion representing the three axis attitude of the STR Measurement Reference Frame with respect to the inertial J2000 reference frame.

• A validity flag indicating whether or not a valid attitude quaternion is available in the delivered telemetry.

• A datation of the measurement (defined as the middle of the integration period) with respect to the latest time reference signal provided by the spacecraft, as defined in STR-66.

• A quality index giving a measure of the expected accuracy of the output quaternion (e.g. via covariance or pattern matching residuals or number of stars used vs expected number of stars)

'Valid' shall represent that the stars used to derive the quaternion have been correctly identified and that delivered quaternion is considered suitable for use by the AOCS.

STR-552/CREATED/T,A

The validity flag cited in STR-62 shall provide the validity status of the STR measurement with a reliability of 95% i.e. the validity status flag must correctly identify the validity of the measurement for 95% of the measurements.

STR-553/CREATED/T,A

The probability of a false positive reading in the Validity Flag cited in STR-62 and STR-552 shall be less than 0.01%.

A false positive is defined as when the validity flag indicates a valid signal when the STR quaternion is not valid.

STR-63/ERS-168/T,R

Irrespective of whether or not a valid three axis attitude is available, the raw data telemetry packet shall, for each measured star (including any that were intended to be measured, but were rejected by the STR processing), contain:

• Direction of the measured star in the STR Measurement Reference Frame.

• Brightness (i.e. magnitude) of the measured star.

• Star index, as stored in the embedded star catalogue

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• Star inertial coordinates.

• A status word detailing the type of corrections (aberration, precession etc.) applied on the star measurement.

STR-64/CREATED/T,R

The accuracy of the star measurements in the raw data telemetry packet shall be at least the same as that used in the computation of the three axis attitude.

STR-340/CREATED/R

If the star measurements are being internally compensated for errors (e.g. relativistic errors, proper motion, biases, focal length etc.) before being used in the three axis attitude computation, then the compensated values of the star measurements shall be the ones reported in the raw telemetry packet i.e. the star measurements actually used to determine the three axis attitude.

STR-65/CREATED/T,R

The maximum delay between the middle of integration period and the availability of the corresponding telemetry packet at the STR interface shall be less than 500ms

STR-66/CREATED/T,R

The STR shall receive an external time reference signal synchronisation pulse at either 1 Pulse per Second (PPS) or 2 Pulse per Second from the satellite through a dedicated interface as defined in section 9.

The supplier is requested to identify which of the PPS frequencies their equipment is compatible with.

STR-67/CREATED/T,R

In the event that the STR does not receive a synchronisation pulse then the STR shall raise a flag that will be made available as part of its output TM packet. This flag shall be reset upon the receipt of the external synchronisation pulse.

STR-68/CREATED/T

The accuracy of the measurement datation (middle of integration period) with respect to the latest time reference signal shall be better than 1ms.

STR-3104/CREATED/T

The synchronisation of the measurement epoch (middle of the integration period) with respect to the latest time reference signal shall be constant to better than 1ms.

3.5 Conditions for performance requirements

3.5.1 General


The performance requirements of the unit or units shall be met under worst case 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 conditions, orientation in the celestial sphere, ageing, nominal radiation environment, sensor bias, sensor noise, quantisation, temperature effects, unit conversion factor errors, 1g to 0g effects and SEU's

STR-1917/CREATED/T,A

The STR shall survive the worst case Solar Flare conditions which shall be taken to be a proton flux of 105proton/(cm2s) at >10MeV and an X-ray flux of 10-3W/m2 at a wavelength of 0.1nm lasting for 1 hour.

No specific measurement performance is requested in these conditions.

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Full performance (as defined according to the appropriate performance condition) shall be autonomously recovered in less than TBD seconds measured from time of return to normal solar environment conditions as defined in section 9.

The Supplier is requested to review the performance requirements defined in Section 3.6 and indicate achievable values in the presence of a worst case Solar Flare in their proposal.

3.5.2 Dynamics conditions

For the GAIA STR, two sets of dynamic conditions are identified. Where appropriate, the requirements in Section 3.6 are specified in respect to the following dynamic condition definitions:

The range of angular rates and accelerations under which "science" performance shall be provided is designated the Science Dynamics Range, and is defined as:

• Rotation rate of 60±5 arcsec/sec around a spin axis at 45°±15° to the STR +Zaxis in the ZX or ZY plane of the STR measurement reference frame

• Rotation rates of <±2 arcsec/sec around axes perpendicular to the spin axis defined above.

• Accelerations of up to 0.001°/s2 over the STR integration period around any axis in the STR measurement reference frame.

STR-1956/ERS-138/T,A

The STR shall acquire and maintain tracking and offer measurement accuracy as cited in section 3.6 with respect to the Science Dynamics Range.

The range of angular rates and accelerations under which "nominal" performance shall be provided is designated the Nominal Dynamics Range, and is defined as:

• Rotation rate of up to 0.25°/sec around any axis in the STR measurement reference frame.

• Accelerations of up to 0.6°/s2 around any axis in the STR measurement reference frame.


The STR shall acquire and maintain tracking and offer measurement accuracy as cited in section 3.6 with respect to the Nominal Dynamics Range.

3.5.3 Optical environment


Science performance shall be guaranteed in the following domain: The angle between the STR line of sight and direction of any spacecraft element (straylight source) is greater than 40°.

During Science performance the STRs will be in the shadow of the spacecraft (see Figure 3.5-1

and Figure 4.2-1).

STR-74/ERS-732/T,A

Nominal performance shall be guaranteed in the following domain:

1) The angle between the STR line of sight and the Sun direction is higher than 40°.

2) The angle between the STR line of sight and the Earth limb is higher than 40°.

3) The angle between the STR line of sight and the Moon direction is higher than 40° (from limb of the Moon).

4) The angle between the STR line of sight and direction of any spacecraft element (straylight source) is greater than 40°.

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STR-3064/CREATED/A,R

No spacecraft system level analysis (e.g. straylight) shall be required to confirm STR performances are met under these optical conditions.

STR-77/CREATED/T,A

For both Science and Nominal performance, the STR shall offer performance levels cited in section 3.6 in the presence of up to 3 (TBC) "false stars" in the FOV, with following characteristics:

• Magnitude between -3 and +5,

• Size similar to the one of stars or planets.


Following a period of "blinding" ( Sun, Earth, Moon or illuminated spacecraft element inside the exclusion angles defined above) of any duration, full performance (as defined according to the appropriate performance condition) shall be autonomously recovered in less than 30 seconds

3.5.4 Orbital Environment

STR-1907/CREATED/R

The unit shall offer Science Performance (section 3.6.2.2)while operating in a Lissajous orbit around the L2 Lagrange point of the Earth/Moon - Sun system, such that the Earth - spacecraft - Sun angle never exceeds 15°. See Figure 3.5-1.

Figure 3.5-1: Earth-Spacecraft-Sun geometry during Scientific Observations

The supplier can assume an orbital velocity knowledge error of 1m/s for any on board compensation processes.

STR-551/RD-1-section 5.2/T,A

The unit shall offer nominal performance while operating in the Earth altitude range between 2900 km and 1.7 million km (direction towards L2 Lagrange point).

3.6 PERFORMANCE

STR-1910/CREATED/R

Unless a specific performance condition ("Science", "Nominal") is explicitly defined within a performance requirement, it shall be assumed that the requirement applies to both sets of performance conditions.

"Science Dynamics Range" and "Nominal Dynamics Range" conditions shall be taken as the appropriate combination of conditions described in Section 3.5.

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3.6.1 Measurement Acquisition and Availability


Apart from the instances when the STR FoV is occluded by the sun, Earth or Moon, the STR shall be able to determine the three axis attitude with full accuracy no matter what the attitude of the spacecraft (i.e. even in those cases when the star tracker's FOV is directed toward a portion of the celestial sphere in which the sparsity of stars is at its worst).


For the 'lost in space' scenario under nominal conditions (as defined by STR-74 and the Nominal Dynamics Range in section 3.5.2) , the time taken for the STR to deliver the quaternion that represents the three axis attitude at full accuracy shall be less than thirty seconds (TBC) from the instant that the STR enters the Acquisition and Tracking Mode.


The accuracy of the quaternion, outside the nominal conditions, may be degraded with respect to the full accuracy levels achieved under nominal conditions. The supplier is to advise as to the accuracy that is achievable when operating under these conditions.

STR-1572/CREATED/A

Under nominal conditions (as defined by STR-74 and the Nominal Dynamics Range in section 3.5.2), the time taken for the STR to deliver the quaternion that represents the three axis attitude at full accuracy shall be less than one second (TBC) from the instant that the STR enters the Aided Acquisition & Tracking Mode.

The supplier should assume an attitude estimate with a knowledge error of 0.5° shall be provided to the STR for Aided Acquisition.


Under nominal conditions (as defined by STR-74 and the Nominal Dynamics Range in section 3.5.2), and over any 100 second period, more than 99% of the delivered quaternions shall be at accuracy as defined in section 3.6.2.

3.6.2 Measurement Errors

The measurement error specifications apply to the output quaternions identified as valid in the telemetry packets. This performance shall be met in the ACQUISITION&TRACKING and AIDED TRACKING modes for 100% of the celestial vault. This means taking into account that the STR may be permanently pointed in the worst area of the celestial vault.

The STR will experience a very stable thermal environment, which will vary by no more than of ±2°Celsius (TBC) about some operating point (see Section 4.3) over the 6 hour spacecraft spin period assuming a constant thermal load from the STR.

STR-1583/GDI-section 4.3.2/R

In determining the performance levels with all error source stipulated herein, the STR supplier shall assume that the temperature of the STR at the temperature reference point (see section 4.3) shall remain stable to within ±2°C over any 6 hour period for science operation.

The supplier is, in the first instance, expected to provide, within his proposal, the temperature range, centred on the temperature reference point, over which the STR can meet all of its performance requirements.


If, in order to meet the performance levels stipulated herein, the STR requires a thermal environment different from that stipulated in requirement STR-1583, then the supplier shall clearly identify the thermal environment that is needed to meet the requirements.

The supplier is, in the first instance, expected to identify the thermal environment cited in requirement STR-1585 within his proposal.

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The conditions under which STR performance has been analysed shall be presented in the proposal.

Measurement errors are split into three classes:

• Bias errors (due to error types which are constant for all stars in FOV and only varying with frequency lower than 0.2mHz)

• Errors which vary with attitude or with time at a fixed attitude, which are to be limited by a Power Spectral Density requirement in frequency interval of 0.2mHz to 0.01Hz . This is intended to cover mainly the errors which vary over the FOV.

• Errors which vary with attitude or with time at a fixed attitude, which are to be limited by a Power Spectral Density requirement in frequency interval of 0.01Hz to Nyquist limit. This is intended to cover mainly the NEA errors.

The performance measurement requirements are written in terms of PSDs of attitude error. As the spacecraft rotates it cannot distinguish between attitude errors which are time or star position dependent, and all such error types are to be considered as contributors to the requirements below. These are intended to envelope effects across all frequencies which may include errors which vary with star position in FOV, and high frequency noise (NEA). All other sources (including residual errors after correction) that leads to high frequency spatial errors, and which will be identified, in the first instance, by the supplier in his proposal

Although the noise requirements are specified as RMS values, information is also required on the frequency dependent behaviour of the noise. As such requirements are placed for the supplier to provide PSD information on the noise characteristics of the unit. The actual PSD shape is not constrained other than that the equivalent integrated RMS noise meets the requirements.

STR-1625/CREATED/R

All PSD figures shall be calculated as a single sided power spectral density and expressed as the square-root PSD with units of arcseconds/sqrt(Hz).

STR-1595/CREATED/R

All performance requirements are to be met at EOL.

3.6.2.1 Bias Errors and Stability

The bias errors include alignment uncertainties and biases. These errors are identical for each measured star.


The supplier shall identify all contributing sources for bias errors. The method for bias error calculation shall be agreed with EADS Astrium.


The STR bias performance shall be better than :

• 13 arcsec (3σ) around X and Y STR Measurement reference frame axes,

• 15 arcsec (3σ) around Z STR Measurement reference frame axes,


Under science conditions the bias per each axis shall vary with temperature change by no more than 0.25 arcsec/Celsius

STR-1911/CREATED/R

The supplier shall advise on the maximum possible change to bias over 5.5 years considering radiation dose and ageing effects.

The 5.5 year period shall include intervals with excursions into the 'nominal' dynamic conditions (for station keeping), with other conditions (optical environment) as for science. The bias stability is to be maintained across the mission during all the science condition phases.

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STR-3081/CREATED/T,R

The supplier shall advise on the change to bias due to the environmental tests, by comparing the bias before and after these tests.

3.6.2.2 Science conditions Measurement Performance Requirements


The supplier shall supply the PSD of the attitude error for each STR axis in science conditions (STR-1956) over the frequency range 0.2 mHz up to the Nyquist limit set by STR data sampling (e.g. 1 Hz for 2 Hz output).


If the requirements in this section are verified using a time history of STR measurements, the STR measurements used to generate the PSD shall be of sufficient duration to ensure that all noise components in the frequency range equal to and above 0.2 mHz are represented.

It is anticipated that the worst case performances are to be verified by analysis (including simulation). But the supplier is asked to provide suitable nominal case test-based results to validate the analytic methods.


If the PSD is generated from a time history of STR measurements, normally the time history should be an order of magnitude longer in duration than the lowest frequency components of interest. The lowest frequency in the requirements are 0.2 mHz meaning that the time series should be at least 50000 seconds in duration.


The supplier shall perform an analysis of frequency dependent noise behaviour against the science dynamics rate conditions and advise on the relationship between spacecraft rate and profile of the spectrum. The supplier shall advise on rates which allow any localised spikes in the spectrum to be minimised or avoided within the stated frequency range.


In science conditions the RMS obtained from integrating the error PSD over the frequency range 0.2 mHz to 0.01 Hz shall be less than [ 1, 1, 8 ] arcsec (1σ values in the given frequency interval) in the [X Y Z] axes of the STR measurement reference frame, respectively.

The equivalent square-root PSD averaged over the stated frequency range is < [10, 10, 81 ]arcsec/root Hz. The PSD within a particular frequency sampling bin is permitted to be higher than this average (see STR-3068). The frequency lower limit is intended to envelope the time span for a single star to cross the FOV under science conditions.

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0.0002 Hz 0.01 Hz

PSD( angle error) in arcsec2/Hz

100 as2/Hz Area= 1.0 arscec

0 as2/Hz

Compliant PSD Area< 1.0 arscec

Frequency

Figure 3.6-1: PSD requirement illustrated with Science phase low frequency requirement values for X

and Y STR axes

In this definition "1σ" values in the given frequency interval interval shall be considered equal to the RMS as given by the equation:

21

2

1

)(

= ∫

f

f

dffPSDRMS


In science conditions the RMS obtained from integrating the error PSD over the frequency range 0.01 Hz to the Nyquist limit shall be less than [ 2, 2, 12 ] arcsec (1σ values in the given frequency interval) in the [X Y Z] axes of the STR measurement reference frame, respectively.

The equivalent square-root of PSD averaged over the stated frequency range is < [2.0, 2.0, 12 ]arcsec/root Hz. The PSD within a particular frequency sampling bin is permitted to be higher than this average. This higher frequency range is expected to cover mainly NEA type errors, although all error types shall be considered.

3.6.2.3 Nominal conditions Measurement Performance Requirements


In nominal conditions the RMS obtained from integrating the error PSD over the frequency range 0.2 mHz to the STR Nyquist frequency shall be less than [ 2.2, 2.2, 14.4 ] arcsec (1σ values in the given frequency interval) in the [X Y Z] axes of the STR measurement reference frame, respectively.

STR-1636/CREATED/R

A range of dynamic conditions shall be considered if there is an error dependence on magnitude or direction of rate vector within the range permitted for nominal conditions (STR-1957).


The thermal environment cited in section 4.3.2 of AD-1 (TBC) shall be assumed for analysis of the performance requirements in STR-3044.

3.7 FDIR

STR-638/ERS-165/T,A

If STR has monolithic configuration, then there shall be no failure propagation between units.

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STR-639/ERS-165/T,A

If both OH's are connected to a single EU, there shall be no failures in the EU which can lead to failure of both STR's. The operations of the two Optical Heads shall be completely independent.

STR-640/ERS-165/T,A

If both OH's are connected to a single EU, there shall be no possible failures in an OH which can lead to failure of both STR's.

STR-641/CREATED/T,A

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

STR-1410/CREATED/R

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

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4 UNIT SPECIFIC DESIGN AND INTERFACE REQUIREMENTS

4.1 Implementation Requirements

Two STRs will be mounted on the GAIA spacecraft. They will potentially be operated in both cold redundancy and fully operated simultaneously, depending on the mission phase.

STR-166/CREATED/R

The STR shall be offered in one of two configurations:

1) Monolithic, in which the optical head and electronics are combined into a single composite assembly, which is then mounted onto the spacecraft or;

2) Disparate, in which the electronics and head are accommodated in separate housings with the optical head mounted onto the spacecraft and the electronics mounted within the spacecraft.

STR-343/CREATED/T

It shall be possible to operate both STRs simultaneously for an indefinite period up to mission life time as defined in section 5.1.1. Simultaneous operation means that each star tracker can be put into any of the required operating states at any time without constraint due to the operating state of the other star tracker.

4.2 Mechanical Design and Interface Requirements

4.2.1 Mass

STR-173/CREATED/T

The complete STR system mass in flight configuration (i.e. optical head, electronics, connectors, interconnect cables and baffle) shall be less than 7 kg. This shall be verified by mass measurement on the fully assembled units.

4.2.2 Centre of Gravity

STR-175/CREATED/T

The Centre of Gravity (CoG) w.r.t. the STR mechanical reference frame (defined by STR-36) shall be provided for each box in the STR system. This shall be a CoG measurement on each fully assembled item.

4.2.3 Finite Element Model

A finite element model of the STR shall be provided by the supplier to sufficient detail to allow assessment of the thermo-elastic distortion effects between the STR and the mounting fixtures. The FEM shall be sufficiently detailed to allow prime to assess the impact from the thermo-elastic distortion in relation to the measurement performance requirements cited in Section 3.6

STR-1947/CREATED/R

The FEM requirements in section 9 and AD-4 and AD-7 shall apply to the FEM provided.

4.2.4 Mounting Location & Alignment

The STRs will be mounted at the base of the spacecraft on the anti-sun side of the Deployable Sun Shield as shown in Figure 4.2-1. They will be aligned such that there is an angle of 30° to 60° between the STR line of sight (designated the sensor Z axis) and the Spacecraft spin axis when properly configured for scientific observations.

At no time will the STRs and the immediate surrounding spacecraft structure be nominally exposed to direct solar flux. Exposure to direct Earth or Moon flux is only possible at the very start of the mission, at which time only the 'nominal' performance requirements defined in section 3.6 are applicable.

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Spacecraft Spin Axis

Star Tracker Locations

Figure 4.2-1: Location of the Autonomous Star Trackers on the GAIA Spacecraft

4.3 Thermal Design and Interface

STR-3084/ERS-733/T,R

The STR shall be able to withstand indefinite direct solar illumination without failure or permanent performance degradation.

STR-181/CREATED/T

The maximum thermal dissipation of one active STR (including OH and EU, if applicable) shall not exceed 15 W.

STR-3067/AD-1/T,A,R

The thermal dissipation of each STR element measured by a rolling average over 0.5 seconds shall be constant to within ±2% over any 6 hour period assuming constant bus voltage and constant thermal environments.

STR-635/CREATED/R

The actual thermal dissipation characteristics exhibited by each STR element shall be provided by the supplier for use in the thermal budget.


The thermal control of the STR (including OH and EU, if applicable) shall be feasible through mainly radiative dissipation and limited thermal conduction.

STR-412/ERS-1027/ERS-1032/R

The selection of the external finishes of the units shall be made in consultation with the spacecraft prime contractor.

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STR-413/CREATED/R

The design and supply of any thermal hardware required to maintain the units(s) within the thermal environments specified shall be the responsibility of EADS Astrium. The STR supplier shall propose such passive thermal control measures as they consider necessary to enable STR performance and functional requirements to be met.

STR-1953/GDI-2584/ERS-722/R

The external optical properties of the spacecraft covering MLI (Kapton VDA) shall be assumed to have an absorptivity of 0.5 and emissivity of 0.75. The heat sink around the internal part of the unit shall be assumed to have temperature range as defined in section 4.3.2 of AD-1. The thermal washer per foot shall be assumed to have conductance to the heat sink with value of 0.015W/K. The size of the additional radiator panel shall be restricted according to the requirements given in E-SVM specification. All reflection shall be considered to be diffuse. The simplified spacecraft external geometry to be assumed for the thermal analysis is shown in Figure 4.3-1., in which L1+L2=3310mm, 270mm<L2<700mm, and L3=3550mm.

Heat sink aroundthe internal part of

the unit

Thermal washerson each unitfixation foot

Additionalradiator plane

STR

External spacecraftMLI (diameter 3400

mm)

Maximum lengthoutside the S/CMLI < 100 mm

(TBC)

Xs axis

Figure 4.3-1: Geometry for Thermal Analysis (viewing along Spacecraft X axis)

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M axim um length outs ide the S /CM LI < 100 m m (TB C )

D eploym ent S unshie ldAssem bly

S /CTherm al

ten tL1 up to the top o f

the therm al ten t

L2 dow nto theD SA L3 up to the edge

of the D SA

Additiona lrad iatorp lane if

necessary

H eat s ink aroundthe in terna l un it

+X s axis

S TR

Figure 4.3-2: Geometry for Thermal Analysis (Viewing perpendicularly to STR radiator plane)

STR-1954/CREATED/R

The above thermal environment applies to the OH or for the monolithic configurations (i.e. including EU). The thermal environment defined in section 4.3.2 of AD-1 shall apply to any separate electronics unit that is internal to the spacecraft.

4.4 Electrical Design and Interface

4.4.1 Power Consumption

STR-651/CREATED/R

The power consumption of each STR while in STAND-BY mode shall be provided by the supplier at the time of the proposal.

4.4.2 Power Interface

STR-569/CREATED/R

The STR shall draw power from the current limited, externally switched 28V regulated power bus via class-A LCLs.

STR-2013/ERS-762/R

The STR DC/DC converters shall be over-voltage protected.

STR-3072/ERS-762/R

There shall be no active current limit protection in series with each Power Bus LCLs

STR-3071/ERS-762/R

The STR shall switch off automatically if the bus voltage falls below (TBC)V

STR-3070/ERS-762/R

In the event of a single EU, this will be supplied by two separate class A LCLs. No failure of the STR shall cause both of these supplies to be overloaded.

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STR-570/CREATED/R

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

The above requirement means that in the case that the STR comprises separate electronics and optical head, then any power required by the optical head must be drawn from the STR electronics and not the external spacecraft power supply.

4.4.3 Harness

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

STR-573/CREATED/R

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

STR-574/CREATED/R

In the case that the STR comprises separate electronics and sensor head, then they shall interface with one another via connectors only (i.e. no flying leads).

STR-575/CREATED/R

In the case that the STR comprises separate electronics and sensor head, then the harness connecting the head to the electronics, up to a maximum length of 2 m, shall be provided by the STR supplier.

STR-576/CREATED/T,A

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

4.4.4 Interface to Satellite Data Handling

STR-578/ERS-64/R

The STR shall provide digital interfaces to the Spacecraft Data Handling system that are compliant to EITHER MIL-STD-1553B OR Space Wire.

4.4.4.1 MIL-STD-1553B Interface

STR-580/AD-1/R

The MIL-STD-1553B interface shall comply with the standard requirements specified in section 9, and with AD-2.

4.4.4.2 Space Wire

STR-2016/AD-1/R

The Space Wire interface shall comply with the standard requirements specified in section 9.

STR-3073/CREATED/R

It is envisaged that all signal links between the STR and the spacecraft shall be via the Spacewire or MIL STD 1553B bus. If this additional signal types are required, these shall be in accordance with the GDIR and identified in the proposal.

4.4.5 Test Equipment

STR-1959/CREATED/R

Electrical ground support equipment (EGSE) that generates the electrical stimulation signals shall be provided by the supplier of the STR

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The STR shall provide a dedicated interface to enable stimulation of the STR electronics to support closed loop testing at both subsystem and spacecraft levels. This shall not be the same interface as used to connect the optical head (in the case of separated OH and EU).


In the case of a unit where a single combined STR Optical head and electronics unit is provided it shall be possible to operate the electronics in isolation from the STR head and connect the electronics to the EGSE.

STR-1963/CREATED/R

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


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

This harness will be connected to the spacecraft skin connector.


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


At spacecraft level, the test harness cited in requirement STR-1965 will be connected to the STR 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 STR shall meet the requirements of this specification with this harness in situ.

STR-1969/CREATED/R

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


The STR stimulation interface circuits shall be compatible with a test harness of 40m length between the test equipment and the skin connector. If any part of the STR EGSE is required to be connected within 20m of the spacecraft skin connector, it shall be compatible with operation within the spacecraft TV chamber.


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

STR-1972/CREATED/I,R

The STR EGSE shall be capable of independently stimulating both the STR A electronics and the STR B electronics simultaneously.


In the case of a STR system containing 2 optical heads and a single electronics unit, the EGSE and stimulation interface shall support simultaneous independent test of both channels.


The STR EGSE shall provide the capability to stimulate the STR electronics with simulated STR optical head outputs (the STR optical heads will only be used for sign verification purposes).


The STR EGSE shall assume a default state when booted, that shall offer non-empty sky simulation.

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STR-3105/CREATED/R

STR EGSE star catalog shall be configurable and shall typically contain 2 times more stars than the embedded STR star catalog

STR-1975/CREATED/R

The STR EGSE shall perform the following tasks:

1) Receive a quaternion that defines the three axis attitude of the STR (and spacecraft body rates, expressed in the STR Measurement Reference Frame, if required) from a simulation of the spacecraft hosted on an external computer.

2) Receive EGSE Command-Control instructions from the overall Test Management Computer (CCS)

3) Return EGSE 'Telemetry' to the CCS computer for the purpose of monitoring and logging test execution and behaviour.

4) Generate a high fidelity image of the stars lying inside the FOV of the STR that is commensurate with the three axis attitude cited above (i.e. simulate the continuous integration process of the detector, for example by providing discrete summation of detector pixel data calculated from each simulation model output).

5) Transmit to the STR electronics the image of the stars lying inside the FOV.


The STR EGSE representation of the STR head output shall provide full modelling of all effects influencing STR performance to sufficient accuracy in the context of the requirements to be met in this specification. The STR EGSE shall include the ability to cause invalid measurements to be output by the STR and the ability to control other STR health telemetry.


The STR EGSE shall represent the STR head performance from beginning to end of life.


The STR EGSE output rate shall be consistent with the data output rate from the real STR head.


The STR EGSE shall accept input as cited in point 1) of STR-1975 at a frequency of up to 40Hz.

STR-1980/CREATED/R

The STR EGSE shall be mechanically and electrically independent of the STR.

STR-3074/CREATED/R

STR EGSE shall be provided with a 20m interface cable to connect the EGSE to the STR test interface connector.

STR-1981/CREATED/R

The STR EGSE shall have a dedicated interface for the purposes of communicating all Command and Control data with the Spacecraft EGSE. The details of this communication interface will be subject to specific agreement with EADS Astrium.

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

STR-1982/CREATED/R

It shall be possible to configure (i.e. start, stop, pause, initialise etc) the STR EGSE remotely via the Command and Control interface.

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STR-3086/CREATED/R

The STR EGSE shall have a dedicated interface for the purposes of receiving attitude data from the spacecraft simulation computer. The details of this interface will be subject to specific agreement with EADS Astrium.

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

STR-1983/CREATED/R

The STR supplier shall provide the optical ground support equipment (OGSE) necessary for the optical stimulation of a single STR head for open loop AOCS testing and output sign verification purposes.

STR-1984/CREATED/R

The STR supplier shall provide a mechanical interface to enable mounting of a static optical stimulator on baffle. This stimulator will be used for output sign verification to support open loop subsystem testing.

STR-3088/ERS-644/R

All STR Ground Support Equipment shall withstand a 5 year lifetime on ground.

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5 GENERAL DESIGN AND INTERFACE REQUIREMENTS

5.1 General Design Requirements

5.1.1 Lifetime

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

The unit shall perform without degradation,

• On ground = 4 years

• During Transfer + operational lifetime = 5.5 years

5.1.2 Reliability


The reliability of an individual STR shall be higher than 0.95 over 5 years in flight.

5.1.3 GDIR Applicability


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


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

5.2 Mechanical


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

5.3 Thermal


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

STR-3077/CREATED/R

Any usage of EEPROM in the STR shall comply with the requirements of AD-10

5.4 Electrical


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

5.5 Identification and Marking

STR-2001/CREATED/I,R

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

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6 VERIFICATION REQUIREMENTS

STR-2004/CREATED/T

Equipment verification shall be performed in accordance with the detailed requirements contained within the specification and AD-1, AD-5, AD-6 and AD-9.

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7 PRODUCT ASSURANCE REQUIREMENTS

STR-2006/CREATED/R

The STR shall be designed, manufactured and tested in accordance with the PA requirements specified in AD-5, AD-6 and AD-9

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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

APS Active pixel sensor

CCD Charge Coupled Device

CoG Centre of Gravity

EGSE Electrical ground support equipment

EOL End Of Life

EU Electronic Unit

FDIR Failure Detection, Isolation and Recovery

FoV Field of View

NEA Noise equivalent angle

OH Optical Head

PPS Pulse Per Second

PSD Power Spectral Density

RMS Root Mean Square

STR autonomous Star TRacker

TBC To Be Confirmed

TC Telecommand

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 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 (in case of a blank entry, TBD should be assumed)

Req No. Reference Applicability Verif. Method

3 General Design and interface Requirements 3.1 General Design Requirements 3.1.1 Lifetime STR-2023 GDI-31:

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

STR-2024 GDI-32: The Unit shall meet the requirements of this speci ...

Y A,R

STR-2025 GDI-33: The in-orbit lifetime of the satellite is defined ...

Y R

STR-2026 GDI-34: The unit shall be designed with positive margins o ...

Y A,R

STR-2027 GDI-35: Maintenance during storage shall be as limited as ...

Y R

3.1.2 Design Safety STR-2029 GDI-37:

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

STR-2030 GDI-38: General safety requirements for units are as follo ...

Y A

3.1.3 Venting STR-2032 GDI-41:

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

STR-2033 GDI-42: For all relevant thermal hardware, explicitly MLI, ...

Y R

STR-2034 GDI-43: Unless a cavity is hermetically sealed adequate me ...

Y R

STR-2035 GDI-44: Structural members (honeycomb panels, in particula ...

Y T,A

3.1.4 Interchangeability STR-2037 GDI-46:

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

3.1.5 Identification & Marking STR-2039 GDI-50:

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

STR-2040 GDI-2253: The unit identification nameplate shall be mounted ...

Y

STR-2041 GDI-2254: For the particular case of connector identificatio ...

Y

3.1.6 Accessibility/Maintainability STR-2043 GDI-52:

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

STR-2044 GDI-53: The equipment shall be designed to require a minim ...

Y R

STR-2045 GDI-54: No field maintenance, servicing or adjustment shal ...

Y R

3.1.7 Transportation, Handling and Storage

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3.1.7.1 Transport STR-2048 GDI-2272:

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

STR-2049 GDI-2273: The transport container shall ensure that the envi ...

Y

STR-2050 GDI-2274: The storage container shall be designed to protect ...

Y

3.1.7.2 Unit packing STR-2052 GDI-2275:

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

STR-2053 GDI-2276: All units shall be packaged to ensure that it is s ...

Y

3.1.7.3 Container identification STR-2055 GDI-2277:

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

STR-2056 GDI-2278: In addition to the above, the container shall also ...

Y

3.1.7.4 Handling STR-2058 GDI-2271:

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

3.1.7.5 Thermally Conductive Materials STR-2060 GDI-70:

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

3.1.7.7 Seals STR-2062 GDI-75:

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

STR-2063 GDI-76: Any seals requiring periodic replacement during gr ...

Y R

3.1.7.8 Lubricants and Sealants STR-2065 GDI-78:

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

3.1.7.9 Screw Locking STR-2067 GDI-80:

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

STR-2068 GDI-2270: All screw type hardware used on the unit shall be ...

Y

3.2 Mechanical Design and Interface Requirements STR-2070 GDI-82:

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

STR-2071 GDI-83: Units shall be compliant with ECSS-E30 Part 2A, an ...

Y R

STR-2072 GDI-84: Following testing the unit shall be inspected to c ...

Y I

STR-2073 GDI-87: No unit shall generate microvibration loads at its ...

Y A,R

3.2.1 Structural Design 3.2.1.1 General Requirements STR-2076 GDI-91:

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

STR-2077 GDI-92: The unit shall be designed to withstand the enviro ...

Y A,R

STR-2078 GDI-2282: The design of the units handling and transportatio ...

Y

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STR-2079 GDI-94: Wherever practical a fail safe design based on red ...

Y A

STR-2080 GDI-95: In cases where a failsafe design cannot be impleme ...

Y A

STR-2081 GDI-2045: All potential fracture critical items shall be sub ...

Y A

3.2.1.2 Mass properties STR-2083 GDI-2284:

A mass justification shall be provided indicating ... Y

STR-2084 GDI-98: All mass estimations shall be accompanied by the d ...

Y T

STR-2085 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 STR-2087 GDI-102:

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

STR-2088 GDI-104: The unit centre of gravity shall be determined wit ...

Y T,A

STR-2089 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 STR-2092 GDI-2288:

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

STR-2093 GDI-2289: The stiffness requirements shall be demonstrated t ...

Y

3.2.1.4.2 Mechanical Analysis STR-2095 GDI-2539:

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

STR-2096 GDI-2540: The adequacy of the FEM to predict thermo-elastic ...

Y

STR-2097 GDI-2541: The FEM of the represented item in its launch conf ...

Y

STR-2098 GDI-2542: The FEM of the equipment shall be verified and cor ...

Y

STR-2099 GDI-2544: Reduced FEM mathematical models to be employed in ...

Y

STR-2100 GDI-2546: Adequate models to calculate Centre of Mass and Mo ...

Y

3.2.1.5 Strength Requirements 3.2.1.5.1 Definitions and General Requirements STR-2103 GDI-2354:

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

STR-2104 GDI-2366: GAIA equipment mechanical testing shall take into ...

Y

STR-2105 GDI-2367: GAIA equipment mechanical testing shall take into ...

Y

STR-2106 GDI-2368: An additional Protoflight Factor of Safety, FOSPF ...

Y

3.2.1.5.2 Margin Of Safety & Safety Factors STR-2108 GDI-2370:

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

STR-2109 GDI-2371: Where design loads are generated using FE analyses ...

Y

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STR-2110 GDI-2372: The GAIA hardware shall be able to withstand, with ...

Y

STR-2111 GDI-2375: All mechanical elements shall demonstrate positive ...

Y

STR-2112 GDI-2380: The margins of safety for all elements of the unit ...

Y

STR-2113 GDI-2381: All bolts shall be sized to prevent sliding under ...

Y

STR-2114 GDI-2502: Initially conservative friction coefficients regar ...

Y

STR-2115 GDI-2382: Wherever applicable, rules for general design of b ...

Y

STR-2116 GDI-2383: In addition, in case of combined loads due to ther ...

Y

STR-2117 GDI-2385: where T, S and M are applied values including safe ...

Y

STR-2118 GDI-2386: Method for evaluation of dimensioning loads/stress ...

Y

STR-2119 GDI-129: The units shall be designed with positive margins ...

Y A

STR-2120 GDI-130: The design loads for the structure elements are to ...

Y A

STR-2121 GDI-131: The internal loads (thermo elastic, pre-stressed m ...

Y A

STR-2122 GDI-132: For the computation of the design loads the maximu ...

Y A

STR-2123 GDI-2297: For sine and random vibrations, the mechanical siz ...

Y

3.2.1.6 Alignment and Stability STR-2125 GDI-2550:

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

STR-2126 GDI-2548: The following causes of misalignment shall be anal ...

Y

3.2.2 Design Requirements 3.2.2.1 Attachment Requirements STR-2129 GDI-160:

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

STR-2130 GDI-161: The attachment points shall provide a controlled s ...

Y I,R

STR-2131 GDI-162: The interface plane flatness of a unit shall be be ...

Y I

STR-2132 GDI-163: The mechanical mounting interface shall be consist ...

Y R

STR-2133 GDI-164: The unit bolts type and number shall be defined to ...

Y R

STR-2134 GDI-165: Unless otherwise specified all units shall be thro ...

Y I,R

STR-2135 GDI-2132: To minimise CoG uncertainty of the unit when mount ...

Y I,R

STR-2136 GDI-168: Unless special conditions override, the thickness ...

Y I,R

STR-2137 GDI-169: For the unit mounting, provision shall be made for ...

Y I,R

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STR-2138 GDI-2123: Unit Lug/Hole Design Requirements: Unit mounting h ...

Y I,R

STR-2139 GDI-170: Sufficient clearance shall be allowed between mech ...

Y I,R

STR-2140 GDI-171: Requirement deleted ...

Y A

STR-2141 GDI-173: Fasteners shall be procured and tested according t ...

Y I

STR-2142 GDI-2599: Fasteners shall comply with the requirements of EC ...

Y

STR-2143 GDI-2600: Fasteners smaller than diameter 5 mm shall not be ...

Y

STR-2144 GDI-2598: Titanium alloy fasteners shall not be used in safe ...

Y

STR-2145 GDI-174: The Flight equipment shall be able to survive:- - ...

Y A

3.2.2.2 Alignment Requirements STR-2147 GDI-176:

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

STR-2148 GDI-177: Optical references are required to withstand all t ...

Y R

STR-2149 GDI-178: Location of optical references for units shall be ...

Y R

STR-2150 GDI-179: The alignment errors shall be included in pointing ...

Y R

STR-2151 GDI-180: Units which require alignment accuracy of ±0.25° o ...

Y R

3.2.2.3 Electrical connectors STR-2153 GDI-2302:

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

STR-2154 GDI-2303: Connectors shall be arranged in such a way that th ...

Y

STR-2155 GDI-2304: Unit shall offer means to mechanically lock male a ...

Y

3.2.3 Mechanical / Optical Interface Control Documents STR-2157 GDI-183:

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

STR-2158 GDI-184: Interfaces will be subjected to a formal inspectio ...

Y T,I

STR-2159 GDI-185: The issues of ICDs have to be released as defined ...

Y A

STR-2160 GDI-186: One of the attachment holes on a unit shall be spe ...

Y R

STR-2161 GDI-187: The unit reference frame shall have its origin at ...

Y R

STR-2162 GDI-188: The unit alignment reference frame shall have its ...

Y R

STR-2163 GDI-190: The dimensioning of the attachment hole pattern sh ...

Y A

STR-2164 GDI-191: Interface Control Drawings shall be provided to th ...

Y R

3.2.4 Mechanical Mathematical Model Requirements

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3.3 Thermal Design and Interface Requirements 3.3.1 Definition of Temperatures and Terms 3.3.1.1 Radiatively Controlled Unit STR-2169 GDI-239:

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

3.3.1.2 Conductively Controlled Unit STR-2171 GDI-241:

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

3.3.1.3 Isothermal Unit STR-2173 GDI-243:

As far as possible thermal gradients across the ba ... Y R

STR-2174 GDI-244: For radiative units the temperature difference bet ...

Y R

STR-2175 GDI-245: For conductive units the temperature difference be ...

Y R

STR-2176 GDI-246: For non-isothermal units a reference temperature s ...

Y R

3.3.1.4 Temperature Reference Point (TRP) STR-2178 GDI-248:

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

3.3.2 Thermal Interface Requirements 3.3.2.2 Radiative Interface STR-2181 GDI-258:

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

STR-2182 GDI-2582: Units shall demonstrate compliance to their design ...

Y

3.3.2.3 Internal Temperature Monitoring STR-2184 GDI-260:

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

STR-2185 GDI-261: The location, type and electrical interface of all ...

Y R

3.3.3 Thermal Design Requirements STR-3047 GDI-2657:

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

STR-2187 GDI-263: The units shall be designed such that all internal ...

Y A

STR-2188 GDI-264: Hot spots on the external surface of the unit are ...

Y A,R

STR-2189 GDI-2656: In the absence of any uncertainty analysis an init ...

Y

STR-2190 GDI-2079: For units located outside of the Focal Plane Assem ...

Y A,R

3.3.4 Thermal Control 3.3.4.1 General STR-2193 GDI-2555:

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

STR-2194 GDI-2556: The equipment thermal control shall be achieved pr ...

Y

STR-2195 GDI-2557: The equipment thermal control design shall permit ...

Y

STR-2196 GDI-2558: The equipment thermal control must be testable on ...

Y

STR-2197 GDI-2559: If special equipment is required to evacuate the h ...

Y

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STR-2198 GDI-2560: No thermal control item shall prevent the spacecra ...

Y

STR-2199 GDI-2561: Deviations and temporal degradations from the nomi ...

Y

STR-2200 GDI-2562: A Thermal Reference Point (TRP) shall be defined a ...

Y

STR-2201 GDI-2563: The TRP temperature also called "interface tempera ...

Y

STR-2202 GDI-2564: In addition, the TRP temperature shall be monitore ...

Y

STR-2203 GDI-2565: The equipment thermal control shall include and mo ...

Y

STR-2204 GDI-2566: The design limits of units are equal to the qualif ...

Y

STR-2205 GDI-2567: The design limits of units are equal to the accept ...

Y

3.3.4.2 Thermal Analysis STR-2207 GDI-2552:

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

STR-2208 GDI-2553: The Geometrical and Thermal Mathematical Models (G ...

Y

3.3.5 Thermal Interface Control Documents STR-2210 GDI-267:

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

STR-2211 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 STR-2214 GDI-2091:

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

STR-2215 GDI-272: The Thermal mathematical model shall be provided f ...

Y A

STR-2216 GDI-273: Units: All units used in thermal models (geometric ...

Y A

3.3.6.2 Thermal Model Correlation STR-2218 GDI-275:

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

3.3.6.3 Reduced Thermal Model STR-2220 GDI-277:

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

STR-2221 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 STR-2225 GDI-282:

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

3.4.1.2 Materials STR-2227 GDI-284:

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

STR-2228 GDI-285: The use of stain sensitive glasses shall be avoide ...

Y R

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STR-2229 GDI-286: The use of optical cements shall be avoided as far ...

Y R

3.4.1.3 Coatings STR-2231 GDI-289:

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

STR-2232 GDI-290: Thermo-optical properties of the coatings shall be ...

Y R

STR-2233 GDI-292: High efficiency anti-reflective coatings shall be ...

Y R

STR-2234 GDI-293: Sensitivity of coatings to polarisation effects as ...

Y T,R

3.4.1.4 Performances STR-2236 GDI-295:

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

STR-2237 GDI-296: Alignment and interface with regard to other optic ...

Y T

3.4.2 Optical Interface Requirements STR-2239 GDI-298:

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

STR-2240 GDI-299: The free mechanical aperture of optical surfaces s ...

Y R

STR-2241 GDI-300: In addition to specific requirements mentioned in ...

Y R

3.4.3 Optical Mathematical Model Requirements STR-2243 GDI-302:

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

STR-2244 GDI-303: The numerical model shall be developed in Code V ® ...

Y A

3.5 Electrical Design and Interface Requirements 3.5.1 General Requirements STR-2247 GDI-308:

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

STR-2248 GDI-309: Beginning-Of-Life criteria shall be derived by the ...

Y R

3.5.2 Power Interface Requirements (LC & FC) 3.5.2.1 Regulated Power Requirements STR-2251 GDI-338:

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

STR-3048 GDI-2696: During all mission phases the spacecraft power bus ...

Y T

STR-2252 GDI-2104: The spacecraft fully regulated bus shall have a no ...

Y T,R

STR-2253 GDI-2103: For load changes of up to 50% of the nominal load ...

Y T,R

STR-2254 GDI-2133: The bus voltage shall remain within 5% of its nomi ...

Y T,R

STR-2255 GDI-339: If undervoltage protection is implemented by the l ...

Y T

STR-2256 GDI-340: In case of an inductive load, when considering the ...

Y T,A

STR-2257 GDI-341: The load shall not be irreversibly degraded for an ...

Y R

STR-2258 GDI-342: No fuse protection shall be implemented. ...

Y R

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STR-2259 GDI-343: Primary current protection shall not be implemente ...

Y R

STR-2260 GDI-344: The contractor shall design the load side of the L ...

Y T,R

STR-2261 GDI-346: All power converters shall be designed to allow op ...

Y T

STR-2262 GDI-347: The free-running frequency shall be limited to ±10 ...

Y T

STR-2263 GDI-348: The as designed free-running frequency and frequen ...

Y T

STR-2264 GDI-349: Units connected to LCL's or FCL's shall be designe ...

Y A

STR-2265 GDI-1273: At the point of regulation, the impedance of the v ...

Y T,R

3.5.2.2 Power Consumption Requirements STR-2267 GDI-361:

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

STR-2268 GDI-362: For each power interface circuit, the following co ...

Y T,A

STR-2269 GDI-363: A power consumption test shall be required at temp ...

Y T,R

3.5.2.3 Tolerance to Power Bus Failures STR-2271 GDI-365:

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

3.5.2.4 Initial Electrical Status STR-2273 GDI-367:

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

3.5.2.5 Special Case: Secondary Power Supplied Units STR-2275 GDI-370:

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

STR-2276 GDI-371: The source unit shall be protected against short-c ...

Y T

STR-2277 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 STR-2280 GDI-378:

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

STR-2281 GDI-379: All data and signal interface drivers shall surviv ...

Y T,A

STR-2282 GDI-380: The unit shall tolerate active signal I/Fs when un ...

Y T,A

STR-2283 GDI-381: In case the electrical architecture does foresee c ...

Y T,R

STR-2284 GDI-382: In case no load is specified, the characteristics ...

Y R

3.5.3.2 Harness Capacitance STR-2286 GDI-391:

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

3.5.4 Connectors General Design Requirements 3.5.4.1 Harness STR-2289 GDI-395:

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

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STR-2290 GDI-396: All cable bundles shall be routed as close as poss ...

Y I,R

STR-2291 GDI-397: In wiring through connectors all leads shall be ke ...

Y I,R

STR-2292 GDI-398: The DC resistance between the single cable shield ...

Y T

STR-2293 GDI-399: The structure termination of shields shall be made ...

Y I,R

3.5.4.2 Connector Types STR-2295 GDI-401:

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

STR-2296 GDI-402: All flight connectors shall be designed to withsta ...

Y I,R

STR-2297 GDI-2158: Individual mate/demates shall be recorded in a mat ...

Y R

STR-2298 GDI-2157: The number of times flight connectors are mated / ...

Y R

STR-2299 GDI-2156: If by prior agreement with S/C Prime the number of ...

Y I,R

STR-2300 GDI-403: Different connector classes shall be implemented i ...

Y R

3.5.4.3 Connector Characteristics STR-2302 GDI-405:

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

STR-2303 GDI-406: Connectors shall not be a source of single point f ...

Y R

STR-2304 GDI-407: Equipment or structure-mounted connectors shall be ...

Y R

STR-2305 GDI-408: Male and female connectors shall be mechanically l ...

Y R

STR-2306 GDI-409: Active lines together with their return shall be o ...

Y I

STR-2307 GDI-410: Connectors shall be made of Non magnetic material ...

Y R

STR-2308 GDI-411: For any unit connector which contains a number of ...

Y T,R

STR-2309 GDI-412: Nominal and redundant lines shall have separated c ...

Y R

3.5.4.4 Connector Mounting STR-2311 GDI-414:

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

STR-2312 GDI-415: Connectors shall be arranged in such a way that th ...

Y R

STR-2313 GDI-416: Mechanical methods in conjunction with identificat ...

Y I,R

STR-2314 GDI-417: Connector savers shall be utilized on all flight s ...

Y R

STR-2315 GDI-418: The connection shield ground pin to case shall be ...

Y R

3.5.4.5 Test Connectors STR-2317 GDI-420:

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

STR-2318 GDI-421: Test connectors shall be protected by EMC metal co ...

Y I,R

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STR-2319 GDI-422: The metallic protection cover shall be capable of ...

Y R

3.5.5 Standard Interfaces 3.5.5.1 ECSS-E-50-12A: SpaceWire STR-2322 GDI-2388:

The applicable version of the ECSS-E-50-12A SpaceW ... Y I

STR-2323 GDI-2387: The terms, definitions, abbreviated terms and conv ...

Y I

STR-2324 GDI-2396: The cable definition and construction requirements ...

Y I,R

STR-2325 GDI-2400: The connector definition and construction requirem ...

Y I,R

STR-2326 GDI-2402: The cable assembly requirement of the ECSS-E-50-12 ...

Y T,I

STR-2327 GDI-2662: For each unit external SpaceWire link connector(s) ...

Y T,A

STR-2328 GDI-2404: The PCB and backplane tracking requirements of the ...

Y I,R

3.5.5.1.3 Signal Layer STR-2330 GDI-2406:

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

STR-2331 GDI-2407: The LVDS driver and receiver interfaces shall be d ...

Y T

3.5.5.1.3.2 Failsafe Operation of LVDS STR-2333 GDI-2410:

The LVDS failsafe operation requirements of the EC ... Y T,I,R

STR-2334 GDI-2408: No LVDS configuration involving more than one (1) ...

Y T,I,R

3.5.5.1.3.3 Signal Coding STR-2336 GDI-2414:

The signal coding requirements of the ECSS-E-50-12 ... Y I,R

STR-2337 GDI-2413: The data-strobe system shall carry an ‘encoded’ cl ...

Y T,I,R

STR-2338 GDI-2412: A SpaceWire data interface shall consist of a link ...

Y I,R

3.5.5.1.3.4 Data Signalling Rate STR-2340 GDI-2416:

After a reset or disconnect the SpaceWire link tra ... Y T

STR-2341 GDI-2515: The lower limit to data signalling rate shall be 2 ...

Y I,R

3.5.5.1.3.5 Skew & Jitter STR-2343 GDI-2423:

In accordance with the definition of skew, jitter ... Y T

STR-2344 GDI-2424: In accordance with the definition of skew, jitter ...

Y T

STR-2345 GDI-2425: In accordance with the definition of skew, jitter ...

Y T

3.5.5.1.4 Character Layer 3.5.5.1.4.1 Data Characters, Control Characters & Codes STR-2348 GDI-2398:

The data character, control character and control ... Y I,R

3.5.5.1.4.2 Parity Coverage STR-2350 GDI-2427:

The parity bit coverage requirements of the ECSS-E ... Y I,R

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3.5.5.1.4.3 First Null Token after Reset or Link Error STR-2352 GDI-2430:

The first Null Token transmitted after reset or li ... Y T

3.5.5.1.4.4 Time Interface 3.5.5.1.5 Exchange Layer 3.5.5.1.5.1 Link-characters & Normal-Characters STR-2356 GDI-2454:

The requirements related to the separation of Spac ... Y R

3.5.5.1.5.2 Flow Control STR-2358 GDI-2455:

The requirements related to the SpaceWire link flo ... Y R

STR-2359 GDI-2457: Any on-board SpaceWire node shall expand the excha ...

Y R

STR-2360 GDI-2495: The SpaceWire link interface "Credit Counter" and ...

Y I,R

STR-2361 GDI-2496: The highest order of priority for transmission of ...

Y I,R

3.5.5.1.5.3 End-to-End Data Flow Architecture STR-2363 GDI-2500:

The host system on SpaceWire TX side shall contain ... Y T,R

STR-2364 GDI-2510: The SpaceWire node TX Output Buffer shall be contr ...

Y T,R

STR-2365 GDI-2511: The host systems on both ends shall allow for the ...

Y T,R

STR-2366 GDI-2512: No desynchronisation of CCSDS packet handling nor ...

Y T,R

STR-2367 GDI-2456: The host system on SpaceWire RX side shall contain ...

Y I,R

3.5.5.1.5.4 State Machine STR-2369 GDI-2513:

Any on-board SpW node shall provide link managemen ... Y I,R

STR-2370 GDI-2514: Any on-board SpW node shall accept the following t ...

Y I,R

STR-2371 GDI-2517: The reset of the SpaceWire link interface state ma ...

Y T

3.5.5.1.5.5 Autostart / Link Initialisation STR-2373 GDI-2448:

The requirements related to the SpaceWire link aut ... Y I,R

STR-2374 GDI-2518: A SpaceWire link interface shall start on command ...

Y T

3.5.5.1.5.6 Normal Operation STR-2376 GDI-2519:

The requirements related to the SpaceWire link nor ... Y I,R

3.5.5.1.5.7 Error Detection STR-2378 GDI-2520:

On exchange level, an on-board SpaceWire node shal ... Y T

STR-2379 GDI-2524: The "exchange of silence" procedure - upon error d ...

Y I,R

STR-2380 GDI-2522: The reporting of errors to the upper levels - pack ...

Y I,R

STR-2381 GDI-2521: Errors that can affect the synchronisation on pack ...

Y I,R

3.5.5.1.5.8 Exception Conditions

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STR-2383 GDI-2525: The requirements related to the SpaceWire link exc ...

Y I,R

3.5.5.1.5.9 Link Timing STR-2385 GDI-2526:

The requirements related to the SpaceWire link tim ... Y I,R

3.5.5.1.6 Packet Layer STR-2387 GDI-2536:

The SpaceWire packet format shall be in accordance ... Y I,R

STR-2388 GDI-2499: Whichever SpaceWire supporting device is used, the ...

Y T,R

3.5.5.1.6.2 CCSDS Packet STR-2390 GDI-2530:

For any on-board SpW node featuring CCSDS packetis ... Y I,R

3.5.5.1.6.4 Maintenance of Synchronisation on SpaceWire Packet Level

STR-2392 GDI-2523: Any on-board SpaceWire node shall provide means to ...

Y T

3.5.5.1.6.5 Maintenance of Synchronisation on CCSDS Packet Level

STR-2394 GDI-2534: Any on-board CCSDS-packetised SpaceWire node shall ...

Y T

3.5.5.1.7 Network Layer 3.5.5.1.7.1 Network Topology for GAIA SpaceWire

Implementation

STR-2397 GDI-2535: Wherever n SpaceWire nodes (e.g., instruments or i ...

Y I,R

3.5.5.1.7.2 Implementation of Routing as per ECSS STR-2399 GDI-2591:

Wherever SpaceWire routing is implemented inside a ... Y T

3.5.5.1.8 SpaceWire Standard Supporting Devices 3.5.5.1.8.1 SMCS & IEEE-1355 Standard STR-2402 GDI-2442:

Any SpaceWire implementation of the existing Europ ... Y I,R

3.5.5.1.8.2 SMCS & SpaceWire STR-2404 GDI-2441:

The European SMCS332SpW and SMCS116SpW shall be th ...

Y I,R

3.5.5.1.8.3 SpaceWire VHDL Core STR-2406 GDI-2587:

In case of custom SpaceWire controllers implemente ... Y I,R

3.5.5.2 MIL-STD-1553 Bus Interfaces (MIL) STR-2408 GDI-426:

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

STR-2409 GDI-427: All units (BC or RT) shall be configured in long s ...

Y R

STR-2410 GDI-2177: The maximum length of the long stub shall be 6 met ...

Y I,R

STR-2411 GDI-2176: Only one RT shall be connected to a stub cable. ...

Y I,R

STR-2412 GDI-428: Each BC and RT (N&R) shall be connected to both 15 ...

Y I,R

STR-2413 GDI-429: Each stub shall be grounded inside each RT or BC d ...

Y R

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STR-2414 GDI-430: The RT address shall be programmable on an externa ...

Y R

STR-2415 GDI-431: The 1553-bus shall be connected on separate connec ...

Y R

STR-2416 GDI-2139: The 1553-bus shall be connected on separate connec ...

Y R

STR-2417 GDI-1198: Unless otherwise agreed with the Prime Contractor, ...

Y R

STR-2418 GDI-432: The 1553-Bus Protocol shall be compliant to the Ga ...

Y R

STR-2419 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 STR-2422 GDI-2460:

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

STR-2423 GDI-2462: These tests shall be performed only in ambient con ...

Y

STR-2424 GDI-2463: ...

Y

STR-2425 GDI-2464: ...

Y

STR-2426 GDI-2465: ...

Y

STR-2427 GDI-2466: ...

Y

STR-2428 GDI-2467: ...

Y

STR-2429 GDI-2468: ...

Y

STR-2430 GDI-2469: ...

Y

STR-2431 GDI-2470: ...

Y

STR-2432 GDI-2471: ...

Y

STR-2433 GDI-2472: ...

Y

STR-2434 GDI-2473: ...

Y

STR-2435 GDI-2474: ...

Y

STR-2436 GDI-2475: ...

Y

STR-2437 GDI-2476: ...

Y

STR-2438 GDI-2477: ...

Y

STR-2439 GDI-2478: ...

Y

STR-2440 GDI-2479: ...

Y

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STR-2441 GDI-2480: Note 1: Functional test through 1553B interface ...

Y

STR-2442 GDI-2481: ...

Y

3.5.5.2.1.2 Acceptance Test STR-2444 GDI-2485:

... Y

STR-2445 GDI-2486: ...

Y

STR-2446 GDI-2487: ...

Y

STR-2447 GDI-2488: ...

Y

STR-2448 GDI-2489: ...

Y

STR-2449 GDI-2490: ...

Y

STR-2450 GDI-2491: ...

Y

STR-2451 GDI-2492: ...

Y

STR-2452 GDI-2493: ...

Y

STR-2453 GDI-2494: Note 1: Functional test through 1553B interface ...

Y

3.5.5.3 Standard Balanced Digital link (SBDL) STR-2455 GDI-438:

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

STR-2456 GDI-1201: The contractor shall design his side of the Standa ...

Y T,R

3.5.5.5 Timing Pulses 3.5.5.5.1 Synchronisation or Datation Pulses (PPS) STR-2459 GDI-460:

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

STR-2460 GDI-462: The active level shall be High level ...

Y R

STR-2461 GDI-463: The synchronisation edge shall be the rising edge ...

Y R

STR-2462 GDI-464: The pulse width shall be ³ 900 ns ...

Y T

3.5.5.5.2 Synchronization Clock Interface (TBC) 3.5.5.7 Temperature Acquisitions (ANY, ANP, ANF, ANT) STR-2465 GDI-482:

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

STR-2466 GDI-483: The temperature aquisition interface circuitry, as ...

Y R

3.5.5.7.1 Thermistor Type1: YSI-44907/-44908 (ANY) STR-2468 GDI-1215:

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

3.5.5.8 Relay Commands (SHP, EHP, SLP) STR-2470 GDI-493:

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

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STR-2471 GDI-494: The High Power On/Off Command receiver shall be is ...

Y R

STR-2472 GDI-495: The High Power On/Off Command receiver shall be eq ...

Y R

STR-2473 GDI-496: The High Power On/Off Command source shall be shor ...

Y R

STR-2474 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) STR-2476 GDI-497:

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

Y T,R

3.5.5.9 Relay Status Acquisitions (RSA) STR-2478 GDI-1229:

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

STR-2479 GDI-516: Relay Status Acquisition The contractor shall desi ...

Y T,R

3.5.6 Electrical Interface Control Document STR-2481 GDI-558:

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

3.5.7 EMC Requirements STR-2483 GDI-2154:

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

3.5.7.1 Bonding STR-2485 GDI-562:

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

STR-2486 GDI-563: Metallic parts of each electrical equipment chassi ...

Y T

STR-2487 GDI-564: Joint faces shall be flat and clean before assembl ...

Y I,R

STR-3049 GDI-565: All non-electrical equipment shall be bonded to th ...

Y T

STR-2488 GDI-566: Each electrical equipment chassis (case) shall be ...

Y T,R

STR-2489 GDI-567: Metallic receptacles of connectors shall be electr ...

Y T

3.5.7.1.1 Ground Reference Rail STR-2491 GDI-569:

Electrical bonding throughout CFRP structure shall ... Y R

STR-2492 GDI-570: The resistance between any adjacent parts of the G ...

Y T,R

STR-2493 GDI-571: The resistance between any two points of the GRR s ...

Y T,R

3.5.7.1.2 Cable and Harness Shields STR-2495 GDI-573:

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

STR-2496 GDI-574: The maximum unshielded length of any shielded wire ...

Y R

STR-2497 GDI-575: Daisy chaining of shield terminations shall be avo ...

Y R

STR-2498 GDI-576: Shields shall not be used as an intentional curren ...

Y R

3.5.7.1.4 Mechanical Parts

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STR-2500 GDI-581: Mechanical Parts without electrical nor shielding ...

Y T,R

STR-2501 GDI-582: Mechanical Parts used for electromagnetic shieldin ...

Y T,R

3.5.7.2 Grounding and Isolation 3.5.7.2.1 General STR-2504 GDI-585:

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

STR-2505 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 STR-2507 GDI-588:

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

STR-2508 GDI-589: Openings for drainage, ventilation, etc... shall n ...

Y I

STR-2509 GDI-590: All units shall have a M4 bonding stud ...

Y I

STR-2510 GDI-591: The design of this bonding stud shall allow the co ...

Y I

3.5.7.2.3 Insulating materials STR-2512 GDI-593:

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

3.5.7.2.4 Thermal parts STR-2514 GDI-595:

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

Y I

STR-2515 GDI-596: MLI: The grounding points shall be in a minimum of ...

Y I,R

STR-2516 GDI-597: MLI: The resistance between each bonding point an ...

Y T

STR-2517 GDI-598: MLI: The resistance between each bonding point an ...

Y T

STR-2518 GDI-599: PAINTS: Refer to Section GDI-592 above. ...

Y R

STR-2519 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 STR-2522 GDI-605:

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

STR-2523 GDI-606: Isolation: All units (except PCDU) shall maintain ...

Y T,R

3.5.7.3.2 Secondary Power Lines STR-2525 GDI-609:

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

STR-2526 GDI-1988: Equipment with its own dedicated DC - DC converter ...

Y T

STR-2527 GDI-610: Isolation: prior to connection of the unit interna ...

Y T,R

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STR-2528 GDI-2106: After grounding, the impedance between the unit se ...

Y T,R

STR-2529 GDI-611: Secondaries distributed between units (1 supplier; ...

Y R

STR-2530 GDI-612: Secondaries distributed between units (1 supplier; ...

Y R

STR-2531 GDI-614: Grounding diagram including zero volts interconnec ...

Y I

STR-2532 GDI-615: The symbols in Figure GDI-2107 below shall be used ...

Y R

3.5.7.3.3 Signal Interfaces STR-2534 GDI-617:

Signal circuits interfacing between Satellite equi ... Y R

STR-2535 GDI-618: Where single-ended signal transmitters are used, i ...

Y R

STR-2536 GDI-619: The use of common signal return paths is only perm ...

Y R

3.5.7.3.4 EGSE Grounding and Isolation STR-2538 GDI-621:

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

3.5.7.4 Magnetic Moment STR-2540 GDI-1997:

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

3.6 Operations Design and Interface Requirements 3.6.1 Bit / Byte Numbering Convention STR-2544 GDI-632:

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

STR-2545 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

STR-2548 GDI-638: Mode/State transitions: Transitions from one mode/ ...

Y R

STR-2549 GDI-639: The unit supplier shall identify appropriate modes ...

Y R

STR-2550 GDI-640: At all times, equipment and units shall be in a cl ...

Y T,R

STR-2551 GDI-641: In addition, modes and the mode transitions manage ...

Y T,R

STR-2552 GDI-642: The unit supplier shall identify all internal and ...

Y R

STR-2553 GDI-643: The unit supplier shall identify all transition ti ...

Y R

STR-2554 GDI-644: Mode/State transitions with duration longer than 1 ...

Y R

STR-2555 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 STR-2558 GDI-648:

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

STR-2559 GDI-649: In operating states of the unit, it shall be possi ...

Y T

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STR-2560 GDI-650: In addition, in non-operating states of the unit, ...

Y T

STR-2561 GDI-651: Individual switching of switchable elements (e.g. ...

Y T

STR-2562 GDI-652: The on-board reception, processing and execution o ...

Y T,R

STR-2563 GDI-653: The function of a command shall not change through ...

Y T,R

STR-2564 GDI-654: A single command may be used to initialise a chang ...

Y T,R

STR-2565 GDI-655: Commands with variable bit-fields meaning shall no ...

Y R

STR-2566 GDI-656: Nominal and the redundant functions or equipments ...

Y T

STR-2567 GDI-657: The unit design shall avoid any conflict between a ...

Y T

3.6.2.3 Observability 3.6.2.3.1 General STR-2570 GDI-660:

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

STR-2571 GDI-661: The unit shall provide in its housekeeping telemet ...

Y T,R

STR-2572 GDI-662: The unit shall provide the necessary instrumentati ...

Y T,R

STR-2573 GDI-663: Telemetry measurement sensors shall be designed su ...

Y T

STR-2574 GDI-664: It shall be possible to determine the status of th ...

Y T

STR-2575 GDI-665: Essential (high-priority) telemetry data enabling ...

Y T,R

STR-2576 GDI-666: Telemetry shall always be provided to identify una ...

Y T,R

STR-2577 GDI-667: Status information in telemetry shall be provided ...

Y T,R

STR-2578 GDI-668: Any TM processing required at a higher operational ...

Y R

STR-2579 GDI-669: Telemetry shall always be available to determine t ...

Y R

STR-2580 GDI-670: When a key parameter is derived on-board from seve ...

Y T,R

3.6.2.3.2 Telemetry Acquisition STR-2582 GDI-672:

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

STR-2583 GDI-673: The unit design shall avoid any conflict between t ...

Y T

STR-2584 GDI-674: TM acquisitions with conditional meaning shall not ...

Y R

STR-2585 GDI-675: The value of a telemetry parameter shall be transm ...

Y R

STR-2586 GDI-676: Analog TM Acquisition: Analog TM acquisitions sha ...

Y T,R

STR-2587 GDI-677: Acquisition of safety critical analog parameters o ...

Y R

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STR-2588 GDI-678: The values of currents or voltages readings shall ...

Y R

STR-2589 GDI-679: The calibration curve of an analog parameter shall ...

Y R

3.6.2.3.3 Observability of Hardware Configuration STR-2591 GDI-681:

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

STR-2592 GDI-682: In case a unit includes several elementary functio ...

Y R

STR-2593 GDI-683: The configuration of any on-board device and any s ...

Y T,R

STR-2594 GDI-684: Any configuration command register shall be observ ...

Y R

STR-2595 GDI-685: The acquisition of the unit configuration/state sh ...

Y R

STR-2596 GDI-686: The acquisition of an ON/OFF status for a relay sh ...

Y R

STR-2597 GDI-687: If the unit controls the redundancy configuration ...

Y T

STR-2598 GDI-688: Nominal and redundant functions shall be observabl ...

Y R

3.6.2.3.4 Observability of Commands STR-2600 GDI-690:

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

STR-2601 GDI-691: Acknowledgement of commands shall be direct (i.e. ...

Y T,R

STR-2602 GDI-692: The association between command acknowledgement ac ...

Y I

STR-2603 GDI-693: Successful execution of a command to the unit shal ...

Y T,R

STR-2604 GDI-694: Failures in the acceptance and /or the execution o ...

Y T,R

3.6.2.3.5 Converters Observability STR-2606 GDI-696:

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

3.6.2.4 Safety Critical and Hazardous Functions STR-2608 GDI-700:

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

STR-2609 GDI-701: The execution of any unit command or command seque ...

Y A

STR-2610 GDI-702: Commanding of critical commands shall be implement ...

Y A,R

STR-2611 GDI-703: The status of inhibition of safety critical functi ...

Y T

STR-2612 GDI-704: Units shall provide an unambiguous health status o ...

Y T

3.6.2.5 Handling of Memories STR-2614 GDI-706:

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

STR-2615 GDI-707: Any part of installed RAM’s shall be overwriteable ...

Y T

STR-2616 GDI-708: Any part of installed ROM’s shall be readable by m ...

Y T

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STR-2617 GDI-709: For failure investigation, it shall be possible to ...

Y T

3.6.2.6 Autonomy STR-2619 GDI-711:

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

STR-2620 GDI-712: All parameters used for autonomous operations and ...

Y T

3.6.2.7 Automatic Functions STR-2622 GDI-714:

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

STR-2623 GDI-715: All actions generated by automatic on-board logic ...

Y T

STR-2624 GDI-716: The automatic function design shall be such that n ...

Y A,R

STR-2625 GDI-717: Telemetry shall be associated to all automatic fun ...

Y T

STR-2626 GDI-718: For all the automatic logic using several criteria ...

Y T

STR-2627 GDI-719: The capability to change all on board logic (hardw ...

Y T,R

3.6.2.8 Time Synchronisation STR-2629 GDI-721:

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

STR-2630 GDI-722: If the unit has the function, all information on h ...

Y R

STR-2631 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 STR-2634 GDI-726:

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

STR-2635 GDI-727: Any unit shall be able to withstand (i.e. remain i ...

Y T,R

STR-2636 GDI-728: It shall be possible to repeat any command several ...

Y T,R

3.6.2.9.2 Unit Self Tests STR-2638 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

STR-2640 GDI-733: FDIR functions shall be implemented in a hierarchi ...

Y A,R

STR-2641 GDI-734: The unit shall automatically detect any failure, w ...

Y T,R

STR-2642 GDI-735: At unit level failures shall be detectable by adeq ...

Y A

STR-2643 GDI-736: Failure detection algorithms shall report in event ...

Y A,R

STR-2644 GDI-737: Failures which require a reaction time less than 1 ...

Y T,A

STR-2645 GDI-738: Failure which requires a reaction time between 10s ...

Y A,R

STR-2646 GDI-739: Failure isolation shall be performed at switchable ...

Y T,A

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STR-2647 GDI-740: Any FDIR actions on unit level shall be reported t ...

Y T,R

STR-2648 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 STR-2651 GDI-744:

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

3.6.3.2 Inputs to Operational Database STR-2653 GDI-746:

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

STR-2654 GDI-747: Data to be provided (the list is not exhaustive): ...

Y R

3.6.3.3 Operation Manual STR-2656 GDI-749:

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

STR-2657 GDI-750: The following standardization (Table GDI-751) shal ...

Y R

3.7 Software Design & Interface Requirements 3.7.1 General STR-2660 GDI-2181:

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

STR-2661 GDI-2182: All on-board software running in sub-systems shall ...

Y R

STR-2662 GDI-2183: The on-board software shall be developed using a h ...

Y R

STR-2663 GDI-2184: The use of a non high-level language code (e.g., a ...

Y A

STR-2664 GDI-2185: The on-board sotware shall be implemented with a l ...

Y R

3.7.2 Flight Processor Resource Sizing STR-2666 GDI-2192:

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

STR-2667 GDI-2193: Any on-board software shall provide the capability ...

Y T,R

STR-2668 GDI-2194: The resource utilisation monitor shall be availabl ...

Y T,R

STR-2669 GDI-2196: Sizing of the software resources shall be done in ...

Y T,A

3.7.3 Robustness 3.7.3.1 Infinite Loops STR-2672 GDI-2197:

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

STR-2673 GDI-2218: Whenever possibility of Warm Restart is implemente ...

Y

3.7.3.2 Overload STR-2675 GDI-2198:

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

STR-2676 GDI-2199: If and only if the overload situation cannot be ab ...

Y T

3.7.4 Events STR-2678 GDI-2214:

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

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STR-2679 GDI-2215: The on-board software shall maintain counters for: ...

Y T

3.7.5 Initialisation STR-2681 GDI-2226:

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

STR-2682 GDI-2228: The Cold Restart shall start execution from a hard ...

Y T

STR-2683 GDI-2229: The Warm Restart shall start from a software comma ...

Y T

STR-2684 GDI-2230: The Warm Restart shall perform a processor reset a ...

Y T

STR-2685 GDI-2227: The Cold Restart and the Warm Restart initialisati ...

Y T

STR-2686 GDI-2234: At a predictible stage of the initialisation, the ...

Y

3.7.6 Testability STR-2688 GDI-2205:

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

3.7.7 SW Maintainability 3.7.7.1 Version Number STR-2691 GDI-2209:

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

STR-2692 GDI-2212: The flight software version number shall be retrie ...

Y T

STR-2693 GDI-2208: The flight software version number shall be modifi ...

Y T

3.7.7.2 In Flight SW Modification STR-2695 GDI-2186:

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

STR-2696 GDI-2187: The on-board software shall be structured such tha ...

Y R

STR-2697 GDI-2231: Any on-board unit embedding software shall support ...

Y T

STR-2698 GDI-2232: Any on-board unit embedding software shall support ...

Y T

STR-2699 GDI-2201: Any on-board unit embedding software shall be repr ...

Y T

3.7.7.3 Ease of SW Operations & Modifications STR-2701 GDI-2206:

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

STR-2702 GDI-2210: All on-board software data that are anticipated to ...

Y R

STR-2703 GDI-2211: The on-board software shall have knowledge of the ...

Y T

STR-2704 GDI-2207: Software-implemented limits and triggers for anoma ...

Y T,R

3.7.8 SafeGuard Memory (SGM) Maintainability STR-2706 GDI-2223:

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

STR-2707 GDI-2224: The on-board software shall implement SGM data str ...

Y T

3.7.9 Independent SW Validation (ISV) STR-2709 GDI-2188:

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

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3.7.10 SW Maintenance Products STR-2711 GDI-2189:

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

STR-2712 GDI-2190: All on-board software resident in ASIC, FPGA, or o ...

Y T

STR-2713 GDI-2233: The SW maintenance environment shall provide the m ...

Y T

STR-2714 GDI-2235: All software licenses for any software used to dev ...

Y T

STR-2715 GDI-2236: For any on-board unit embedding software, a softwa ...

Y T

STR-2716 GDI-2237: The software development and maintenance facility ...

Y T

4 Environment Design Requirements STR-2718 GDI-2315:

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

4.1 Ground operation phase STR-2720 GDI-2318:

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

4.1.1 Thermal and climatic environment STR-2722 GDI-2320:

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

STR-2723 GDI-2321: Assembly, integration and verification of flight h ...

Y

STR-2724 GDI-2322: During transport prior to integration on the space ...

Y

STR-2725 GDI-2323: The flight hardware transportation containers shal ...

Y

4.1.2 Mechanical environment STR-2727 GDI-790:

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

STR-2728 GDI-793: During ground transportation the equipments shall ...

Y T,A

STR-2729 GDI-2327: All MGSE, containers, transportation and handling ...

Y

STR-2730 GDI-2328: Sine and random vibrations: the unit transport con ...

Y

STR-2731 GDI-2329: For containers, the shock requirement is a drop of ...

Y

STR-2732 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 STR-2735 GDI-780:

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

4.2.2 Contamination STR-2737 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 STR-2740 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

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STR-2743 GDI-808: All units mounted on the SCM structure shall be de ...

Y T,A

4.2.3.2.2 Random Environment STR-2745 GDI-812:

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

4.2.3.2.3 Acoustic environment STR-2747 GDI-2338:

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

4.2.3.2.4 Shock Environment STR-2749 GDI-818:

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

4.2.4 Thermal environment STR-2751 GDI-2508:

During the Launch and early Operation phase, the s ... Y

STR-2752 GDI-2602: For units having a view factor to external space, ...

Y

4.2.5 Electromagnetic and radio frequency environment 4.3 In orbit Environment 4.3.1 In orbit mechanical loads 4.3.1.1 Quasi-static & Thermo-elastic Loads STR-2757 GDI-823:

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

STR-2758 GDI-2131: The unit shall be compatible with internal loads g ...

Y A

4.3.1.2 Micro-vibrations STR-2760 GDI-825:

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

4.3.1.3 Dynamical distrurbances STR-2762 GDI-2677:

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

STR-2763 GDI-2678: Once the equipment operational conditions have bee ...

Y

4.3.2 In orbit thermal STR-2765 GDI-841:

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

STR-2766 GDI-2583: During the In Orbit phase, the spacecraft units wi ...

Y

STR-2767 GDI-2603: For units having a view factor to external space, ...

Y

4.4 Radiation Environment 4.4.1 Introduction STR-2770 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

STR-2773 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 4.4.3 Long Term Effect Considerations 4.4.3.1 Ionizing Dose Depth Curve STR-2777 GDI-1966:

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

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4.4.3.2 Displacement Damage 4.4.4 Rules for Design and Performance STR-2780 GDI-876:

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

STR-2781 GDI-877: Unit shall take into account the shielding provide ...

Y A,R

4.4.5 Radiation Sensitive Components STR-2783 GDI-1969:

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

STR-2784 GDI-1970: All parts shall be reviewed by the Subcontractor t ...

Y R

STR-2785 GDI-1971: The Subcontractor shall issue a Radiation Assessme ...

Y R

4.4.5.1 Total Dose STR-2787 GDI-1975:

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

4.4.5.2 Single Event Effects (SEE) STR-2789 GDI-1977:

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

STR-2790 GDI-1978: The component shall be designed to tolerate GCR, p ...

Y T,A,R

4.4.5.3 Single Event Latch-up STR-2792 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...)

STR-2794 GDI-1982: Part types shall be acceptable according to the ac ...

Y A,R

STR-2795 GDI-2681: Memory circuits shall have sufficient error det ...

Y

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

STR-2797 GDI-1984: For SEB and SEGR, error rate prediction techniques ...

Y A,R

4.4.5.6 Displacement Damage STR-2799 GDI-1986:

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

STR-2800 GDI-1987: The reset or data corruption occurrence rate due t ...

Y A,R

4.5 EMC Environment 4.5.1 EMC Performance Requirements 4.5.1.1 Inrush Current STR-2804 GDI-895:

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

4.5.1.2 Voltage Transients STR-2806 GDI-897:

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

STR-2807 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

STR-2810 GDI-902: Conducted narrow band current emissions (different ...

Y T

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STR-2811 GDI-904: Conducted narrow band current emissions (common mo ...

Y T

4.5.1.3.2 Conducted Emissions on Power Leads, Time Domain

STR-2813 GDI-907: Time domain conducted differential mode voltage ri ...

Y T

STR-2814 GDI-908: Time domain conducted voltage spikes on the primar ...

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

STR-2817 GDI-918: The maximum voltage emission levels for secondary ...

Y T

4.5.1.4.2 CE for Secondary Power Supply Units, Time Domain

STR-2819 GDI-920: The voltage ripple and spikes on secondary power s ...

Y T

4.5.2 Radiated Emissions - E field STR-2821 GDI-922:

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

4.5.3 Radiated Emissions - H field STR-2823 GDI-926:

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

4.5.4 Radiated Emissions Fluctuations - E Field STR-2825 GDI-2013:

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

4.5.5 Radiated Emissions Fluctuations - H Field STR-2827 GDI-2022:

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

4.5.6 Radiated Susceptibility - E field STR-2829 GDI-928:

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

STR-2830 GDI-929: No unit that is powered On at launch shall show an ...

Y T

4.5.7 Radiated Susceptibility - H field STR-2832 GDI-932:

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

4.5.8 Units linked by Secondary Power Lines STR-2834 GDI-934:

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

STR-2835 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

STR-2838 GDI-938: Primary power bus powered units shall not exhibit ...

Y T

4.5.9.2 Conducted Susceptibility Sine Wave - Common Mode

STR-2840 GDI-2000: The unit shall not exhibit any malfunction, degrad ...

Y T

4.5.9.3 Conducted Susceptibility - Transient STR-2842 GDI-2007:

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

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STR-2843 GDI-2009: Transient Type 1 With reference to (figure GDI-941 ...

Y T

STR-2844 GDI-2010: Transient Type 2 With reference to (figure GDI-941 ...

Y T

4.5.9.4 CE / CS on Interface signal lines STR-2846 GDI-944:

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

STR-2847 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

STR-2850 GDI-949: The conducted susceptibility specification for sec ...

Y T,R

4.5.10.2 Requirement at subsystem or system level STR-2852 GDI-951:

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

STR-2856 GDI-958: The use of relays shall be limited to the most cri ...

Y R

4.5.12 ESD Susceptibility STR-2859 GDI-962:

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

4.5.13.2 Corona Gas Discharge STR-2861 GDI-2693:

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

STR-2862 GDI-2694: Adequate venting shall be provided to ensure that ...

Y

STR-2863 GDI-2695: If the above requirements GDI-2693 and GDI-2694 ca ...

Y

4.5.14 Micrometeoroid environement STR-2865 GDI-2683:

The micrometeoroid environment for the mission sha ... Y

STR-2866 GDI-2686: A damage assessment based on the micrometeoroid en ...

Y

5 Unit Level Test Requirements 5.1 General 5.1.1 Test Definition 5.1.1.1 Qualification tests STR-2871 GDI-967:

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

5.1.1.2 Acceptance Tests STR-2873 GDI-969:

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

5.1.1.3 Functional Performance Tests STR-2875 GDI-971:

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

5.1.2 Test Facilities RequirementsY STR-2877 GDI-973:

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

5.1.2.1 Accuracy of Test Instrumentation STR-2879 GDI-975:

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

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5.1.2.2 Tolerances of Test Parameters STR-2881 GDI-977:

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

5.1.2.3 Facility Ambient Condition STR-2883 GDI-981:

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

5.1.3 Test Execution STR-2885 GDI-983:

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

5.1.4 Success Criteria STR-2887 GDI-985:

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

5.2 Unit Tests STR-2889 GDI-2679:

The qualification and acceptance tests to be perfo ... Y

5.2.1 Mechanical Environment Tests 5.2.1.1 Vibration Test Set Up STR-2892 GDI-989:

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

STR-2893 GDI-990: At least one triaxial sensor shall be mounted on t ...

Y T

STR-2894 GDI-991: At least two axis aligned sensors shall be mounted ...

Y T

STR-2895 GDI-992: All units powered on during launch shall be powere ...

Y T

5.2.1.2 Test Fixture STR-2897 GDI-995:

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

STR-2898 GDI-996: The variation of transmissibility between test ite ...

Y T

STR-2899 GDI-997: Adequate fixture design and specimen installation ...

Y T

STR-2900 GDI-998: A pre-test of the empty fixture shall be performed ...

Y T

5.2.1.3 Frequency Search STR-2902 GDI-1000:

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

STR-2903 GDI-1002: Frequency search tests shall be conducted along ea ...

Y T

5.2.1.4 Vibration Tests Level STR-2905 GDI-1005:

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

5.2.1.5 Sine And Random Vibration Test STR-2907 GDI-1011:

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

STR-2908 GDI-1012: Prior and after sine and random vibration qualific ...

Y T

STR-2909 GDI-1013: Before applying full levels, a test at intermediat ...

Y T

STR-2910 GDI-1014: This Requirement has been Deleted. ...

Y

STR-2911 GDI-1015: The vibration facility shall include a shock free ...

Y T

5.2.1.6 Shock Tests

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STR-2913 GDI-1017: Units shall demonstrate by test their ability to w ...

Y T

STR-2914 GDI-1018: Prior and after shock tests a low level sine frequ ...

Y T

5.2.1.7 Static tests STR-2916 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 STR-2919 GDI-1024:

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

STR-2920 GDI-1025: The test arrangement shall be as shown in Figure G ...

Y R

STR-2921 GDI-1026: The unit shall be bolted to a thermally controlled ...

Y R

STR-2922 GDI-1027: On all external surfaces flight representative the ...

Y R

STR-2923 GDI-1028: The heat sink (HS) plates shall be black painted ( ...

Y R

STR-2924 GDI-1029: The conductive heat sink temperature and the chamb ...

Y R

STR-2925 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 STR-2928 GDI-1034:

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

STR-2929 GDI-1036: The TV test on unit level shall be performed as in ...

Y R

STR-2930 GDI-1037: The qualification temperatures for the different u ...

Y R

STR-2931 GDI-1038: The units shall be tested following the thermal va ...

Y T,R

5.2.2.2.2 Acceptance Thermal Vacuum STR-2933 GDI-1044:

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

STR-2934 GDI-1045: The thermal vacuum acceptance test shall be perfor ...

Y T,R

5.2.2.2.3 Protoflight Thermal Vacuum STR-2936 GDI-1049:

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

STR-2937 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 STR-2941 GDI-1057:

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

5.2.3.1.2 EMC Qualification Test STR-2943 GDI-1059:

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

5.2.3.1.3 EMC Acceptance Test STR-2945 GDI-1061:

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

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5.2.3.1.4 EMC Integration Test STR-2947 GDI-1063:

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

5.2.3.1.5 Retest Criteria STR-2949 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 STR-2951 GDI-1067:

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

5.2.3.1.7 Test Sequence STR-3051 GDI-2155:

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

5.2.3.2 Test Facility 5.2.3.2.1 EMC Test Environment STR-2955 GDI-1072:

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

5.2.3.2.2 Capabilities STR-2957 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 STR-2960 GDI-1077:

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

5.2.3.3.2 Accuracy of the Test Measurement Equipment STR-2962 GDI-1079:

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

5.2.3.3.3 Special Requirements on the Test Equipment STR-2964 GDI-1081:

Grounding of Test Equipment: Measurement equipment ...

Y R

STR-2965 GDI-1082: Antenna Placement: For radiated emission measureme ...

Y R

STR-2966 GDI-1083: Receiver Bandwidth: The following receiver bandwid ...

Y R

STR-2967 GDI-1085: Power Adjustment: The primary power for unit level ...

Y R

5.2.3.3.4 Line Impedance Stabilisation Network (LISN): STR-2969 GDI-1087:

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

STR-2970 GDI-1090: The LISN has to be designed and provided by the co ...

Y T

STR-2971 GDI-2116: Derivation of the bus impedance shall be performae ...

Y T

5.2.3.3.5 Test Conditions STR-2973 GDI-1095:

The equipment under test shall be switched on in t ... Y R

STR-2974 GDI-1096: For emission testing the unit shall operate within ...

Y R

STR-2975 GDI-1097: For susceptibility testing the suitable operationa ...

Y R

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STR-2976 GDI-1098: After testing the equipment shall be switched off ...

Y R

STR-2977 GDI-1099: Both operational modes shall provide operational c ...

Y R

STR-2978 GDI-1100: The particular test set-up shall represent the fli ...

Y R

5.2.3.3.6 Susceptibility Testing STR-2980 GDI-2142:

The applicable pass/fail criteria for susceptibili ... Y R

STR-2981 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 STR-2984 GDI-1107:

The bonding test shall be performed with the unit ... Y R

STR-2985 GDI-1108: The bonding test shall be performed without any ha ...

Y R

5.2.3.4.2 Isolation STR-2987 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 STR-2990 GDI-1116:

UUT operation shall be selected in order to maximi ... Y R

STR-2991 GDI-1118: Ripple and transient interference tests on the pow ...

Y R

5.2.3.4.3.2 CE on Secondary Power Lines STR-2993 GDI-1123:


STR-2994 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

STR-2996 GDI-2090: The mode selection for susceptibility testing shal ...

Y T,R

5.2.3.4.5 Conducted Susceptibility on Power Lines STR-2998 GDI-1133:

The mode selection for susceptibility testing shal ... Y R

STR-2999 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

STR-3001 GDI-1140: The mode selection for susceptibility testing shal ...

Y R

STR-3002 GDI-1141: The test set-ups are shown in Figure GDI-1142 (CS0 ...

Y T

5.2.3.4.7 Radiated Emission, Electric Field STR-3004 GDI-1151:


5.2.3.4.8 Radiated Emissions, E-Field Fluctuations 5.2.3.4.9 Radiated Emission, Magnetic Field STR-3007 GDI-1155:


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5.2.3.4.11 Radiated Susceptibility, Electric Field STR-3010 GDI-1159:


5.2.3.4.12 Radiated Susceptibility, Magnetic Field STR-3012 GDI-1163:


5.2.3.4.13 Electrostatic Discharge (ESD) STR-3014 GDI-1167:


5.2.4 Life Test STR-3016 GDI-1185:

A life test shall be required for all the assembli ... Y T,R

5.2.5 Space Conditioning STR-3018 GDI-1187:

Space conditioning shall be performed whenever des ... Y T,R

STR-3019 GDI-1188: The contractors shall propose the corresponding te ...

Y R

STR-3020 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

STR-36 ............... 3.1.1.................9 STR-38 ............... 3.1.2.................9 STR-40 ............... 3.1.4.................10 STR-41 ............... 3.1.3.................9 STR-44 ............... 3.2....................10 STR-45 ............... 3.2....................10 STR-46 ............... 3.2....................10 STR-47 ............... 3.2....................10 STR-48 ............... 3.2....................10 STR-51 ............... 3.2....................10 STR-54 ............... 3.3....................12 STR-56 ............... 3.3....................12 STR-57 ............... 3.3....................12 STR-59 ............... 3.4....................12 STR-60 ............... 3.4....................12 STR-61 ............... 3.4....................12 STR-62 ............... 3.4....................12 STR-63 ............... 3.4....................12 STR-64 ............... 3.4....................12 STR-65 ............... 3.4....................12 STR-66 ............... 3.4....................12 STR-67 ............... 3.4....................12 STR-68 ............... 3.4....................12 STR-74 ............... 3.5.3.................15 STR-77 ............... 3.5.3.................15 STR-166 ............. 4.1....................22 STR-173 ............. 4.2.1.................22 STR-175 ............. 4.2.2.................22 STR-181 ............. 4.3....................23 STR-316 ............. 3.1.3.................9 STR-327 ............. 3.1.2.................9 STR-328 ............. 3.1.3.................9 STR-330 ............. 3.2....................10 STR-333 ............. 3.2....................10 STR-335 ............. 3.3....................12 STR-337 ............. 3.3....................12 STR-338 ............. 3.3....................12 STR-340 ............. 3.4....................12 STR-343 ............. 4.1....................22 STR-402 ............. 3.1.5.................10 STR-412 ............. 4.3....................23 STR-413 ............. 4.3....................23 STR-548 ............. 3.5.1.................14 STR-551 ............. 3.5.4.................16 STR-552 ............. 3.4....................12 STR-553 ............. 3.4....................12 STR-569 ............. 4.4.2.................25 STR-570 ............. 4.4.2.................25 STR-573 ............. 4.4.3.................26 STR-574 ............. 4.4.3.................26 STR-575 ............. 4.4.3.................26 STR-576 ............. 4.4.3.................26 STR-578 ............. 4.4.4.................26 STR-580 ............. 4.4.4.1..............26 STR-635 ............. 4.3....................23 STR-638 ............. 3.7....................20 STR-639 ............. 3.7....................20

STR-640..............3.7 ................... 20 STR-641..............3.7 ................... 20 STR-646..............3.2 ................... 10 STR-649..............3.3 ................... 12 STR-651..............4.4.1 ................ 25 STR-1410............3.7 ................... 20 STR-1411............3.4 ................... 12 STR-1416............3.3 ................... 12 STR-1565............3.6.1 ................ 17 STR-1566............3.6.1 ................ 17 STR-1572............3.6.1 ................ 17 STR-1576............3.6.1 ................ 17 STR-1583............3.6.2 ................ 17 STR-1585............3.6.2 ................ 17 STR-1595............3.6.2 ................ 17 STR-1604............3.6.2.1 ............. 18 STR-1625............3.6.2 ................ 17 STR-1626............3.6.2.2 ............. 19 STR-1627............3.6.2.2 ............. 19 STR-1629............3.6.2.2 ............. 19 STR-1636............3.6.2.3 ............. 20 STR-1671............5.1.1 ................ 30 STR-1906............3.5.3 ................ 15 STR-1907............3.5.4 ................ 16 STR-1910............3.6 ................... 16 STR-1911............3.6.2.1 ............. 18 STR-1917............3.5.1 ................ 14 STR-1921............3.5.3 ................ 15 STR-1923............4.3 ................... 23 STR-1947............4.2.3 ................ 22 STR-1953............4.3 ................... 23 STR-1954............4.3 ................... 23 STR-1956............3.5.2 ................ 15 STR-1957............3.5.2 ................ 15 STR-1959............4.4.5 ................ 26 STR-1960............4.4.5 ................ 26 STR-1961............4.4.5 ................ 26 STR-1963............4.4.5 ................ 26 STR-1965............4.4.5 ................ 26 STR-1967............4.4.5 ................ 26 STR-1968............4.4.5 ................ 26 STR-1969............4.4.5 ................ 26 STR-1970............4.4.5 ................ 26 STR-1971............4.4.5 ................ 26 STR-1972............4.4.5 ................ 26 STR-1973............4.4.5 ................ 26 STR-1974............4.4.5 ................ 26 STR-1975............4.4.5 ................ 26 STR-1976............4.4.5 ................ 26 STR-1977............4.4.5 ................ 26 STR-1978............4.4.5 ................ 26 STR-1979............4.4.5 ................ 26 STR-1980............4.4.5 ................ 26 STR-1981............4.4.5 ................ 26 STR-1982............4.4.5 ................ 26 STR-1983............4.4.5 ................ 26 STR-1984............4.4.5 ................ 26

STR-1987 ........... 5.1.3 .................30 STR-1989 ........... 5.1.3 .................30 STR-1991 ........... 5.2 ....................30 STR-1996 ........... 5.3 ....................30 STR-1999 ........... 5.4 ....................30 STR-2001 ........... 5.5 ....................30 STR-2004 ........... 6 .......................31 STR-2006 ........... 7 .......................32 STR-2013 ........... 4.4.2 .................25 STR-2016 ........... 4.4.4.2 ..............26 STR-3036 ........... 3.6.2.2 ..............19 STR-3037 ........... 3.6.2.2 ..............19 STR-3039 ........... 3.6.2.2 ..............19 STR-3044 ........... 3.6.2.3 ..............20 STR-3045 ........... 3.6.2.3 ..............20 STR-3063 ........... 3.5.1 .................14 STR-3064 ........... 3.5.3 .................15 STR-3065 ........... 3.6.1 .................17 STR-3066 ........... 3.6.2 .................17 STR-3067 ........... 4.3 ....................23 STR-3070 ........... 4.4.2 .................25 STR-3071 ........... 4.4.2 .................25 STR-3072 ........... 4.4.2 .................25 STR-3073 ........... 4.4.4.2 ..............26 STR-3074 ........... 4.4.5 .................26 STR-3077 ........... 5.3 ....................30 STR-3078 ........... 5.1.2 .................30 STR-3080 ........... 3.6.2.1 ..............18 STR-3081 ........... 3.6.2.1 ..............18 STR-3083 ........... 3.6.2.1 ..............18 STR-3084 ........... 4.3 ....................23 STR-3086 ........... 4.4.5 .................26 STR-3088 ........... 4.4.5 .................26 STR-3089 ........... 3.3 ....................12 STR-3101 ........... 4.4.5 .................26 STR-3104 ........... 3.4 ....................12 STR-3105 ........... 4.4.5 .................26

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