Sun Sensor Specification - European Space Agencyemits.sso.esa.int/emits-doc/ASTRIUMLIM/LISA_DSS/S2.ASU... · 2010-01-13 · LISA Pathfinder S2.ASU.RS.2026 Issue 1 Page 10 of 54 EADS

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S2.ASU.RS.2026 ISS01 Sun Sensor Requirement Spec.doc

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CONTENTS

1. INTRODUCTION AND SCOPE.....................................................................................................................6 1.1 Introduction.............................................................................................................................................6 1.2 Scope .....................................................................................................................................................8 1.3 Summary Description .............................................................................................................................8 1.4 Definition of Terms .................................................................................................................................8

2. DOCUMENTS................................................................................................................................................9 2.1 Applicable Documents............................................................................................................................9 2.2 Applicable Standards .............................................................................................................................9 2.3 Reference Documents............................................................................................................................9

3. FUNCTIONAL AND PERFORMANCE REQUIREMENTS..........................................................................10 3.1 Reference frames definition .................................................................................................................10

3.1.1 SS Mechanical reference frame definition .................................................................................10 3.1.2 SS Alignment reference frame definition ...................................................................................10 3.1.3 SS Measurement reference frame definition .............................................................................10

3.2 Statistical Definition ..............................................................................................................................11 3.3 Conditions for performance requirements............................................................................................11

3.3.1 General.......................................................................................................................................11 3.3.2 Dynamics conditions ..................................................................................................................11 3.3.3 Operating Environment ..............................................................................................................11

3.4 Albedo Rejection ..................................................................................................................................11 3.5 Field of View .........................................................................................................................................11 3.6 Calibration ............................................................................................................................................12 3.7 Output ...................................................................................................................................................12 3.8 FDIR/Redundancy................................................................................................................................13 3.9 Performance Requirements .................................................................................................................13

3.9.1 Accuracy.....................................................................................................................................13 3.9.2 Quantisation ...............................................................................................................................13 3.9.3 Local Linearity ............................................................................................................................13 3.9.4 Alignment ...................................................................................................................................13 3.9.5 Bandwidth and Sampling Frequency .........................................................................................13 3.9.6 Delay ..........................................................................................................................................13

3.10 Unit Modes .........................................................................................................................................14

4. UNIT SPECIFIC DESIGN AND INTERFACE REQUIREMENTS ...............................................................15 4.1 Implementation .....................................................................................................................................15

4.1.1 On/Off Relay...............................................................................................................................15 4.2 Mechanical Design and Interfaces .......................................................................................................15

4.2.1 Mass...........................................................................................................................................15 4.2.2 Envelope ....................................................................................................................................15 4.2.3 Unit Attachment..........................................................................................................................15

4.3 Thermal Design and Interface ..............................................................................................................15 4.4 Electrical Design and Interface.............................................................................................................17

4.4.1 Power .........................................................................................................................................17 4.4.2 Power Interface ..........................................................................................................................17 4.4.3 Harness ......................................................................................................................................17 4.4.4 Interface to Satellite Data Handling............................................................................................17 4.4.5 Test Equipment ..........................................................................................................................17

5. GENERAL DESIGN AND INTERFACE REQUIREMENTS ........................................................................20

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5.1 General .................................................................................................................................................20 5.2 Mechanical ...........................................................................................................................................20 5.3 Thermal ................................................................................................................................................20 5.4 Electrical ...............................................................................................................................................20 5.5 Identification & Marking ........................................................................................................................22

6. VERIFICATION REQUIREMENTS .............................................................................................................23

7. PRODUCT ASSURANCE REQUIREMENTS .............................................................................................24

8. ACRONYMS................................................................................................................................................25

9. GDIR APPLICABILITY MATRIX..................................................................................................................26

TABLES Table 4.3-1: Sun Sensor External Thermal Environment................................................................................16 Table 5.4-1: Magnetic Fields ...........................................................................................................................21

FIGURES Figure 1.1-1: The LISA mission will use an ultra-precise interferometry through three satellites flying in

formation on an Earth-like orbit to measure ripples in space-time ............................................................7

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1. INTRODUCTION AND SCOPE

1.1 Introduction LISA is a co-operative program between ESA and NASA to detect and measure `ripples' in the fabric of space-time to verify tenets of fundamental physics. The program includes two space missions; The LISA PATHFINDER mission and the LISA mission itself. LISA will consist of three spacecraft flying in a quasi-equilateral triangular formation, in a trailing Earth orbit at some 20 deg behind the Earth. Within each spacecraft, a measurement system consisting of two test masses, associated laser interferometer measurement systems, and electronics will detect and measure low frequency gravitational waves. The test masses are maintained in a drag-free environment, i.e. shielded from spurious external forces, by using low thrust propulsion. This mission is currently in its formulation stage. LISA PATHFINDER is a precursor mission to LISA that aims to verify most of the challenging technologies necessary for LISA.

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Figure 1.1-1: The LISA mission will use an ultra-precise interferometry through three satellites flying

in formation on an Earth-like orbit to measure ripples in space-time

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1.2 Scope This document defines the mission, performances, environment, interface and design requirements for the Sun Sensor for the Lisa Pathfinder Attitude and Orbit Control Subsystem (AOCS). Each requirement is identified by a unique requirement number and is written in italics. Each requirement is proceeded by a summary line that contains the following fields, delimited by "/". � <Doors Requirement Number> TKS-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 Text that is not written in italics is there for information purposes only (e.g. background information that clarifies the origins of the requirement): it does not constitute part of the requirement itself.

1.3 Summary Description This section provides a general introduction into the sun sensor usage and necessary functionality for the LISA Pathfinder mission. The Sun Sensor for LISA Pathfinder will be used during certain mission phases, covering the LEOP, the transfer, and mission operations in the Lagrange 1 (L1) orbit. The specification is for a unit providing measurement in 2 orthogonal axes, typically with respect to the Sun direction. The sun sensor requirements for the mission is for a set of units which allows simultaneous use for a) nominal control b) failure detection and c) Safe mode control. Each of these functions must be independent of each other so that a failure in the nominal sensors does not affect the failure detection or safe mode usage. It is therefore envisaged that the suite of sun sensors as a whole will include 3 independent 2 axis measurements. It is recognised that the above mentioned functionality can be provided in two ways under the current availability: Either by using 3 distinct 2 axis units OR with 2, 2 axis units which have internal redundancy. The specification is written to refer to a single 2 axis unit. In some instances the unit requirements vary depending on whether 2 units or 3 units are applicable. For example, a slightly increased unit mass is permitted for the 2 unit scenario compared with 3 units. This is clearly stated where it is applied.

1.4 Definition of Terms The Sun Sensor (SS) is defined as a complete 2 axis Sun Sensor unit including any electronics, data interface and power interface.

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2. DOCUMENTS The following documents, at the latest issue unless otherwise stated, are relevant documents to this specification. In case of conflict between any of these documents and the contents of this specification, the requirements of this specification shall take precedence. Any such conflict shall be reported to Astrium.

2.1 Applicable Documents The following documents form a part of this specification to the extent specified.

AD-14 S2.ASU.RS.1005 PA Requirements for Subcontractors

AD-15 S2.SYS.RS.1001 Software PA Requirements for Subcontractors

AD-17 S2.ASU.RS.2031 LISA Pathfinder GDIR

AD-21 S2.ASU.LI.1006 Acronyms and Abbreviations

AD-22 S2.ASU.RS.5038 EGSE Overall Requirements Specification

2.2 Applicable Standards The following Engineering Documents and Standards form part of this specification to the extent specified.

STD-1 Space Engineering - Space Environment, ECSS-E-10-04A, 21.01.2000

STD-2 Space Engineering - Electrical and Electronic, ECSS-E-20A, 04.10.99

STD-3 Space Engineering - Mechanical, ECSS-E-30 Part 1A to 8A, 25.04.2000

STD-4 ESA Error Handbook, EHB.DGD.REP.002, Iss. 1, 19.02.1993

STD-6 Packet Telemetry Standard, PSS-04-106, Issue 1, January 1988

STD-7 Telemetry Channel Coding Standard, PSS-04-103 Issue 1, September 1989

STD-12 Space Engineering - Software, ECSS-E-40B, November 2003

STD-16 Space Engineering - Verification, ECSS-E-10-02A, 17.11.1998

STD-17 Space Engineering - Testing, ECSS-E-10-03A, 15.02.2002

STD-19 Structural Materials Handbook, PSS-03-203, Volumes 1 & 2

STD-27 MIL-STD-1553B 21 September 1978 + Notice 2 8 September 1986, Notice 3 31 January 1993, Notice 4 15 January 1996.

2.3 Reference Documents The following documents do not form part of this specification but were used during its preparation.

None

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3. FUNCTIONAL AND PERFORMANCE REQUIREMENTS

3.1 Reference frames definition

3.1.1 SS Mechanical reference frame definition SS-412/CREATED/I,R

The SS (optical head and electronics) shall employ a right handed Cartesian reference frame with its origin at the reference point of the SS, and the orientation of the axes as defined below. The Z_SS_mF axis is aligned with the SS line of sight and oriented from the platform to space. The X_SS_mF axis shall be in the mounting plate plane and shall be clearly identified on the SS hardware. The Y_SS_mF axis is defined in order to have a right-hand orthogonal referential. The definition of this reference frame shall be defined in the SS Mechanical Interface Control Document.

3.1.2 SS Alignment reference frame definition SS-415/CREATED/I,R

The SS shall include an optical reference cube (or other alignment device) for the purpose of aligning the SS onto the spacecraft.

SS-416/CREATED/R The alignment device shall be used to form a right handed Cartesian reference frame, the Alignment Reference Frame (O_SS_aF, X_SS_aF, Y_SS_aF, Z_SS_aF) as shown in the figure cited in requirement GDI-188 of AD-17.

3.1.3 SS Measurement reference frame definition SS-418/CREATED/R

The SS shall employ a right handed orthogonal Cartesian reference frame that has one of its axes perpendicular to the photo detector and pointing away from the image detector towards Space. The reference frame shall be designated Sun Sensor Measurement Reference Frame. This measurement reference frame shall be defined such that when the Sun vector is Normal to the X_SS_pF/ Y_SS_pF plane, output from the unit indicates nominal Sun pointing (before sensor measurement errrors) . The Z_SS_pF axis is aligned as defined as the outward normal from the image detector plane towards space. The X_SS_pF axis shall be in the image detector plane and shall be clearly identified. The Y_SS_pF axis is defined in order to have a right-hand orthogonal referential. The definition of this reference frame shall be defined in the SS Mechanical Interface Control Document.

SS-419/CREATED/R The SS supplier shall deliver the 3x3-transfer matrix from the SS Alignment reference frame to the SS Measurement Reference Frame.

SS-420/CREATED/T,A,R The delivered transfer matrix referred to in requirement SS-419 above shall be measured before and after all the environment tests performed during the acceptance phase.

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3.2 Statistical Definition SS-605/CREATED/R

All performance requirements where applicable shall be met at the 3 sigma confidence level.

The 3 sigma confidence level is defined as the percentage of samples which fall within 3 standard deviations of the mean for a population with Normal/Gaussian distribution.

3.3 Conditions for performance requirements

3.3.1 General SS-602/CREATED/T,A

The performance requirements (cited in Section 3.9) shall be met under worst case BOL and EOL conditions in the presence of all known effects influencing this performance to include (where appropriate) but not restricted to environmental, launch loads, spacecraft dynamic conditions, ageing, radiation environment, sensor bias, sensor noise, quantisation, temperature effects, unit conversion factor errors, 1g to 0g effects and SEU's.

3.3.2 Dynamics conditions SS-561/CREATED [RP-3]/T,A

The SS shall offer the performance as cited Section 3.9 with rates of up to 5 deg/s (TBC) around any axis in the SS measurement reference frame.

3.3.3 Operating Environment SS-593/CREATED/A

The sun sensor shall offer nominal performance while operating in the Earth altitude range between 200 km and 1.8 million km (direction towards L1 Lagrange point).

SS-594/CREATED/A The sun sensor shall offer continuous nominal performance as cited in Section 3.9 in the presence of the environment specified in AD-17 section 4.

3.4 Albedo Rejection SS-589/CREATED/T,A

The sun sensor shall offer the performance levels cited in Section 3.9 in the presence of Earth Albedo coefficient in the range 0.2 to 0.85.

SS-591/CREATED/T,A The sun sensor shall offer albedo rejection (sufficient to give performance levels cited in Section 3.9) with: �� minimum altitude of 200 km, �� orbital inclination of between 30 and 75 degrees and �� any angle between Sun/Spacecraft/Earth.

3.5 Field of View SS-408/CREATED [RP-3]/R

Each SS shall have a useable Field of View (FoV) of at least ±60° in the sensor's X_SS_pF/Z_SS_pF and Y_SS_pF/Z_SS_pF planes.

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SS-608/CREATED/T,A Nominal performance as cited in Section 3.9 shall be achieved for the entire sensor field of view.

3.6 Calibration SS-618/CREATED/T,A

The unit shall meet all nominal performance requirements as cited in Section 3.9 without need for any in orbit calibration.

3.7 Output SS-574/CREATED/T,A,R

The unit shall output a signal which unambiguously indicates when the Sun is in the sensor field of view

SS-575/CREATED/R The unit shall output data which allows alpha and beta Sun angles to be obtained which shall be defined as follows: The alpha angle shall be a measure of the angle between the Z_SS_pF axis of the unit and the projection of the Sun vector in the Y_SS_pF/Z_SS_pF plane. The beta angle shall be a measure of the angle between the Z_SS_pF axis of the unit and the projection of the Sun vector in the X_SS_pF/Z_SS_pF plane.

SS-587/CREATED/R If an alternative definition of alpha and beta angle output measurements are proposed, these shall be clearly defined by the supplier at the time of proposal.

SS-586/CREATED/R The sign convention of the alpha and beta measurements shall be clearly defined by the supplier.

SS-583/CREATED/R If the alpha and beta output from the unit is not in a recognised physical angle measurement (e.g. radians, degrees etc), the supplier shall provide the conversion algorithm to convert from the output signal to the equivalent angle measurement.

SS-584/CREATED/T,A,R The measurement performance requirements shall include effects from conversions from raw output to physical angle measurements.

SS-576/CREATED/R The unit shall output a health status flag indicating the status of the unit.

SS-1489/CREATED/T,A,R The precise coverage of the health status flag shall be defined by the supplier, in the first instance, at the time of the proposal.

SS-1490/CREATED/T,A,R The reliability of the health status flag shall be indicated, in the first instance, at the time of the proposal.

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3.8 FDIR/Redundancy SS-582/CREATED/T,A

In the unit proposed has internal redundancy, all alpha channels shall be fully independent such that any failure in one alpha channel shall not propagate to any other alpha channel.

SS-730/CREATED/T,A In the unit proposed has internal redundancy, all beta channels shall be fully independent such that any failure in one beta channel shall not propagate to any other beta channel.

3.9 Performance Requirements

3.9.1 Accuracy SS-603/CREATED [RD-134]/T,A

The sun sensor unit alpha and beta measurement accuracy shall be better than 0.5 degrees (3 sigma) including all noise and bias effects.

3.9.2 Quantisation SS-1575/CREATED [RD-134]/T,A

The quantisation of the sun sensor unit alpha and beta measured output shall be better than 0.04 �/bit.

3.9.3 Local Linearity SS-1577/CREATED [RD-134]/T,A

The local slope of the actual (input) angle to measured angle (for alpha and beta angles) curve shall not vary by more than +/-5% from unity.

3.9.4 Alignment SS-611/CREATED/T,A

The alignment error between Sun Sensor Measurement Reference Frame and Sun Sensor Alignment Reference Frame shall be better than 1 degree (3 sigma) after launch.

SS-612/CREATED/T,A The knowledge accuracy of the alignment between Sun Sensor Measurement Reference Frame and Sun Sensor Alignment Reference Frame shall be provided in the first instance at the time of the proposal.

3.9.5 Bandwidth and Sampling Frequency SS-615/CREATED/T,A

The measurement bandwidth of the unit shall be 5 Hz or faster.

SS-1565/CREATED/T,A The measurement sampling frequency of the unit shall be at least 10 Hz.

3.9.6 Delay SS-1581/CREATED/T,A

The maximum delay between the middle of period over which measurements are acquired and the availability of the corresponding telemetry packet at the Sun sensor interface shall be less than 150ms.

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3.10 Unit Modes SS-620/CREATED/T,A

Once powered ON, the unit shall reach its operational state (such that all functionality as defined in Section 3 is provided) without need for any commands to be sent from the spacecraft or ground.

SS-624/CREATED/R Any unit internal mode switching shall be handled autonomously by the unit.

SS-621/CREATED/T,A A maximum time of 5 minutes (TBC) shall be allowed from unit being powered until reaching its operational state.

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4. UNIT SPECIFIC DESIGN AND INTERFACE REQUIREMENTS

4.1 Implementation

4.1.1 On/Off Relay SS-678/CREATED/R

There shall be no on/off relay.

Power switching is performed by the Satellite Power Subsystem.

4.2 Mechanical Design and Interfaces

4.2.1 Mass SS-682/CREATED/T,A

The mass of each Sun Sensor unit shall be minimised and shall have a maximum mass of 0.5 kg (3 units) or 0.75 kg (2 units).

4.2.2 Envelope SS-684/CREATED/I

The dimensions of each sun sensor unit shall not exceed 130mm x 120mm x 55mm (for 3 units) or 163 mm x 146 mm x 56 mm (for 2 units).

SS-1488/CREATED/R The overall footprint of the sun sensor shall be minimised.

4.2.3 Unit Attachment SS-744/CREATED/T,A,R

The Sun sensors shall be directly mounted onto CFRP on the top floor of the SCM. This shall be taken into account with respect to the unit attachment requirements in AD-17.

4.3 Thermal Design and Interface SS-1568/CREATED/R

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

SS-738/CREATED/T,A The unit thermal design shall consider the worst case thermal environment. As the SS unit is exposed to the external environment of the spacecraft, the enveloping thermal boundary conditions and environment for the SS shown in Table 4.3-1 must be considered. Combinations of these environment parameters that produce the worst case conditions shall be assumed in the unit level thermal analysis.

Max Min

Spacecraft Interface Temperature, Operation (�C) 130 -60 (TBC)1

Solar Flux (W/m2) 1464.0 1316.0

Planet Albedo (LEOP and Transfer) 0.36 0

Earth Temperature, (LEOP and Transfer) (K) 265.0 N/A

Space Temperature (K) 3

1: This minimum temperature may occur during LEOP and transfer phase sun off pointing manoeuvres

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Thermal Environment Parameter

Table 4.3-1: Sun Sensor External Thermal Environment

All temperatures shown apply to the acceptance limits of the unit. The interface temperature applies to the conductive interface temperature of the spacecraft sun shield to which the unit is attached.

SS-1570/CREATED/A,R During LEOP and the transfer phase the incidence angle of the flux from the Sun and flux from the Earth can be from any direction and the worst case direction shall be assumed in the analysis. (Including the unit being shadowed by the spacecraft). During the on-station phase the sun sensor will be in direct solar flux with a solar angle approximately normal to the sun shield.

SS-1571/CREATED/A,R The external optical properties of the spacecraft shall be assumed to have an absorptivity of 0.92 and emissivity of 0.78. All reflections shall be considered to be diffuse.

SS-740/CREATED/T,A,R The On-ground thermal requirements specified in the GDIR (AD-17) shall still apply.

SS-741/CREATED/R The selection of the external finishes of the units shall be made in consultation with the spacecraft prime contractor.

SS-1572/CREATED/R The design goal that the thermal control of the sun sensor equipment shall be via passive means only. (i.e. MLI, radiators, conductive isolation) However if the need for thermal heaters is identified the design shall minimise the power required. The spacecraft will supply any necessary heaters. The design goal that the thermal control of the sun sensor equipment shall be via passive means only. (i.e. MLI, radiators, conductive isolation) However if the need for thermal heaters is identified the design shall minimise the power required. The spacecraft will supply any necessary heaters. A simple fixed heater power level (i.e. not thermostatically controlled) shall be used with power not exceeding 1W.

SS-742/CREATED/R The design and supply of any thermal hardware (excluding heaters) required to maintain the units(s) within the thermal environments specified shall be the responsibility of the equipment supplier.

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4.4 Electrical Design and Interface

4.4.1 Power SS-690/CREATED/T,A

The power consumption of each Sun Sensor unit shall not exceed 1.8 W (for 3 units) or 2.7 W (for 2 units).

4.4.2 Power Interface SS-692/CREATED/R

The SS is designated a Platform Equipment and shall draw power from the current limited, externally switched sunlight regulated power bus as defined in section 3.5.2.1 of AD-17.

4.4.3 Harness All power and signal interfaces between the Sun Sensor unit and other units and subsystems will be made via the harness subsystem.

SS-696/CREATED/R The sun sensor unit shall interface with other units and subsystems via connectors only (i.e. no flying leads of any description).

4.4.4 Interface to Satellite Data Handling SS-728/CREATED/R

Control and monitoring interfaces to the Spacecraft shall be via dedicated data interfaces which shall be implemented either as: �� RS422/UART interfaces, �� dedicated 16 bit serial telemetry and/or command interfaces or �� Analog interfaces.

SS-713/CREATED/T,R For digital and analog interfaces the electrical interface and implementation shall comply with the requirements defined in AD-17.

4.4.5 Test Equipment SS-1645/CREATED/R

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

SS-1646/CREATED/T,R The Sun Sensor shall provide an interface to enable stimulation of the Sun Sensor electronics to support closed loop testing at both subsystem and spacecraft level.

SS-1647/CREATED/R It shall be possible to operate the electronics in isolation from the Sun Sensor head and connect the electronics to the EGSE.

SS-1648/CREATED/R The blanking caps for the stimulation interface connector shall be removable.

SS-1649/CREATED/R The Sun Sensor shall meet all of the requirements specified herein with a test harness, 5m in length, connected to the Sun Sensor test connector.

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This harness will be connected to the spacecraft skin connector.

SS-1651/CREATED/T,R The presence of the stimulation interface when no stimulation is applied shall not affect the performance of the Sun Sensor.

SS-1652/CREATED/T,R At spacecraft level, the test harness cited in requirement SS-1649 will be connected to the Sun Sensor electronics stimulation interface and routed to the spacecraft skin connector. This harness, which may be up to 5m (TBC) long, may be left in situ for flight and therefore the Sun Sensor shall meet the requirements of this specification with this harness in situ.

SS-1653/CREATED/R Requirements for termination of the in situ test harness shall be defined by the supplier.

SS-1654/CREATED/T,R The Sun Sensor stimulation interface circuits shall be compatible with a test harness of 30m, length between the test equipment and the skin connector.

SS-1655/CREATED/T,A,R The stimulation signal shall be independent of the sensor signal so that no compensation will be required for ground test.

SS-1656/CREATED/I,R The Sun Sensor EGSE shall be capable of stimulating all units simultaneously.

SS-1658/CREATED/R The Sun Sensor EGSE shall provide the capability to stimulate the Sun Sensor electronics with simulated Sun Sensor optical element outputs (the actual optical element will only be used for sign verification purposes).

SS-1659/CREATED/R The Sun Sensor EGSE shall perform the following tasks: (a) Receive a quaternion that defines the three axis attitude of the Sun Sensor (and spacecraft body rates, expressed in the Sun Sensor Measurement Reference Frame, if required) from a simulation of the spacecraft hosted on an external computer (b) Generate a high fidelity image consistent with that which is generated by the optical element (as sent to the electronics) and which is commensurate with the attitude cited above in point a) (i.e. simulate the continuous integration process of the detector, for example by providing discrete summations of detector pixel data calculated from each simulation model output). (c) Transmit to the Sun sensor electronics element the image generated in point b) above.

SS-1660/CREATED/T,A,R The Sun Sensor EGSE representation of the Sun Sensor optical element output shall provide full modelling of all effects influencing Sun Sensor performance to sufficient accuracy in the context of the requirements to be met in this specification.

SS-1661/CREATED/R The Sun Sensor EGSE shall represent the Sun Sensor optical element performance from beginning to end of life.

SS-1662/CREATED/R The Sun Sensor EGSE output rate shall be consistent with the data output rate from the real Sun Sensor optical element.

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SS-1663/CREATED/R The Sun Sensor EGSE shall accept input as cited in point (a) of SS-1659 at a frequency of up to 40 Hz.

SS-1664/CREATED/R The Sun Sensor EGSE shall be mechanically and electrically independent of the Sun Sensor.

SS-1665/CREATED/R The Sun Sensor EGSE shall have an Ethernet interface for the purposes of communicating all data with the Core EGSE (CCS).

SS-1666/CREATED/R It shall be possible to configure (i.e. start, stop, pause, initialise etc) the Sun Sensor EGSE remotely via an Ethernet interface.

SS-1667/CREATED/R The Sun Sensor supplier shall provide the optical ground support equipment (OGSE) necessary for the optical stimulation of the sensor optical element for open loop AOCS testing and output sign verification purposes.

SS-1668/CREATED/R The Sun Sensor shall provide a mechanical interface to enable mounting of a static optical stimulator on the unit. This stimulator will be used for output sign verification to support open loop subsystem testing.

SS-1669/CREATED/R AD-22 EGSE Overall Requirements Specification shall be applicable to the Sun sensor EGSE requirements presented in this section.

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5. GENERAL DESIGN AND INTERFACE REQUIREMENTS

5.1 General SS-1493/CREATED/A,R

The sun sensor unit shall be designed to withstand the environmental requirements specified in AD-17. See details in GDIR Applicability Matrix Section 9.

SS-1494/CREATED/T,R The sun sensor unit shall comply to the general design requirement of AD-17. See details in GDIR Applicability Matrix Section 9.

5.2 Mechanical SS-1496/CREATED/T,R

The sun sensor unit shall comply to the mechanical design requirements of AD-17. See details in GDIR Applicability Matrix Section 9.

5.3 Thermal SS-1498/CREATED/T,R

The sun sensor unit shall comply to the Thermal design requirements of AD-17. See details in GDIR Applicability Matrix Section 9.

5.4 Electrical SS-1500/CREATED/T,R

The sun sensor unit shall comply to the Electrical design requirements of AD-17. See details in GDIR Applicability Matrix Section 9.

SS-1503/CREATED/R Tight control over DC and AC magnetic and electric fields at the experiments is essential for the successful achievement of the mission objectives. Critical frequencies span the range .01 milliHz to 10 kHz. Rigorous, documented application of good design practices shall be employed to minimize unit-generated fields at the experiments including careful frequency planning and design analysis to eradicate the generation of spurious frequencies in the bands of interest. Fields, field gradients and fluctuation of fields over time are all important parameters. It is important that frequencies not required for system level use are not allowed to radiate or conduct from the sun sensor to avoid the risk of beat frequencies being generated with other signals. For magnetic fields good design practices include employing minimum currents and loop areas on circuit boards and in wiring, including the use of twisted pairs as appropriate. Strict avoidance of all magnetic materials is essential except where required for correct functioning of the unit. All potential applications of such materials shall be reported to prime before use. For electric field reduction, the minimization of voltages, close proximity of live and return wires and employment of good shielding practices at board level, unit level and in wiring shall all be employed.

SS-1504/CREATED/T The magnetic moment of each unit shall be measured and shall be less than 50 mAm^2 (irrespective of number of units).

SS-1505/CREATED/T Stability of magnetic field and magnetic field gradient to within 0.5%/sqrt(Hz) (TBC) must be demonstrated.

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SS-1506/CREATED/T Measurements of stability shall be made over a 1000 second period (TBC).

SS-1507/CREATED/T The above requirements shall be met in all modes of operation although the stability requirements only apply during measurement modes of the experiments.

SS-1508/CREATED/T Magnetic measurements shall be made in a appropriately compensated facility to ensure that effects due to the Earth's field are negated.

SS-1509/CREATED/T To ensure that sufficient information is available for the spacecraft magnetic model, measurements shall be made of the magnetic field at various positions relative to the test item. These may comprise a series of measurements at a fixed distance from the unit and at equal angles to cover a complete revolution around the item; alternatively measurements may be made at several distances from each face of the item, a suggested minimum set of such measurement ranges being 0.1, 0.3, 0.5 and 1 metre, although the calculation of magnetic moment could be based solely on the 1 metre measurements. The proposed method must be agreed by prime in advance to ensure that sufficient data is provided for the overall spacecraft analysis.

SS-1510/CREATED/T,A An analysis shall be performed to predict the levels of DC and AC electric and magnetic fields from the sun sensor, at a distance of 0.5m from the unit's geometric centre ( i.e. at the experiment test masses) with appropriate use of testing to identify or confirm the results. The following table (Table 5.4-1) gives specific requirements for DC and AC electric and magnetic fields from the sun sensor. Other measurement distances are acceptable providing the results can be shown to be correctable to a distance of 0.5m.

Parameter Value DC Magnetic Field Meeting the dc magnetic field requirements shall be achieved by compliance with

the magnetic moment requirement for each unit of not greater than 50 mAm^2 (irrespective of number of units) which shall be measured as detailed above.

DC Magnetic Field Gradient

Meeting the dc magnetic field gradient requirements shall be achieved by compliance with the magnetic moment requirement for each unit of not greater than than 50 mAm^2 (irrespective of number of units), which shall be measured as detailed above.

AC Magnetic Field For frequencies below 10 kHz the magnitude of a high frequency magnetic field shall be less than 100 nT at 0.5 metres from the field generator This is in addition to the field stability requirement detailed above.

AC Magnetic Field Gradient

For frequencies below 10 kHz the magnitude of a high frequency magnetic field gradient shall be less than 675 nT/m at 0.5 metres from the field generator This is in addition to the field gradient stability requirement detailed above.

Table 5.4-1: Magnetic Fields

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The magnetic moment requirements per unit cannot be relaxed even if the number of units is less than the maximum of 3.

5.5 Identification & Marking SS-1556/CREATED/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-14 section 3.14.

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6. VERIFICATION REQUIREMENTS SS-1558/CREATED/T

Equipment verification shall be performed in accordance with the detailed requirements contained within the specification and AD-14, AD-15 and AD-17.

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7. PRODUCT ASSURANCE REQUIREMENTS SS-1560/CREATED/R

The sun sensor shall be designed, manufactured and tested in accordance with the PA requirements specified in AD-14 and AD-15.

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8. ACRONYMS Acronyms are defined in [AD-21].

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9. GDIR APPLICABILITY MATRIX

Req No. Reference Applicability Verif. Method

3 General Design and interface Requirements 3.1 General Design Requirements 3.1.1 Lifetime SS-747 GDI-31:

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

SS-748 GDI-32: The Unit shall meet the requirements of this speci ...

Y A,R

SS-749 GDI-33: The in-orbit lifetime of the satellite is defined ...

Y R

SS-750 GDI-34: The unit shall be designed with positive margins o ...

Y A,R

SS-751 GDI-35: Maintenance during storage shall be as limited as ...

Y R

3.1.2 Design Safety SS-753 GDI-37:

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

SS-754 GDI-38: General safety requirements for units are as follo ...

Y A

3.1.3 Venting SS-756 GDI-41:

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

SS-757 GDI-42: For all relevant thermal hardware, explicitly MLI, ...

Y R

SS-758 GDI-43: Unless a cavity is hermetically sealed adequate me ...

Y R

SS-759 GDI-44: Structural members (honeycomb panels, in particula ...

Y T,A

3.1.4 Interchangeability SS-761 GDI-46:

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

3.1.5 Identification & Marking SS-763 GDI-50:

For the particular case of connector identificatio ... Y I

3.1.6 Accessibility/Maintainability SS-765 GDI-52:

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

SS-766 GDI-53: The equipment shall be designed to require a minim ...

Y R

SS-767 GDI-54: No field maintenance, servicing or adjustment shal ...

Y R

3.1.7 Transportation, Handling and Storage 3.1.7.1 Thermally Conductive Materials SS-770 GDI-70:

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

3.1.7.3 Seals SS-772 GDI-75:

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

SS-773 GDI-76: Any seals requiring periodic replacement during gr ...

Y R

3.1.7.4 Lubricants and Sealants SS-775 GDI-78:

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

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3.1.7.5 Screw Locking SS-777 GDI-80:

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

3.2 Mechanical Design and Interface Requirements SS-779 GDI-82:

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

SS-780 GDI-83: Units shall be compatible with mechanical testing. ...

Y R

SS-781 GDI-84: Following testing the unit shall be inspected to c ...

Y I

SS-782 GDI-87: No unit shall generate microvibration loads at its ...

Y A,R

SS-783 GDI-2058: This Requirement has been Deleted. ...

Y A,R

3.2.1 Structural Design 3.2.1.1 General Requirements SS-786 GDI-91:

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

SS-787 GDI-92: The unit shall be designed to withstand the enviro ...

Y A,R

SS-788 GDI-93: For sine and random vibrations, the mechanical siz ...

Y A

SS-789 GDI-94: Wherever practical a fail safe design based on red ...

Y A

SS-790 GDI-95: In cases where a failsafe design cannot be impleme ...

Y A

SS-791 GDI-2045: All potential fracture critical items shall be sub ...

Y A

3.2.1.2 Mass properties SS-793 GDI-98:

All mass estimations shall be accompanied by the d ... Y T

SS-794 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 SS-796 GDI-102:

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

SS-797 GDI-104: The unit centre of gravity shall be determined wit ...

Y T,A

SS-798 GDI-105: The unit moment of inertia shall be determined wit ...

Y A

3.2.1.4 Stiffness requirement SS-800 GDI-113:

Unless otherwise specified, units shall have their ... Y T,A

SS-801 GDI-114: The stiffness requirements shall be demonstrated t ...

Y T,A

3.2.1.5 Strength Requirements 3.2.1.5.1 Definitions and General Requirements SS-804 GDI-117:

The design load factor philosophy of the LISA PF s ... Y A

SS-805 GDI-2077: LPF mechanical testing shall take into account an ...

Y T

SS-806 GDI-2076: LPF mechanical testing shall take into account a Q ...

Y T,A

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SS-807 GDI-2057: An additional Protoflight Factor of Safety, FOSPF ...

Y T,A

SS-808 GDI-129: The units shall be designed with positive margins ...

Y A

SS-809 GDI-130: The design loads for the structure elements are to ...

Y A

SS-810 GDI-131: The internal loads (thermo elastic, pre-stressed m ...

Y A

SS-811 GDI-132: For the computation of the design loads the maximu ...

Y A

3.2.1.5.2 Margin Of Safety & Safety Factors SS-813 GDI-2121:

For all Lisa-Pathfinder elements the design factor ... Y A

SS-814 GDI-2120: Where design loads are generated using FE analyses ...

Y A

SS-815 GDI-136: The LPF hardware shall be able to withstand, witho ...

Y A,R

SS-816 GDI-137: All mechanical elements shall demonstrate positive ...

Y T,R

SS-817 GDI-147: The margins of safety for all elements of the unit ...

Y A

SS-818 GDI-148: All bolts shall be sized to prevent sliding under ...

Y A

SS-819 GDI-149: Wherever applicable, rules for general design of b ...

Y R

SS-820 GDI-150: In addition, in case of combined loads due to ther ...

Y A

SS-821 GDI-153: Method for evaluation of dimensioning loads/stress ...

Y A

3.2.2 Design Requirements 3.2.2.1 Attachment Requirements SS-824 GDI-160:

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

SS-825 GDI-161: The attachment points shall provide a controlled s ...

Y I,R

SS-826 GDI-162: The interface plane flatness of a unit shall be be ...

Y I

SS-827 GDI-163: The mechanical mounting interface shall be consist ...

Y R

SS-828 GDI-164: The unit bolts type and number shall be defined to ...

Y R

SS-829 GDI-165: Unless otherwise specified all units shall be thro ...

Y I,R

SS-830 GDI-2132: To minimise CoG uncertainty of the unit when mount ...

Y I,R

SS-831 GDI-167: Thermally dissipative units shall have proper prov ...

Y I,R

SS-832 GDI-168: Unless special conditions override, the thickness ...

Y I,R

SS-833 GDI-169: For the unit mounting, provision shall be made for ...

Y I,R

SS-834 GDI-2123: Unit Lug/Hole Design Requirements: Unit mounting h ...

Y I,R

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SS-835 GDI-170: Sufficient clearance shall be allowed between mech ...

Y I,R

SS-836 GDI-171: Fasteners shall be verified similarly to other str ...

Y A

SS-837 GDI-173: Fasteners shall be procured and tested according t ...

Y I

SS-838 GDI-174: The Flight equipment shall be able to survive:- - ...

Y A

SS-839 GDI-176: Units requiring alignment with an accuracy better ...

Y R

SS-840 GDI-177: Optical references are required to withstand all t ...

Y R

SS-841 GDI-178: Location of optical references for units shall be ...

Y R

SS-842 GDI-179: The alignment errors shall be included in pointing ...

Y R

SS-843 GDI-180: Units which require alignment accuracy of ±0.25° o ...

Y R

3.2.3 Mechanical / Optical Interface Control Documents SS-845 GDI-183:

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

SS-846 GDI-184: Interfaces will be subjected to a formal inspectio ...

Y T,I

SS-847 GDI-185: The issues of ICDs have to be released as defined ...

Y A

SS-848 GDI-186: One of the attachment holes on a unit shall be spe ...

Y R

SS-849 GDI-187: The unit reference frame shall have its origin at ...

Y R

SS-850 GDI-188: The unit alignment reference frame shall have its ...

Y R

SS-851 GDI-190: The dimensioning of the attachment hole pattern sh ...

Y A

SS-852 GDI-191: Interface Control Drawings shall be provided to th ...

Y R

3.2.4 Mechanical Mathematical Model Requirements SS-853 GDI-197:

Finite elements models shall be provided for all i ... Y A

3.2.4.1 Software/Electronic Files Delivery SS-1584 GDI-200:

The model shall be prepared using NASTRAN Software ... Y R

SS-1585 GDI-201: Finite elements models shall be provided for all u ...

Y R

SS-1586 GDI-202: For the FEM delivery, the following list of inform ...

Y R

3.2.4.2 Units SS-1588 GDI-204:

S.I. units are to be used: · Newton (N) for force ...

Y R

3.2.4.3 Coordinate system SS-1590 GDI-206:

The FEM shall use the Units/assembly Reference Fra ... Y R

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3.2.4.4 Model Identity/Comment SS-1592 GDI-208:

The model name, issue and date must be included at ... Y R

SS-1593 GDI-209: The model description shall refer to a configured ...

Y R

SS-1594 GDI-210: The following comment cards must be included in th ...

Y R

3.2.4.5 Model Size and Identification Numbering SS-1596 GDI-212:

Numbering of BULK data cards: Each Nastran BULK ca ...

Y R

SS-1597 GDI-213: Excluded BULK data cards: All data cards used to d ...

Y R

SS-1598 GDI-214: The authorised NASTRAN elements are the following: ...

Y R

SS-1599 GDI-215: The use of MSG-MESH data cards is prohibited. A pu ...

Y R

SS-1600 GDI-216: Structural and equipment masses: For the structura ...

Y R

SS-1601 GDI-217: When necessary, equipments may be represented by C ...

Y R

3.2.4.6 FEM Checks 3.2.4.6.1 Mass Distribution Check SS-1604 GDI-221:

The outputs of the NASTRAN “Grid Point Weight Gene ... Y A

3.2.4.6.2 Strain Energy and Max Ratio Check SS-1606 GDI-223:

Strain energy and stiffness maxratio are requested ... Y A

3.2.4.6.3 Conditioning Checking SS-1608 GDI-225:

The purpose of the conditioning check is to identi ... Y A

3.2.4.6.4 Constraint Check SS-1610 GDI-227:

The purpose of the constraint check is to verify t ... Y R

3.2.4.6.5 "Free-Free" Check. SS-1612 GDI-229:

The purpose of the "Free-Free" check is to verify ... Y R

3.2.4.6.6 Static Load Check SS-1614 GDI-231:

The purpose of the static load check is to confirm ... Y R

3.2.4.6.7 "Zero" Stress Thermo-elastic Check SS-1616 GDI-233:

The purpose of the "Zero" stress check is to verif ... Y R

3.2.4.7 FEM correlation. SS-1618 GDI-235:

Full finite element models shall be correlated wit ... Y T,A

SS-1619 GDI-2102: For modes with effective masses > 10% of the total ...

Y T,A

SS-1620 GDI-2101: Damping shall take measured values as input for th ...

Y R

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SS-1621 GDI-2100: The cross-orthogonality checks shall comply with; ...

Y T,A

SS-1622 GDI-2099: For other significant modes, · MAC shall be > 0.85 ...

Y T,A

SS-1623 GDI-2098: For modes with effective masses >10%of the total m ...

Y T,A

SS-1624 GDI-2097: For fundamental modes, · MAC shall be > 0.95 · Eig ...

Y T,A

SS-1625 GDI-2096: The difference between the Centre of Gravity posit ...

Y T,A

SS-1626 GDI-2095: The mass difference between the measured and FEM f ...

Y T,A

3.2.5 Gravitational Mathematical Model Requirements SS-855 GDI-2043:

For gravitational modelling purposes, the mass dis ... Y A,R

3.3 Thermal Design and Interface Requirements 3.3.1 Definition of Temperatures and Terms 3.3.1.1 Radiatively Controlled Unit SS-859 GDI-239:

In the frame of LISA Pathfinder, all units with th ... Y R

3.3.1.3 Isothermal Unit SS-863 GDI-243:

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

SS-864 GDI-244: For radiative units the temperature difference bet ...

Y R

SS-866 GDI-246: For non-isothermal units a reference temperature s ...

Y R

3.3.1.4 Temperature Reference Point (TRP) SS-868 GDI-248:

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

3.3.2 Thermal Interface Requirements 3.3.2.2 Radiative Interface SS-1628 GDI-258:

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

3.3.2.3 Internal Temperature Monitoring SS-876 GDI-260:

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

SS-877 GDI-261: The location, type and electrical interface of all ...

Y R

3.3.3 Thermal Design Requirements SS-879 GDI-263:

The units shall be designed such that all internal ... Y A

SS-880 GDI-264: Hot spots on the external surface of the unit are ...

Y A,R

SS-881 GDI-2079: Average dissipation of the unit operating with sta ...

Y A,R

3.3.4 Thermal Control SS-883 GDI-267:

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

3.3.5 Thermal Interface Control Documents

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SS-885 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 SS-888 GDI-2091:

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

SS-889 GDI-272: The Thermal mathematical model shall be provided f ...

Y A

SS-890 GDI-273: Units: All units used in thermal models (geometric ...

Y A

3.3.6.2 Thermal Model Correlation SS-892 GDI-275:

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

3.3.6.3 Reduced Thermal Model SS-894 GDI-277:

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

SS-895 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 SS-899 GDI-282:

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

3.4.1.2 Materials SS-901 GDI-284:

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

SS-902 GDI-285: The use of stain sensitive glasses shall be avoide ...

Y R

SS-903 GDI-286: The use of optical cements shall be avoided as far ...

Y R

3.4.1.3 Coatings SS-905 GDI-289:

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

SS-906 GDI-290: Thermo-optical properties of the coatings shall be ...

Y R

SS-907 GDI-292: High efficiency anti-reflective coatings shall be ...

Y R

SS-908 GDI-293: Sensitivity of coatings to polarisation effects as ...

Y T,R

3.4.1.4 Performances SS-910 GDI-295:

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

SS-911 GDI-296: Alignment and interface with regard to other optic ...

Y T

3.4.2 Optical Interface Requirements SS-913 GDI-298:

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

SS-914 GDI-299: The free mechanical aperture of optical surfaces s ...

Y R

SS-915 GDI-300: In addition to specific requirements mentioned in ...

Y R

3.4.3 Optical Mathematical Model Requirements

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SS-917 GDI-302: The unit supplier shall use an optical model for n ...

Y A

SS-918 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 SS-921 GDI-308:

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

SS-922 GDI-309: Beginning-Of-Life criteria shall be derived by the ...

Y R

SS-923 GDI-2024: All PROM's shall be accessible and removeable afte ...

Y R

3.5.2 Power Interface Requirements (LC & FC) SS-925 GDI-2046:

The design of all essential loads (i.e those suppl ... Y A,R

3.5.2.1 Sunlight Regulated Power Requirements SS-927 GDI-338:

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

SS-928 GDI-2104: The spacecraft sunlight regulated bus shall have a ...

Y T,R

SS-929 GDI-2103: For load changes of up to 50% of the nominal load ...

Y T,R

SS-930 GDI-2133: The bus voltage shall remain within 5% of its nomi ...

Y T,R

SS-931 GDI-339: If undervoltage protection is implemented by the l ...

Y T

SS-932 GDI-340: In case of an inductive load, when considering the ...

Y T,A

SS-933 GDI-341: The load shall not be irreversibly degraded for an ...

Y R

SS-934 GDI-342: No fuse protection shall be implemented. ...

Y R

SS-935 GDI-343: Primary current protection shall not be implemente ...

Y R

SS-936 GDI-344: The contractor shall design the load side of the L ...

Y T,R

SS-937 GDI-346: All power converters shall be designed to allow op ...

Y T

SS-938 GDI-347: The free-running frequency shall be limited to ±10 ...

Y T

SS-939 GDI-348: The as designed free-running frequency and frequen ...

Y T

SS-940 GDI-349: Units connected to LCL's or FCL's shall be designe ...

Y A

SS-941 GDI-1273: At the point of regulation, the impedance of the v ...

Y T,R

SS-942 GDI-352: The contractor shall design his side of the Regula ...

Y T,R

SS-943 GDI-354: Following switch-ON, and during input filter charg ...

Y T,R

3.5.2.2 Power Consumption Requirements SS-945 GDI-361:

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

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SS-946 GDI-362: For each power interface circuit, the following co ...

Y T,A

SS-947 GDI-363: A power consumption test shall be required at temp ...

Y T,R

3.5.2.3 Tolerance to Power Bus Failures SS-949 GDI-365:

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

3.5.2.4 Initial Electrical Status SS-951 GDI-367:

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

3.5.2.5 Special Case: Secondary Power Supplied Units SS-953 GDI-370:

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

SS-954 GDI-371: The source unit shall be protected against short-c ...

Y T

SS-955 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 SS-958 GDI-378:

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

SS-959 GDI-379: All data and signal interface drivers shall surviv ...

Y T,A

SS-960 GDI-380: The unit shall tolerate active signal I/Fs when un ...

Y T,A

SS-961 GDI-381: In case the electrical architecture does foresee c ...

Y T,R

SS-962 GDI-382: In case no load is specified, the characteristics ...

Y R

3.5.3.2 Harness Capacitance SS-964 GDI-391:

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

3.5.4 Connectors General Design Requirements 3.5.4.1 Harness SS-967 GDI-395:

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

SS-968 GDI-396: All cable bundles shall be routed as close as poss ...

Y I,R

SS-969 GDI-397: In wiring through connectors all leads shall be ke ...

Y I,R

SS-970 GDI-398: The DC resistance between the single cable shield ...

Y T

SS-971 GDI-399: The structure termination of shields shall be made ...

Y I,R

3.5.4.2 Connector Types SS-973 GDI-401:

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

SS-974 GDI-402: All flight connectors shall be designed to withsta ...

Y I,R

SS-1629 GDI-2158: Individual mate/demates shall be recorded in a mat ...

Y R

SS-1630 GDI-2157: The number of times flight connectors are mated / ...

Y R

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SS-1631 GDI-2156: If by prior agreement with ASU the number of mates ...

Y I,R

SS-975 GDI-403: Different connector classes shall be implemented i ...

Y R

3.5.4.3 Connector Characteristics SS-977 GDI-405:

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

SS-978 GDI-406: Connectors shall not be a source of single point f ...

Y R

SS-979 GDI-407: Equipment or structure-mounted connectors shall be ...

Y R

SS-980 GDI-408: Male and female connectors shall be mechanically l ...

Y R

SS-981 GDI-409: Active lines together with their return shall be o ...

Y I

SS-982 GDI-410: Connectors shall be made of Non magnetic material ...

Y R

SS-983 GDI-411: For any unit connector which contains a number of ...

Y T,R

SS-984 GDI-412: Nominal and redundant lines shall have separated c ...

Y R

3.5.4.4 Connector Mounting SS-986 GDI-414:

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

SS-987 GDI-415: Connectors shall be arranged in such a way that th ...

Y R

SS-988 GDI-416: Mechanical methods in conjunction with identificat ...

Y I,R

SS-989 GDI-417: Connector savers shall be utilized on all flight s ...

Y R

SS-990 GDI-418: The connection shield ground pin to case shall be ...

Y R

3.5.4.5 Test Connectors SS-992 GDI-420:

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

SS-993 GDI-421: Test connectors shall be protected by EMC metal co ...

Y I,R

SS-994 GDI-422: The metallic protection cover shall be capable of ...

Y R

3.5.5 Standard Interfaces 3.5.5.1 MIL-STD-1553 Bus Interfaces (MIL) 3.5.5.2 Standard Balanced Digital link (SBDL) SS-1008 GDI-438:

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

SS-1009 GDI-1201: The contractor shall design his side of the Standa ...

Y T,R

3.5.5.3 UART Serial Link (USL) SS-1011 GDI-450:

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

SS-1012 GDI-451: The UART RS-422 Serial Link Interface shall be imp ...

Y R

SS-1013 GDI-452: The contractor shall design his part of the UART R ...

Y R

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SS-1014 GDI-453: Figure GDI-456 shows an example for data transmiss ...

Y R

SS-1015 GDI-1274: The OBC shall be able to send commands on the Tran ...

Y T

SS-1016 GDI-1275: No data repetition mechanism in both directions sh ...

Y T

SS-1017 GDI-1276: Command messsages sent by the OBC to the user and ...

Y T

3.5.5.4 Timing Pulses 3.5.5.4.1 Synchronisation or Datation Pulses (PPS) 3.5.5.5 Housekeeping Analog Acquisitions SS-1633 GDI-471:

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

3.5.5.5.1 Analogue Telemetry Aquisition (AN1) SS-1635 GDI-1205:

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


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


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

3.5.5.6 Temperature Acquisitions (ANY, ANP, ANF, ANT) SS-1022 GDI-482:

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

SS-1023 GDI-483: The temperature aquisition interface circuitry, as ...

Y R

3.5.5.6.1 Thermistor Type1: YSI-44907/-44908 (ANY) SS-1025 GDI-1215:

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

3.5.6 Electrical Interface Control Document SS-1027 GDI-558:

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

3.5.7 EMC Requirements 3.5.7.1 Bonding SS-1030 GDI-562:

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

SS-1031 GDI-563: Metallic parts of each electrical equipment chassi ...

Y T

SS-1032 GDI-564: Joint faces shall be flat and clean before assembl ...

Y I,R

SS-1033 GDI-566: Each electrical equipment chassis (case) shall be ...

Y T,R

SS-1034 GDI-567: Metallic receptacles of connectors shall be electr ...

Y T

3.5.7.1.1 Ground Reference Rail SS-1036 GDI-569:

Electrical bonding throughout CFRP structure shall ... Y R

SS-1037 GDI-570: The resistance between any adjacent parts of the G ...

Y T,R

SS-1038 GDI-571: The resistance between any two points of the GRR s ...

Y T,R

3.5.7.1.2 Cable and Harness Shields

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SS-1040 GDI-573: Where shielded wires are used, the shield shall be ...

Y R

SS-1041 GDI-574: The maximum unshielded length of any shielded wire ...

Y R

SS-1042 GDI-575: Daisy chaining of shield terminations shall be avo ...

Y R

SS-1043 GDI-576: Shields shall not be used as an intentional curren ...

Y R

3.5.7.1.4 Mechanical Parts SS-1045 GDI-581:

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

SS-1046 GDI-582: Mechanical Parts used for electromagnetic shieldin ...

Y T,R

3.5.7.2 Grounding and Isolation 3.5.7.2.1 General SS-1049 GDI-585:

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

SS-1050 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 SS-1052 GDI-588:

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

SS-1053 GDI-589: Openings for drainage, ventilation, etc... shall n ...

Y I

SS-1054 GDI-590: All units shall have a M4 bonding stud ...

Y I

SS-1055 GDI-591: The design of this bonding stud shall allow the co ...

Y I

3.5.7.2.3 Insulating materials SS-1057 GDI-593:

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

SS-1058 GDI-595: MLI: MLI shall carry at least 1 conductive layer ...

Y I

SS-1059 GDI-596: MLI: The grounding points shall be in a minimum of ...

Y I,R

SS-1060 GDI-597: MLI: The resistance between each bonding point an ...

Y T

SS-1061 GDI-598: MLI: The resistance between each bonding point an ...

Y T

SS-1062 GDI-599: PAINTS: Refer to Section GDI-592 above. ...

Y R

SS-1063 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 SS-1066 GDI-605:

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

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SS-1067 GDI-606: Isolation: All units (except PCDU) shall maintain ...

Y T,R

3.5.7.3.2 Secondary Power Lines SS-1069 GDI-609:

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

SS-1070 GDI-1988: Equipment with its own dedicated DC - DC converter ...

Y T

SS-1071 GDI-610: Isolation: prior to connection of the unit interna ...

Y T,R

SS-1072 GDI-2106: After grounding, the impedance between the unit se ...

Y T,R

SS-1073 GDI-611: Secondaries distributed between units (1 supplier; ...

Y R

SS-1074 GDI-612: Secondaries distributed between units (1 supplier; ...

Y R

SS-1075 GDI-614: Grounding diagram including zero volts interconnec ...

Y I

SS-1076 GDI-615: The symbols in Figure GDI-2107 below shall be used ...

Y R

3.5.7.3.3 Signal Interfaces SS-1078 GDI-617:

Signal circuits interfacing between Satellite equi ... Y R

SS-1079 GDI-618: Where single-ended signal transmitters are used, i ...

Y R

SS-1080 GDI-619: The use of common signal return paths is only perm ...

Y R

3.5.7.3.4 EGSE Grounding and Isolation SS-1082 GDI-621:

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

3.5.7.4 Magnetic Moment SS-1084 GDI-1997:

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

SS-1085 GDI-1998: All equipments shall provide magnetic dipole momen ...

Y T

3.6 Operations Design and Interface Requirements 3.6.1 Bit / Byte Numbering Convention SS-1088 GDI-632:

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

SS-1089 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

SS-1092 GDI-638: Mode/State transitions: Transitions from one mode/ ...

Y R

SS-1093 GDI-639: The unit supplier shall identify appropriate modes ...

Y R

SS-1094 GDI-640: At all times, equipment and units shall be in a cl ...

Y T,R

SS-1095 GDI-641: In addition, modes and the mode transitions manage ...

Y T,R

SS-1096 GDI-642: The unit supplier shall identify all internal and ...

Y R

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SS-1097 GDI-643: The unit supplier shall identify all transition ti ...

Y R

SS-1098 GDI-644: Mode/State transitions with duration longer than 1 ...

Y R

SS-1099 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 SS-1102 GDI-648:

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

SS-1103 GDI-649: In operating states of the unit, it shall be possi ...

Y T

SS-1104 GDI-650: In addition, in non-operating states of the unit, ...

Y T

SS-1105 GDI-651: Individual switching of switchable elements (e.g. ...

Y T

SS-1106 GDI-652: The on-board reception, processing and execution o ...

Y T,R

SS-1107 GDI-653: The function of a command shall not change through ...

Y T,R

SS-1108 GDI-654: A single command may be used to initialise a chang ...

Y T,R

SS-1109 GDI-655: Commands with variable bit-fields meaning shall no ...

Y R

SS-1110 GDI-656: Nominal and the redundant functions or equipments ...

Y T

SS-1111 GDI-657: The unit design shall avoid any conflict between a ...

Y T

3.6.2.3 Observability 3.6.2.3.1 General SS-1114 GDI-660:

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

SS-1115 GDI-661: The unit shall provide in its housekeeping telemet ...

Y T,R

SS-1116 GDI-662: The unit shall provide the necessary instrumentati ...

Y T,R

SS-1117 GDI-663: Telemetry measurement sensors shall be designed su ...

Y T

SS-1118 GDI-664: It shall be possible to determine the status of th ...

Y T

SS-1119 GDI-665: Essential (high-priority) telemetry data enabling ...

Y T,R

SS-1120 GDI-666: Telemetry shall always be provided to identify una ...

Y T,R

SS-1121 GDI-667: Status information in telemetry shall be provided ...

Y T,R

SS-1122 GDI-668: Any TM processing required at a higher operational ...

Y R

SS-1123 GDI-669: Telemetry shall always be available to determine t ...

Y R

SS-1124 GDI-670: When a key parameter is derived on-board from seve ...

Y T,R

3.6.2.3.2 Telemetry Acquisition

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SS-1126 GDI-672: The TM acquisition process by the data bus shall n ...

Y T

SS-1127 GDI-673: The unit design shall avoid any conflict between t ...

Y T

SS-1128 GDI-674: TM acquisitions with conditional meaning shall not ...

Y R

SS-1129 GDI-675: The value of a telemetry parameter shall be transm ...

Y R

SS-1130 GDI-676: Analog TM Acquisition: Analog TM acquisitions sha ...

Y T,R

SS-1131 GDI-677: Acquisition of safety critical analog parameters o ...

Y R

SS-1132 GDI-678: The values of currents or voltages readings shall ...

Y R

SS-1133 GDI-679: The calibration curve of an analog parameter shall ...

Y R

3.6.2.3.3 Observability of Hardware Configuration SS-1135 GDI-681:

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

SS-1136 GDI-682: In case a unit includes several elementary functio ...

Y R

SS-1137 GDI-683: The configuration of any on-board device and any s ...

Y T,R

SS-1138 GDI-684: Any configuration command register shall be observ ...

Y R

SS-1139 GDI-685: The acquisition of the unit configuration/state sh ...

Y R

SS-1140 GDI-686: The acquisition of an ON/OFF status for a relay sh ...

Y R

SS-1141 GDI-687: If the unit controls the redundancy configuration ...

Y T

SS-1142 GDI-688: Nominal and redundant functions shall be observabl ...

Y R

3.6.2.3.4 Observability of Commands SS-1144 GDI-690:

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

SS-1145 GDI-691: Acknowledgement of commands shall be direct (i.e. ...

Y T,R

SS-1146 GDI-692: The association between command acknowledgement ac ...

Y I

SS-1147 GDI-693: Successful execution of a command to the unit shal ...

Y T,R

SS-1148 GDI-694: Failures in the acceptance and /or the execution o ...

Y T,R

3.6.2.3.5 Converters Observability SS-1150 GDI-696:

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

3.6.2.4 Safety Critical and Hazardous Functions SS-1152 GDI-700:

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

SS-1153 GDI-701: The execution of any unit command or command seque ...

Y A

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SS-1154 GDI-702: Commanding of critical commands shall be implement ...

Y A,R

SS-1155 GDI-703: The status of inhibition of safety critical functi ...

Y T

SS-1156 GDI-704: Units shall provide an unambiguous health status o ...

Y T

3.6.2.5 Handling of Memories SS-1158 GDI-706:

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

SS-1159 GDI-707: Any part of installed RAM’s shall be overwriteable ...

Y T

SS-1160 GDI-708: Any part of installed ROM’s shall be readable by m ...

Y T

SS-1161 GDI-709: For failure investigation, it shall be possible to ...

Y T

3.6.2.6 Autonomy SS-1163 GDI-711:

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

SS-1164 GDI-712: All parameters used for autonomous operations and ...

Y T

3.6.2.7 Automatic Functions SS-1166 GDI-714:

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

SS-1167 GDI-715: All actions generated by automatic on-board logic ...

Y T

SS-1168 GDI-716: The automatic function design shall be such that n ...

Y A,R

SS-1169 GDI-717: Telemetry shall be associated to all automatic fun ...

Y T

SS-1170 GDI-718: For all the automatic logic using several criteria ...

Y T

SS-1171 GDI-719: The capability to change all on board logic (hardw ...

Y T,R

3.6.2.8 Time Synchronisation SS-1173 GDI-721:

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

SS-1174 GDI-722: If the unit has the function, all information on h ...

Y R

SS-1175 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 SS-1178 GDI-726:

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

SS-1179 GDI-727: Any unit shall be able to withstand (i.e. remain i ...

Y T,R

SS-1180 GDI-728: It shall be possible to repeat any command several ...

Y T,R

3.6.2.9.2 Unit Self Tests SS-1182 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

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SS-1184 GDI-733: FDIR functions shall be implemented in a hierarchi ...

Y A,R

SS-1185 GDI-734: The unit shall automatically detect any failure, w ...

Y T,R

SS-1186 GDI-735: At unit level failures shall be detectable by adeq ...

Y A

SS-1187 GDI-736: Failure detection algorithms shall report in event ...

Y A,R

SS-1188 GDI-737: Failures which require a reaction time less than 1 ...

Y T,A

SS-1189 GDI-738: Failure which requires a reaction time between 10s ...

Y A,R

SS-1190 GDI-739: Failure isolation shall be performed at switchable ...

Y T,A

SS-1191 GDI-740: Any FDIR actions on unit level shall be reported t ...

Y T,R

SS-1192 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 SS-1195 GDI-744:

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

3.6.3.2 Inputs to Operational Database SS-1197 GDI-746:

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

SS-1198 GDI-747: Data to be provided (the list is not exhaustive): ...

Y R

3.6.3.3 Operation Manual SS-1200 GDI-749:

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

SS-1201 GDI-750: The following standardization (Table GDI-751) shal ...

Y R

4 Environment Design Requirements 4.1 Atmospheric Conditions 4.1.1 Humidity SS-1205 GDI-771:

The unit shall be designed to withstand a relative ... Y R

4.1.2 Cleanliness SS-1207 GDI-773:

The cleanliness design requirements on the unit H/ ... Y R

4.1.3 Storage time SS-1209 GDI-775:

The S/C units flight H/W shall be designed to with ... Y R

4.1.4 Pressure Environment SS-1211 GDI-780:

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

4.1.5 Contamination SS-1213 GDI-782:

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

4.2 Mechanical Environment 4.2.1 Ground Operations Loads SS-1216 GDI-790:

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

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SS-1217 GDI-793: During ground transportation the equipments shall ...

Y T,A

SS-1218 GDI-795: The design of transport containers shall be such t ...

Y T,A

4.2.2 Launch and Early Orbit Phase. 4.2.2.1 Quasi static and low frequency loads SS-1221 GDI-799:

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

4.2.2.2 Dynamic Environment 4.2.2.2.1 Sinusoidal Environment SS-1224 GDI-808:

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

4.2.2.2.2 Random Environment SS-1226 GDI-812:

Units mounted on the SCM structure shall be desig ... Y T,A

4.2.2.2.3 Shock Environment SS-1228 GDI-818:

Units mounted on the SCM Structure shall be design ... Y A,R

4.2.3 In Orbit Phase 4.2.3.1 Quasi-static & Thermo-elastic Loads SS-1231 GDI-823:

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

SS-1232 GDI-2131: The unit shall be compatible with internal loads g ...

Y A

4.3 Thermal Environment 4.3.1 On-ground phase SS-1235 GDI-838:

During transportation and storage, the spacecraft ... Y R

SS-1236 GDI-2051: This requirement applies to external items only. P ...

Y A,R

SS-1237 GDI-2052: This requirement applies to external items only. M ...

Y A,R

4.4 Radiation Environment 4.4.1 Introduction SS-1240 GDI-847:

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

4.4.2 LISA-PF Radiation Environment 4.4.2.1 Galactic Cosmic Ray (GCR) and Solar Energetic

Particle Environment

SS-1243 GDI-2087: The data provided for 0.66 g/cm2 shielding shall b ...

Y R

SS-1244 GDI-1946: The integral LET spectra generated using CREME96 ( ...

Y R

SS-1245 GDI-2088: The proton flux data generated using CREME96 are s ...

Y R

4.4.2.2 Trapped Proton Environment 4.4.2.3 Solar Proton Environment 4.4.2.4 Trapped Electron Environment 4.4.3 Long Term Effect Considerations 4.4.3.1 Ionizing Dose Depth Curve SS-1249 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 SS-1252 GDI-876:

Protective shielding by the outer panels of the sa ... Y R

SS-1253 GDI-877: Any unit shall take into account the shielding pro ...

Y A,R

4.4.5 Radiation Sensitive Components SS-1255 GDI-1969:

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

SS-1256 GDI-1970: All parts shall be reviewed by the Subcontractor t ...

Y R

SS-1257 GDI-1971: The Subcontractor shall issue a Radiation Assessme ...

Y R

4.4.5.1 Total Dose SS-1259 GDI-1975:

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

4.4.5.2 Single Event Effects (SEE) SS-1261 GDI-1977:

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

SS-1262 GDI-1978: The component shall be designed to tolerate GCR, p ...

Y T,A,R

4.4.5.3 Single Event Latch-up SS-1264 GDI-1980:

Devices with a LETth for SEL less than 60 MeV-cm2/ ... Y A,R

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

SS-1266 GDI-1982: Part types shall be acceptable according to the ac ...

Y A,R

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

SS-1268 GDI-1984: For SEB and SEGR, error rate prediction techniques ...

Y A,R

4.4.5.6 Displacement Damage SS-1270 GDI-1986:

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

SS-1271 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 SS-1275 GDI-895:

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

4.5.1.2 Voltage Transients SS-1277 GDI-897:

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

SS-1278 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

SS-1281 GDI-902: Conducted narrow band current emissions (different ...

Y T

SS-1282 GDI-904: Conducted narrow band current emissions (common mo ...

Y T

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4.5.1.3.2 Conducted Emissions on Power Leads, Time Domain

SS-1284 GDI-907: Time domain conducted differential mode voltage ri ...

Y T

SS-1285 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

SS-1288 GDI-918: The maximum voltage emission levels for secondary ...

Y T

4.5.1.4.2 CE for Secondary Power Supply Units, Time Domain

SS-1290 GDI-920: The voltage ripple and spikes on secondary power s ...

Y T

4.5.2 Radiated Emissions - E field SS-1292 GDI-922:

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

4.5.3 Radiated Emissions - H field SS-1294 GDI-926:

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

4.5.4 Radiated Emissions Fluctuations - E Field SS-1296 GDI-2013:

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

4.5.5 Radiated Emissions Fluctuations - H Field SS-1298 GDI-2022:

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

4.5.6 Radiated Susceptibility - E field SS-1300 GDI-928:

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

SS-1301 GDI-929: No unit that is powered On at launch shall show an ...

Y T

4.5.7 Radiated Susceptibility - H field SS-1303 GDI-932:

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

4.5.8 Units linked by Secondary Power Lines SS-1305 GDI-934:

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

SS-1306 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

SS-1309 GDI-938: Primary power bus powered units shall not exhibit ...

Y T

4.5.9.2 Conducted Susceptibility Sine Wave - Common Mode

SS-1311 GDI-2000: The unit shall not exhibit any malfunction, degrad ...

Y T

4.5.9.3 Conducted Susceptibility - Transient SS-1313 GDI-2007:

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

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SS-1314 GDI-2009: Transient Type 1 With reference to (figure GDI-941 ...

Y T

SS-1315 GDI-2010: Transient Type 2 With reference to (figure GDI-941 ...

Y T

4.5.9.4 CE / CS on Interface signal lines SS-1317 GDI-944:

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

SS-1318 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

SS-1321 GDI-949: The conducted susceptibility specification for sec ...

Y T,R

4.5.10.2 Requirement at subsystem or system level SS-1323 GDI-951:

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

4.5.11 DC Magnetic Requirements SS-1325 GDI-954:

The use of ferro-magnetics shall be avoided for pa ... Y I,R

SS-1326 GDI-956: Steel or other magnetic materials shall be avoided ...

Y I,R

SS-1327 GDI-958: The use of relays shall be limited to the most cri ...

Y R

SS-1328 GDI-959: The permitted magnetic moment of equipments shall ...

Y R

4.5.12 ESD Susceptibility SS-1330 GDI-962:

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

5 Unit Level Environment Test Requirements 5.1 General 5.1.1 Test Definition 5.1.1.1 Qualification tests SS-1335 GDI-967:

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

5.1.1.2 Acceptance Tests SS-1337 GDI-969:

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

5.1.1.3 Functional Performance Tests SS-1339 GDI-971:

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

5.1.2 Test Facilities Requirements SS-1341 GDI-973:

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

5.1.2.1 Accuracy of Test Instrumentation SS-1343 GDI-975:

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

5.1.2.2 Tolerances of Test Parameters SS-1345 GDI-977:

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

5.1.2.3 Facility Ambient Condition

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SS-1347 GDI-981: Unless otherwise specified herein, all measurement ...

Y A,I,R

5.1.3 Test Execution SS-1349 GDI-983:

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

5.1.4 Success Criteria SS-1351 GDI-985:

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

5.2 Unit Tests 5.2.1 Mechanical Environment Tests 5.2.1.1 Vibration Test Set Up SS-1355 GDI-989:

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

SS-1356 GDI-990: At least one triaxial sensor shall be mounted on t ...

Y T

SS-1357 GDI-991: At least two axis aligned sensors shall be mounted ...

Y T

SS-1358 GDI-992: All units powered on during launch shall be powere ...

Y T

5.2.1.2 Test Fixture SS-1360 GDI-995:

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

SS-1361 GDI-996: The variation of transmissibility between test ite ...

Y T

SS-1362 GDI-997: Adequate fixture design and specimen installation ...

Y T

SS-1363 GDI-998: A pre-test of the empty fixture shall be performed ...

Y T

5.2.1.3 Frequency Search SS-1365 GDI-1000:

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

SS-1366 GDI-1002: Frequency search tests shall be conducted along ea ...

Y T

5.2.1.4 Vibration Tests Level SS-1368 GDI-1005:

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

5.2.1.5 Sine And Random Vibration Test SS-1370 GDI-1011:

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

SS-1371 GDI-1012: Prior and after sine and random vibration qualific ...

Y T

SS-1372 GDI-1013: Before applying full levels, a test at intermediat ...

Y T

SS-1373 GDI-1014: This Requirement has been Deleted. ...

Y

SS-1374 GDI-1015: The vibration facility shall include a shock free ...

Y T

5.2.1.6 Shock Tests SS-1376 GDI-1017:

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

SS-1377 GDI-1018: Prior and after shock tests a low level sine frequ ...

Y T

5.2.1.7 Static tests

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SS-1379 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 SS-1382 GDI-1024:

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

SS-1383 GDI-1025: The test arrangement shall be as shown in Figure G ...

Y R

SS-1384 GDI-1026: The unit shall be bolted to a thermally controlled ...

Y R

SS-1385 GDI-1027: On all external surfaces flight representative the ...

Y R

SS-1386 GDI-1028: The heat sink (HS) plates shall be black painted ( ...

Y R

SS-1387 GDI-1029: The conductive heat sink temperature and the chamb ...

Y R

SS-1388 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 SS-1391 GDI-1034:

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

SS-1392 GDI-1036: The TV test on unit level shall be performed as in ...

Y R

SS-1393 GDI-1037: The qualification temperatures for the different u ...

Y R

SS-1394 GDI-1038: The units shall be tested following the thermal va ...

Y T,R

5.2.2.2.2 Acceptance Thermal Vacuum SS-1396 GDI-1044:

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

SS-1397 GDI-1045: The thermal vacuum acceptance test shall be perfor ...

Y T,R

5.2.2.2.3 Protoflight Thermal Vacuum SS-1399 GDI-1049:

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

SS-1400 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 SS-1404 GDI-1057:

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

5.2.3.1.2 EMC Qualification Test SS-1406 GDI-1059:

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

5.2.3.1.3 EMC Acceptance Test SS-1408 GDI-1061:

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

5.2.3.1.4 EMC Integration Test SS-1410 GDI-1063:

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

5.2.3.1.5 Retest Criteria

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SS-1412 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 SS-1414 GDI-1067:

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

5.2.3.1.7 Test Sequence SS-1642 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 SS-1419 GDI-1072:

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

5.2.3.2.2 Capabilities SS-1421 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 SS-1424 GDI-1077:

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

5.2.3.3.2 Accuracy of the Test Measurement Equipment SS-1426 GDI-1079:

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

5.2.3.3.3 Special Requirements on the Test Equipment SS-1428 GDI-1081:

Grounding of Test Equipment: Measurement equipment ...

Y R

SS-1429 GDI-1082: Antenna Placement: For radiated emission measureme ...

Y R

SS-1430 GDI-1083: Receiver Bandwidth: The following receiver bandwid ...

Y R

SS-1431 GDI-1085: Power Adjustment: The primary power for unit level ...

Y R

5.2.3.3.4 Line Impedance Stabilisation Network (LISN): SS-1433 GDI-1087:

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

SS-1434 GDI-1090: The LISN has to be designed and provided by the co ...

Y T

SS-1435 GDI-2116: Derivation of the bus impedance shall be performae ...

Y T

5.2.3.3.5 Test Conditions SS-1437 GDI-1095:

The equipment under test shall be switched on in t ... Y R

SS-1438 GDI-1096: For emission testing the unit shall operate within ...

Y R

SS-1439 GDI-1097: For susceptibility testing the suitable operationa ...

Y R

SS-1440 GDI-1098: After testing the equipment shall be switched off ...

Y R

SS-1441 GDI-1099: Both operational modes shall provide operational c ...

Y R

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SS-1442 GDI-1100: The particular test set-up shall represent the fli ...

Y R

5.2.3.3.6 Susceptibility Testing SS-1444 GDI-2142:

The applicable pass/fail criteria for susceptibili ... Y R

SS-1445 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 SS-1448 GDI-1107:

The bonding test shall be performed with the unit ... Y R

SS-1449 GDI-1108: The bonding test shall be performed without any ha ...

Y R

5.2.3.4.2 Isolation SS-1451 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 SS-1454 GDI-1116:

UUT operation shall be selected in order to maximi ... Y R

SS-1455 GDI-1118: Ripple and transient interference tests on the pow ...

Y R

5.2.3.4.3.2 CE on Secondary Power Lines SS-1457 GDI-1123:


SS-1458 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

SS-1460 GDI-2090: The mode selection for susceptibility testing shal ...

Y T,R

5.2.3.4.5 Conducted Susceptibility on Power Lines SS-1462 GDI-1133:

The mode selection for susceptibility testing shal ... Y R

SS-1463 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

SS-1465 GDI-1140: The mode selection for susceptibility testing shal ...

Y R

SS-1466 GDI-1141: The test set-ups are shown in Figure GDI-1142 (CS0 ...

Y T

5.2.3.4.7 Radiated Emission, Electric Field SS-1468 GDI-1151:


5.2.3.4.8 Radiated Emissions, E-Field Fluctuations 5.2.3.4.9 Radiated Emission, Magnetic Field SS-1471 GDI-1155:


5.2.3.4.10 Radiated Emissions, Magnetic Field Fluctuations

5.2.3.4.11 Radiated Susceptibility, Electric Field

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SS-1474 GDI-1159: UUT operation shall be selected in order to maximi ...

Y R

5.2.3.4.12 Radiated Susceptibility, Magnetic Field SS-1476 GDI-1163:


5.2.3.4.13 Electrostatic Discharge (ESD) SS-1478 GDI-1167:


5.2.3.4.14 Magnetic Moment SS-1480 GDI-1173:

Verification by similarity may be applied to equip ... Y A,R

5.2.4 Life Test SS-1482 GDI-1185:

A life test shall be required for all the assembli ... Y T,R

5.2.5 Space Conditioning SS-1484 GDI-1187:

Space conditioning shall be performed whenever des ... Y T,R

SS-1485 GDI-1188: The contractors shall propose the corresponding te ...

Y R

SS-1486 GDI-1189: For example, but without limitation to, materials ...

Y T

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Requirement/Section Cross Reference

SS-408 ............3.5 SS-412 ............3.1.1

SS-416 ............3.1.2 SS-418 ............3.1.3 SS-419 ............3.1.3 SS-420 ............3.1.3

SS-574 ............3.7 SS-575 ............3.7 SS-576 ............3.7 SS-582 ............3.8

SS-584 ............3.7 SS-586 ............3.7 SS-587 ............3.7 SS-589 ............3.4

SS-593 ............3.3.3 SS-594 ............3.3.3 SS-602 ............3.3.1 SS-603 ............3.9.1

SS-608 ............3.5 SS-611 ............3.9.4 SS-612 ............3.9.4 SS-615 ............3.9.5

SS-620 ............3.10 SS-621 ............3.10 SS-624 ............3.10 SS-678 ............4.1.1

SS-684 ............4.2.2 SS-690 ............4.4.1 SS-692 ............4.4.2 SS-696 ............4.4.3

SS-728 ............4.4.4 SS-730 ............3.8 SS-738 ............4.3 SS-740 ............4.3

SS-742 ............4.3 SS-744 ............4.2.3 SS-1488...........4.2.2 SS-1489...........3.7

SS-1493...........5.1 SS-1494...........5.1 SS-1496...........5.2 SS-1498...........5.3

SS-1503...........5.4 SS-1504...........5.4 SS-1505...........5.4 SS-1506...........5.4

SS-1508...........5.4 SS-1509...........5.4 SS-1510...........5.4 SS-1556...........5.5

SS-1560...........7 SS-1565...........3.9.5 SS-1568...........4.3 SS-1570...........4.3

SS-1572...........4.3 SS-1575...........3.9.2 SS-1577...........3.9.3 SS-1581...........3.9.6

SS-1646...........4.4.5 SS-1647...........4.4.5 SS-1648...........4.4.5 SS-1649...........4.4.5

SS-1652...........4.4.5 SS-1653...........4.4.5 SS-1654...........4.4.5 SS-1655...........4.4.5

SS-1658...........4.4.5 SS-1659...........4.4.5 SS-1660...........4.4.5 SS-1661...........4.4.5

SS-1663...........4.4.5 SS-1664...........4.4.5 SS-1665...........4.4.5 SS-1666...........4.4.5

SS-1668...........4.4.5 SS-1669...........4.4.5

SS-415 ............3.1.2

SS-1558...........6

SS-561 ............3.3.2

SS-1571...........4.3

SS-583 ............3.7

SS-1645...........4.4.5

SS-591 ............3.4

SS-1651...........4.4.5

SS-605 ............3.2

SS-1656...........4.4.5

SS-618 ............3.6

SS-1662...........4.4.5

SS-682 ............4.2.1

SS-1667...........4.4.5

SS-713 ............4.4.4

SS-741 ............4.3

SS-1490...........3.7

SS-1500...........5.4

SS-1507...........5.4 Document Autogenerated from DOORS Module : /LISA Pathfinder/Level 3/AOCS/Sun Sensor S2.ASU.RS.2026 ISS01 Sun Sensor Requirement Spec.doc

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INTENTIONALLY BLANK

Document Autogenerated from DOORS Module : /LISA Pathfinder/Level 3/AOCS/Sun Sensor S2.ASU.RS.2026 ISS01 Sun Sensor Requirement Spec.doc

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