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Gaia PCDU Requirement Specification
CI CODE: 13310
DRL Refs : N/A
UK EXPORT CONTROL RATING : Not Listed
Rated By : D. Perkins
Prepared by:
Date:
J. Holroyd
Checked by:
Date:
A. Dyne
Approved by:
Date:
S. King / D. Perkins
Authorised by:
Date:
R. Emery
This document is produced under ESA contract, ESA export exemptions may therefore apply.
These Technologies may require an export licence if exported from the EU
©
EADS Astrium Limited 2006
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for
any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or
communicated to any person without written permission from the owner.
EADS Astrium Limited, Registered in England and Wales No. 2449259
Registered Office: Gunnels Wood Road, Stevenage, Hertfordshire, SG1 2AS, England
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CONTENTS
1
Introduction and Scope ..............................................................................................................................6
1.1
Introduction..........................................................................................................................................6
1.2
Scope ..................................................................................................................................................8
1.3
Summary Description..........................................................................................................................8
1.3.1
Power System Architecture .........................................................................................................8
2 Documents ...............................................................................................................................................12
2.1
Applicable Documents ......................................................................................................................12
2.2
Reference Documents ......................................................................................................................12
3 Functional and Performance Requirements.............................................................................................13
3.1
PCDU General Requirements...........................................................................................................13
3.2
PCDU Primary Power Grounding / Star Point...................................................................................15
3.3
Main Power Bus Protection...............................................................................................................16
3.4
Operating Voltage Range..................................................................................................................16
3.5
Power Control and Distribution Unit (PCDU) Definition ...................................................................16
3.5.1
PCDU Functions ........................................................................................................................16
3.5.2
Power Regulation;......................................................................................................................17
3.5.3
Discrete Telecommand (SHP) Interface and Relays Status Acquisition (RSA) ........................17
3.5.4
Mil Bus Interface Module ...........................................................................................................18
3.6
Power Regulation Method................................................................................................................19
3.6.1
Maximum Power Point Tracker (MPPT) ....................................................................................19
3.7
Battery Charge and Discharge Control By Hardware .......................................................................24
3.7.1
General ......................................................................................................................................24
3.7.2
Lithium-Ion Battery.....................................................................................................................25
3.8
Bus Performance ..............................................................................................................................26
3.8.1
Maximum Bus Voltage ...............................................................................................................26
3.8.2
Nominal Bus Voltage .................................................................................................................26
3.8.3
Main Bus Source Impedance....................................................................................................26
3.8.4
Load Step Transient...................................................................................................................26
3.8.5
Steady-State Bus Ripple Voltage ..............................................................................................27
3.8.6
Steady-State Bus Commutation Spike Voltage .........................................................................27
3.8.7
Bus Stability ...............................................................................................................................27
3.9
Power Distribution & Conditioning ....................................................................................................27
3.9.1
General Requirements...............................................................................................................27
3.9.2
Latching Current Limiter Outputs (LCL)....................................................................................29
3.9.3
Heater Outputs...........................................................................................................................31
3.9.4
Mechanical Actuator/Release Initiator Activation Outlets ..........................................................33
3.9.5
Auxiliary Power Supply .............................................................................................................36
3.10
Monitoring, Control and Communication .......................................................................................37
3.10.1 General; .....................................................................................................................................37
3.10.2 Battery Voltage Measurement ...................................................................................................38
3.10.3 Housekeeping ............................................................................................................................38
3.11
Battery Connection ........................................................................................................................39
3.12
Operational Requirements ............................................................................................................39
3.12.1 Autonomous Operation ..............................................................................................................39
3.12.2 Initial Configuration of Regulators..............................................................................................39
3.12.3 Power Recovery.........................................................................................................................40
3.12.4 Operation on The Ground..........................................................................................................40
3.12.5 Ground Verification ....................................................................................................................40
3.13
Failure Tolerance and Redundancy ..............................................................................................40
3.13.1 Single Failure Tolerance ............................................................................................................40
3.13.2 Redundant Functions Physical Location....................................................................................40
3.13.3 Routing of Redundant Functions ...............................................................................................40
3.13.4 Other Protection.........................................................................................................................41
3.13.5 LCL Command (Cmd) Failure....................................................................................................41
3.13.6 Discrete Command (Cmd) I/F Failures ......................................................................................41
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3.14
Power Consumption / Dissipation .................................................................................................41
3.14.1 PCDU Power Consumption .......................................................................................................41
3.14.2 PCDU Power Conditioning Losses ............................................................................................41
3.14.3 PCDU Power Distribution Losses ..............................................................................................41
3.14.4 PCDU Power Dissipation ...........................................................................................................41
Unit Specific Design and Interface Requirements ...................................................................................42
4.1
Mechanical Design and Interface Requirements ..............................................................................42
4.1.1
Mass...........................................................................................................................................42
4.1.2
Envelope ....................................................................................................................................42
4.2
Thermal Design and Interface Requirements ...................................................................................42
4.2.1
Unit Thermal Design ..................................................................................................................42
4.2.2
Temperature Requirements .......................................................................................................43
4.3
Electrical Design and Interface Requirements..................................................................................44
4.3.1
Electrical Interface Description ..................................................................................................44
4.3.2
Hardware Data Interface Description.........................................................................................44
4.3.3
Reliability....................................................................................................................................44
Verification Requirements ........................................................................................................................45
Product Assurance Requirements ...........................................................................................................46
GDIR Applicability Matrix..........................................................................................................................47
Accronym List ...........................................................................................................................................77
TABLES
Table 3.6-1: Solar Array BoL Electrical Characteristics ..................................................................................22
Table 3.9-1: LCL / FCL Quantities...................................................................................................................29
Table 3.9-2: Heater Interface Summary ..........................................................................................................32
Table 3.9-3: Pyro Activation Device Characteristics .......................................................................................35
FIGURES
Figure 1.1-1: Gaia General Overview...............................................................................................................7
Figure 1.3-1: EPS System Architecture...........................................................................................................10
Figure 3.1-1: PCDU Voltage Operating Points................................................................................................14
Figure 3.8-1: Main Bus Impedance .................................................................................................................26
Figure 3.9-1: Heater Output Principle..............................................................................................................31
Figure 4.2-1: Overview of the thermal environment for internal units .............................................................42
Figure 4.2-2: Alternative unit thermal accommodation with additional radiator plane.....................................43
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INTRODUCTION AND SCOPE
1.1 Introduction
This document specifies the requirements for the Power Control and Distribution Unit (PCDU) which is
installed on the Gaia satellite.
The Gaia satellite is an ESA cornerstone mission to conduct a census of up to 1 billion stars in our galaxy.
Figure 1.1-1 shows the overall satellite configuration.
+
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Gaia
Xs, Xp, Xa
Thermal Tent
Deployable
Sunshield Assembly
DSA Interface Ring
Deployable Solar
Panels
Payload Module
Optical Bench
ASTRO LOS 2
Za
Ya
Payload Module
Focal Plane Assembly
Launch Lock Bipods (amber)
In-Orbit Bipods (grey)
ASTRO LOS 1
Equipped Service
Module Structure
Zp
Yp
Zs
Ys
Propellant &
Pressurant Tanks
Propulsion Ring
Equipped Phase
Array Antenna Panel
Fixed Solar
Array Panels
Figure 1.1-1: Gaia General Overview
The general requirements for the Gaia missions are:
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•
a continuously scanning instrument capable of measuring simultaneously the angular separation of
thousands of star images as they pass across a field of view of about one degree diameter.
•
multi-colour photometry of all astrometric targets is a necessary and integral part of the concept.
•
The whole sky is systematically scanned in such a manner that observations extending over several
years permit a complete separation of the astrometric parameters describing the motions and
distances of the stars.
The Gaia mission will rely on the proven principles of ESA's Hipparcos mission to solve one of the most
difficult yet deeply fundamental challenges in modern astronomy: to create an extraordinarily precise threedimensional map of about one billion stars throughout our Galaxy and beyond. In the process, it will map
their motions, which encode the origin and subsequent evolution of the Galaxy. Through comprehensive
photometric classification, it will provide the detailed physical properties of each star observed:
characterizing their luminosity, temperature, gravity, and elemental composition. This massive stellar census
will provide the basic observational data to tackle an enormous range of important problems related to the
origin, structure, and evolutionary history of our Galaxy.
1.2 Scope
The document in hand comprises the contractually relevant requirements and constraints for the Power
Control and Distribution (PCDU) Unit. These include:
- the performance as well as design and interface requirements of the subject hardware
- the product assurance requirements
- the testing and verification requirements
1.3 Summary Description
1.3.1
Power System Architecture
The Gaia PCDU is part of the power generation, storage and distribution system. There are two separate
solar arrays, one set of panels which are fixed to the -X face of the spacecraft, which is called the Fixed
Solar Array (FSA) and a second set of panels which are attached to the deployable sun shield, which is
called the Deployable Solar Array (DSA). These consists of triple junction solar cells mounted on each
panel. There is one Power Control and Distribution Unit, (PCDU), which combines the available power from
either the solar arrays or the one Lithium-Ion battery installed on the spacecraft.
Figure 1.3-1 shows the basic power system architecture.
Note: The solar array power may be split up to 70% Fixed Array and 30% Deployed Array
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Sunlight Processing Power
Overall 2000 Watts
BUS SUPPORT
Deployed SA MPPT
Split up to 70:30%
Fixed SA MPPT
Individually
Protected Outputs
for all main power
bus usres
LCL
FCL
Thermal
BCRs 200 W
After any single Failure
BATTERY
BDRs 750 W
After any single Failure
PCDU (part)
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Figure 1.3-1: EPS System Architecture
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PCDU-23/Created/R
The power generation, storage and distribution system functions are allocated to four distinct units:
- fixed solar generator array (FSA),
- deployed solar generator array (DSA)
- lithium - ion battery (BAT),
- power control and distribution (PCDU) unit.
PCDU-24/ERS_411/R
The PCDU shall provide the processing and interface means to operate autonomously without the
need for CDMU control in the areas of battery charge/ discharge control, solar array power control
and main bus voltage control.
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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 1.
General Design and Interface Requirements GAIA.ASF.SP.SAT.00002
AD 2.
Product Assurance Requirements for Subcontractors GAIA-ASF-SP-SAT-00004
AD 3.
Gaia Mil-1553 Data Bus Protocol Specification. GAIA.ASF.SP.SAT.00059
AD 4.
Mechanical - Part 6: Pyrotechnics ECSS-E-30. Part 6A.
AD 5.
Gaia nonvolatile Memory Protection. GAIA.ASF.TCN.CSW.00019
2.2 Reference Documents
The following documents form a part of this specification to the extent specified.
None.
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FUNCTIONAL AND PERFORMANCE REQUIREMENTS
3.1 PCDU General Requirements
PCDU-49/ERS_366/T,A,R
The PCDU shall condition, control and distribute electrical energy during the individual spacecraft
mission phases corresponding to the requirements of the various primary power users of the
spacecraft.
PCDU-50/ ERS_405/I,R
Inside the PCDU, all power carrying assemblies (including wiring) before the first level of electrical
failure protection (LCL/ FCL), shall be double insulated either by two layers of suitable insulating
material or one layer of insulating material plus adequate spacing (minimum of 1 mm)
PCDU-51/ERS_403/T,A,R
The PCDU shall recover automatically from any event, even if the battery is fully discharged, when
the Solar Array is illuminated adequately.
Notes:
The 'event' is envisaged as any source or load anomaly. A source anomaly can be typically a loss of
solar array power for a longer time than can be covered by the battery capacity. Internal PCDU
failures are covered by the single point failure requirements. Load anomalies are protected by the
LCL's/FCL's and the PCDU continues to regulate the main power bus once the current limiter has
operated.
Any operator induced overload of the power bus is protected by the defined voltage switch off levels
of the non-essential and essential LCL's.
Recovery means back to nominal operation as detailed in the PCDU start up sequence and full bus
performance is regained.
PCDU-52/ERS_410, Created/T,A,R
The default PCDU start up mode shall be the following:
•
Array Power regulators shall automatically switch on,
•
At a bus voltage (at the Main Regulation Point) of 20.0 V (+/-0.25V), the FCLs shall be
functional,
•
At a bus voltage (at the Main Regulation Point) of 19.0 V (+/-0.25V), the PCDU Mil 1553 Bus
interface auxiliary
supplies including TM/TC shall switch on,
•
At a bus voltage (at the Main Regulation Point) of 25.0 or 26.0 V (+/- 0.25 V), voltage level
depending if the attached load is classed as essential or non-essential, all LCL's shall be enabled,
and set to their specific default state.
PCDU-53/Created/T,A,R
The PCDU LCL's shall have differing switch off voltages dependent on the type of load they are
supplying as shown in Figure 3.1-1.
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PCDU-1249/Created/T,A,R
PCDU Overvoltage protection invoked (absolute max transient)
34.0
28.14
27.86
Bus Regulation Point voltage over life
26.0
25.5
25.0
24.5
Non-Essentials LCLs ON
Non-Essentials LCLs OFF (delay <0.5mS)
Essential Load LCLs ON
Essential Load LCLs OFF (delay <0.5mS)
20.0
FCL User operating range
18.0
PCDU switches off (not latched).
Battery <18V BDRs stop battery discharge (non-latched)
LCL OFF only
On Function
OFF Function. strength = severity
Tolerance for all but Bus Regulation, 250mV
Figure 3.1-1: PCDU Voltage Operating Points
PCDU-56/Created/A,R
All LCL's shall be capable of having their individual switch off voltages adjustable up to start of
manufacture, within the voltage ranges shown in Figure 3.1-1
PCDU-57/Created/T,A,R
LCL's supplying non-essential loads shall be switched off automatically when the bus voltage drops to
25.5 V +/-250mV, at the main regulation point, for a duration of more than 0.5 ms.
PCDU-58/Created/T,A,R
LCL's supplying essential loads shall not be automatically switched off until the bus voltage drops to
24.5 V +/- 250 mV at the main regulation point, for a duration of more than 0.5 ms.
PCDU-59/Created/T,R
All the platform LCL outlets shall be switchable by external command via the Platform Mil 1553 bus.
PCDU-61/Created/T,R
All the TCS LCL outlets shall be switchable by external command via the Platform Mil 1553 bus.
PCDU-62/ERS_384/A,R
Sufficient telemetry shall be made available to allow monitoring of functions to allow for possible
diagnostic purposes. This shall consist of, but not be limited to the following:
Internal unit temperature, LCL status, LCL current TM, FCL current TM, bus voltage / current,
auxiliary supply voltages, APR currents and states, BDR/BCR currents and states
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This is to allow for diagnostics during system integration and during the spacecraft mission after
launch.
PCDU-63/Created/R
Conditioning of the 2 solar array power outputs shall be performed by :
Independent Maximum power point tracker (MPPT) controlled dc-dc converter power modules of the
step-down regulator type. Both FSA and DSA shall be regulated independently. The number of
modules shall be defined by the supplier.
PCDU-64/Created/T,A,R
The bus power regulator function of the MPPT regulators shall be single fault tolerant without any
reduction in the available main bus power.
PCDU-1253/ERS_411, ERS_404/A,R
The PCDU bus power regulator function shall be totally autonomous and not rely on any external
control hardware or commands.
PCDU-65/ERS_427/T,A,R
The PCDU internal redundancy concept shall operate such that in case of failure of any part of the
PCDU's bus power control function, no abnormal operation of the electrical power system shall occur.
PCDU-66/ERS_426/T,A,R
The bus power regulator functions shall be implemented in a control loop covering all operational
domains with a control loop stability margin as referenced in AD 1, i. e. at least 10 dB gain margin,
and 60 degrees phase margin condition under all environmental conditions and over life.
PCDU-67/Created/T,R
The EPS data management interface to the CDMU shall be by incorporation of a redundant fullduplex serial databus, based on MIL-STD-1553 interface hardware.
PCDU-1254/Created/T,R
It shall be possible to control and acquire TM from any nominal or redundant function in the PCDU
from either Mil-Bus.
3.2 PCDU Primary Power Grounding / Star Point
PCDU-69/Created/T,R
All primary power return lines shall be brought together at the negative side of the main bus capacitor
which is the unique common ground point (CGP). This is to be used as the grounding star point of the
primary power system, and referenced to the PCDU housing.
PCDU-70/Created/A,I,R
The grounding star point shall be made available by a bonding stud at the exterior of the PCDU
housing, able to be grounded to the spacecraft Ground Reference Rail (GRR), which is used as a
Earth Reference Plane only, by a low impedance interconnection, capable of sustaining, without
degradation, the worst case fault current.
PCDU-71/Created/T,R
The star point ground shall be routed from the PCDU’s bonding stud via a removable ground strap
interconnection which will have a resistance of no greater than 2.5 mOhms to the Spacecraft GRR at
a single ground point (SGP) located adjacent to the PCDU.
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It shall be noted that the GRR is only used as a Earth Reference Plane and will not carry any
intentional load currents.
3.3 Main Power Bus Protection
PCDU-73/ ERS_371/T,A,R
The PCDU shall protect the primary power bus against load faults, e.g. overload and short circuit,
such that no external load failure, or internal single component failure can cause a permanent
shutdown, or permanent voltage drop.
PCDU-74/ ERS_371/T,A,R
The PCDU shall protect against overload and short circuit, such that the primary power bus recovers
automatically to nominal operation after isolation of the fault condition.
PCDU-75/Created/T,R
The PCDU shall be capable of executing external received commands via either the Platform Mil
1553 Bus or by discrete SHP commands for TM/TC interface switching, in any spacecraft mode (i.e.
eclipse, sunlight, launch, AIV).
3.4 Operating Voltage Range
PCDU-77/ERS_369, Created/T,A,R
The PCDU shall be designed such that it controls the bus voltage to 28 +/- 0.5% Volts throughout the
mission lifetime.
PCDU-78/ERS_920, Created/T,A,R
The PCDU shall be designed such that it controls the bus voltage to 28 +/- 0.25% Volts over any 6
hour period in Science Mode. Note: It can be assumed the spacecraft load is constant during this
time.
PCDU-80/Created/T,A,R
The PCDU shall perform as specified operating over an output voltage (Vbus) of 18 V to 28.14 V.
PCDU-81/Created/T,A,R
The expected normal in flight operating range of the PCDU is Bus voltage 24.5 V to 28.14 V,
nominally fully regulated at 28 +/- 0.5% Volts except in a failure condition
PCDU-82/Created/A
The PCDU shall safely survive any standing or fluctuating output voltage in the full range 0 to 35 V.
3.5 Power Control and Distribution Unit (PCDU) Definition
3.5.1
PCDU Functions
PCDU-85/ERS_46, ERS_366, ERS_745, ERS_382, ERS_384, ERS_388/T,A,R
The PCDU shall provide, but not be limited to the following functions:
·
Regulation and conditioning of the power from the solar array ( full load capability)
Regulation and conditioning of the power from the battery ( reduced load capability)
·
Distribution and protection of regulated power to all spacecraft loads
·
Regulation of the battery charge power
·
Main bus filtering
·
Pyrotechnic pulse generation, distribution and circuit protection
·
Monitoring and control of the above functions as well as communication with the CDMU via the
Platform Mil
1553 data bus
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⋅
Heater circuit switching and protection
⋅
Battery Monitoring
⋅
Battery End Of Charge Level control
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Battery End Of Discharge Control
⋅
Thermistor monitoring including the battery and solar array temperatures (if required for the
operation of the PCDU)
⋅
EGSE Interfaces
⋅
Internal Operating Telemetry (internal voltages, currents, temperatures, and others as required)
3.5.1.1 Power Capability
PCDU-87/Created/T,A,R
The PCDU shall provide the following power bus capabilities:
•
Regulated Bus Voltage 28 V +/-0.14V, with nominal sunlight load power of 1800 W (tbc)
•
Regulated Bus Voltage 28 V +/-0.14V, with nominal battery load power of 750 W (tbc)
•
Battery Charge Power from the power bus at the battery voltage with a nominal power of
200 W (tbc)
PCDU-1256/ERS_399/A,R
The PCDU shall be capable of providing both solar array and battery power as specified in PCDU-87
simultaneously and continuously without damage
3.5.2
Power Regulation;
PCDU-89/ERS_404, Created/T,A,R
The solar array and battery power regulation and conditioning shall operate independent of the status
of any other PCDU electronics. Their nominal operations and power capability shall be ensured after
any single failure.
PCDU-90/Created/A,R
The PCDU shall be capable of processing the maximum available solar array power at any time when
either or both of the two solar array assemblies are illuminated.
PCDU-91/ERS_426, Created/T,A,R
The PCDU shall maintain Solar Array voltage and power regulation stability (phase and gain margin
of 60 degrees and 10 dB respectively), even if no load is connected to its output terminals, (any
minimum load constraints shall be identified by the contractor)
PCDU-92/ERS_403, ERS_408, ERS_427/T,A,R
The primary power bus shall recover automatically from any condition that prevents the normal
voltage being achieved, once the cause of the condition is removed. This applies to both overload on
the outputs or loss of the energy source on the input. The PCDU shall recover its performance when
either the solar array or battery sources recover and shall be capable of meeting the requirement
under any rate of rise of voltage.
3.5.3
Discrete Telecommand (SHP) Interface and Relays Status Acquisition (RSA)
PCDU-94/Created/T,R
The SHP I/F shall be used for commanding the switching ON and OFF of the cold-redundant Mil 1553
Bus interfaces , within the PCDU.
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PCDU-95/Created/T,R
The PCDU shall provide redundant interfaces for the Discrete TC's and associated Discrete TM data.
PCDU-1252/Created/T,R
Up to 10 (tbc) LCL's shall also be switchable by SHP command. Allocation of commands to the LCL's
shall be selectable up to the unit manufacture
3.5.4
Mil Bus Interface Module
PCDU-97/Created/T,R
The PCDU shall provide two MIL 1553 Bus interfaces, Prime and Redundant, operated in cold
redundancy.
PCDU-98/Created/T,R
The default interface shall be the Prime side with the ability to be switched from Prime to Redundant
and Redundant to Prime.
PCDU-99/Created/T,R
Each MIL1553 Bus interface (Prime and Redundant) shall provide full TM/TC access to all the Prime
and Redundant TM/TC functions of the PCDU.
PCDU-100/Created/A,R
No failure inside a MIL 1553 Bus interface shall affect the other MIL 1553 Bus interface and shall not
prevent use or access of any other part of the PCDU or any telemetry or telecommand unless solely
related to the failed MIL 1553 Bus interface
PCDU-101/Created/T,R
The Mil 1553 Bus I/F shall be used for commanding of the PCDU and for transmission of
housekeeping (HK) data to the CDMU.
PCDU-102/Created/T,R
The PCDU shall interface with the Mil 1553 Bus consisting of redundant Remote Terminals as
detailed in AD 3
PCDU-104/ERS_448/T,R
The CDMU will be the Bus Controller as defined in AD 3.
The CDMU has prime and redundant Bus Controllers. The PCDU shall provide prime and redundant
Remote Terminal interfaces each transformer coupled to both prime and redundant Mil buses.
PCDU-105/Created/T,R
The Mil-Bus addresses shall be agreed and fixed in the ICD. As detailed in AD 3.
PCDU-106/Created/T,R
The switching between the redundant parts of the Mil 1553 Bus shall be selectable by command, as
specified within requirement PCDU-309.
PCDU-1257/Created/T,R
No failure within any Mil 1553 Bus Terminal or Controller shall affect the ON/ OFF SHP's ability to
switch On or OFF its associated Mil Bus Interface
PCDU-107/Created/T,R
The electrical interface and implementation shall comply with the requirements defined in AD 1.
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PCDU-108/Created/T,R
The PCDU shall support the Mil Bus Cmds and corresponding digital and analogue telemetry's as
listed in TBC
PCDU-2318/ERS_440/T,R
Any EEPROM devices used within the PCDU shall have the capability of being reprogrammed in flight
by ground command, and meet the requirements of AD 5
3.6 Power Regulation Method
PCDU-1258/Created/A,R
The Bus shall be fully regulated at 28 Volts and have the capability of charging the battery to a
defined voltage via battery charge regulators.
PCDU-1259/Created/T,A,R
The Regulation system shall be capable of controlling the power provided to the Bus from the solar
arrays or battery and maintain the battery at the required state of charge. In cases where the load
condition including battery charge requirement exceeds the solar array capability, then the battery
charge current is reduced to maintain the bus voltage regulation
PCDU-1260/Created/T,A,R
The PCDU shall (subject to sufficient power being available) meet all the regulation requirements with
either the solar array, the battery, or both being connected.
PCDU-2314/Created/T,R
The PCDU shall also meet the power bus regulation requirements when sufficient power is available
from the EGSE power sources.
PCDU-135/Created/T,A,R
The PCDU shall incorporate hot-redundant bus power regulation control electronics.
3.6.1
Maximum Power Point Tracker (MPPT)
3.6.1.1 Solar Array Power Regulation Principle
PCDU-122/Created/A,R
Two independent sets of hot redundant operating MPPT's, one for the Deployed Solar Array and one
for the Fixed Solar Array, shall be employed and controlled such that all available Solar Array power
is available to the primary power bus, when requested by the regulation system, to satisfy the power
demand of the Spacecraft.
PCDU-2316/Created/T,R
The operating status of each MPPT system shall be available as status telemetry
PCDU-1261/Created/T,A,R
It shall be possible to set the power limit of each MPPT controller by telecommand in order to operate
the associated solar array in a constant power source mode whenever the load required from that
array exceeds the limit value. In this mode the other MPPT shall perform the active bus regulation.
PCDU-2317/Created/T,R
The status of the power limit of each MPPT system shall be available in telemetry
PCDU-123/ERS_404/A,R
The MPPT control function shall not be part of any switchable (A to B) auxiliary supply used to power
TM/TC control (for example).
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PCDU-124/ERS_404/A,R
The MPPT control loops shall functionally independently of any failure in the rest of the PCDU (for
example loss of the TM/TC interface and control shall not prevent the MPPT correctly controlling the
power bus).
PCDU-125/ERS_404/A,R
The MPPT regulation loops shall be autonomous within the PCDU and shall not rely on any other
functions for its operation.
PCDU-1262/Created/T,A
The MPPT location time shall be < 1 second from any point on the solar array current/voltage
characteristic.
PCDU-129/Created/T,A,R
The array regulator modules shall be controlled, such that they can maintain the solar array within 1%
of the array maximum power , when maximum power tracking is required.
3.6.1.1.1
Array Regulator Modules
PCDU-127/Created/A,R
The PCDU shall provide as many array regulator modules as necessary, to condition the Solar Array
power from both the Fixed Solar Array and the Deployed Solar Array without reduction of the required
power conditioning capability even in case of a single failure inside the PCDU.
PCDU-128/Created/A,R
The PCDU array regulator modules shall not place a short circuit across the solar arrays, even in
case of any single point failure.
PCDU-130/Created/T,A,R
Input current distribution between paralleled array regulators shall be matched within a 5% (TBC)
spread of the module maximum designed input current. This shall be under all nominal operating
conditions.
PCDU-131/ERS_384/T,A
The input current of each module shall be available by telemetry to determine the operating
characteristics of the modules and in determining any failure.
PCDU-1263/ERS_384/T,A
Any latching protection included to isolate the Array regulator modules shall have the capability of
being reset by telecommand. This shall not prevent the module being latched off again should the
fault reoccur.
PCDU-1264/Created/T,R
Any latching protection included to isolate the Array regulator modules shall be automatically reset if
the Bus fails below 20 V (TBC). This shall not prevent the modules being latched off again should the
fault reoccur
PCDU-132/Created/T,A,R
Array regulator module converter switching shall have the ability if required to be synchronized by
means of an external source. No failure in a regulator module or synchronization circuit shall affect
any other regulators.
3.6.1.2 Solar Array Interface
It shall be assumed by the PCDU supplier that the solar array cannot fail in itself to ground. This will be
implemented within the solar array by the use of series string diodes, double insulation and careful harness
routing up to the PCDU input interface and use of double insulation in the solar array construction.
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not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
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PCDU-138/Created/T,R
The PCDU shall provide a minimum of two sets of thermistor conditioning circuits for the thermistor
type PT1000 (as defined in AD-2), if required for PCDU functionality. These shall be used for Solar
Array temperature monitoring.
PCDU-139/Created/T,R
If it is required to combine the solar array power inputs together for correct operation of the regulator
modules, this shall be accomplished by the PCDU in such a way that each array regulator can still be
individually functionally verified.
PCDU-140/Created/T,I,R
The PCDU shall not rely on any external harness combining to perform the Solar Array power input
combining
PCDU-141/Created/I,R
The PCDU shall consider each solar array input as a block of power, that is, it will not be
sectionalised. This is to avoid any thermal gradients on the array due to the failure of an array
regulator module. Each array is required to operate isothermally.
PCDU-142/Created/I,R
The two solar array power inputs shall each interface with the PCDU via two sets of connectors, one
for the prime harness and one for the redundant harness.
PCDU-143/Created/T,R
It shall be possible to verify the correct performance and operation of each regulator module
(including any critical protection or active redundancy) with the PCDU in its full flight configuration.
PCDU-144/Created/R
The PCDU Solar Array interface and internal PCDU wiring to the Array regulator modules shall not,
even in the event of a single failure, cause a short circuit to ground.
3.6.1.2.1
Solar Array Characteristics
The Solar Array will comprise of two separate assemblies. The Fixed Solar Array (FSA) and the Deployable
Solar Array (DSA).
PCDU-147/Created/A,R
The PCDU shall be designed to operate with the two different arrays, each having its own MPPT and
Array Regulators. Each part has the following array input power.
•
Each set of regulators shall be able to accept up to a 70:30 % split of available input power
•
The total solar array power input at BoL is characterized as below.
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PCDU-148/Created/A,R
Characteristic
Isc
BoL
85A
75V
Voc
45V
>34V (EOL)
2000W
Vmp
Pmp
Capacitance
Inductance
<30uF
<8uH
Table 3.6-1: Solar Array BoL Electrical Characteristics
The electrical characteristics detailed above are those at the PCDU input.
PCDU-1274/Created/T,A,R
In LEOP either one of the two arrays may be partially or fully in shadow and not illuminated. The
PCDU shall remain fully operational within the constraints of the available solar array power.
PCDU-1280/Created/A,R
The FSA and DSA will be operated at different temperatures to each other, at any one time. However
preliminary estimates shows that the operating temperature range of each one is the same. Each
array shall be provided with a dedicated MPPT system as the actual maximum power point of each
array will be different at any one time.
3.6.1.3 Battery Charge and Discharge Interface
PCDU-1267/Created/T,A
The BDR shall be defined as a step up regulator with an efficiency of 95% at an output power of >50
W. The maximum capability shall be power limited to at least 750 W +10%
PCDU-1276/ Created/T,A,R
The BDR output power capability to the main power bus shall be at least 750 W + 10% after a single
failure
PCDU-1268/ERS_356/T,A
The PCDU shall provide a Battery End Of Charge (EOC) function which terminates the battery charge
current when a pre-set battery terminal voltage is reached. The EOC voltage level shall be selectable
by ground command and shall have a range of at least 8 different step values.
PCDU-1269/Created/A,R
The EOC function shall be one failure tolerant. Any single failure shall not result in the battery being
charged above the EOC voltage level.
PCDU-1277/Created/T,A
The EOC function when operated shall reduce the battery charge current in a tapered fashion
depending on the battery voltage down to 0 Amps.
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PCDU-1270/ERS_82, Created/T,A
The PCDU shall provide a Battery End Of Discharge (EOD) function which stops the battery
discharge power when the battery voltage falls below 18 Volts (tbc). The EOD function shall be reset
when the battery voltage rises above 20 Volts (tbc).
PCDU-1278/Created/T,A
Any latched input or output protection or a previously sent TC OFF command that has operated
previously shall be reset when the bus voltage falls below 20 Volts (tbc). This reset shall not preclude
the protection from operating again if the fault reoccurs.
PCDU-2306/Created/T,R
For any latched input or output protection circuit of the BDR modules the automatic reset capability
defined in PCDU 1278 shall be capable of being inhibited by means of an external strap or signal.
PCDU-2307/Created/T,R
It shall be possible to switch off each BDR by telecommand (SHP). This function shall be protected by
means of an Arm command and a separate Execute command before the BDR is switched Off.
PCDU-2308/Created/T,A,R
When the BDR modules are commanded Off the resulting discharge current from the battery shall be
less than 10 mA in total.
PCDU-1271/ERS_384/T,A,R
The Battery Charge and Discharge currents shall be available in TM. The operating range shall be
the I max. +10% . (Ilimit + 15%)
PCDU-1279/Created/T,R
Each BDR/BCR module shall be enabled or disabled by SHP commands.
PCDU-1272/ERS_377, Created/T,A
The BCR's shall provide a charge current to the battery with at least 2 selectable rates. A high rate of
6A (tbc) total and a low rate of 2A (tbc). Both values +/- 0.25A
PCDU-1273/Created/T,A
Current sharing between any BDR or BCR modules shall be better than 3%.
3.6.1.4 Solar Array Simulator Interface
PCDU-151/Created/R
The PCDU shall be able to regulate Solar Array Simulator (SAS) power via a separate interconnection
interface having an electrical interface equivalent to the Solar Array power interface.
PCDU-152/Created/R
An individual SAS interface shall always be connected inside the PCDU directly in parallel to the
related Solar Array connection.
PCDU-153/Created/R
All SAS regulator modules and associated interfaces shall be protected from a short circuit to ground.
3.6.1.5 Solar Array I/F Power
PCDU-155/Created/T,A,R
The PCDU applying MPPT controlled Solar Array power transfer, shall be capable to condition the
beginning of life (BOL) Solar Array characteristic defined within Table 3.6-1 with an output power
capability defined in PCDU-87.
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3.6.1.6 Solar Array I/F Voltage
PCDU-157/Created/T,A,R
The input circuits of the PCDU shall be compatible with a voltage range as specified in Table 3.6-1
3.6.1.7 Solar Array Effective Capacitance
PCDU-159/Created/T,A,R
The input circuits of the PCDU shall be compatible with a maximum solar array capacitance as
defined in Table 3.6-1.
3.6.1.8 Array Regulator Failure
PCDU-161/ERS_384/A,R
Status TLM signals shall enable fault detection at a single array regulator of a permanent off-state of
that regulator.
PCDU-2315/Created/T,R
The input current to each array regulator shall be available in TM. 8--Bit resolution is required (TBC)
3.6.1.9 Array Regulator Efficiency
PCDU-163/Created/T,A,R
Conditioning of Solar Array power by the PCDU MPPT controlled array regulation shall be performed
with an average throughput efficiency of at least 95% at a solar array voltage of 34V and nominal load
power of 1750W (TBC), at a bus voltage of 28.14V.
3.7 Battery Charge and Discharge Control By Hardware
3.7.1
General
PCDU-166/ERS_377/T,A,R
During sunlight periods, in LEOP, Transfer and On-Station modes, the battery shall be charged from
the power bus with a charge current limited by the PCDU battery charge regulators to a maximum
value of 6A(TBC) +0% / -10%.
PCDU-167/ERS_388/T,A,R
The PCDU shall monitor and condition the battery charge and discharge currents and make them
available as TM.
PCDU-1283/ERS_388, Created/T,A,R
The range of the TM shall be at least 25% higher than the maximum expected value during normal
operation for battery charge and discharge phases. This is to retain valid TM in the case of an
overload condition.
PCDU-1284/Created/R
PCDU-1283 may be accomplished by using the current sensors within the BCR and BDR modules
providing these readings are still valid in a current overload situation.
PCDU-1285/Created/T,R
The PCDU shall monitor and condition the battery voltage and make it available in TM. The battery
voltage inputs will be via dedicated battery sense wires which are protected against any potential
short circuit by resistors located at the battery interface.
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PCDU-1286/Created/T,R
The PCDU shall monitor and condition at least 2 (tbc) battery temperature thermistors if required for
the correct operation of the PCDU.
This telemetry will be used as PCDU housekeeping telemetry passed to the CDMU via the Mil 1553 data
bus.
3.7.2
Lithium-Ion Battery
3.7.2.1 General
PCDU-171/ERS_82/A,R
The charge control method applied shall protect the battery from both over charge by the BCR's and
over discharge by the BDR's.
3.7.2.2 Battery Characteristics
The battery characteristics below are to be confirmed on selection of the battery supplier, values below
indicate typical expected performance.
PCDU-174/Created/A,R
Type:
Li-Ion
Nameplate capacity:
≥ 60 Ah
Typical Battery D.C. resistance
20 mohm to 150 mohm @ 20degrees C (TBC)
Battery Impedance
with frequency
D.C. resistance plus 3dB at 1kHz then rising inductively
Maximum charge voltage
25.2V (TBC)
Minimum discharge voltage
18.0V (TBC)
Maximum charge current
6.0A +/-10%
Maximum discharge current
60A +/-10%
3.7.2.3 Battery Management
3.7.2.4 Undervoltage Reaction
PCDU-180/Created/T,A,R
In case of a main bus undervoltage of 25.5V, as seen at the PCDU main regulation point for more
than 0.5 mSec, the PCDU shall automatically switch off the non essential load LCL's.
PCDU-181/Created/T,A,R
In case of a main bus undervoltage of 24.5V, as seen at the PCDU main regulation point, for more
than 0.5 msec, the PCDU shall automatically switch off the essential load LCL's
PCDU-182/Created/T,A,R
In case of a main bus undervoltage of 20.0V, as seen at the PCDU main regulation point the FCL's
are not required to maintain their function.
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3.8 Bus Performance
3.8.1
Maximum Bus Voltage
PCDU-185/Created/T,A,R
The maximum transient or continuous voltage at the main bus regulation point shall never exceed
34.0 V DC under all conditions including any failures and recovery circuits within the PCDU, and in
minimum load case.
3.8.2
Nominal Bus Voltage
PCDU-1290/ERS_369/T,A
The PCDU shall be designed such that it controls the bus voltage to 28 +/- 0.5% Volts throughout the
mission lifetime.
PCDU-1291/Created/T,A
The PCDU shall be designed such that it controls the bus voltage to 28 +/- 0.25% Volts over any 6
hour period in Science Mode. Note: It can be assumed the spacecraft load is constant during this
time.
3.8.3
Main Bus Source Impedance
PCDU-187/ERS_387/T,A,R
The Main Bus impedance mask below shall apply at the point of regulation operating in either or both
the Battery or Solar Array regulated mode over the satellite lifetime, after any single failure, and under
all environmental conditions specified. The impedance mask in either mode shall be met even if the
other source is not connected.
PCDU-188/ERS_387/T,A,R
Source Impedance (mOhm)
9
8
7
6
5
4
3
2
1
0
0.001
0.01
0.1
1
10
100
1000
Frequency (kHz)
Figure 3.8-1: Main Bus Impedance
3.8.4
Load Step Transient
PCDU-191/Created/T,A,R
During sunlight whilst on-station, the spacecraft power bus voltage shall keep its nominal value at the
main regulation point within +/- 0.14 V ( +/- 0.5%) under all load conditions and over the operational
lifetime
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PCDU-192/Created/R
The Main Bus Regulation point is at the level of the bus capacitors before the LCL / FCL protection
devices.
PCDU-193/Created/T,A,R
For load transients of up to 50 % of the nominal load, bus voltage transients shall not exceed 1% and
shall recover to the nominal range within a time constant of 2 mS
PCDU-194/Created/T,A,R
The bus voltage shall remain within 5.0 % of its nominal value during all source transients and load
transients in nominal operation with a recovery time constant of 2ms.
3.8.5
Steady-State Bus Ripple Voltage
PCDU-196/Created/T,A,R
The spacecraft regulated bus shall have a nominal ripple voltage in the time domain below 0.5%
(TBC) peak to peak of the nominal bus voltage.
3.8.6
Steady-State Bus Commutation Spike Voltage
PCDU-1293/Created/T,A,R
Bus commutation spikes associated with changes between battery mode of operation and solar array
mode of operation ( transitions in either direction) shall not exceed 2% of the nominal 28V bus and
shall recover to the nominal range with a time constant of less than 2 mS.
3.8.7
Bus Stability
3.9 Power Distribution & Conditioning
3.9.1
General Requirements
PCDU-204/ERS_371/A,R
Full protection against any short circuit at all primary power outlets shall be provided, so that no single
failure of a primary power user including the associated harness between PCDU and power user can
propagate a permanent shutdown of the primary power bus, or result in any performance or lifetime
degradation.
3.9.1.1 Definition of LCL
PCDU-207/ERS_371, ERS_402/T,A,R
A LCL is a commandable solid state switch, which after switch on and in case of any overload on the
output shall provide current limiting capability for a defined time. If the overcurrent condition exceeds
this definite time, the outlet shall autonomously switch off.
There are two groups of LCL's, those supplying essential loads and those supplying non-essential
loads. The only difference between the two is the bus voltage level at which the undervoltage
protection activates
3.9.1.2 Definition of FCL
PCDU-209/ERS_385, Created/T,A,R
An FCL is a non-commandable solid state switch, which provides current limiting capability for an
indefinite time in case of any overload on the output. The limiting current reduces (folds back) to a
value that can be sustained thermally.
The outlet cannot be switched off.
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3.9.1.3 Redundant Operability
PCDU-211/Created/T,A,R
All outlets of the PCDU shall be fully operational (TM & TC) from either of the nominal or redundant
platform Mil 1553 bus interfaces.
Normally only one platform Mil 1553 bus interface will be powered at any one time, to operate in cold
redundancy. The Mil 1553 bus interface is switched over is by the SHP commands from the CDMU.
On PCDU switch on or recovery, the platform Mil 1553 bus A shall be selected.
PCDU-212/Created/T,A,R
LCL's shall keep their status independent of the configuration of the auxiliary supplies associated with
any central control or management function or any Mil 1553 controller supplies
PCDU-213/Created/T,A,R
Commanding of an output shall be independent of any command sent previously via the other
command chain.
PCDU-1298/Created/T,R
It shall be possible to control up to 10 LCL's (tbc) via direct SHP telecommands. The specific LCL's to
be commanded in this manner will be identified at an agreed time after PDR but prior to manufacture.
3.9.1.4 FCL / LCL Failure Modes
PCDU-215/Created/A,R
FCL's and LCL’s shall be independent in such a way, that no single point failure can lead to the
permanent loss of more than one output, and any failure of one FCL/LCL shall not propagate to other
FCL's or LCL’s.
PCDU-1294/Created/T,R
It shall be possible to verify the functionality of the LCL/FCL including its current limiting function
external to the PCDU at spacecraft level without recourse to physically overloading the outputs. Built
In Test is acceptable for this function.
Note: It is expected that verification at Unit level testing will involve full functional testing including
physical current overload of the LCLs.
Information:
The ability to test this function is requested because a load fault occurring and a distribution line
which has a non-functional current limiter can lead to complete loss of the power bus and thus the
spacecraft.
It is preferred that this verification can be made without having to disconnect the main power harness
to the power bus users after spacecraft environmental testing.
The purpose of this verification is to provide confidence that the current limiter part of the LCL is still
functional. It is not necessary to demonstrate this by physically overloading the LCL at its normal
operating levels and steady state operating levels via the power bus outputs.
Methods can be proposed that reduce the current limiter levels (so that the normal load cause trip off),
test ports can be proposed.
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Alternatively, provided the LCL current telemetry circuit uses the same components as the LCL
current limiting circuits and interfaces with the LCL ON /OFF route this could also demonstrate
integrity of the function.
It must be possible to fully, positively and demonstrably inhibit any test function that affects the LCL
current limiter levels or switch off time, at spacecraft level prior to flight.
3.9.1.5 Distribution Overview
PCDU-217/Created/T,A,R
The PCDU shall provide the following number of power interfaces as detailed in Table 3.9-1,
(excluding heater outputs).
PCDU-218/Created/R
LCA
LCB
LCC
LCD
LCE
LCF
FCA
FCB
LCL Type
LCL Class A (LCA)
LCL Class B (LCB)
LCL Class C (LCC)
LCL Class D (LCD)
LCL Class E (LCE)
LCL Class F (LCF)
Total
FCL Class A (FCA)
FCL Class B (FCB)
Total
Current Number Off Spares
1A
25
4
2A
18
4
3A
14
4
5A
4
2
8A
0
6
10A
0
2
61
22
1A
4
2
2A
0
2
4
4
Note: Alternative LCL current limiting values may be proposed providing the above loads can be
sustained.
Table 3.9-1: LCL / FCL Quantities
3.9.2
Latching Current Limiter Outputs (LCL)
3.9.2.1 LCL Output Current Limiting Time
PCDU-225/Created/T,A,R
In the case of an overcurrent event which exceeds the specified trip-off current or during switch-on of
the load unit, the Latching Current Limiters shall limit the output current for a time delay of between
8mS ≤ t ≥ 15mS for LCL A to LCL D and between 5mS to 8mS for LCL E and F before switching off.
In case the current limiting times of an existing LCL design are different from what is specified here,
the manufacturer shall propose limits based on his heritage. This shall be not less than 80% of the
trip-off time with the switches remaining de-rated.
PCDU-226/Created/A
The LCL's shall be capable of delivering their limiting current for the duration as specified above
without exceeding their thermal de-rating.
3.9.2.2 Operational Voltage Range
PCDU-228/Created/T,A,R
The LCLs shall keep their commanded status safely in the operating voltage shown in Figure 3.1-1
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PCDU-1295/Created/T,R
The LCL's shall autonomously switch OFF when subjected to undervoltage conditions at the bus
regulation point as defined in Figure 3.1-1
Note: The voltage switch off threshold of each LCL shall be individually adjustable up to the time of
unit manufacture. The values stated in Figure 3.1-1 are typical.
PCDU-1297/ERS_410/T,A,R
The LCL's shall be enabled and reset in the default state when subjected to undervoltage conditions
at the bus regulation point as defined in Figure 3.1-1
Note: The voltage switch off threshold of each LCL shall be individually adjustable up to the time of
unit manufacture. The values stated in Figure 3.1-1 are typical.
3.9.2.2.1
Nom. Voltage Drop
PCDU-230/Created/T,A,R
The voltage drop between Main Bus regulation point within the PCDU and the PCDU outlet connector
shall not exceed those below:
For LCL sized at Imax ≤3A
Vd ≤ 0.25V
For LCL sized at Imax >3A and ≤5A
Vd ≤ 0.28V
For LCL sized at Imax >5A and ≤10A
3.9.2.2.2
Vd ≤ 0.31V
LCL Sizing
PCDU-232/Created/T,A,R
The LCL shall be designed to operate in current limit and then switch OFF at 125% (+/-10%) of the
nominal LCL rating. Derating analysis shall be in accordance with this requirement.
3.9.2.3 LCL Status
3.9.2.3.1
Initial LCL Status
PCDU-235/ERS_410/T,A,R
The LCL’s shall go into a default state at initial switch-on of the PCDU and after recovery from an
under-voltage. The default state (On or Off) may be selectable either by a connection on the module
or by the use of other suitable methods for the modules.
This default state will be determined at the time of unit manufacture.
3.9.2.3.2
Status Signal
PCDU-239/Created/T,R
Each FCL/LCL shall provide an ‘on/off’ status signal and an analogue output current signal to the Mil
1553 interface of the PCDU.
PCDU-1314/Created/T,A,R
Each LCL shall provide current telemetry of the LCL current, with an 8 bit resolution of the current limit
value +25%. Accuracy shall be 3% of the full scale value.
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3.9.3
Heater Outputs
PCDU-241/Created/R
Heaters are controlled in groups of four. Each group of four heaters is supplied by a single 4 Amp
LCL which provides bus protection and current monitoring. The output of the LCL feeds 4 individual
solid state heater switches, enabling control of individual heater control. This is shown in Figure 3.9-1
Note: The preferred design is for four heaters per LCL, if the contractor has an existing design using
an alternative number of switches this may be acceptable provided the number of heaters does not
exceed 6 from a single LCL.
.
PCDU-242/Created/R
The normal function of the heater outputs is to turn on or off the power to the heaters by means of
Transistor Switches (TS's).
The heaters may be uncontrolled (fixed), Software controlled, or thermostat controlled.
PCDU-243/Created/R
The outputs shall be grouped and each group shall be protected by a dedicated LCL.
PCDU-244/Created/R
The principle configuration of these outputs is shown in the Figure 3.9-1
PCDU-245/Created/R
TS
LCL Switch
On / Off
On / Off
Status
On / Off
Status
On / Off
Status
On / Off
Status
TS
MAIN BUS
I TM
ITM
Status
TS
TS
Figure 3.9-1: Heater Output Principle
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PCDU-1299/Created/T,R
Heater switch telemetry as shown in Figure 3.9-1, shall be made available by the PCDU to be passed
to the CDMU forming part of the PCDU housekeeping telemetry
3.9.3.1 Number of Outputs
PCDU-247/Created/R
The PCDU shall provide a total of 52 (TBC) off 4 Amp LCLs having the above heater switch
configuration to be used as commandable outlets for heater control.
Table 3.9-2 shows the proposed heater configuration to be used.
Gaia Heater LCL Allocations
Sub-System
FEEP (TBC)
PCGS (TBC)
CPS
SVM Thermal
SPARES
UNIT
Protection Type
Interface Module
7 LCL
Motor Drive Electronics (P+R)
2 LCL
Optical Source Electronics (P+R)
2 LCL
Focal Plane Array Decontamination Heaters
5 LCL
Mirror Decontamination Heaters
10 LCL
FEEP Heaters Prime
( tbc)
FEEP Heaters Redundant
( tbc)
PCGS Heaters Prime
( tbc)
PCGS Heaters Redundant
( tbc)
Bi-Propellant 10N Thrusters, pipe-work heaters
.tank heaters, additional tank heaters. Prime
Bi-Propellant 10N Thrusters, pipe-work heaters
.tank heaters, additional tank heaters.
Redundant
Survival Heaters (P+R)
(tbc) LCL
(tbc) LCL
REMARKS
All heater circuits are
distributed according to
the philosophy as shown
in Figure 3.9-1
(tbc) LCL
(tbc) LCL
5 LCL
5 LCL
14 LCL
SPARE PRIME (tbc)
(TBC) LCL
SPARE REDUNDANT (tbc)
(TBC) LCL
Table 3.9-2: Heater Interface Summary
3.9.3.2 Heater Switch Output Characteristics
PCDU-251/Created/T,A,R
In the case of an overcurrent event in a heater LCL, which exceeds the specified trip-off current or
during switch-on of the load unit, the Latching Current Limiters shall limit the output current for a time
delay of between 8mS ≤ t ≥ 15mS before switching off.
Remark: In case the current limiting times of an existing LCL design are different from what is
specified here, the manufacturer shall propose limits based on his heritage. This shall be not less
than 80% of the trip-off time with the switches remaining de-rated.
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3.9.3.3 TS Output Current
PCDU-2309/Created/T,A,R
Each TS shall be capable of providing the full output current of the LCL.
3.9.3.4 Voltage Drop
3.9.3.5 Operational Voltage Range
PCDU-257/Created/T,A,R
The heater LCLs shall have a bus undervoltage response characteristic as for standard LCLs shown
in specified in PCDU-58 and PCDU-60.
Heater LCLs will be individually defined as essential or non-essential prior to manufacture
3.9.3.6 Initial TS Status
PCDU-259/ERS_410/T,R
The controlling LCL and its associated Transistor Switches shall be in a pre-defined state at initial
switch-on of the PCDU and after recovery from an under-voltage.
3.9.4
Mechanical Actuator/Release Initiator Activation Outlets
3.9.4.1 Configuration of Pyro Modules
PCDU-262/Created/R
Each Pyro module shall have a configuration similar to that below in terms of enable / disable, arming,
device selection, protection and status.
PCDU-1245/Created/R
Pyro Electronic Circuit
Arm Plug
Safe Plug
Pyro User
Arm
Switch
Current
Limiter
Current
Limiter
Selection
Switch
360
Bridgewire
Antistatic
Resistor
Structure
Ground
Mainbus /
Battery
Return
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PCDU-2312/Created/T,A,R
The pyrotechnic and NED firing pulse generation function shall be powered by the spacecraft battery
via suitably sized regulators within the PCDU.
PCDU-2311/Created/A,R
The protection devices in each pyrotechnic module shall ensure that after a single failure the
pyrotechnic circuit cannot impose a constant load or short circuit to the battery. This includes the time
after device activation.
PCDU-2310/Created/R
The requirements of AD 4. shall apply to all pyrotechnic circuits.
PCDU-2313/Created/R
There shall be at least 3 (three) independent safety barriers before a pyrotechnic device can be
activated. No single failure shall cause more than one of these barriers to operate at any time. At
least one of these has to be a mechanical barrier. See AD 4.
PCDU-264/Created/R
For each type of actuator specified in PCDU-274, the PCDU shall provide a nominal and redundant
set of firing lines for pyro device activation or NED activation.
PCDU-265/Created/T,R
Each set shall be protected by suitable means to allow for enable / inhibit switching to the individual
outlets.
PCDU-266/Created/T,R
Each set of pyro outlets ( prime and redundant) shall provide one latch relay for arming / disarming
switching. This may be implemented by relay or solid state switch.
PCDU-267/Created/T,R
Each set of pyro outlets shall provide the required number of mono-stable switches for pyro selection
(switching) as defined in Section 3.9.4.3.
PCDU-268/Created/T,R
Selection switches shall break both the Positive and return lines.
PCDU-269/Created/T,R
All Fire Switches shall be located in the positive line.
PCDU-270/Created/T,R
Command management will be performed within the CDMU
PCDU-271/Created/T,R
The selection switching shall be commanded via the Platform Mil 1553 Bus Interface and shall be of
the mono-stable type. The CDMU command will ensure these switches close before the FIRE
command and open after the FIRE command.
PCDU-272/Created/T,R
The PCDU shall implement Source Circuit Grounding resistors specified within Table 3.9-3 inside the
PCDU.
3.9.4.2 Types of Actuators
PCDU-274/Created/R
The PCDU shall be capable of providing firing lines for the following type of actuators:
·Pyro Initiator devices and Non Explosive Deployment Devices
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3.9.4.3 No. of Outlets
PCDU-276/Created/R
The PCDU shall provide 40 nominal and 40 redundant Pyro/ NED actuation device outlets. The split
between pyrotechnic and NED actuators is TBC.
3.9.4.3.1
Pyro Activation Devices/ Non Explosive Devices
PCDU-278/Created/R
The PCDU shall provide functionality to allow up to 40 nominal and 40 redundant pyrotechnic/ NED
deployment devices.
PCDU-279/Created/R
The electrical characteristics of individual pyro outlets are defined in Table 3.9-3
PCDU-280/Created/R
INTERFACE DATA SHEET
IF Designation:
Pyro Interface
Page 1 / 1
PYR
IF-Code:
Req Source Circuit Specification
Ver.
Iss.
-1
-2
-3
-4
Req
-5
-6
-7
-8
Firing Pulse Duration:
(24 ± 2)ms
Repetition Rate:
> 100ms
Firing Current:
4.5A < Ifire < 6.0A
Grounding Resistor:
1MOhm to structure ground
Receiver Circuit Specification
Max No-Fire Current:
1A for 5 minutes
All Fire Current:
4.0A within 20msec
Input Resistance:
Ri < 1.3Ohm
Isolation Resistance:
> 2MOhm at 250±5% VDC for > 15s
Harness Specification
Ver.
Iss.
-9
-10
Wiring Type:
Antistatic Resistor
Twisted Shielded Pair (TSP)
300Ohm < RAS < 390Ohm
R
Fault Voltages shall be verified by Worst Case Analysis.
Table 3.9-3: Pyro Activation Device Characteristics
PCDU-1301/Created/R
The electrical characteristics required for the NED actuation are detailed below
A typical heater style of NED requires 1A for 1 minute (tbc)
3.9.4.4 Separation of nom. and red. functions
PCDU-288/Created/R
Nominal and redundant functions shall be implemented on distinct boards / modules.
PCDU-1315/Created/T,A,R
Pyrotechnic pulse driver design shall be compliant with ECSS-E-30 Part 6A (AD 4.)
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3.9.4.5 Selection Switch Commanding
PCDU-290/Created/R
If the Inhibit switch functions are implemented using relays, they shall be mounted in orthogonally
perpendicular axes to each other.
3.9.4.6 Commanding Characteristics
PCDU-292/Created/T,A,R
All activation commanding shall be performed via the Mil 1553 bus by commands from the CDMU.
Protection functions for firing of the Pyro module shall be 5.5A (TBC), current limiting time shall be 30
ms (TBC).
3.9.4.7 Simultaneous Operation of Pyros/Release Initiator
PCDU-294/Created/T,R
It shall be possible to operate both the Nominal and Redundant sides of a pyro device simultaneously
from both N and R drives.
3.9.4.8 Cross-strapping;
PCDU-298/Created/T,R
Each selection relay and fire switch shall be commandable via both Platform Mil 1553 Bus Interface
units.
3.9.4.9 Independent Control;
PCDU-300/Created/R
The fire and select functions shall be independent
3.9.4.10
Freewheeling Diodes;
PCDU-302/Created/T,R
On each nominal and redundant section, redundant free-wheeling diodes shall be implemented
between both polarities of the power lines, at the initiator side of the selection relays, within the
PCDU.
3.9.4.11
Status Signals;
PCDU-304/Created/T,A,R
The status monitoring of the Arm Switches, all Selection relays and the Fire protection devices along
with the Fire current telemetry during the firing sequence shall be provided to the Platform Mil 1553
Bus interface.
The Fire current telemetry for the NED actuators shall consist of a fixed number of samples (256 tbc)
compatible with pyro actuator current monitoring, taken at a variable rate depending on the NED
device. Data shall be provided from at least 200 us before the pulse up to the end of the designated
pulse duration. The data shall be buffered and read out in TM on command. 8 bit current resolution
shall be provided.
PCDU-2304/Created/T,R
The PCDU shall provide a latched TM parameter to indicate that a pyrotechnic fire pulse has been
generated
3.9.5
Auxiliary Power Supply
3.9.5.1 Auxiliary Supplies;
PCDU-307/Created/R
The command and control power supply and Platform Mil 1553 Bus interface function shall be
independently powered and can be cold redundant.
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3.9.5.2 Auxiliary Supply Configuration Commands;
PCDU-309/Created/T,R
The PCDU shall be able to receive and process High Priority Commands (I/F type SHP) for switching
on or off the auxiliary supplies for the Platform Mil 1553 Bus interfaces.
For each of the commands specified, the PCDU shall provide redundant receiver interfaces.
3.9.5.3 Platform Mil 1553 Bus I/F Power;
PCDU-311/Created/R
Each of the Platform Mil 1553 Bus I/F's (nom. and redundant) shall be supplied by a dedicated
auxiliary supply.
3.9.5.4 Regulator Control Power;
3.9.5.5 Protections
PCDU-315/Created/T,A,R
The auxiliary supplies shall include under/over-voltage protection.
The auxiliary supply shall be in an OFF state for an input voltage value as specified in Figure 3.1-1,
and switch on again at an input voltage complying with the requirements of PCDU-52
PCDU-316/ERS_404/T,A,R
The switch OFF of these supplies shall not in any way affect the Bus power generation or the ability to
charge the battery.
PCDU-1227/Created/T,A,R
The PCDU shall ensure that the capability of receiving and executing auxiliary supply commands is
not lost in case of powering off of both interfaces.
3.9.5.6 Auxiliary Supply Protection
PCDU-318/Created/A,R
No failure in the PCDU shall allow the control power consumption to increase by that specified in
PCDU-384.
3.9.5.7 Auxiliary supply failure
PCDU-320/Created/R
Possible failure within the auxiliary supplies shall be covered by the Platform Mil 1553 Bus
reconfiguration commands. This command interface shall not be powered by the switched auxiliary
supply. No failure in the supply shall cause damage to any load connected to it
3.10
Monitoring, Control and Communication
3.10.1 General;
PCDU-323/Created/T,R
The PCDU shall communicate with the Data Management System via two cold redundant Platform Mil
1553 Bus interfaces
PCDU-324/Created/T,R
Each Interface Module shall be supplied by a dedicated auxiliary power supply, switchable by discrete
commands.
PCDU-325/Created/T,R
The Platform Mil 1553 Bus shall be able to
- Receive and decode the serial data strings from the CDMU
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- Acknowledge the data received from the CDMU
- Control the outputs of the PCDU as commanded by the CDMU
- Generate and transmit serial PCDU telemetry data to the CDMU
PCDU-326/Created/T,R
Each Platform Mil 1553 Bus shall interface to both, the nominal and redundant data-bus I/F of the
PCDU.
PCDU-1302/Created/T,R
It shall be possible to activate any redundant function in the PCDU in conjunction with the prime
function for diagnostic purposes, without impacting on the PCDU operation.
3.10.2 Battery Voltage Measurement
3.10.2.1
Battery Voltage Measurement
PCDU-329/ERS_388/T,A,R
The PCDU shall precisely measure the terminal voltage of the battery and provide this data via the
serial link in a digitized 12 bit ( 0 to 33V) format. This data is passed to the CDMU to provide visibility
of the status of the battery via the Mil 1553 Bus.
3.10.2.2
Redundancy
PCDU-332/Created/R
The battery voltage detection shall be one failure tolerant (two sensors / signals) for each side of the
TM/ TC interfaces within the PCDU (4 in total). Telemetry lines will be protected by TBD kohm
resistors at source in the battery.
3.10.2.3
Accuracy
PCDU-334/Created/T,A,R
The maximum error of the battery voltage detection circuit including digitalization error shall be less
than 0.5%
3.10.3 Housekeeping
3.10.3.1
General
PCDU-337/ERS_384/T,A,R
The PCDU shall provide sufficient information of monitoring points to allow for a health check and
FDIR evaluation of the PCDU.
In particular, each of the PCDU Platform Mil 1553 I/F controllers shall provide the following Digital
Status Signals via the serial link:
Source Identification (TM from A or B I/F)
Status of each switchable element.
Status of automatic functions
3.10.3.2
Digitized Analogue Measurement Signals
PCDU-339/ERS_384/T,A,R
Each of the PCDU Platform Mil 1553 I/F controllers shall provide as a minimum (but not be limited to)
the following digitized Analogue Measurement Signals via the serial link:
Current of all inputs, each acquired by redundant means
Currents of all outputs (single sensor)
Battery and Main Bus Voltages
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Internal auxiliary power supply voltage
Internal auxiliary power supply current
Array Regulator currents
BDR currents
BCR currents
PCDU temperatures
Solar Array Temperature (If required for correct operation of PCDU conversion circuitry)
Battery Temperature (If required for correct operation of PCDU conversion circuitry)
Solar Array Voltage / Current
Sufficient thermal and housekeeping data to monitor health and correct operation of the PCDU and
diagnose failures.
3.10.3.3
Current Monitoring Accuracy
PCDU-341/Created/T,A,R
The PCDU shall perform current monitoring with a maximum error, including all contributions, of 3% of
full scale
3.10.3.4
Voltage Monitoring Accuracy;
PCDU-343/Created/T,A,R
The PCDU shall perform voltage monitoring with a maximum error, including all contributions, of 1%
of full scale except for battery voltage and bus voltage when a maximum permitted error, including all
contributions, of 0.5% shall apply.
3.10.3.5
Temperature Monitoring Accuracy;
PCDU-345/Created/T,A
The PCDU shall perform internal temperature monitoring with a maximum error of 2°C
3.11
Battery Connection
PCDU-347/Created/T,R
The PCDU shall provide all interfaces to allow for the Battery connection to the battery charge and
discharge Regulators in order to support the Main Bus and battery charging.
3.12
Operational Requirements
3.12.1 Autonomous Operation
PCDU-358/ERS_411/T,R
The PCDU shall control the Solar Array Power, the battery power, and the bus voltage, (including the
battery charge status) autonomously without the need for control by the CDMU or ground TC
intervention.
3.12.2 Initial Configuration of Regulators
PCDU-360/ERS_403, ERS_404/T,A,R
On initial switch on or recovering from loss of satellite power, and supplied by either the Battery or the
Solar Array, the Main Bus regulation shall be performed autonomously, independent of the
configuration prior to switch-off, and independent of the status of any operational PCDU function
module (e.g. auxiliary supplies).
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PCDU-1275/ERS_399/T,A,R
The PCDU shall safely and correctly start up under any rate of rise of source voltage
3.12.3 Power Recovery
PCDU-362/ERS_403, Created/T,R
After a loss of satellite power, the PCDU shall be able to recover autonomously when the solar panels
are illuminated by the sun. The PCDU shall switch into its default status which allows battery
recharging and a reboot of the electrical distribution system as well as any heaters or loads defined to
be enabled/ON at start up in the PCDU initialization status.
3.12.4 Operation on The Ground
PCDU-364/Created/T,R
The PCDU shall be capable of operation with appropriate electrical ground support equipment during
spacecraft integration, environmental tests, and during launch site preparation phases.
Note: These interfaces shall be via dedicated test connectors unless otherwise specified
3.12.5 Ground Verification
PCDU-366/Created/T,R
All protection elements (including internal protection elements), shall be designed such that they can
be tested at unit level and during unit integration onto the spacecraft.
All circuits and their redundant paths inside the PCDU shall be verifiable during any ground operation
phase, this especially includes all self-compensating redundancy such as majority voters and hot
redundant regulators which shall be testable at spacecraft level such that all necessary paths can be
exercised.
3.13
Failure Tolerance and Redundancy
3.13.1 Single Failure Tolerance
PCDU-370/Created/A,R
No single failure in the PCDU shall lead to a degradation of performance or a loss of function.
3.13.2 Redundant Functions Physical Location
PCDU-373/Created/R
Redundant functions shall be physically separated, as a minimum, in a different package (e.g. PCB,
hybrid, IC), to avoid failure propagation. The physical separation shall ensure that any over
dissipation of the prime function does not affect the redundant one.
3.13.3 Routing of Redundant Functions
PCDU-375/Created/R
Redundant functions shall be routed via redundant harness via physically separated connectors.
PCDU-1316/Created/R
Solar array inputs shall be via redundant harnesses to separate connectors
PCDU-1317/Created/R
Battery input shall be via redundant harness to separate connectors
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
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3.13.4 Other Protection
3.13.5 LCL Command (Cmd) Failure
PCDU-379/Created/A,R
A single failure within the nominal LCL command path in the PCDU (up to the LCL control input) shall
not lead to a non-recoverable commanding of an LCL, by the redundant command path.
3.13.6 Discrete Command (Cmd) I/F Failures
PCDU-381/Created/A,R
Any single failure in a discrete command interface inside the PCDU shall not propagate to other
outputs except those directly related to the command.
3.14
Power Consumption / Dissipation
3.14.1 PCDU Power Consumption
PCDU-384/Created/T,A,R
The PCDU power consumption shall not exceed 21 W when connected to the Battery, with no primary
power bus load connected.
3.14.2 PCDU Power Conditioning Losses
PCDU-386/Created/T,A,R
The averaged primary power losses in the power conditioning part of the PCDU, including the battery
power path, shall not exceed 5% of the power conditioned.
3.14.3 PCDU Power Distribution Losses
PCDU-388/Created/T,A,R
The averaged primary power losses in the power distribution part of the PCDU shall be less than 1%
of the output power. This includes the loss due to the LCL/ FCL
3.14.4 PCDU Power Dissipation
PCDU-390/Created/T,A,R
The orbit average power dissipation of the PCDU in any operational condition shall not exceed a
value resultant from a combination of the values specified above in PCDU-384, PCDU-386 and
PCDU-388.
PCDU-391/Created/A,R
The PCDU contractor shall provide a model (spreadsheet format acceptable) of the following for
system level analysis to allow an estimate to be made for dissipation for any load case. The
parameters to be considered are:
•
Solar Array regulation losses vs Load
•
Battery regulation losses vs Load
•
LCL/ FCL losses vs Load (resistance)
•
Static dissipation loss for each module ( or total PCDU consumption)
PCDU-1303/Created/T,A
Under conditions of constant input power, constant load and constant temperature the PCDU
dissipation shall not vary by more than 2% over any 6 hour period.
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
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UNIT SPECIFIC DESIGN AND INTERFACE REQUIREMENTS
PCDU-394/Created/R
Note, that further requirements are defined in the Product Assurance requirements [AD-2] made
applicable by the Statement of Work (SOW) to the subcontractors.
PCDU-395/Created/R
The General Design and Interface Requirements (GDIR) [AD-1] are applicable as defined in Section
7
4.1 Mechanical Design and Interface Requirements
PCDU-397/Created/R
The PCDU shall comply with the mechanical design requirements of AD-1. See details in GDIR
Applicability Matrix Section 7
4.1.1
Mass
PCDU-402/Created/T,A,R
The unit mass in flight configuration shall be less than 20.0 kg. This shall be verified by mass
measurement on the fully assembled unit.
4.1.2
Envelope
PCDU-404/Created/T,R
The PCDU including mounting feet and connectors (except bonding stud) shall not exceed TBC (to be
proposed by the supplier)
4.2 Thermal Design and Interface Requirements
4.2.1
Unit Thermal Design
PCDU-412/Created/R
The unit exterior surface shall have an infrared emissivity coefficient of greater than or equal to 0.8.
PCDU-1304/Created/R
Heat sink all
around the unit
Unit
Therm al washers
on each unit
fixation foot
Figure 4.2-1: Overview of the thermal environment for internal units
.
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
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Gaia
PCDU-1305/Created/R
The unit thermal design shall consider a heat sink all around the unit (of 4 PI steradian) with a
temperature range defined in AD1.
PCDU-1306/Created/A,R
The unit thermal design shall consider a maximum thermal conductance of 0.015 W/K at each
unit fixation foot (e.g. commensurate with insulation through GFRP washers)
PCDU-1307/Created/I,R
The unit fixation plane shall be left unpainted to minimise radiative coupling with the structure.
PCDU-1309/Created/I,R
All other unit box faces shall have an emissivity greater than 0.8
PCDU-1308/Created/R
To allow re-use of potential off the shelf units, the unit supplier may propose to add a radiator plane
between the unit and the SVM panel as described below :
Heat sink all
around the unit
U nit
Additional
radiator plane
Therm al washers
on each unit
fixation foot
Figure 4.2-2: Alternative unit thermal accommodation with additional radiator plane
PCDU-1310/Created/R
If such alternative unit thermal accommodation is necessary to allow reuse of an existing unit:
4.2.2
•
the size of the additional radiator plane shall be agreed with Gaia prime thermal
architect
•
the upper side of the radiator panel shall have an emissivity higher than 0.8
•
the lower side of the radiator panel shall be left unpainted
Temperature Requirements
PCDU-1311/Created/R
As detailed in AD1
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
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4.3 Electrical Design and Interface Requirements
4.3.1
Electrical Interface Description
PCDU-417/Created/R
The PCDU shall comply with the Electrical design requirements of AD 1. See details in GDIR
Applicability Matrix Section 7
4.3.2
Hardware Data Interface Description
4.3.3
Reliability
PCDU-1313/Created/A
The PCDU design shall achieve a reliability of 0.996 taking into account the periods for
•
on-ground testing and storage as defined in [AD 1].
•
in-orbit operation of 5 years
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
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VERIFICATION REQUIREMENTS
PCDU-433/Created/T,A,I,R
Equipment verification shall be performed in accordance with the detailed requirements contained
within AD-1
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
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PRODUCT ASSURANCE REQUIREMENTS
PCDU-435/Created/R
The PCDU shall be designed, manufactured and tested in accordance with the PA requirements
specified in AD-2
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
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GDIR APPLICABILITY MATRIX
Req No.
PCDU-1320
PCDU-1321
PCDU-1322
PCDU-1323
PCDU-1324
PCDU-1325
PCDU-1327
PCDU-1328
PCDU-1330
PCDU-1331
PCDU-1332
PCDU-1333
PCDU-1335
PCDU-1337
PCDU-1338
PCDU-1339
PCDU-1341
PCDU-1342
PCDU-1343
PCDU-1346
PCDU-1347
Reference
3 General Design and interface Requirements
3.1 General Design Requirements
3.1.1 Lifetime
GDI-31:
The on-ground lifetime of flight hardware is defin ...
GDI-32:
The Unit shall meet the requirements of this speci ...
GDI-33:
The in-orbit lifetime of the satellite is defined ...
GDI-34:
The unit shall be designed with positive margins o ...
GDI-2700:
The units shall be compatible with a storage perio ...
GDI-35:
Maintenance during storage shall be as limited as ...
3.1.2 Design Safety
GDI-37:
The unit shall be designed and fabricated with com ...
GDI-38:
General safety requirements for units are as follo ...
3.1.3 Venting
GDI-41:
The unit shall be able to operate within a pressur ...
GDI-42:
For all relevant thermal hardware, explicitly MLI, ...
GDI-43:
Unless a cavity is hermetically sealed adequate me ...
GDI-44:
Structural members (honeycomb panels, in particula ...
3.1.4 Interchangeability
GDI-46:
All spacecraft units of the same part or configura ...
3.1.5 Identification & Marking
GDI-50:
The unit hardware shall be identified with a namep ...
GDI-2253:
The unit identification nameplate shall be mounted ...
GDI-2254:
For the particular case of connector identificatio ...
3.1.6 Accessibility/Maintainability
GDI-52:
The design of the unit, the position of the connec ...
GDI-53:
The equipment shall be designed to require a minim ...
GDI-54:
No field maintenance, servicing or adjustment shal ...
3.1.7 Transportation, Handling and Storage
3.1.7.1 Transport
GDI-2272:
The unit containers, covers (for optics and expose ...
GDI-2273:
The transport container shall ensure that the envi ...
Applicability
Verif.
Method
Y
R
Y
A,R
Y
R
Y
A,R
Y
Y
R
Y
A
Y
A
Y
A,R
Y
R
Y
R
Y
T,A
Y
R
Y
I
Y
Y
Y
R
Y
R
Y
R
Y
Y
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
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Req No.
Reference
Applicability
PCDU-1348
GDI-2274:
The storage container shall be designed to protect ...
3.1.7.2 Unit packing
GDI-2275:
Where applicable blanking caps shall be fitted to ...
GDI-2276:
All units shall be packaged to ensure that it is s ...
3.1.7.3 Container identification
GDI-2277:
Each container shall be labelled, tagged or marked ...
GDI-2278:
In addition to the above, the container shall also ...
3.1.7.4 Handling
GDI-2271:
Units weighing more than 10 kg shall be equipped w ...
3.1.7.5 Thermally Conductive Materials
GDI-70:
Unless justified and agreed beforehand, any therma ...
3.1.7.7 Seals
GDI-75:
Any seals used shall comply with all the applicabl ...
GDI-76:
Any seals requiring periodic replacement during gr ...
3.1.7.8 Lubricants and Sealants
GDI-78:
No lubricants shall be used without the prior writ ...
3.1.7.9 Screw Locking
GDI-80:
All fasteners used on the unit shall be locked by ...
GDI-2270:
All screw type hardware used on the unit shall be ...
3.2 Mechanical Design and Interface Requirements
GDI-82:
All drawings, specifications and engineering data ...
GDI-83:
Units shall be compliant with ECSS-E30 Part 2A, an ...
GDI-84:
Following testing the unit shall be inspected to c ...
GDI-87:
No unit shall generate microvibration loads at its ...
3.2.1 Structural Design
3.2.1.1 General Requirements
GDI-91:
The following failure modes, for units at all leve ...
GDI-92:
The unit shall be designed to withstand the enviro ...
GDI-2282:
The design of the units handling and transportatio ...
GDI-94:
Wherever practical a fail safe design based on red ...
GDI-95:
In cases where a failsafe design cannot be impleme ...
GDI-2045:
All potential fracture critical items shall be sub ...
Y
PCDU-1350
PCDU-1351
PCDU-1353
PCDU-1354
PCDU-1356
PCDU-1358
PCDU-1360
PCDU-1361
PCDU-1363
PCDU-1365
PCDU-1366
PCDU-1368
PCDU-1369
PCDU-1370
PCDU-1371
PCDU-1374
PCDU-1375
PCDU-1376
PCDU-1377
PCDU-1378
PCDU-1379
Verif.
Method
Y
Y
Y
Y
Y
Y
I,R
Y
R
Y
R
Y
R
Y
I,R
Y
Y
R
Y
R
Y
I
Y
A,R
Y
A
Y
A,R
Y
Y
A
Y
A
Y
A
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
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Req No.
PCDU-1381
PCDU-1382
PCDU-1383
PCDU-1385
PCDU-1386
PCDU-1387
PCDU-1390
PCDU-1391
PCDU-1393
PCDU-1394
PCDU-1395
PCDU-1396
PCDU-1397
PCDU-1398
PCDU-1401
PCDU-1402
PCDU-1403
PCDU-1404
PCDU-1406
PCDU-1407
PCDU-1408
PCDU-1409
PCDU-1410
Reference
3.2.1.2 Mass properties
GDI-2284:
A mass justification shall be provided indicating ...
GDI-98:
All mass estimations shall be accompanied by the d ...
GDI-100:
The mass of an item must be measured with the foll ...
3.2.1.3 Centre of Gravity and Moment of Inertia
GDI-102:
All COG and MOI estimates shall be accompanied by ...
GDI-104:
The unit centre of gravity shall be determined wit ...
GDI-105:
The unit moment of inertia shall be determined wit ...
3.2.1.4 Stiffness requirement
3.2.1.4.1 Definitions and General Requirements
GDI-2288:
Units fixed on a rigid interface shall have their ...
GDI-2289:
The stiffness requirements shall be demonstrated t ...
3.2.1.4.2 Mechanical Analysis
GDI-2539:
Finite Elements Models (FEM) shall be prepared to ...
GDI-2540:
The adequacy of the FEM to predict thermo-elastic ...
GDI-2541:
The FEM of the represented item in its launch conf ...
GDI-2542:
The FEM of the equipment shall be verified and cor ...
GDI-2544:
Reduced FEM mathematical models to be employed in ...
GDI-2546:
Adequate models to calculate Centre of Mass and Mo ...
3.2.1.5 Strength Requirements
3.2.1.5.1 Definitions and General Requirements
GDI-2354:
The design load factor philosophy of the GAIA spac ...
GDI-2366:
GAIA equipment mechanical testing shall take into ...
GDI-2367:
GAIA equipment mechanical testing shall take into ...
GDI-2368:
An additional Protoflight Factor of Safety, FOSPF ...
3.2.1.5.2 Margin Of Safety & Safety Factors
GDI-2370:
For all Gaia elements the design factor, FOSD = 1. ...
GDI-2371:
Where design loads are generated using FE analyses ...
GDI-2372:
The GAIA hardware shall be able to withstand, with ...
GDI-2375:
All mechanical elements shall demonstrate positive ...
GDI-2380:
The margins of safety for all elements of the unit ...
Gaia.ASU.SP.ESM.00018
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Applicability
Verif.
Method
Y
Y
T
Y
T
Y
A
Y
T,A
Y
A
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
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Req No.
Reference
Applicability
PCDU-1411
GDI-2381:
All bolts shall be sized to prevent sliding under ...
GDI-2502:
Initially conservative friction coefficients regar ...
GDI-2382:
Wherever applicable, rules for general design of b ...
GDI-2383:
In addition, in case of combined loads due to ther ...
GDI-2385:
where T, S and M are applied values including safe ...
GDI-2386:
Method for evaluation of dimensioning loads/stress ...
GDI-129:
The units shall be designed with positive margins ...
GDI-130:
The design loads for the structure elements are to ...
GDI-131:
The internal loads (thermo elastic, pre-stressed m ...
GDI-132:
For the computation of the design loads the maximu ...
GDI-2297:
For sine and random vibrations, the mechanical siz ...
3.2.1.6 Alignment and Stability
GDI-2550:
The stability of the equipment shall comply with r ...
GDI-2548:
The following causes of misalignment shall be anal ...
3.2.2 Design Requirements
3.2.2.1 Attachment Requirements
GDI-160:
For the preliminary determination of the requested ...
GDI-161:
The attachment points shall provide a controlled s ...
GDI-162:
The interface plane flatness of a unit shall be be ...
GDI-163:
The mechanical mounting interface shall be consist ...
GDI-164:
The unit bolts type and number shall be defined to ...
GDI-165:
Unless otherwise specified all units shall be thro ...
GDI-2132:
To minimise CoG uncertainty of the unit when mount ...
GDI-168:
Unless special conditions override, the thickness ...
GDI-169:
For the unit mounting, provision shall be made for ...
GDI-2123:
Unit Lug/Hole Design Requirements:
Unit mounting h ...
GDI-170:
Sufficient clearance shall be allowed between mech ...
GDI-171:
Requirement deleted ...
Y
PCDU-1412
PCDU-1413
PCDU-1414
PCDU-1415
PCDU-1416
PCDU-1417
PCDU-1418
PCDU-1419
PCDU-1420
PCDU-1421
PCDU-1423
PCDU-1424
PCDU-1427
PCDU-1428
PCDU-1429
PCDU-1430
PCDU-1431
PCDU-1432
PCDU-1433
PCDU-1434
PCDU-1435
PCDU-1436
PCDU-1437
PCDU-1438
Verif.
Method
Y
Y
Y
Y
Y
Y
A
Y
A
Y
A
Y
A
Y
Y
Y
Y
A
Y
I,R
Y
I
Y
R
Y
R
Y
I,R
Y
I,R
Y
I,R
Y
I,R
Y
I,R
Y
I,R
Y
A
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
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Req No.
Reference
Applicability
PCDU-1439
GDI-173:
Fasteners shall be procured and tested according t ...
GDI-2599:
Fasteners shall comply with the requirements of EC ...
GDI-2600:
Fasteners smaller than diameter 5 mm shall not be ...
GDI-2598:
Titanium alloy fasteners shall not be used in safe ...
GDI-174:
The Flight equipment shall be able to survive:...
3.2.2.3 Electrical connectors
GDI-2302:
All electrical connectors shall be located at a mi ...
GDI-2303:
Connectors shall be arranged in such a way that th ...
GDI-2304:
Unit shall offer means to mechanically lock male a ...
3.2.3 Mechanical / Optical Interface Control Documents
GDI-183:
The mechanical and optical configuration and its i ...
GDI-184:
Interfaces will be subjected to a formal inspectio ...
GDI-185:
The issues of ICDs have to be released as defined ...
GDI-186:
One of the attachment holes on a unit shall be spe ...
GDI-187:
The unit reference frame shall have its origin at ...
GDI-188:
The unit alignment reference frame shall have its ...
GDI-190:
The dimensioning of the attachment hole pattern sh ...
GDI-191:
Interface Control Drawings shall be provided to th ...
3.2.4 Mechanical Mathematical Model Requirements
3.3 Thermal Design and Interface Requirements
3.3.1 Definition of Temperatures and Terms
3.3.1.1 Radiatively Controlled Unit
GDI-239:
In the frame of GAIA, all units shall be radiativ ...
3.3.1.2 Conductively Controlled Unit
GDI-241:
All units which were conductively controlled in pr ...
3.3.1.3 Isothermal Unit
GDI-244:
For radiative units the temperature difference bet ...
GDI-245:
For conductive units the temperature difference be ...
GDI-246:
For units not fulfilling GDI-244/245 additional th ...
3.3.1.4 Temperature Reference Point (TRP)
GDI-248:
The temperature reference point (TRP) shall be sel ...
Y
PCDU-1440
PCDU-1441
PCDU-1442
PCDU-1443
PCDU-1445
PCDU-1446
PCDU-1447
PCDU-1449
PCDU-1450
PCDU-1451
PCDU-1452
PCDU-1453
PCDU-1454
PCDU-1455
PCDU-1456
PCDU-1461
PCDU-1463
PCDU-1465
PCDU-1466
PCDU-1467
PCDU-1469
Verif.
Method
I
Y
Y
Y
Y
A
Y
Y
Y
Y
A
Y
T,I
Y
A
Y
R
Y
R
Y
R
Y
A
Y
R
Y
R
Y
R
Y
R
Y
R
Y
R
Y
R
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
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Req No.
PCDU-1472
PCDU-2242
PCDU-2243
PCDU-2244
PCDU-1474
PCDU-1475
PCDU-1477
PCDU-1478
PCDU-1480
PCDU-1481
PCDU-1482
PCDU-1483
PCDU-1484
PCDU-1487
PCDU-1488
PCDU-1489
PCDU-1490
PCDU-1491
PCDU-1492
PCDU-1493
PCDU-1494
PCDU-1495
PCDU-1496
Reference
3.3.2 Thermal Interface Requirements
3.3.2.1 Conductive Interface
GDI-252:
The mounting interface shall comply with the mecha ...
GDI-253:
Unit mounting areas shall not be painted or anodis ...
GDI-254:
All units dissipating significantly through their ...
GDI-255:
Local heat flux shall not be greater than 1.5x spe ...
3.3.2.2 Radiative Interface
GDI-258:
Units shall be designed with an emittance > 0.8 (b ...
GDI-2582:
Units shall demonstrate compliance to their design ...
3.3.2.3 Internal Temperature Monitoring
GDI-260:
Temperature monitoring of selected points within a ...
GDI-261:
The location, type and electrical interface of all ...
3.3.3 Thermal Design Requirements
GDI-2657:
The units shall take into account the following de ...
GDI-263:
The units shall be designed such that all internal ...
GDI-264:
Hot spots on the external surface of the unit are ...
GDI-2656:
In the absence of any uncertainty analysis an init ...
GDI-2079:
For units located outside of the Focal Plane Assem ...
3.3.4 Thermal Control
3.3.4.1 General
GDI-2555:
The equipment thermal control shall comply with EC ...
GDI-2556:
The equipment thermal control shall be achieved pr ...
GDI-2557:
The equipment thermal control design shall permit ...
GDI-2558:
The equipment thermal control must be testable on ...
GDI-2559:
If special equipment is required to evacuate the h ...
GDI-2560:
No thermal control item shall prevent the spacecra ...
GDI-2561:
Deviations and temporal degradations from the nomi ...
GDI-2562:
A Thermal Reference Point (TRP) shall be defined a ...
GDI-2563:
The TRP temperature also called "interface tempera ...
GDI-2564:
In addition, the TRP temperature shall be monitore ...
Gaia.ASU.SP.ESM.00018
Issue 1
Page 52 of 81
Applicability
Verif.
Method
Y
A
Y
R
Y
R
Y
A
Y
R
Y
Y
R
Y
R
Y
Y
A
Y
A,R
Y
Y
A,R
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
Gaia
Gaia.ASU.SP.ESM.00018
Issue 1
Page 53 of 81
Req No.
Reference
Applicability
PCDU-1497
GDI-2565:
The equipment thermal control shall include and mo ...
GDI-2566:
The design limits of units are equal to the qualif ...
GDI-2567:
The design limits of units are equal to the accept ...
3.3.4.2 Thermal Analysis
GDI-2552:
Mathematical models in ESARAD and ESATAN shall be ...
GDI-2553:
The Geometrical and Thermal Mathematical Models (G ...
3.3.5 Thermal Interface Control Documents
GDI-267:
All thermal hardware mounted on the unit shall be ...
GDI-269:
All unit thermal interfaces shall be described wit ...
3.3.6 Thermal Mathematical Model Requirements
3.3.6.1 Thermal Interface Modeling
GDI-2091:
The use of the ESARAD and ESATAN software packages ...
GDI-272:
The Thermal mathematical model shall be provided f ...
GDI-273:
Units:
All units used in thermal models (geometric ...
3.3.6.2 Thermal Model Correlation
GDI-275:
The detailed thermal model of a unit shall be veri ...
3.3.6.3 Reduced Thermal Model
GDI-277:
The consistency between reduced and detailed therm ...
GDI-278:
The convergence of the thermal models shall be dem ...
3.5 Electrical Design and Interface Requirements
3.5.1 General Requirements
GDI-308:
All electrical performances are specified under Wo ...
GDI-309:
Beginning-Of-Life criteria shall be derived by the ...
3.5.2 Power Interface Requirements (LC & FC)
GDI-2046:
The design of the FCLs and of all essential loads ...
3.5.2.1 Regulated Power Requirements
GDI-338:
All units connected to the fully regulated bus sha ...
GDI-2696:
During all mission phases the spacecraft power bus ...
GDI-2104:
The spacecraft fully regulated bus shall have a no ...
GDI-2103:
For load changes of up to 50% of the nominal load ...
GDI-2133:
The bus voltage shall remain within 5% of its nomi ...
Y
PCDU-1498
PCDU-1499
PCDU-1501
PCDU-1502
PCDU-1504
PCDU-1505
PCDU-1508
PCDU-1509
PCDU-1510
PCDU-1512
PCDU-1514
PCDU-1515
PCDU-1518
PCDU-1519
PCDU-1521
PCDU-1523
PCDU-1524
PCDU-1525
PCDU-1526
PCDU-1527
Verif.
Method
Y
Y
Y
Y
Y
R
Y
R
Y
A,R
Y
A
Y
A
Y
T,A
Y
A
Y
A
Y
R
Y
R
Y
T,A
Y
T,A
Y
T
Y
T,R
Y
T,R
Y
T,R
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
Gaia
Gaia.ASU.SP.ESM.00018
Issue 1
Page 54 of 81
Req No.
Reference
Applicability
PCDU-1528
GDI-339:
If undervoltage protection is implemented by the l ...
GDI-340:
In case of an inductive load, when considering the ...
GDI-341:
The load shall not be irreversibly degraded for an ...
GDI-342:
No fuse protection shall be implemented. ...
GDI-343:
Primary current protection shall not be implemente ...
GDI-344:
The contractor shall design the load side of the L ...
GDI-346:
All power converters shall be designed to allow op ...
GDI-347:
The free-running frequency shall be limited to ±10 ...
GDI-348:
The as designed free-running frequency and frequen ...
GDI-349:
Units connected to LCL's or FCL's shall be designe ...
GDI-1273:
At the point of regulation, the impedance of the v ...
GDI-352:
The contractor shall design his side of the Regula ...
GDI-354:
Following switch-ON, and during input filter charg ...
3.5.2.2 Power Consumption Requirements
GDI-361:
The compliance versus the power allocations shall ...
GDI-362:
For each power interface circuit, the following co ...
GDI-363:
A power consumption test shall be required at temp ...
3.5.2.3 Tolerance to Power Bus Failures
GDI-365:
When a unit is internally redundant, and the suppl ...
3.5.2.4 Initial Electrical Status
GDI-367:
Upon application of power in nominal conditions al ...
3.5.3 Standard Signals
3.5.3.1 General Conventions
GDI-378:
Specified driver (or source) characteristics shall ...
GDI-379:
All data and signal interface drivers shall surviv ...
GDI-380:
The unit shall tolerate active signal I/Fs when un ...
GDI-381:
In case the electrical architecture does foresee c ...
GDI-382:
In case no load is specified, the characteristics ...
3.5.3.2 Harness Capacitance
GDI-391:
Interface signal drivers shall consider the capaci ...
Y
Verif.
Method
T
Y
T,A
Y
R
Y
R
Y
R
Y
T,R
Y
T
Y
T
Y
T
Y
T,A
Y
T,R
Y
T,R
Y
T,R
Y
T,A
Y
T,A
Y
T,R
Y
T,A
Y
T
Y
R
Y
T,A
Y
T,A
Y
T,R
Y
R
Y
A
PCDU-1529
PCDU-1530
PCDU-1531
PCDU-1532
PCDU-1533
PCDU-1534
PCDU-1535
PCDU-1536
PCDU-1537
PCDU-1538
PCDU-1539
PCDU-1540
PCDU-1542
PCDU-1543
PCDU-1544
PCDU-1546
PCDU-1548
PCDU-1551
PCDU-1552
PCDU-1553
PCDU-1554
PCDU-1555
PCDU-1557
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
Gaia
Req No.
PCDU-1560
PCDU-1561
PCDU-1562
PCDU-1563
PCDU-1564
PCDU-1566
PCDU-1567
PCDU-1568
PCDU-1569
PCDU-1570
PCDU-1571
PCDU-1573
PCDU-1574
PCDU-1575
PCDU-1576
PCDU-1577
PCDU-1578
PCDU-1579
PCDU-1580
PCDU-1582
PCDU-1583
PCDU-1584
PCDU-1585
PCDU-1586
Reference
3.5.4 Connectors General Design Requirements
3.5.4.1 Harness
GDI-395:
Cables falling into different EMC classifications ...
GDI-396:
All cable bundles shall be routed as close as poss ...
GDI-397:
In wiring through connectors all leads shall be ke ...
GDI-398:
The DC resistance between the single cable shield ...
GDI-399:
The structure termination of shields shall be made ...
3.5.4.2 Connector Types
GDI-401:
All connectors mounted on units shall be D*MA** co ...
GDI-402:
All flight connectors shall be designed to withsta ...
GDI-2158:
Individual mate/demates shall be recorded in a mat ...
GDI-2157:
The number of times flight connectors are mated / ...
GDI-2156:
If by prior agreement with S/C Prime the number of ...
GDI-403:
Different connector classes shall be implemented i ...
3.5.4.3 Connector Characteristics
GDI-405:
Connectors at interfaces shall be clearly identifi ...
GDI-406:
Connectors shall not be a source of single point f ...
GDI-407:
Equipment or structure-mounted connectors shall be ...
GDI-408:
Male and female connectors shall be mechanically l ...
GDI-409:
Active lines together with their return shall be o ...
GDI-410:
Connectors shall be made of Non magnetic material ...
GDI-411:
For any unit connector which contains a number of ...
GDI-412:
Nominal and redundant lines shall have separated c ...
3.5.4.4 Connector Mounting
GDI-414:
All electrical connectors shall be located at a mi ...
GDI-415:
Connectors shall be arranged in such a way that th ...
GDI-416:
Mechanical methods in conjunction with identificat ...
GDI-417:
Connector savers shall be utilized on all flight s ...
GDI-418:
The connection shield ground pin to case shall be ...
3.5.4.5 Test Connectors
Gaia.ASU.SP.ESM.00018
Issue 1
Page 55 of 81
Applicability
Verif.
Method
Y
I,R
Y
I,R
Y
I,R
Y
T
Y
I,R
Y
R
Y
I,R
Y
R
Y
R
Y
I,R
Y
R
Y
R
Y
R
Y
R
Y
R
Y
I
Y
R
Y
T,R
Y
R
Y
R
Y
R
Y
I,R
Y
R
Y
R
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
Gaia
Gaia.ASU.SP.ESM.00018
Issue 1
Page 56 of 81
Req No.
Reference
Applicability
PCDU-1588
GDI-420:
Test connectors shall have sufficient protection t ...
GDI-421:
Test connectors shall be protected by EMC metal co ...
GDI-422:
The metallic protection cover shall be capable of ...
3.5.5 Standard Interfaces
3.5.5.2 MIL-STD-1553 Bus Interfaces (MIL)
GDI-426:
Each data bus subscriber equipment shall comply wi ...
GDI-427:
All units (BC or RT) shall be configured in long s ...
GDI-2177:
The maximum length of the long stub shall be 6 met ...
GDI-2176:
Only one RT shall be connected to a stub cable. ...
GDI-428:
Each BC and RT (N&R) shall be connected to both 15 ...
GDI-429:
Each stub shall be grounded inside each RT or BC d ...
GDI-430:
The RT address shall be programmable on an externa ...
GDI-431:
The 1553-bus shall be connected on separate connec ...
GDI-2139:
The 1553-bus shall be connected on separate connec ...
GDI-1198:
Unless otherwise agreed with the Prime Contractor, ...
GDI-432:
The 1553-Bus Protocol shall be compliant to the Ga ...
GDI-434:
The unit shall be compatible with the setup as def ...
3.5.5.2.1 BC/RT Test Requirements
3.5.5.2.1.1 Qualification Test
GDI-2460:
For each part assessed as already qualified, the s ...
GDI-2462:
These tests shall be performed only in ambient con ...
GDI-2463:
...
GDI-2464:
...
GDI-2465:
...
GDI-2466:
...
GDI-2467:
...
GDI-2468:
...
GDI-2469:
...
GDI-2470:
...
Y
Verif.
Method
R
Y
I,R
Y
R
Y
R
Y
R
Y
I,R
Y
I,R
Y
I,R
Y
R
Y
R
Y
R
Y
R
Y
R
Y
R
Y
R
PCDU-1589
PCDU-1590
PCDU-1593
PCDU-1594
PCDU-1595
PCDU-1596
PCDU-1597
PCDU-1598
PCDU-1599
PCDU-1600
PCDU-1601
PCDU-1602
PCDU-1603
PCDU-1604
PCDU-1607
PCDU-1608
PCDU-1609
PCDU-1610
PCDU-1611
PCDU-1612
PCDU-1613
PCDU-1614
PCDU-1615
PCDU-1616
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
Gaia
Gaia.ASU.SP.ESM.00018
Issue 1
Page 57 of 81
Req No.
Reference
Applicability
PCDU-1617
GDI-2471:
...
GDI-2472:
...
GDI-2473:
...
GDI-2474:
...
GDI-2475:
...
GDI-2476:
...
GDI-2477:
...
GDI-2478:
...
GDI-2479:
...
GDI-2480:
Y
PCDU-1618
PCDU-1619
PCDU-1620
PCDU-1621
PCDU-1622
PCDU-1623
PCDU-1624
PCDU-1625
PCDU-1626
PCDU-1627
PCDU-1629
PCDU-1630
PCDU-1631
PCDU-1632
PCDU-1633
PCDU-1634
PCDU-1635
PCDU-1636
PCDU-1637
PCDU-1638
PCDU-1640
PCDU-1642
PCDU-1644
Note 1: Functional test through 1553B interface ...
GDI-2481:
...
3.5.5.2.1.2 Acceptance Test
GDI-2485:
...
GDI-2486:
...
GDI-2487:
...
GDI-2488:
...
GDI-2489:
...
GDI-2490:
...
GDI-2491:
...
GDI-2492:
...
GDI-2493:
...
GDI-2494:
Note 1: Functional test through 1553B interface ...
3.5.5.6.2 Analogue Telemetry Aquisition (AN2)
GDI-1210:
Analogue Telemetry Acquisition 0V to +5V Interface ...
3.5.5.6.3 Analogue Telemetry Aquisition (AN3)
GDI-1211:
Analogue Telemetry Acquisition -10V to +10V Interf ...
3.5.5.7 Temperature Acquisitions (ANY, ANP, ANF, ANT)
GDI-482:
The signal shall be transmitted via twisted shield ...
Verif.
Method
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
T,R
Y
T,R
Y
R
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
Gaia
Gaia.ASU.SP.ESM.00018
Issue 1
Page 58 of 81
Req No.
Reference
Applicability
PCDU-1645
GDI-483:
The temperature aquisition interface circuitry, as ...
3.5.5.7.1 Thermistor Type1: YSI-44907/-44908 (ANY)
GDI-1215:
Temperature Acquisition Type 1: YSI 44907/YSI-4490 ...
3.5.5.7.2 Thermistor Type2: PT-1000 (ANP)
GDI-487:
Temperature Acquisition Type 2: PT-1000 (ANP) Inte ...
3.5.5.7.3 Thermistor Type3: Fenwell (ANF)
GDI-1216:
Temperature Acquisition Type 3: Fenwall (ANF) Inte ...
3.5.5.7.4 Thermistor Type4: PT-200 (ANT)
GDI-2136:
Temperature Acquisition Type 4: PT-200 (ANT) Inter ...
3.5.5.8 Relay Commands (SHP, EHP, SLP)
GDI-493:
The High Power On/Off Command source shall be refe ...
GDI-494:
The High Power On/Off Command receiver shall be is ...
GDI-495:
The High Power On/Off Command receiver shall be eq ...
GDI-496:
The High Power On/Off Command source shall be shor ...
GDI-1220:
The Standard High Power On/Off Command interface s ...
3.5.5.8.1 Standard High Power On/Off Command (SHP)
GDI-497:
Standard High Power On/Off Command:
The contractor ...
3.5.5.9 Relay Status Acquisitions (RSA)
GDI-1229:
The open/closed status of a relay/switch contact ( ...
GDI-516:
Relay Status Acquisition
The contractor shall desi ...
3.5.5.11 Pyrotechnics (PYR)
3.5.5.11.1 General Concept
GDI-1255:
Items which require pyrotechnic release shall inco ...
GDI-1256:
All EED's shall be initiated via the spacecraft de ...
GDI-1257:
Only qualified initiators shall be accepted for us ...
GDI-1258:
Only one firing command to a single filament shall ...
GDI-1259:
Redundancy shall be provided for each function by ...
GDI-2701:
Nominal and redundant pyrotechnic items shall be p ...
3.5.5.11.2 EED Interface Characteristics
GDI-1264:
Pyro Firing Characteristics
The contractor shall d ...
3.5.5.11.3 Shape Memory Device Interface (SMD)
Y
Verif.
Method
R
Y
T,R
Y
T,R
Y
T,R
Y
T,R
Y
R
Y
R
Y
R
Y
R
Y
R
Y
T,R
Y
R
Y
T,R
Y
R
Y
T,R
Y
R
Y
T,R
Y
R
PCDU-1647
PCDU-1649
PCDU-1651
PCDU-1653
PCDU-1655
PCDU-1656
PCDU-1657
PCDU-1658
PCDU-1659
PCDU-1661
PCDU-1663
PCDU-1664
PCDU-1667
PCDU-1668
PCDU-1669
PCDU-1670
PCDU-1671
PCDU-1673
PCDU-1675
Y
Y
T,R
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
Gaia
Gaia.ASU.SP.ESM.00018
Issue 1
Page 59 of 81
Req No.
Reference
Applicability
PCDU-1677
GDI-2163:
SMD Firing Characteristics:
The contractor shall d ...
3.5.5.11.4 Motor Actuator Device Interface (MDD)
GDI-2161:
Motor Actuator Characteristics:
The contractor sha ...
3.5.5.12 Digital Bi-Level TM Acquisitions (BLD)
GDI-523:
Each bi-level digital channel shall be used to acq ...
GDI-1232:
The OBC shall acquire via the Bi-Level Digital Acq ...
GDI-1233:
Each channel shall be allocated to a specific bit ...
GDI-524:
Bi-level Digital Interface
The contractor shall de ...
3.5.5.14.3.2 Pressure Transducer Supply Interface (PTS)
GDI-1790:
The contractor shall design his part of the Pressu ...
3.5.5.15 Battery Power Interface (PBA)
GDI-2150:
Deleted ...
3.5.5.16 Solar Array Power Interface (PSA)
GDI-2152:
Deleted ...
3.5.6 Electrical Interface Control Document
GDI-558:
Interfaces will be formally controlled within the ...
3.5.7 EMC Requirements
GDI-2154:
In order to achieve compliance with the requiremen ...
3.5.7.1 Bonding
GDI-562:
The bond shall be resistant against corrosion and ...
GDI-563:
Metallic parts of each electrical equipment chassi ...
GDI-564:
Joint faces shall be flat and clean before assembl ...
GDI-565:
All non-electrical equipment shall be bonded to th ...
GDI-566:
Each electrical equipment chassis (case) shall be ...
GDI-567:
Metallic receptacles of connectors shall be electr ...
3.5.7.1.1 Ground Reference Rail
GDI-569:
Electrical bonding throughout CFRP structure shall ...
GDI-2715:
the GRR shall be attahced at less than or equal to ...
GDI-570:
The resistance between any adjacent parts of the G ...
GDI-571:
The resistance between any two points of the GRR s ...
Y
Verif.
Method
T,R
Y
T,R
Y
R
Y
R
Y
R
Y
T,R
Y
T,R
Y
T,R
Y
T,R
Y
R
Y
A,R
Y
R
Y
T
Y
I,R
Y
T
Y
T,R
Y
T
Y
R
Y
R
Y
T,R
Y
T,R
PCDU-1679
PCDU-1681
PCDU-1682
PCDU-1683
PCDU-1684
PCDU-1686
PCDU-1688
PCDU-1690
PCDU-1692
PCDU-1694
PCDU-1696
PCDU-1697
PCDU-1698
PCDU-1699
PCDU-1700
PCDU-1701
PCDU-1703
PCDU-1704
PCDU-1705
PCDU-1706
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
Gaia
Req No.
PCDU-1708
PCDU-1709
PCDU-1710
PCDU-1711
PCDU-1713
PCDU-1714
PCDU-1715
PCDU-1716
PCDU-1717
PCDU-1718
PCDU-1719
PCDU-1720
PCDU-1721
PCDU-1722
PCDU-1723
PCDU-1725
PCDU-1726
PCDU-1729
PCDU-1730
PCDU-1732
PCDU-1733
PCDU-1734
PCDU-1735
Reference
3.5.7.1.2 Cable and Harness Shields
GDI-573:
Where shielded wires are used, the shield shall be ...
GDI-574:
The maximum unshielded length of any shielded wire ...
GDI-575:
Daisy chaining of shield terminations shall be avo ...
GDI-576:
Shields shall not be used as an intentional curren ...
3.5.7.1.3 Structure Parts
GDI-578:
Conductive structure components shall be electrica ...
GDI-1990:
The DC resistance between two mating metal strutur ...
GDI-1991:
Across moveable parts, a bond strap shall be appli ...
GDI-1992:
For CFRP structure without shielding function, the ...
GDI-2093:
This Requirement has been Deleted. ...
GDI-2092:
For CFRP structure used for electromagnetic shield ...
GDI-1989:
Metal fittings shall be bonded to the structure wi ...
GDI-579:
Metal fittings shall be bonded to CFRP with a DC r ...
GDI-2105:
The DC resistance from any metal structure part an ...
GDI-2094:
The DC resistance between any other conductive com ...
GDI-1993:
The GRR shall be attached at less than or equal to ...
3.5.7.1.4 Mechanical Parts
GDI-581:
Mechanical Parts without electrical nor shielding ...
GDI-582:
Mechanical Parts used for electromagnetic shieldin ...
3.5.7.2 Grounding and Isolation
3.5.7.2.1 General
GDI-585:
Each unit shall provide a grounding point, which i ...
GDI-586:
CFRP and SiC shall not be used as an electrical bo ...
3.5.7.2.2 Electrical and Electronic Unit Requirement
GDI-588:
The structure of electrical and electronic unit sh ...
GDI-589:
Openings for drainage, ventilation, etc... shall n ...
GDI-590:
All units shall have a M4 bonding stud ...
GDI-591:
The design of this bonding stud shall allow the co ...
3.5.7.2.3 Insulating materials
Gaia.ASU.SP.ESM.00018
Issue 1
Page 60 of 81
Applicability
Verif.
Method
Y
R
Y
R
Y
R
Y
R
Y
I,R
Y
T,R
Y
T,R
Y
T,R
Y
Y
T,R
Y
T,R
Y
T,R
Y
T,R
Y
T,R
Y
T,R
Y
T,R
Y
T,R
Y
I
Y
R
Y
T
Y
I
Y
I
Y
I
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
Gaia
Gaia.ASU.SP.ESM.00018
Issue 1
Page 61 of 81
Req No.
Reference
Applicability
PCDU-1737
GDI-593:
Space exposed insulating material having a bulk re ...
3.5.7.3 Primary and Secondary Power Lines
3.5.7.3.1 Primary Power Lines
GDI-605:
Isolation: Within all units the primary power buse ...
3.5.7.3.2 Secondary Power Lines
GDI-609:
Grounding: All secondary supplies, inside a unit, ...
GDI-1988:
Equipment with its own dedicated DC - DC converter ...
GDI-610:
Isolation: prior to connection of the unit interna ...
GDI-2106:
After grounding, the impedance between the unit se ...
GDI-611:
Secondaries distributed between units (1 supplier; ...
GDI-612:
Secondaries distributed between units (1 supplier; ...
GDI-614:
Grounding diagram including zero volts interconnec ...
GDI-615:
The symbols in Figure GDI-2107 below shall be used ...
3.5.7.3.3 Signal Interfaces
GDI-617:
Signal circuits interfacing between Satellite equi ...
GDI-618:
Where single-ended signal transmitters are used, i ...
GDI-619:
The use of common signal return paths is only perm ...
3.5.7.3.4 EGSE Grounding and Isolation
GDI-621:
EGSE signal and power circuits interfacing with fl ...
3.5.7.4 Magnetic Moment
GDI-1997:
Each equipment shall be designed and fabricated to ...
3.6 Operations Design and Interface Requirements
3.6.1 Bit / Byte Numbering Convention
GDI-632:
In all project specific documentation including co ...
GDI-634:
During file transfer, within any data type structu ...
3.6.2 Operational Functions
3.6.2.1 Handling of Operational Configuration, Modes and
States
GDI-638:
Mode/State transitions: Transitions from one mode/ ...
GDI-639:
The unit supplier shall identify appropriate modes ...
GDI-640:
At all times, equipment and units shall be in a cl ...
GDI-641:
In addition, modes and the mode transitions manage ...
Y
Verif.
Method
R
Y
R
Y
I,R
Y
T
Y
T,R
Y
T,R
Y
R
Y
R
Y
I
Y
R
Y
R
Y
R
Y
R
Y
R
Y
T,R
Y
T,R
Y
T,R
Y
R
Y
R
Y
T,R
Y
T,R
PCDU-1740
PCDU-1742
PCDU-1743
PCDU-1744
PCDU-1745
PCDU-1746
PCDU-1747
PCDU-1748
PCDU-1749
PCDU-1751
PCDU-1752
PCDU-1753
PCDU-1755
PCDU-1757
PCDU-1760
PCDU-1761
PCDU-1764
PCDU-1765
PCDU-1766
PCDU-1767
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
Gaia
Gaia.ASU.SP.ESM.00018
Issue 1
Page 62 of 81
Req No.
Reference
Applicability
PCDU-1768
GDI-642:
The unit supplier shall identify all internal and ...
GDI-643:
The unit supplier shall identify all transition ti ...
GDI-644:
Mode/State transitions with duration longer than 1 ...
GDI-645:
It shall be possible to command the unit into each ...
3.6.2.2 Commandability
3.6.2.2.1 General
GDI-648:
Commandability is characterised by the set of comm ...
GDI-649:
In operating states of the unit, it shall be possi ...
GDI-650:
In addition, in non-operating states of the unit, ...
GDI-651:
Individual switching of switchable elements (e.g. ...
GDI-652:
The on-board reception, processing and execution o ...
GDI-653:
The function of a command shall not change through ...
GDI-654:
A single command may be used to initialise a chang ...
GDI-655:
Commands with variable bit-fields meaning shall no ...
GDI-656:
Nominal and the redundant functions or equipments ...
GDI-657:
The unit design shall avoid any conflict between a ...
3.6.2.3 Observability
3.6.2.3.1 General
GDI-660:
Observability is characterised by the set of telem ...
GDI-661:
The unit shall provide in its housekeeping telemet ...
GDI-662:
The unit shall provide the necessary instrumentati ...
GDI-663:
Telemetry measurement sensors shall be designed su ...
GDI-664:
It shall be possible to determine the status of th ...
GDI-665:
Essential (high-priority) telemetry data enabling ...
GDI-666:
Telemetry shall always be provided to identify una ...
GDI-667:
Status information in telemetry shall be provided ...
GDI-668:
Any TM processing required at a higher operational ...
GDI-669:
Telemetry shall always be available to determine t ...
GDI-670:
When a key parameter is derived on-board from seve ...
Y
Verif.
Method
R
Y
R
Y
R
Y
T,R
Y
T
Y
T
Y
T
Y
T
Y
T,R
Y
T,R
Y
T,R
Y
R
Y
T
Y
T
Y
R
Y
T,R
Y
T,R
Y
T
Y
T
Y
T,R
Y
T,R
Y
T,R
Y
R
Y
R
Y
T,R
PCDU-1769
PCDU-1770
PCDU-1771
PCDU-1774
PCDU-1775
PCDU-1776
PCDU-1777
PCDU-1778
PCDU-1779
PCDU-1780
PCDU-1781
PCDU-1782
PCDU-1783
PCDU-1786
PCDU-1787
PCDU-1788
PCDU-1789
PCDU-1790
PCDU-1791
PCDU-1792
PCDU-1793
PCDU-1794
PCDU-1795
PCDU-1796
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
Gaia
Req No.
PCDU-1798
PCDU-1799
PCDU-1800
PCDU-1801
PCDU-1802
PCDU-1803
PCDU-1804
PCDU-1805
PCDU-1807
PCDU-1808
PCDU-1809
PCDU-1810
PCDU-1811
PCDU-1812
PCDU-1813
PCDU-1814
PCDU-1816
PCDU-1817
PCDU-1818
PCDU-1819
PCDU-1820
PCDU-1822
PCDU-1824
PCDU-1825
Reference
3.6.2.3.2 Telemetry Acquisition
GDI-672:
The TM acquisition process by the data bus shall n ...
GDI-673:
The unit design shall avoid any conflict between t ...
GDI-674:
TM acquisitions with conditional meaning shall not ...
GDI-675:
The value of a telemetry parameter shall be transm ...
GDI-676:
Analog TM Acquisition:
Analog TM acquisitions sha ...
GDI-677:
Acquisition of safety critical analog parameters o ...
GDI-678:
The values of currents or voltages readings shall ...
GDI-679:
The calibration curve of an analog parameter shall ...
3.6.2.3.3 Observability of Hardware Configuration
GDI-681:
At switch on, the configuration of the unit at ele ...
GDI-682:
In case a unit includes several elementary functio ...
GDI-683:
The configuration of any on-board device and any s ...
GDI-684:
Any configuration command register shall be observ ...
GDI-685:
The acquisition of the unit configuration/state sh ...
GDI-686:
The acquisition of an ON/OFF status for a relay sh ...
GDI-687:
If the unit controls the redundancy configuration ...
GDI-688:
Nominal and redundant functions shall be observabl ...
3.6.2.3.4 Observability of Commands
GDI-690:
Commands to the unit shall be acknowledged in an u ...
GDI-691:
Acknowledgement of commands shall be direct (i.e. ...
GDI-692:
The association between command acknowledgement ac ...
GDI-693:
Successful execution of a command to the unit shal ...
GDI-694:
Failures in the acceptance and /or the execution o ...
3.6.2.3.5 Converters Observability
GDI-696:
Sufficient data to monitor the converters shall be ...
3.6.2.4 Safety Critical and Hazardous Functions
GDI-700:
All critical commands shall be identified at equip ...
GDI-701:
The execution of any unit command or command seque ...
Gaia.ASU.SP.ESM.00018
Issue 1
Page 63 of 81
Applicability
Verif.
Method
Y
T
Y
T
Y
R
Y
R
Y
T,R
Y
R
Y
R
Y
R
Y
T
Y
R
Y
T,R
Y
R
Y
R
Y
R
Y
T
Y
R
Y
R
Y
T,R
Y
I
Y
T,R
Y
T,R
Y
T
Y
A
Y
A
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
Gaia
Gaia.ASU.SP.ESM.00018
Issue 1
Page 64 of 81
Req No.
Reference
Applicability
PCDU-1826
GDI-702:
Commanding of critical commands shall be implement ...
GDI-703:
The status of inhibition of safety critical functi ...
GDI-704:
Units shall provide an unambiguous health status o ...
3.6.2.5 Handling of Memories
GDI-706:
Any part of installed RAM’s shall be readable by m ...
GDI-707:
Any part of installed RAM’s shall be overwriteable ...
GDI-708:
Any part of installed ROM’s shall be readable by m ...
GDI-709:
For failure investigation, it shall be possible to ...
3.6.2.6 Autonomy
GDI-711:
Apart from failure situations, the unit shall oper ...
GDI-712:
All parameters used for autonomous operations and ...
3.6.2.7 Automatic Functions
GDI-714:
It shall be possible to inhibit and to override al ...
GDI-715:
All actions generated by automatic on-board logic ...
GDI-716:
The automatic function design shall be such that n ...
GDI-717:
Telemetry shall be associated to all automatic fun ...
GDI-718:
For all the automatic logic using several criteria ...
GDI-719:
The capability to change all on board logic (hardw ...
3.6.2.9 Fault Management / FDIR
3.6.2.9.1 Unit Fault Protection
GDI-726:
Any unit shall be able to withstand (i.e. remain i ...
GDI-727:
Any unit shall be able to withstand (i.e. remain i ...
GDI-728:
It shall be possible to repeat any command several ...
3.6.2.9.2 Unit Self Tests
GDI-730:
All units that perform regular self-tests shall re ...
3.6.2.9.3 Failure Detection, Isolation and Recovery (FDIR)
Functions
GDI-733:
FDIR functions shall be implemented in a hierarchi ...
GDI-734:
The unit shall automatically detect any failure, w ...
GDI-735:
At unit level failures shall be detectable by adeq ...
GDI-736:
Failure detection algorithms shall report in event ...
Y
Verif.
Method
A,R
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
A,R
Y
T
Y
T
Y
T,R
Y
T,R
Y
T,R
Y
T,R
Y
R
Y
A,R
Y
T,R
Y
A
Y
A,R
PCDU-1827
PCDU-1828
PCDU-1830
PCDU-1831
PCDU-1832
PCDU-1833
PCDU-1835
PCDU-1836
PCDU-1838
PCDU-1839
PCDU-1840
PCDU-1841
PCDU-1842
PCDU-1843
PCDU-1846
PCDU-1847
PCDU-1848
PCDU-1850
PCDU-1852
PCDU-1853
PCDU-1854
PCDU-1855
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
Gaia
Gaia.ASU.SP.ESM.00018
Issue 1
Page 65 of 81
Req No.
Reference
Applicability
PCDU-1856
GDI-737:
Failures which require a reaction time less than 1 ...
GDI-738:
Failure which requires a reaction time between 10s ...
GDI-739:
Failure isolation shall be performed at switchable ...
GDI-740:
Any FDIR actions on unit level shall be reported t ...
GDI-741:
The need for intervention of higher levels to reac ...
3.6.3 Other Requirements
3.6.3.1 Inputs to Design Justification File
GDI-744:
The unit supplier shall provide a design justifica ...
3.6.3.2 Inputs to Operational Database
GDI-746:
The unit supplier shall provide inputs to the Oper ...
GDI-747:
Data to be provided (the list is not exhaustive):
...
3.6.3.3 Operation Manual
GDI-749:
The unit supplier shall provide an Operations Manu ...
GDI-750:
The following standardization (Table GDI-751) shal ...
3.7 Software Design & Interface Requirements
3.7.1 General
GDI-2181:
All sotfware production and test shall follow the ...
GDI-2182:
All on-board software running in sub-systems shall ...
GDI-2183:
The on-board software shall be developed using a h ...
GDI-2184:
The use of a non high-level language code (e.g., a ...
GDI-2185:
The on-board sotware shall be implemented with a l ...
3.7.2 Flight Processor Resource Sizing
GDI-2192:
During development, flight processors providing co ...
GDI-2193:
Any on-board software shall provide the capability ...
GDI-2194:
The resource utilisation monitor shall be availabl ...
GDI-2196:
Sizing of the software resources shall be done in ...
3.7.3 Robustness
3.7.3.1 Infinite Loops
GDI-2197:
The on-board software shall protect itself against ...
GDI-2218:
Whenever possibility of Warm Restart is implemente ...
3.7.3.2 Overload
Y
Verif.
Method
T,A
Y
A,R
Y
T,A
Y
T,R
Y
T,A,R
Y
R
Y
R
Y
R
Y
R
Y
R
Y
R
Y
R
Y
R
Y
A
Y
R
Y
T,A
Y
T,R
Y
T,R
Y
T,A
PCDU-1857
PCDU-1858
PCDU-1859
PCDU-1860
PCDU-1863
PCDU-1865
PCDU-1866
PCDU-1868
PCDU-1869
PCDU-1872
PCDU-1873
PCDU-1874
PCDU-1875
PCDU-1876
PCDU-1878
PCDU-1879
PCDU-1880
PCDU-1881
PCDU-1884
PCDU-1885
Y
Y
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
Gaia
Gaia.ASU.SP.ESM.00018
Issue 1
Page 66 of 81
Req No.
Reference
Applicability
PCDU-1887
GDI-2198:
Any on-board software product shall provide a tabl ...
GDI-2199:
If and only if the overload situation cannot be ab ...
3.7.4 Events
GDI-2214:
The on-board software shall provide a means to fil ...
GDI-2215:
The on-board software shall maintain counters for: ...
3.7.5 Initialisation
GDI-2226:
Any on-board unit embedding software shall provide ...
GDI-2228:
The Cold Restart shall start execution from a hard ...
GDI-2229:
The Warm Restart shall start from a software comma ...
GDI-2230:
The Warm Restart shall perform a processor reset a ...
GDI-2227:
The Cold Restart and the Warm Restart initialisati ...
GDI-2234:
At a predictible stage of the initialisation, the ...
3.7.6 Testability
GDI-2205:
Any on-board unit embedding software shall provide ...
3.7.7 SW Maintainability
3.7.7.1 Version Number
GDI-2209:
All software products shall store their version nu ...
GDI-2212:
The flight software version number shall be retrie ...
GDI-2208:
The flight software version number shall be modifi ...
3.7.7.2 In Flight SW Modification
GDI-2186:
Any on-board unit embedding software shall support ...
GDI-2187:
The on-board software shall be structured such tha ...
GDI-2231:
Any on-board unit embedding software shall support ...
GDI-2232:
Any on-board unit embedding software shall support ...
GDI-2201:
Any on-board unit embedding software shall be repr ...
3.7.7.3 Ease of SW Operations & Modifications
GDI-2206:
Wherever possible, the software shall be table-dri ...
GDI-2210:
All on-board software data that are anticipated to ...
GDI-2211:
The on-board software shall have knowledge of the ...
GDI-2207:
Software-implemented limits and triggers for anoma ...
3.7.8 SafeGuard Memory (SGM) Maintainability
Y
Verif.
Method
T,A
Y
T
Y
T
Y
T
Y
T,R
Y
T
Y
T
Y
T
Y
T
PCDU-1888
PCDU-1890
PCDU-1891
PCDU-1893
PCDU-1894
PCDU-1895
PCDU-1896
PCDU-1897
PCDU-1898
PCDU-1900
PCDU-1903
PCDU-1904
PCDU-1905
PCDU-1907
PCDU-1908
PCDU-1909
PCDU-1910
PCDU-1911
PCDU-1913
PCDU-1914
PCDU-1915
PCDU-1916
Y
Y
T,R
Y
T
Y
T
Y
T
Y
T
Y
R
Y
T
Y
T
Y
T
Y
R
Y
R
Y
T
Y
T,R
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
Gaia
Gaia.ASU.SP.ESM.00018
Issue 1
Page 67 of 81
Req No.
Reference
Applicability
PCDU-1918
GDI-2223:
In case of Cold Restart, any on-board unit embeddi ...
GDI-2224:
The on-board software shall implement SGM data str ...
3.7.9 Independent SW Validation (ISV)
GDI-2188:
The software components that are critical for the ...
3.7.10 SW Maintenance Products
GDI-2189:
All on-board software, including new and reused SW ...
GDI-2190:
All on-board software resident in ASIC, FPGA, or o ...
GDI-2233:
The SW maintenance environment shall provide the m ...
GDI-2235:
All software licenses for any software used to dev ...
GDI-2236:
For any on-board unit embedding software, a softwa ...
GDI-2237:
The software development and maintenance facility ...
4 Environment Design Requirements
GDI-2315:
All component of the spacecraft shall be designed ...
4.1 Ground operation phase
GDI-2318:
To allow validation and integration operations, al ...
4.1.1 Thermal and climatic environment
GDI-2320:
For AIV and storage, the climatic conditions shall ...
GDI-2321:
Assembly, integration and verification of flight h ...
GDI-2322:
During transport prior to integration on the space ...
GDI-2323:
The flight hardware transportation containers shal ...
4.1.2 Mechanical environment
GDI-790:
The equipment/assembly and associated transport co ...
GDI-793:
During ground transportation the equipments shall ...
GDI-2327:
All MGSE, containers, transportation and handling ...
GDI-2328:
Sine and random vibrations: the unit transport con ...
GDI-2329:
For containers, the shock requirement is a drop of ...
GDI-2663:
Fatigue loads : in case of a launch from Baikonur, ...
4.2 Launch and Early Operation phase
4.2.1 Pressure Environment
GDI-780:
Units mounted on the S/C shall be designed to with ...
4.2.2 Contamination
Y
Verif.
Method
R
Y
T
Y
R
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T
PCDU-1919
PCDU-1921
PCDU-1923
PCDU-1924
PCDU-1925
PCDU-1926
PCDU-1927
PCDU-1928
PCDU-1930
PCDU-1932
PCDU-1934
PCDU-1935
PCDU-1936
PCDU-1937
PCDU-1939
PCDU-1940
PCDU-1941
PCDU-1942
PCDU-1943
PCDU-1944
PCDU-1947
Y
Y
Y
Y
Y
Y
Y
T,A
Y
T,A
Y
Y
Y
Y
A
Y
T
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
Gaia
Gaia.ASU.SP.ESM.00018
Issue 1
Page 68 of 81
Req No.
Reference
Applicability
PCDU-1949
GDI-782:
Cleanliness requirements are as defined in the PA ...
4.2.3 Mechanical environment
4.2.3.1 Quasi static and low frequency loads
GDI-799:
The quasi-static and low frequency flight limit ac ...
4.2.3.2 Dynamic Environment
4.2.3.2.1 Sinusoidal Environment
GDI-808:
All units mounted on the SCM structure shall be de ...
4.2.3.2.2 Random Environment
GDI-812:
Units shall be designed and tested to withstand, ...
4.2.3.2.3 Acoustic environment
GDI-2338:
Units shall be designed and tested to withstand, ...
4.2.3.2.4 Shock Environment
GDI-818:
Units mounted on the S/C Structure shall be design ...
4.2.4 Thermal environment
GDI-2602:
For units having a view factor to external space, ...
4.2.5 Electromagnetic and radio frequency environment
4.3 In orbit Environment
4.3.1 In orbit mechanical loads
4.3.1.1 Quasi-static & Thermo-elastic Loads
GDI-823:
During orbit and attitude correction manoeuvres, u ...
GDI-2131:
The unit shall be compatible with internal loads g ...
4.3.1.2 Micro-vibrations
GDI-825:
Equipment generating micro-vibrations shall not be ...
4.3.1.3 Dynamical distrurbances
GDI-2677:
In equipment operating mode, any potential equipme ...
GDI-2678:
Once the equipment operational conditions have bee ...
4.3.2 In orbit thermal
GDI-841:
During the In Orbit phase, the spacecraft units TR ...
GDI-2583:
During the In Orbit phase, the spacecraft units wi ...
GDI-2878:
The units listed in the above table shall consider ...
GDI-2603:
For units having a view factor to external space, ...
4.4 Radiation Environment
4.4.1 Introduction
GDI-847:
The radiation environment for the mission is shown ...
4.4.2 GAIA Radiation Environment
4.4.2.1 Galactic Cosmic Ray (GCR) and Solar Energetic
Particle Environment
Y
Verif.
Method
T,R
Y
T,A
Y
T,A
Y
T,A
PCDU-1952
PCDU-1955
PCDU-1957
PCDU-1959
PCDU-1961
PCDU-1963
PCDU-1968
PCDU-1969
PCDU-1971
PCDU-1973
PCDU-1974
PCDU-1976
PCDU-1977
PCDU-1978
PCDU-1979
PCDU-1982
Y
Y
A,R
Y
Y
T,A,R
Y
A
Y
T,R
Y
Y
Y
A,R
Y
Y
Y
Y
A,R
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
Gaia
Gaia.ASU.SP.ESM.00018
Issue 1
Page 69 of 81
Req No.
Reference
Applicability
PCDU-1985
GDI-1946:
The integral LET spectra generated using CREME96 ( ...
4.4.2.2 Trapped Proton Environment during transfer
4.4.2.3 Solar Proton Environment on station
4.4.2.4 Trapped Electron Environment
4.4.3 Long Term Effect Considerations
4.4.3.1 Ionizing Dose Depth Curve
GDI-1966:
The radiation environment for the mission shall be ...
4.4.3.2 Displacement Damage
4.4.4 Rules for Design and Performance
GDI-876:
No protective shielding by the outer panels of the ...
GDI-877:
Unit shall take into account the shielding provide ...
4.4.5 Radiation Sensitive Components
GDI-1969:
The Subcontractor shall implement a Radiation Hard ...
GDI-1970:
All parts shall be reviewed by the Subcontractor t ...
GDI-1971:
The Subcontractor shall issue a Radiation Assessme ...
4.4.5.1 Total Dose
GDI-1975:
The total dose to be taken into account is defined ...
4.4.5.2 Single Event Effects (SEE)
GDI-1977:
Parts are considered SEE immune when the LETth is ...
GDI-1978:
The component shall be designed to tolerate GCR, p ...
4.4.5.3 Single Event Latch-up
GDI-1980:
Devices which are known to be susceptible to latch ...
4.4.5.4 Non Destructive Single Event (Single Event Upset,
Single Event Transient...)
GDI-1982:
Part types shall be acceptable according to the ac ...
GDI-2681:
Memory circuits shall have sufficient error det ...
4.4.5.5 Single Event Burnout (SEB) and Single Event Gate
Rupture (SEGR)
GDI-1984:
For SEB and SEGR, error rate prediction techniques ...
4.4.5.6 Displacement Damage
GDI-1986:
Parametric and functional sensitivity of an EEE pa ...
GDI-1987:
The reset or data corruption occurrence rate due t ...
4.5 EMC Environment
4.5.1 EMC Performance Requirements
4.5.1.1 Inrush Current
GDI-895:
Inrush current at unit switch on shall not exceed ...
4.5.1.2 Voltage Transients
Y
Verif.
Method
R
Y
A,R
Y
R
Y
A,R
Y
R
Y
R
Y
R
Y
A,R
Y
R
Y
T,A,R
Y
A,R
Y
A,R
PCDU-1991
PCDU-1994
PCDU-1995
PCDU-1997
PCDU-1998
PCDU-1999
PCDU-2001
PCDU-2003
PCDU-2004
PCDU-2006
PCDU-2008
PCDU-2009
PCDU-2011
PCDU-2013
PCDU-2014
PCDU-2018
Y
Y
A,R
Y
R
Y
A,R
Y
T,R
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
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Issue 1
Page 70 of 81
Req No.
Reference
Applicability
PCDU-2020
GDI-897:
The transient on the primary power bus distributio ...
GDI-899:
Conducted voltage transients on the primary power ...
4.5.1.3 Conducted Emissions on Regulated Power Bus
4.5.1.3.1 Conducted Emissions on Power Leads,
Frequency Domain
GDI-902:
Conducted narrow band current emissions (different ...
GDI-904:
Conducted narrow band current emissions (common mo ...
GDI-2716:
In case of internal redundancy, conducted emission ...
4.5.1.3.2 Conducted Emissions on Power Leads, Time
Domain
GDI-907:
Time domain conducted differential mode voltage ri ...
GDI-908:
For Primary Power users, time domain conducted emi ...
GDI-2709:
Time domain current emissions shall be < 10% of th ...
GDI-2717:
In case of internal redundancy, time domain emissi ...
4.5.1.4 Conducted Emissions on Secondary Power Lines
4.5.1.4.1 CE for Secondary Power Supply Units, Frequency
Domain
GDI-918:
The maximum voltage emission levels for secondary ...
4.5.1.4.2 CE for Secondary Power Supply Units, Time
Domain
GDI-920:
The voltage ripple and spikes on secondary power s ...
4.5.1.5 Conducted Emissions Signal lines Common Mode
GDI-2711:
Conducted Narrow band conducted emissions (common ...
GDI-2712:
Y
Verif.
Method
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T
PCDU-2021
PCDU-2024
PCDU-2025
PCDU-2026
PCDU-2028
PCDU-2029
PCDU-2030
PCDU-2031
PCDU-2034
PCDU-2036
PCDU-2038
PCDU-2039
PCDU-2041
PCDU-2042
PCDU-2044
PCDU-2046
PCDU-2048
Conducted Emission on Signal Bundle
4.5.2 Radiated Emissions - E field
GDI-922:
The unit shall not exceed the specified limits in ...
GDI-2704:
On board Receiver Notch:
20 dBµV/M between 7190 an ...
4.5.3 Radiated Emissions - H field
GDI-926:
The radiated H field generated by Units, shall be ...
4.5.4 Radiated Emissions Fluctuations - E Field
GDI-2013:
Any specific requirements on E-field will be detai ...
4.5.5 Radiated Emissions Fluctuations - H Field
GDI-2022:
Any specific requirements on H-field will be detai ...
4.5.6 Radiated Susceptibility - E field
Y
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
R
Y
R
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
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Issue 1
Page 71 of 81
Req No.
Reference
Applicability
PCDU-2050
GDI-928:
The unit shall not show any malfunction or deviati ...
GDI-2705:
The unit shall not show any malfunction or deviati ...
GDI-929:
No unit that is powered On at launch shall show an ...
4.5.7 Radiated Susceptibility - H field
GDI-932:
Units shall not be susceptible when submitted to t ...
4.5.8 Units linked by Secondary Power Lines
GDI-934:
When secondary lines power a unit, the unit shall ...
GDI-935:
When a unit delivers secondary lines, the unit sha ...
4.5.9 Conducted Susceptibility Power Lines
4.5.9.1 Conducted Susceptibility Sine Wave - Differential
Mode
GDI-938:
Primary power bus powered units shall not exhibit ...
4.5.9.2 Conducted Susceptibility Sine Wave - Common
Mode
GDI-2000:
Primary power bus powered units shall not exhibt a ...
4.5.9.3 Conducted Susceptibility - Transient
GDI-2007:
The unit shall not exhibit any malfunctions, degra ...
GDI-2009:
Transient Type 1
With reference to (figure GDI-941 ...
GDI-2010:
Transient Type 2
With reference to (figure GDI-941 ...
4.5.9.4 CE / CS on Interface signal lines
GDI-944:
No unit shall exhibit any malfunction, degradation ...
GDI-2089:
The unit shall not exhibit any malfunction, degrad ...
4.5.10 Secondary Power Lines Susceptibility
4.5.10.1 CS Sinewave injection for secondary power
supply units
GDI-949:
The conducted susceptibility specification for sec ...
4.5.10.2 Requirement at subsystem or system level
GDI-951:
In addition, a margin of at least +6dB shall be de ...
4.5.11 DC Magnetic Requirements
GDI-958:
The use of relays shall be limited to the most cri ...
4.5.12 ESD Susceptibility
GDI-962:
The unit shall not be susceptible when submitted t ...
4.5.13.2 Corona Gas Discharge
GDI-2693:
Equipments and sub-systems shall be free from gas ...
Y
Verif.
Method
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T,R
Y
T,R
Y
R
Y
T
PCDU-2051
PCDU-2052
PCDU-2054
PCDU-2056
PCDU-2057
PCDU-2060
PCDU-2062
PCDU-2064
PCDU-2065
PCDU-2066
PCDU-2068
PCDU-2069
PCDU-2072
PCDU-2074
PCDU-2076
PCDU-2078
PCDU-2080
Y
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
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Issue 1
Page 72 of 81
Req No.
Reference
Applicability
PCDU-2081
GDI-2694:
Adequate venting shall be provided to ensure that ...
GDI-2695:
If the above requirements GDI-2693 and GDI-2694 ca ...
4.5.14 Micrometeoroid environement
GDI-2683:
The micrometeoroid environment for the mission sha ...
GDI-2686:
A damage assessment based on the micrometeoroid en ...
5 Unit Level Test Requirements
5.1 General
5.1.1 Test Definition
5.1.1.1 Qualification tests
GDI-967:
Qualification of the design shall be accomplished ...
5.1.1.2 Acceptance Tests
GDI-969:
Environmental acceptance testing shall be performe ...
5.1.1.3 Functional Performance Tests
GDI-971:
The objective of the test item functional performa ...
5.1.2 Test Facilities RequirementsY
GDI-973:
Any test facility to be used within the instrument ...
5.1.2.1 Accuracy of Test Instrumentation
GDI-975:
The accuracy of instrument and test equipment used ...
5.1.2.2 Tolerances of Test Parameters
GDI-977:
The allowed test condition tolerances shall be app ...
5.1.2.3 Facility Ambient Condition
GDI-981:
Unless otherwise specified herein, all measurement ...
5.1.3 Test Execution
GDI-983:
Test execution shall be started only if all starti ...
5.1.4 Success Criteria
GDI-985:
The test is successfully performed if all measurem ...
5.2 Unit Tests
GDI-2679:
The qualification and acceptance tests to be perfo ...
5.2.1 Mechanical Environment Tests
5.2.1.1 Vibration Test Set Up
GDI-989:
The unit under test shall be mounted (to a rigid f ...
GDI-990:
At least one triaxial sensor shall be mounted on t ...
GDI-991:
At least two axis aligned sensors shall be mounted ...
GDI-992:
All units powered on during launch shall be powere ...
5.2.1.2 Test Fixture
Y
PCDU-2082
PCDU-2084
PCDU-2085
PCDU-2090
PCDU-2092
PCDU-2094
PCDU-2096
PCDU-2098
PCDU-2100
PCDU-2102
PCDU-2104
PCDU-2106
PCDU-2108
PCDU-2111
PCDU-2112
PCDU-2113
PCDU-2114
Verif.
Method
Y
Y
Y
Y
T,A
Y
T,A,R
Y
T,A
Y
A,R
Y
A,R
Y
A,I,R
Y
A,I,R
Y
A,I,R
Y
T,A
Y
Y
T
Y
T
Y
T
Y
T
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
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Issue 1
Page 73 of 81
Req No.
Reference
Applicability
PCDU-2116
GDI-995:
The test item shall be attached to the vibration e ...
GDI-996:
The variation of transmissibility between test ite ...
GDI-997:
Adequate fixture design and specimen installation ...
GDI-998:
A pre-test of the empty fixture shall be performed ...
5.2.1.3 Frequency Search
GDI-1000:
Frequency search tests shall be conducted in order ...
GDI-1002:
Frequency search tests shall be conducted along ea ...
5.2.1.4 Vibration Tests Level
GDI-1005:
For units the vibration test levels that are appli ...
5.2.1.5 Sine And Random Vibration Test
GDI-1011:
Sine and random vibration tests shall be performed ...
GDI-1012:
Prior and after sine and random vibration qualific ...
GDI-1013:
Before applying full levels, a test at intermediat ...
GDI-1015:
The vibration facility shall include a shock free ...
5.2.1.6 Shock Tests
GDI-1017:
Units shall demonstrate by test their ability to w ...
GDI-1018:
Prior and after shock tests a low level sine frequ ...
5.2.1.7 Static tests
GDI-1020:
Static tests shall be performed by applying the sp ...
5.2.2 Units Thermal Environment Tests
5.2.2.1 Thermal Test Setup
GDI-1024:
The temperatures shall be selected and controlled ...
GDI-1025:
The test arrangement shall be as shown in Figure G ...
GDI-1026:
The unit shall be bolted to a thermally controlled ...
GDI-1027:
On all external surfaces flight representative the ...
GDI-1028:
The heat sink (HS) plates shall be black painted ( ...
GDI-1029:
The conductive heat sink temperature and the chamb ...
GDI-1030:
For vacuum tests the pressure inside the chamber s ...
5.2.2.2 Thermal Test Sequences
5.2.2.2.1 Qualification Thermal Vacuum
GDI-1034:
Unit’s suppliers shall perform Thermal Vacuum (TV) ...
Y
Verif.
Method
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
A,R
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
T
Y
R
Y
R
Y
R
Y
R
Y
R
Y
R
Y
R
Y
T
PCDU-2117
PCDU-2118
PCDU-2119
PCDU-2121
PCDU-2122
PCDU-2124
PCDU-2126
PCDU-2127
PCDU-2128
PCDU-2129
PCDU-2131
PCDU-2132
PCDU-2134
PCDU-2137
PCDU-2138
PCDU-2139
PCDU-2140
PCDU-2141
PCDU-2142
PCDU-2143
PCDU-2146
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
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Issue 1
Page 74 of 81
Req No.
Reference
Applicability
PCDU-2147
GDI-1036:
The TV test on unit level shall be performed as in ...
GDI-1037:
The qualification temperatures for the different u ...
GDI-1038:
The units shall be tested following the thermal va ...
5.2.2.2.2 Acceptance Thermal Vacuum
GDI-1044:
Unit suppliers shall perform thermal vacuum (TV) a ...
GDI-1045:
The thermal vacuum acceptance test shall be perfor ...
5.2.2.2.3 Protoflight Thermal Vacuum
GDI-1049:
Unit suppliers shall perform thermal vacuum (TV) p ...
GDI-1050:
The thermal vacuum protoflight test shall be perfo ...
5.2.3 Electromagnetic Compatibility Tests
5.2.3.1 General EMC Test Requirements
5.2.3.1.1 EMC Development Test
GDI-1057:
Development tests may be performed to evaluate the ...
5.2.3.1.2 EMC Qualification Test
GDI-1059:
Qualification tests for PFM shall be performed as ...
5.2.3.1.3 EMC Acceptance Test
GDI-1061:
Acceptance tests for FM shall be performed as spec ...
5.2.3.1.4 EMC Integration Test
GDI-1063:
In order to ensure the proper grounding of the sec ...
5.2.3.1.5 Retest Criteria
GDI-1065:
A retest may be required in case a test result is ...
5.2.3.1.6 Pre and Post Test Inspection
GDI-1067:
The pre- and post-test inspection is specified in ...
5.2.3.1.7 Test Sequence
GDI-2155:
The actual EMC test sequence shall be agreed with ...
5.2.3.2 Test Facility
5.2.3.2.1 EMC Test Environment
GDI-1072:
All EMC tests shall be conducted at standard ambie ...
5.2.3.2.2 Capabilities
GDI-1074:
The test facilities used for the EMC test program ...
5.2.3.3 Test Instrumentation
5.2.3.3.1 General Tolerances and Test Parameters
GDI-1077:
The maximum allowable tolerance for the test param ...
5.2.3.3.2 Accuracy of the Test Measurement Equipment
GDI-1079:
The accuracy of measurement equipment and test equ ...
5.2.3.3.3 Special Requirements on the Test Equipment
Y
Verif.
Method
R
Y
R
Y
T,R
Y
T
Y
T,R
Y
T
Y
T,R
Y
T,R
Y
T,R
Y
T,R
Y
T,R
Y
R
Y
R
Y
R
Y
R
Y
R
Y
R
Y
R
PCDU-2148
PCDU-2149
PCDU-2151
PCDU-2152
PCDU-2154
PCDU-2155
PCDU-2159
PCDU-2161
PCDU-2163
PCDU-2165
PCDU-2167
PCDU-2169
PCDU-2171
PCDU-2174
PCDU-2176
PCDU-2179
PCDU-2181
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
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Issue 1
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Req No.
Reference
Applicability
PCDU-2183
GDI-1081:
Grounding of Test Equipment:
Measurement equipment ...
GDI-1082:
Antenna Placement:
For radiated emission measureme ...
GDI-1083:
Receiver Bandwidth:
The following receiver bandwid ...
GDI-1085:
Power Adjustment:
The primary power for unit level ...
5.2.3.3.4 Line Impedance Stabilisation Network (LISN):
GDI-1087:
For the conducted emission and susceptibility test ...
GDI-1090:
The LISN has to be designed and provided by the co ...
GDI-2116:
Derivation of the bus impedance shall be performae ...
5.2.3.3.5 Test Conditions
GDI-1095:
The equipment under test shall be switched on in t ...
GDI-1096:
For emission testing the unit shall operate within ...
GDI-1097:
For susceptibility testing the suitable operationa ...
GDI-1098:
After testing the equipment shall be switched off ...
GDI-1099:
Both operational modes shall provide operational c ...
GDI-1100:
The particular test set-up shall represent the fli ...
5.2.3.3.6 Susceptibility Testing
GDI-2142:
The applicable pass/fail criteria for susceptibili ...
GDI-1103:
Data Acquisition:
The item under test shall be mon ...
5.2.3.4 Specific EMC Test Requirement
5.2.3.4.1 Electrical Bonding
GDI-1107:
The bonding test shall be performed with the unit ...
GDI-1108:
The bonding test shall be performed without any ha ...
5.2.3.4.2 Isolation
GDI-1111:
The isolation test shall be performed with the UUT ...
5.2.3.4.3 Conducted Emissions on Power Lines
5.2.3.4.3.1 CE on Primary Power Lines
GDI-1116:
UUT operation shall be selected in order to maximi ...
GDI-1118:
Ripple and transient interference tests on the pow ...
5.2.3.4.3.2 CE on Secondary Power Lines
Y
Verif.
Method
R
Y
R
Y
R
Y
R
Y
R
Y
T
Y
T
Y
R
Y
R
Y
R
Y
R
Y
R
Y
R
Y
R
Y
T
Y
R
Y
R
Y
R
Y
R
Y
R
PCDU-2184
PCDU-2185
PCDU-2186
PCDU-2188
PCDU-2189
PCDU-2190
PCDU-2192
PCDU-2193
PCDU-2194
PCDU-2195
PCDU-2196
PCDU-2197
PCDU-2199
PCDU-2200
PCDU-2203
PCDU-2204
PCDU-2206
PCDU-2209
PCDU-2210
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
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Issue 1
Page 76 of 81
Req No.
Reference
Applicability
PCDU-2212
GDI-1123:
UUT operation shall be selected in order to maximi ...
GDI-1124:
When the secondary power provider and user need to ...
5.2.3.4.4 Conducted Susceptibility, Signal Harnesses, Bulk
Current Injection
GDI-2090:
The mode selection for susceptibility testing shal ...
5.2.3.4.5 Conducted Susceptibility on Power Lines
GDI-1133:
The mode selection for susceptibility testing shal ...
GDI-1134:
The test set-ups are shown in Figure GDI-1135 (CS0 ...
5.2.3.4.6 Conducted Susceptibility on Secondary Power
Lines
GDI-1140:
The mode selection for susceptibility testing shal ...
GDI-1141:
The test set-ups are shown in Figure GDI-1142 (CS0 ...
5.2.3.4.7 Radiated Emission, Electric Field
GDI-1151:
UUT operation shall be selected in order to maximi ...
5.2.3.4.8 Radiated Emissions, E-Field Fluctuations
5.2.3.4.9 Radiated Emission, Magnetic Field
GDI-1155:
UUT operation shall be selected in order to maximi ...
5.2.3.4.10 Radiated Emissions, Magnetic Field
Fluctuations
5.2.3.4.11 Radiated Susceptibility, Electric Field
GDI-1159:
UUT operation shall be selected in order to maximi ...
5.2.3.4.12 Radiated Susceptibility, Magnetic Field
GDI-1163:
UUT operation shall be selected in order to maximi ...
5.2.3.4.13 Electrostatic Discharge (ESD)
GDI-1167:
UUT operation shall be selected in order to maximi ...
5.2.3.4.14 Magnetic Moment
GDI-1173:
Verification by similarity may be applied to equip ...
5.2.4 Life Test
GDI-1185:
A life test shall be required for all the assembli ...
5.2.5 Space Conditioning
GDI-1187:
Space conditioning shall be performed whenever des ...
GDI-1188:
The contractors shall propose the corresponding te ...
GDI-1189:
For example, but without limitation to, materials ...
Y
Verif.
Method
R
Y
R
Y
T,R
Y
R
Y
T
Y
R
Y
T
Y
R
Y
R
Y
R
Y
R
Y
R
Y
A,R
Y
T,R
Y
T,R
Y
R
Y
T
PCDU-2213
PCDU-2215
PCDU-2217
PCDU-2218
PCDU-2220
PCDU-2221
PCDU-2223
PCDU-2226
PCDU-2229
PCDU-2231
PCDU-2233
PCDU-2235
PCDU-2237
PCDU-2239
PCDU-2240
PCDU-2241
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
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8
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Page 77 of 81
ACCRONYM LIST
AD
Applicable Document
AIT
Assembly Integration and Test
AIV
Assembly Integration Verification
AOCS Attitude and Orbit Control Subsystem
APR
Array Power Regulator
BAT
Battery
BC
Mil 1553 Bus Controller
BCR
Battery Charge Regulator
BDR
Battery Discharge Regulator
CDMU Central Data Management Unit
CGP
Common Ground Point
CMD
Command
CPS
Chemical Propulsion System
DSA
Deployable Solar Array
ECSS European Cooperation for Space Standardization
EGSE Electrical Ground Support Equipment
EIU
Electrical Integration Unit
EMC
Electromagnetic Compatibility
EOC
End Of Charge
EPS
Electrical Power System
ESA
European Space Agency
FCL
Fold-back Current Limiter
FMECA Failure Modes Effects and Criticality Analysis
FSA
Fixed Solar Array
GRR
Ground Reference Rail
HK
House-Keeping
I/F
Interface
ICD
Interface Control Drawing
LCL
Latching Current Limiter
MPPS Maximum Power Point Tracker
MPS
Micro-propulsion System
N/A
Not Applicable
NED
None Explosive Device (Actuator)
PA
Product Assurance
PCDU Power Control and Distribution Unit
PYRO Pyrotechnic Actuator
SHP
Standard High Power Telecommand
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Gaia
TCS
Thermal Control System
TM
Telemetry
Gaia.ASU.SP.ESM.00018
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Gaia
Requirement/Section Cross Reference
Page numbers are the pages where the sections start
PCDU-23 ............ 1.3.1 ................8
PCDU-24 ............ 1.3.1 ................8
PCDU-49 ............ 3.1 ...................13
PCDU-50 ............ 3.1 ...................13
PCDU-51 ............ 3.1 ...................13
PCDU-52 ............ 3.1 ...................13
PCDU-53 ............ 3.1 ...................13
PCDU-56 ............ 3.1 ...................13
PCDU-57 ............ 3.1 ...................13
PCDU-58 ............ 3.1 ...................13
PCDU-59 ............ 3.1 ...................13
PCDU-61 ............ 3.1 ...................13
PCDU-62 ............ 3.1 ...................13
PCDU-63 ............ 3.1 ...................13
PCDU-64 ............ 3.1 ...................13
PCDU-65 ............ 3.1 ...................13
PCDU-66 ............ 3.1 ...................13
PCDU-67 ............ 3.1 ...................13
PCDU-69 ............ 3.2 ...................15
PCDU-70 ............ 3.2 ...................15
PCDU-71 ............ 3.2 ...................15
PCDU-73 ............ 3.3 ...................16
PCDU-74 ............ 3.3 ...................16
PCDU-75 ............ 3.3 ...................16
PCDU-77 ............ 3.4 ...................16
PCDU-78 ............ 3.4 ...................16
PCDU-80 ............ 3.4 ...................16
PCDU-81 ............ 3.4 ...................16
PCDU-82 ............ 3.4 ...................16
PCDU-85 ............ 3.5.1 ................16
PCDU-87 ............ 3.5.1.1 .............17
PCDU-89 ............ 3.5.2 ................17
PCDU-90 ............ 3.5.2 ................17
PCDU-91 ............ 3.5.2 ................17
PCDU-92 ............ 3.5.2 ................17
PCDU-94 ............ 3.5.3 ................17
PCDU-95 ............ 3.5.3 ................17
PCDU-97 ............ 3.5.4 ................18
PCDU-98 ............ 3.5.4 ................18
PCDU-99 ............ 3.5.4 ................18
PCDU-100 .......... 3.5.4 ................18
PCDU-101 .......... 3.5.4 ................18
PCDU-102 .......... 3.5.4 ................18
PCDU-104 .......... 3.5.4 ................18
PCDU-105 .......... 3.5.4 ................18
PCDU-106 .......... 3.5.4 ................18
PCDU-107 .......... 3.5.4 ................18
PCDU-108 .......... 3.5.4 ................18
PCDU-122 .......... 3.6.1.1 .............19
PCDU-123 .......... 3.6.1.1 .............19
PCDU-124 .......... 3.6.1.1 .............19
PCDU-125 .......... 3.6.1.1 .............19
PCDU-127 .......... 3.6.1.1.1...........20
PCDU-128 .......... 3.6.1.1.1...........20
PCDU-129 .......... 3.6.1.1 .............19
PCDU-130 .......... 3.6.1.1.1...........20
PCDU-131 .......... 3.6.1.1.1...........20
PCDU-132 .......... 3.6.1.1.1 .......... 20
PCDU-135 .......... 3.6 ................... 19
PCDU-138 .......... 3.6.1.2 ............. 20
PCDU-139 .......... 3.6.1.2 ............. 20
PCDU-140 .......... 3.6.1.2 ............. 20
PCDU-141 .......... 3.6.1.2 ............. 20
PCDU-142 .......... 3.6.1.2 ............. 20
PCDU-143 .......... 3.6.1.2 ............. 20
PCDU-144 .......... 3.6.1.2 ............. 20
PCDU-147 .......... 3.6.1.2.1 .......... 21
PCDU-148 .......... 3.6.1.2.1 .......... 21
PCDU-151 .......... 3.6.1.4 ............. 23
PCDU-152 .......... 3.6.1.4 ............. 23
PCDU-153 .......... 3.6.1.4 ............. 23
PCDU-155 .......... 3.6.1.5 ............. 23
PCDU-157 .......... 3.6.1.6 ............. 24
PCDU-159 .......... 3.6.1.7 ............. 24
PCDU-161 .......... 3.6.1.8 ............. 24
PCDU-163 .......... 3.6.1.9 ............. 24
PCDU-166 .......... 3.7.1 ................ 24
PCDU-167 .......... 3.7.1 ................ 24
PCDU-171 .......... 3.7.2.1 ............. 25
PCDU-174 .......... 3.7.2.2 ............. 25
PCDU-180 .......... 3.7.2.4 ............. 25
PCDU-181 .......... 3.7.2.4 ............. 25
PCDU-182 .......... 3.7.2.4 ............. 25
PCDU-185 .......... 3.8.1 ................ 26
PCDU-187 .......... 3.8.3 ................ 26
PCDU-188 .......... 3.8.3 ................ 26
PCDU-191 .......... 3.8.4 ................ 26
PCDU-192 .......... 3.8.4 ................ 26
PCDU-193 .......... 3.8.4 ................ 26
PCDU-194 .......... 3.8.4 ................ 26
PCDU-196 .......... 3.8.5 ................ 27
PCDU-204 .......... 3.9.1 ................ 27
PCDU-207 .......... 3.9.1.1 ............. 27
PCDU-209 .......... 3.9.1.2 ............. 27
PCDU-211 .......... 3.9.1.3 ............. 28
PCDU-212 .......... 3.9.1.3 ............. 28
PCDU-213 .......... 3.9.1.3 ............. 28
PCDU-215 .......... 3.9.1.4 ............. 28
PCDU-217 .......... 3.9.1.5 ............. 29
PCDU-218 .......... 3.9.1.5 ............. 29
PCDU-225 .......... 3.9.2.1 ............. 29
PCDU-226 .......... 3.9.2.1 ............. 29
PCDU-228 .......... 3.9.2.2 ............. 29
PCDU-230 .......... 3.9.2.2.1 .......... 30
PCDU-232 .......... 3.9.2.2.2 .......... 30
PCDU-235 .......... 3.9.2.3.1 .......... 30
PCDU-239 .......... 3.9.2.3.2 .......... 30
PCDU-241 .......... 3.9.3 ................ 31
PCDU-242 .......... 3.9.3 ................ 31
PCDU-243 .......... 3.9.3 ................ 31
PCDU-244 .......... 3.9.3 ................ 31
PCDU-245 .......... 3.9.3 ................ 31
PCDU-247 .......... 3.9.3.1 ............. 32
PCDU-251 .......... 3.9.3.2 ............. 32
PCDU-257.......... 3.9.3.5............. 33
PCDU-259.......... 3.9.3.6............. 33
PCDU-262.......... 3.9.4.1............. 33
PCDU-264.......... 3.9.4.1............. 33
PCDU-265.......... 3.9.4.1............. 33
PCDU-266.......... 3.9.4.1............. 33
PCDU-267.......... 3.9.4.1............. 33
PCDU-268.......... 3.9.4.1............. 33
PCDU-269.......... 3.9.4.1............. 33
PCDU-270.......... 3.9.4.1............. 33
PCDU-271.......... 3.9.4.1............. 33
PCDU-272.......... 3.9.4.1............. 33
PCDU-274.......... 3.9.4.2............. 34
PCDU-276.......... 3.9.4.3............. 35
PCDU-278.......... 3.9.4.3.1.......... 35
PCDU-279.......... 3.9.4.3.1.......... 35
PCDU-280.......... 3.9.4.3.1.......... 35
PCDU-288.......... 3.9.4.4............. 35
PCDU-290.......... 3.9.4.5............. 36
PCDU-292.......... 3.9.4.6............. 36
PCDU-294.......... 3.9.4.7............. 36
PCDU-298.......... 3.9.4.8............. 36
PCDU-300.......... 3.9.4.9............. 36
PCDU-302.......... 3.9.4.10........... 36
PCDU-304.......... 3.9.4.11........... 36
PCDU-307.......... 3.9.5.1............. 36
PCDU-309.......... 3.9.5.2............. 37
PCDU-311.......... 3.9.5.3............. 37
PCDU-315.......... 3.9.5.5............. 37
PCDU-316.......... 3.9.5.5............. 37
PCDU-318.......... 3.9.5.6............. 37
PCDU-320.......... 3.9.5.7............. 37
PCDU-323.......... 3.10.1.............. 37
PCDU-324.......... 3.10.1.............. 37
PCDU-325.......... 3.10.1.............. 37
PCDU-326.......... 3.10.1.............. 37
PCDU-329.......... 3.10.2.1........... 38
PCDU-332.......... 3.10.2.2........... 38
PCDU-334.......... 3.10.2.3........... 38
PCDU-337.......... 3.10.3.1........... 38
PCDU-339.......... 3.10.3.2........... 38
PCDU-341.......... 3.10.3.3........... 39
PCDU-343.......... 3.10.3.4........... 39
PCDU-345.......... 3.10.3.5........... 39
PCDU-347.......... 3.11................. 39
PCDU-358.......... 3.12.1.............. 39
PCDU-360.......... 3.12.2.............. 39
PCDU-362.......... 3.12.3.............. 40
PCDU-364.......... 3.12.4.............. 40
PCDU-366.......... 3.12.5.............. 40
PCDU-370.......... 3.13.1.............. 40
PCDU-373.......... 3.13.2.............. 40
PCDU-375.......... 3.13.3.............. 40
PCDU-379.......... 3.13.5.............. 41
PCDU-381.......... 3.13.6.............. 41
PCDU-384.......... 3.14.1.............. 41
PCDU-386.......... 3.14.2.............. 41
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
GAIA_ASU_SP_ESM_00018.doc
Gaia
PCDU-388 .......... 3.14.3 ..............41
PCDU-390 .......... 3.14.4 ..............41
PCDU-391 .......... 3.14.4 ..............41
PCDU-394 .......... 4 ......................42
PCDU-395 .......... 4 ......................42
PCDU-397 .......... 4.1 ...................42
PCDU-402 .......... 4.1.1 ................42
PCDU-404 .......... 4.1.2 ................42
PCDU-412 .......... 4.2.1 ................42
PCDU-417 .......... 4.3.1 ................44
PCDU-433 .......... 5 ......................45
PCDU-435 .......... 6 ......................46
PCDU-1227 ........ 3.9.5.5 .............37
PCDU-1245 ........ 3.9.4.1 .............33
PCDU-1249 ........ 3.1 ...................13
PCDU-1252 ........ 3.5.3 ................17
PCDU-1253 ........ 3.1 ...................13
PCDU-1254 ........ 3.1 ...................13
PCDU-1256 ........ 3.5.1.1 .............17
PCDU-1257 ........ 3.5.4 ................18
PCDU-1258 ........ 3.6 ...................19
PCDU-1259 ........ 3.6 ...................19
PCDU-1260 ........ 3.6 ...................19
PCDU-1261 ........ 3.6.1.1 .............19
PCDU-1262 ........ 3.6.1.1 .............19
PCDU-1263 ........ 3.6.1.1.1...........20
PCDU-1264 ........ 3.6.1.1.1...........20
PCDU-1267 ........ 3.6.1.3 .............22
PCDU-1268 ........ 3.6.1.3 .............22
PCDU-1269 ........ 3.6.1.3 .............22
PCDU-1270 ........ 3.6.1.3 .............22
PCDU-1271 ........ 3.6.1.3 .............22
PCDU-1272 ........ 3.6.1.3 .............22
PCDU-1273 ........ 3.6.1.3 .............22
PCDU-1274 ........ 3.6.1.2.1...........21
PCDU-1275 ........ 3.12.2 ..............39
PCDU-1276 ........ 3.6.1.3 .............22
PCDU-1277 ........ 3.6.1.3 .............22
PCDU-1278 ........ 3.6.1.3 .............22
PCDU-1279 ........ 3.6.1.3 .............22
PCDU-1280 ........ 3.6.1.2.1...........21
PCDU-1283 ........ 3.7.1 ................24
PCDU-1284 ........ 3.7.1 ................24
PCDU-1285 ........ 3.7.1 ................24
PCDU-1286 ........ 3.7.1 ................24
PCDU-1290 ........ 3.8.2 ................26
PCDU-1291 ........ 3.8.2 ................26
PCDU-1293 ........ 3.8.6 ................27
PCDU-1294 ........ 3.9.1.4 .............28
PCDU-1295 ........ 3.9.2.2 .............29
PCDU-1297 ........ 3.9.2.2 .............29
PCDU-1298 ........ 3.9.1.3 .............28
PCDU-1299 ........ 3.9.3 ................31
PCDU-1301 ........ 3.9.4.3.1...........35
PCDU-1302 ........ 3.10.1 ..............37
PCDU-1303 ........ 3.14.4 ..............41
PCDU-1304 ........ 4.2.1 ................42
PCDU-1305 ........ 4.2.1 ................42
PCDU-1306 ........ 4.2.1 ................42
PCDU-1307 ........ 4.2.1 ................42
Gaia.ASU.SP.ESM.00018
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PCDU-1308 ........ 4.2.1 ................ 42
PCDU-1309 ........ 4.2.1 ................ 42
PCDU-1310 ........ 4.2.1 ................ 42
PCDU-1311 ........ 4.2.2 ................ 43
PCDU-1313 ........ 4.3.3 ................ 44
PCDU-1314 ........ 3.9.2.3.2 .......... 30
PCDU-1315 ........ 3.9.4.4 ............. 35
PCDU-1316 ........ 3.13.3 .............. 40
PCDU-1317 ........ 3.13.3 .............. 40
PCDU-2304 ........ 3.9.4.11 ........... 36
PCDU-2306 ........ 3.6.1.3 ............. 22
PCDU-2307 ........ 3.6.1.3 ............. 22
PCDU-2308 ........ 3.6.1.3 ............. 22
PCDU-2309 ........ 3.9.3.3 ............. 33
PCDU-2310 ........ 3.9.4.1 ............. 33
PCDU-2311 ........ 3.9.4.1 ............. 33
PCDU-2312 ........ 3.9.4.1 ............. 33
PCDU-2313 ........ 3.9.4.1 ............. 33
PCDU-2314 ........ 3.6 ................... 19
PCDU-2315 ........ 3.6.1.8 ............. 24
PCDU-2316 ........ 3.6.1.1 ............. 19
PCDU-2317 ........ 3.6.1.1 ............. 19
PCDU-2318 ........ 3.5.4 ................ 18
EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall
not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.
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Gaia.ASU.SP.ESM.00018
Issue 1
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