INTERNAL THALES ALENIA SPACEemits.esa.int/.../MTG/MTG-Generic-ADs/MTG-TAF-SA-SS-0353_02_sig… · INTERNAL THALES ALENIA SPACE – COMMERCIAL IN CONFIDENCE 100173569N-10 Iss ue §

INTERNAL THALES ALENIA SPACE

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ISSUE : 02 PAGE : 2/38

All rights reserved, 2011, Thales Alenia Space

INTERNAL THALES ALENIA SPACE – COMMERCIAL IN CONFIDENCE

100173569N-10

CHANGE RECORDS

Paragraphs Change Record (List of paragraphs modified, new or deleted)

Issue Date Change Record Description Author

Draft 15/09/2010 First issue MTG team

01 08/02/2011 Document updated according to ESA comments during KO meeting MTG team

02 30/05/2011 Document updated according to SRR colocation meeting 05-06/04/2011 and TAS/OHBteleconf dated 11/05/2011

Statistics:

This issue contains 129 requirements published.

he Requirements Change Record lists 26 requirements impacted by issue 02 (17modified + 9 deleted)

Document generated from DOORS 9.2.0.5 and T-REK 5.4.0.3 to Word 2000

MTG team

Requirements Change Record (List of requirements modified, new or deleted, sorted byascending document issue)

Issue

§ PUID Status

Reason of Change CR Requirement Diff

02 3.2.1

[MTG-SA-GDIS-REQ-004 a]

Change

Updated accordingTAS/OHB; GDIS excel fileagreements applied asconfirmed via MH e-maildated 11/05/2011 12:23.

MTG-GAD-AD-GDICR001

The supplier shall provide, on the ICDR itself and on the IDS itself, amaturity table to be updated at each ICDR and/or IDS formal issue asdefined in MTG Requirements for preparing ICDRs and IDS [AD-47C].

02 3.2.2


Change


MTG-GAD-AD-GDICR001

The ICDR and IDS shall be configured as specified in MTGRequirements for preparing ICDsaccording andto IDSapplicable [AD-47C].documentation

02 3.2.3


Deletion


MTG-GAD-AD-GDICR001

02 3.2.4


Deletion


MTG-GAD-AD-GDICR001

02 3.3.1


Deletion


Already covered.

MTG-GAD-AD-GDICR001

02 3.3.2


Deletion


MTG-GAD-AD-GDICR001

02 3.3.2

[MTG-SA-GDIS-REQ-

Deletion

Updated accordingTAS/OHB; GDIS excel fileagreements applied asconfirmed via MH e-mail

MTG-GAD-AD-GDICR001


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Issue

§ PUID Status


017 a] dated 11/05/2011 12:23.

02 3.4


Deletion


MTG-GAD-AD-GDICR001

02 3.7


Change


MTG-GAD-AD-GDICR001

The satellite, instruments, subsystems and units shall be designed topermit a maximum satellite on-groundonground storage of 10 yearsfollowing completion of all AIT activities at satellite level, and prior tolaunch, under conditions as specified in [AD-27C] (Satellite andSubsystem Design Considerations and Requirements for LongTermapplicable Storage)documentation.

02 3.7


Change

Update accordingTAS/OHB agreement e-mail MT dated 05/05/201116:26

Zaxis replaced by allaxes.

MTG-GAD-AD-GDICR001

It shall be possible to perform equipment/sub-system maintenanceoperations within the storage environment withwhatever spacecrafttheZspacecraft axisorientation horizontalis.

02 3.9


Change


MTG-GAD-AD-GDICR001

The overall system design shall ensure that the failed item/function canbe isolated from the main bus power supply.

02 3.9


Deletion


MTG-GAD-AD-GDICR001

02 3.9


Change


Change wording.

MTG-GAD-AD-GDICR001

Each redundant path or function shall meetprovide the full performanceto fulfill the specified requirements.

02 3.9


Change


Supress confirmationmechanism.

MTG-GAD-AD-GDICR001

Design shall be protected against spurious anomaly detection (falsealarm) by filtering and confirmation mechanism.

02 3.11


Deletion


MTG-GAD-AD-GDICR001

02 3.12


Change


CI number added.

MTG-GAD-AD-GDICR001

Each separately identifiable part or sub-assembly shall carry anidentification consisting of at least the following information:

Part/unit name

End item number (this includes the box code)

Serial number and modification index

Model (QM, PFM,FM, ...)

S/W identification code and version (if embedded)

Configuration Item number

Contract number

Quality control stamp (if applicable)

Name and plant of the Manufacturer

Date of manufacture.

02 3. [MTG- Chan Updated according MTG- TheEach identificationconnector label shall be legible with unaided


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Issue

§ PUID Status


12

SA-GDIS-REQ-079 a]

ge TAS/OHB; GDIS excel fileagreements applied asconfirmed via MH e-maildated 11/05/2011 12:23.

Wording changed.

GAD-AD-GDICR001

eyehuman-readable from 0.5 m distance.5m

02 3.13


Change


CI number added.

MTG-GAD-AD-GDICR001

The container for the units shall be labelled, tagged or marked to allowdetailed identification of the contents of the container, with at least thefollowing:

Name of manufacturer

Project name

Unit name / model


Part number

Serial number

Date of manufacture

Purchase order number

Contact number (where applicable)

Quantity or weight (kg)

Any recommendation necessary for the protection of the unit.

02 3.13


Change


Cleanliness class updatedand shock/humidityindicators added.

MTG-GAD-AD-GDICR001

The packing of all unit shall be such that:

Pre-cleaned unit first placed in a bag and sealed within the bag

Protected unit then placed in a second bag with a dehydrating agentand a label stating “open in a contamination controlled environment”

Second bag also sealed

Sealing of both bags performed in clean room conditions, ofcomplyingclasswith 100000ISO-8 rules at least for the first bag, and a dryatmosphere

Double packaged unit placed in a container protected against all risksof degradation during transportation and storage.

Shock and humidity indicators corresponding to adequate definition ofmeasurement range, axes and redundancy level.

02 3.15.1


Change


"In-flight" suppressed.

MTG-GAD-AD-GDICR001

The over sizing of the optical surface dimension shall be determinedand justified by the supplier taking into account manufacturing andalignment inaccuracies and all on flight instabilities.

02 3.15.2


Deletion


MTG-GAD-AD-GDICR001

02 3.15.2


Change


"Avoided" deleted.

MTG-GAD-AD-GDICR001

The use of stain sensitive glasses shall be avoidedprohibited.

02 3.15.2


Change


"Avoided" deleted.

MTG-GAD-AD-GDICR001

The use of optical cements shall be avoided as far aspossibleprohibited.

02 3.15.4

[MTG-SA-GDIS-REQ-

Change

Updated accordingTAS/OHB; GDIS excel fileagreements applied asconfirmed via MH e-mail

MTG-GAD-AD-GDICR001

The optical performance of the unit shall be verifiable on ground underambient pressure and Earth gravity conditions, unless otherwiseexplicitly specified in the relevant unit specification.


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Issue

§ PUID Status


117 a] dated 11/05/2011 12:23.

"Unless" added.

02 3.15.5


Change


"For the relevant....conditions" added andOptical Data Sheetupdated.

MTG-GAD-AD-GDICR001

TheFor the relevant spectral range and environmental conditions, theunit supplier shall provide the optical interface data within a unit opticalinterface control data sheet clearly indicating information as definedbelow:

General optical data parameter values

Pupil

Entrance pupil distance vs. first optical surface

Exit pupil distance vs. last optical surface

Entrance pupil size

Exit pupil size

Object/image

Object location vs. first optical surface

Image location vs. first optical surface

Object height / object FoV

Image height / image FoV

Transmission and wavefront errors

Image flip

Polarisation

Input polarisation

Input polarisation orientation

Output polarisation

Output polarisation orientation

Note : distance between 2 surfaces has to be calculated on optical axisfor assymetric design.

Table 3-1 Optical data interface control data sheet

02 3.15.6


Change


"launch, lifetime andstorage effects" added.

MTG-GAD-AD-GDICR001

Performance analyses shall take into account the diffraction effects,misalignments and manufacturing tolerances, andlaunch theeffects, on-flight effects (zero gravity, radiations, vacuum ...), as well as lifetimeand storage effects.


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100173569N-10

TABLE OF CONTENTS

TABLE OF CONTENTS ................................................................................................................................6

LIST OF FIGURES ..............................................................................................................................................8

LIST OF TABLES ...................................................................................................................................................8

1. INTRODUCTION ...............................................................................................................................................9

1.1 SCOPE .............................................................................................................................................................9

1.2 REQUIREMENT NUMBERING SYSTEM ..................................................................................................................9

2. APPLICABLE DOCUMENTS..........................................................................................................................10

2.1 APPLICABLE DOCUMENTS ................................................................................................................................10

2.2 APPLICABLE NORMS AND STANDARDS ..............................................................................................................10

2.3 REFERENCE DOCUMENTS................................................................................................................................10

2.4 ORDER OF PRECEDENCE .................................................................................................................................10

3. GENERAL DESIGN AND INTERFACE REQUIREMENTS............................................................................11

3.1 ENGINEERING DATA ........................................................................................................................................11

3.2 INTERFACE CONTROL ......................................................................................................................................11

3.2.1 Data maturity status ..............................................................................................................................12

3.2.2 Configuration control .............................................................................................................................12

3.2.3 ICDR .....................................................................................................................................................12

3.2.4 IDS ........................................................................................................................................................12

3.3 PARTS, MATERIAL AND PROCESSES .................................................................................................................13

3.3.1 General .................................................................................................................................................13

3.3.2 Corrosion...............................................................................................................................................14

3.4 HARDWARE PRODUCTION REQUIREMENTS........................................................................................................14

3.5 VENTING ........................................................................................................................................................14

3.6 INTER CHANGEABILITY.....................................................................................................................................16

3.7 LIFETIME AND ON-GROUND STORAGE ...............................................................................................................16

3.8 MAINTAINABILITY, ACCESSIBILITY, REPAIRABILITY AND TESTABILITY....................................................................18

3.9 RELIABILITY, FAULT TOLERANCE AND SINGLE POINT FAILURES ...........................................................................23

3.10 SAFETY ......................................................................................................................................................25

3.11 WORKMANSHIP ...........................................................................................................................................26

3.12 IDENTIFICATION AND PRODUCT MARKING ......................................................................................................26

3.13 HANDLING, PACKING AND TRANSPORTATION .................................................................................................28


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3.14 DEBRIS.......................................................................................................................................................31

3.15 OPTICAL DESIGN AND INTERFACE REQUIREMENTS.........................................................................................32

3.15.1 General optical design ..........................................................................................................................32

3.15.2 Materials................................................................................................................................................32

3.15.3 Coatings ................................................................................................................................................33

3.15.4 Performances........................................................................................................................................34

3.15.5 Optical interface requirements ..............................................................................................................34

3.15.6 Optical mathematical model requirements ...........................................................................................36

4. LIST OF REQUIREMENTS INCLUDING TBC / TBD .....................................................................................38


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LIST OF FIGURES

Figure 3-1 Definition of on-ground and in-orbit lifetime ..............................................................16

LIST OF TABLES

Table 3-1 Optical data interface control data sheet....................................................................35


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1. INTRODUCTION

1.1 Scope

This specification establishes the general design and interface requirements that are to be metby the MTG-I and MTG-S satellites units to ensure the correct hardware performances duringassembly, integration, testing, storage, transportation, launch and orbital operations.

Unit has to be understood as any equipment, assembly (group of units or componentseventually delivered with dedicated structures and thermal control hardware), subsystem orelement (such as platform or instrument) which are assembled before delivery to the next higherlevel.

This specification is at the same level as all other support specifications.

1.2 Requirement numbering system

Each requirement will be unambiguously identified by a requirement identifier that has thefollowing structure:

MTG-SA-GDIS-REQ-nnnn

where nnnn is a sequential number.

The text which is not identified as a requirement can be considered as a guideline or aclarification for the proper use of requirements.

However, figures or tables which are called by a requirement are part of the requirement.


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2. APPLICABLE DOCUMENTS

2.1 Applicable documents

Refer to the list of applicable documents provided in the unit dedicated SOW.

2.2 Applicable norms and standards

Refer to the list of applicable documents provided in the unit dedicated SOW.

2.3 Reference documents

NA

2.4 Order of precedence

In case of conflict between a subsystem/unit specification, this applicable document and allgeneral design requirement specifications, any discrepancy shall be notified to the attention ofthe Prime Contractor for clarification, resolution and approval.

Tailored ECSS supersede the ECSS.


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3. GENERAL DESIGN AND INTERFACE REQUIREMENTS

3.1 Engineering data

# Reference [MTG-SA-GDIS-REQ-001]

All drawings, specifications and engineering data shall only use the International System ofUnits (SI units).

# *


Whenever engineering data from other projects are used, these data shall be identified to allowtraceability.

# *

3.2 Interface control


Each unit and subsystem shall be designed so as to ensure compatibility and proper interactionwith other equipment and subsystems under all specified environmental conditions.

# *

ICDR and IDS, defined hereunder, are the main supports for information exchanges regardingthe interfaces between the equipment and the system. Therefore, it is essential that theircontent and format are clearly defined and their current status explicitly identified, in order toavoid any misunderstanding between the two parties.

The Interface Control Drawing (ICDR) of an equipment is part of its definition file. It contains thecurrent definition of its mechanical and thermal interfaces with the system. All the required dataare supplied in a CAD drawing.

The Interface Data Sheet (IDS) of an equipment is part of its definition file. It contains thecurrent definition of its external electrical interfaces with the system as defined within MTGRequirements for preparing ICDRs and IDS [AD-47C].

The ICDR and the IDS together contain all the interface data between the equipment and thesystem.

It is the responsibility of the equipment supplier to provide and to update the ICDR and IDS inaccordance with all the requirements described in this document and in MTG Requirements forpreparing ICDRs and IDS [AD-47C].


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100173569N-10

3.2.1 Data maturity status

# Reference [MTG-SA-GDIS-REQ-004 a]

The supplier shall provide, on the ICDR itself and on the IDS itself, a maturity table to beupdated at each ICDR and/or IDS formal issue.

# *

3.2.2 Configuration control


The ICDR and IDS shall be configured according to applicable documentation

# *


Initial ICDR’s and IDS’s may use estimated values (clearly identified as an estimated value);final issue of ICDR’s and IDS’s shall contain measured values with associated measurementuncertainty.

# *

3.2.3 ICDR


The unit ICDR shall include at least all the items specified in MTG Requirements for preparingICDRs and IDS [AD-47C].

# *

The unit ICDR will include at least all the items mentionned in applicable documentation.

3.2.4 IDS


The IDS files shall be structured and filled as specified in MTG Requirements for preparingICDRs and IDS [AD-47C].

# *

The IDS files will be structured and filled as described in applicable documentation.


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100173569N-10

Note: The IDS templates are defined in MTG Requirements for preparing ICDRs and IDS [AD-47C].

3.3 Parts, material and processes

3.3.1 General


A standard thermal cycling method is defined in Thermal testing for the evaluation of spacematerials, processes, mechanical parts and assemblies [NDPA 36] but the Contractor shall asnecessary perform, for qualification, specific thermal cycling tests representative of actualqualification temperatures for the application, with at least a factor of 1.5 on the number ofcycles expected until the end of the nominal lifetime (minimum 10 cycles).

# *


The Prime Contractor, Instruments contractor and Platform contractor shall determine whichenvironments will be received by materials and parts used in various locations.

# *

Note: Refer to Environmental Design and Test requirements specification [AD-36C].


ITAR free material and components shall be used unless previously agreed by the Prime.

# *


All parts, materials and processes selected for the satellite shall demonstrate their compatibilitywith MTG on-ground lifetime durations as defined in section 3.7. with minimum refurbishment.

# Parents : [SA-STO-120]*


Adhesives, coatings and non metallic materials selection shall consider the required on-groundlifetime period as defined in section 3.7.



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3.3.2 Corrosion


The selection of a material for corrosion resistance shall be in accordance with Materialselection for controlling stress-corrosion cracking [NDPA 53] and Determination of thesusceptibility of metals to stress-corrosion cracking [NDPA 54].

# *


The selection of a material for corrosion resistance shall take into account the specificenvironment, the design and fabrication of individual and assembled components, compatibilityof dissimilar materials, susceptibility to fretting and crack initiation.

# *

3.4 Hardware production requirements


Each unit delivered for installation, assembly and integration into the satellite for qualification,flight and flight spare(s) shall meet the requirements of this specification, of Electrical DesignRequirements Specification [AD-34C], of Mechanical and Thermal Design RequirementsSpecification [AD-35C], and, in particular, will have passed the inspections and tests describedin the applicable unit specification and in Subcontractor & suppliers PA Requirements document[AD-06C-01].

# *

3.5 Venting


Units shall have suitable venting provision that is equal or higher than 2 mm² hole area per litreof volume.

# *


The diameter of out gassing vents shall be above 1.5 mm and less than 5 mm.

# *


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Outgassing vents shall be close to but not within the unit mounting plane.

# *


For all relevant thermal hardware, explicitly MLI, tapes and heater mats, venting provisions shallbe incorporated.

# *


Venting of all the cavities including the interspacing of the MLI shall be designed to avoiddamaging overpressure during the ascent.

# *


The method of venting shall prevent the release of contaminants toward the sensitivecomponents, i.e. toward the +Zs side.

# *


Unless a cavity is hermetically sealed, adequate means of venting shall be provided in thedesign to prevent the contamination of the cavity by the external environment and the release ofcontaminants from the cavity.

# *


Structural items (honeycomb panels, in particular) shall include provisions to enable venting ofany hermetically sealed volumes during launch ascent and during thermal balance and thermalvacuum tests.

# *


Adequate safety margins shall be demonstrated by analysis or by a 1.5 ATM proof test for itemsthat do not include venting provisions and, as a consequence, are to be treated as sealedcontainers.

# *


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3.6 Inter changeability


Each item of the spacecraft shall be interchangeable in form, fit and function with another itemof the same part number (configuration item number).

# *

3.7 Lifetime and on-ground storage

The lifetime of a unit starts at unit delivery (Delivery Review Board) and ends at the beginning ofthe disposal phase. The satellite on-ground lifetime will be very long due to the missiondeployment scenario spanning over 15 years or so.

Figure 3-1 Definition of on-ground and in-orbit lifetime


The satellite, instruments, subsystems and units shall be designed for a satellite specifiedlifetime of 8.5 years.

# Parents : [SA-LTM-010], [SA-LTM-020], [SA-POW-420], [SA-SE-450]*


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100173569N-10


The satellite, instruments, subsystems and units shall be designed to permit a maximumsatellite onground storage of 10 years following completion of all AIT activities at satellite level,and prior to launch, under conditions as specified in applicable documentation.

# Parents : [SA-LTM-010], [SA-LTM-020], [SA-MTB-090], [SA-POW-420], [SA-SE-450], [SA-STO-110]*

Note: The satellite on-ground storage will start after the successful completion of the Pre-Storage Review (PSR).


The flight hardware shall be designed for an on-ground lifetime extending from the unit delivery(Delivery Review Board) to satellite launch, including storage at any level.

# Parents : [SA-LTM-030], [SA-MTB-090], [SA-POW-420], [SA-SE-450]*

Note: The relevant AIT and storage duration will therefore be added to the maximum satelliteon-ground storage duration (10 years) to compute the on-ground lifetime of each unit.


The AIT phase and Launch preparation maximum duration to be considered for On-groundlifetime shall be as follows:

Platform level

AIT Platform 18 months

Platform storage 6 months

Instrument level

AIT Instrument 15 months

Instrument storage 24 months

Satellite level

AIT satellite 17 months

AIT storage period (before PSR) 6 months

Launch campaign 3 months

Launch preparation delay 6 months minimum

# Parents : [SA-MTB-020]*


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100173569N-10


It shall be possible to perform equipment/sub-system maintenance operations within the storageenvironment whatever the spacecraft orientation is.

# *


Material susceptible to degradation during long term storage, such as adhesives, thermo-opticaland optical properties, shall be clearly identified and submitted to periodic test to demonstrateno degradation during storage.

# *


Test pieces and/or samples needed to support the confirmation that unacceptablematerial/performances degradation has not occurred during storage period, shall be identifiedand delivered for storage close or with satellite.

# *

3.8 Maintainability, accessibility, repairability and testability


The design of the spacecraft and of its constituents shall consider the need for accessibility andthe method to be employed for removal of units, placement of test aids, for equipment requiringadjustment or maintenance with the aim of eliminating or minimizing:

The possibility of injury to personnel

The possibility of damage to equipment or facility

The possibility of incorrect assembly

Task complexity

Use of special tools or equipment

Use of non-standard hardware

Design complexity

The need for special skills

The activity duration.

# *


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100173569N-10


In case of delay during the final phase of the launch preparation, the satellite and itsconstituents shall be able to stay on-ground in the launch configuration, e.g. fully loaded andpressurized, for a minimum duration of 6 months with minimum maintenance activities.


Note: The minimum maintenance corresponds to activities done through the use of umbilicallines or skin connectors, e.g. battery charge, TM/TC health check, pyro disarming.


The design of the satellite shall ensure suitable access to those items that may requireperiodical health check or inspection during the AIT activities and/or long-term on-groundstorage, without the need for extensive disassembly and/or removal of other satellite elements.



The satellite design shall allow for periodic inspection, maintenance and local testing to beperformed during on-ground storage (e.g. exercising of mechanisms to allow lubricantredistribution) without the need to remove equipments or activate the complete satellite.



The satellite design shall facilitate easy access for those equipments that must be removed,replaced, or maintained as part of the long term storage phase or require specialprocedures/inspections.



The need for satellite intervention during the storage period shall be minimised by design.

# Parents : [SA-MTB-090], [SA-STO-160]*


The detailed design and implementation of the satellite structure and the instruments andequipment interfaces shall support multiple assembly and disassembly activities, consistent withthe anticipated AIT and storage needs.



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For alignment critical items, the mechanical interfaces shall be implemented to allow removaland replacement without the need to repeat the optical alignment procedures.



The design of the platform and instrument secondary structure shall be such that removal ofpanels and/or covers required to gain access to internal equipments does not impact the criticalalignments throughout the satellite.



When specific tools are required for alignment or mass reasons, they shall be delivered with theunit and with a written procedure for the proper use of this tool.

# *


It shall be possible to repair, remove or replace any satellite equipment or instrument, should itrequire maintenance, repair or modification, with minimum disturbance to the satellite designelements or activities.



In case a unit configuration hinders the installation and removal of the attachment bolts, the unitsupplier shall provide a kit of tools as a part of the unit MGSE such that the mounting bolts canbe tightened from an accessible position.

# *


The equipment shall be designed to require a minimum of special tools and test equipment tomaintain calibration, perform adjustments and accomplish fault identification.

# *


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Unit including an on board software loaded in a PROM shall allow easy access to this PROM bya trap door or an external plug.

# *


The PROM replacement shall not require a delta-qualification of the unit.

# *


PROM box, if any shall be tested before delivery with levels derived from unit tests by theSubcontractor.

# *


Specific tools and procedure for PROM installation shall be provided by the unit Subcontractor.

# *


Items to be removed before flight (red tag items) shall be visible after integration on thespacecraft.

# *


Items requiring integration for safety, logistical or life reasons, close to the launch, shall beaccessible without removing any equipment from the spacecraft.



Items which require adjustment, servicing or maintenance before launch shall be accessiblewithout removing any equipment from the spacecraft.



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Test/stimulus points shall be accessible without the need to modify the electrical configuration ofan item of equipment.

# *


Test points on equipment shall be protected against damage up to the maximum fault voltagepresent on the connector either coming from the equipment or from the EGSE.

# *


Unintentional connections of test points on equipment to satellite or EGSE ground shall notdamage the equipment.

# *


Unused stimulus points on equipment and payload shall not provoke unexpected operation.

# *


Periodic maintenance requirements during storage and ground life shall:

avoid exchange of components affecting performance of the HW

never affect alignment performances

have a period higher than 6 months

be declared



The spacecraft and its constituting modules/assemblies and sub-assemblies shall survive allenvironmental testing without the need for refurbishment.

# *


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3.9 Reliability, fault tolerance and single point failures


The failure tolerance needs not to be applied to:

Primary structures

Load-carrying structures

Structural fasteners

Load-carrying elements of mechanisms

Pressure vessels

for which fracture control shall be applied based on Fracture requirements [ND 16].

# Parents : [SA-FTF-050]*

Note : Modified requirement, based on Safety requirements [NDPA 16], section 6.4.3.3b.


Hardware failures or software errors shall not cause additional failures with hazardous effects orpropagate to cause the hazardous operation of interfacing hardware.


Note : Derived from Safety requirements [NDPA 16], section 6.5.3a.


The system shall provide failure tolerance and redundancy status information of safety-criticalfunctions.


Note : Derived from Safety requirements [NDPA 16], section 6.5.3a.


Failure containment and redundancy shall comply with section 4.2.1 of Electric and Electronicrequirements [ND 9].

# - Parents : ND-09: [§4.2.1]*


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100173569N-10


A failure in one satellite function/equipment shall not cause a failure or a degradation of anotherfunction/equipment.


Note 1: Additional requirement, derived from Safety requirements [NDPA 16], section 6.5.3a.

Note 2 : The requirement implies:

Implementation of the necessary redundancy to avoid SPF at subsystem/equipment level

The redundant function to not be lost after a single failure of the nominal one (i. e. no failurepropagation between the redundant functions).


No single point failure shall lead to unpredictable behaviour, i.e. unexpected activation ofoutputs or automatic sequences.

# *


No single point failure shall lead to the loss of the instrumentation used for monitoring ofassociated functional path.

# *


The overall system design shall ensure that the failed item/function can be isolated from thepower supply.

# *

Note: Essential loads will not be commanded-off but will incorporate a protection device withinthe dedicated power system unit to isolate the failed function from the main bus.


Where redundancy is implemented, the design shall allow operating and verifying the redundantitem/function independently of the nominal use.

# *


Functional redundancy or protection features shall be verified by test.

# *


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100173569N-10


Each redundant path or function shall provide the performance to fulfill the specifiedrequirements

# *


Design shall be protected against spurious anomaly detection (false alarm) by filtering.

# *

3.10 Safety

Deleted.


All electronic unit guards and covers provided for personnel protection shall be clearly markedto indicate the voltage potential.

# *


All units that represent a hazard to personnel shall be clearly marked.

# *


No single satellite failure (including hardware failure, software failure or human error) shall leadto critical or catastrophic consequences.


Note : Derived from Safety requirements [NDPA 16], section 6.4.2.1b.


No combination of two independent satellite failures or operator errors shall have catastrophicconsequences.


Note : Derived from Safety requirements [NDPA 16], section 6.4.2.1c.


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100173569N-10

3.11 Workmanship


Particular attention shall be paid in the consideration, definition, implementation and inspectionof workmanship standards to:

Contamination

Surface finish

Elimination of sharp edges and burns

Routing and layout of wiring

Part mounting

Joint including soldered connections

Connector assembly

Conformal coating.

# *

3.12 Identification and product marking


Each separately identifiable part or sub-assembly shall carry an identification consisting of atleast the following information:

Part/unit name

End item number (this includes the box code)

Serial number and modification index

Model (QM, PFM,FM, ...)

S/W identification code and version (if embedded)


Contract number

Quality control stamp (if applicable)

Name and plant of the Manufacturer

Date of manufacture.

# *


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All marking shall be in English.

# *


Each connector label shall be human-readable from 0.5m

# *


The location of the identification shall be noted on the Interface Control Drawing for the unit.

# *


The identification label, as any other part of the unit, shall meet all the requirements relevant tothe equipment.

# *


The location and content of the connector identification labels shall be included in the ICDR ofthe relevant unit.

# *

Note: This applies to equipment connectors as well as to interface brackets connectors.


The connector identification label shall be mounted on the connector face and visible wheninstalled on the unit.

# *


Each unit or bracket shall bear visible connector labels closely adjacent to the appropriateconnector to allow a correct mating of the corresponding harness connector.

# *


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For each unit or bracket, the connector identification shall consist in three alphanumericcharacters with:

First character: “J” for fixed (hard-mounted) connectors

Two last characters: 2 digit sequential number starting from 01.

# *


Each mobile connector shall have its identification number marked on the shell or on a sleevearound the wires close to the connector.

# *


For each mobile connector, the connector identification shall consist in seven alphanumericcharacters with:

The first four for unit or bracket identification

The fifth character: “P” for mobile connectors

The two last characters: 2 digit sequential number starting from 01.

# *

3.13 Handling, packing and transportation


The design of the equipment shall make easy integration, transportation and access toconnectors and fixation points for the operators during AIT.

# *


During transportation of hardware, packing and special precautions shall be such that theenvironments specified in Satellite Environmental Design & Tests Requirements Specification[AD-36C] can be withstood.

# *


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Packing provisions shall prevent damage and contamination during transportation.

# *


Special covers shall protect optics, connectors, mounting surfaces subject to alignmentprocedures and all sensitive parts.

# *


The storage container shall be designed to protect the unit without causing deterioration for thespecified storage period.

# *


The container for the units shall be labelled, tagged or marked to allow detailed identification ofthe contents of the container, with at least the following:

Name of manufacturer

Project name

Unit name / model


Part number

Serial number

Date of manufacture

Purchase order number

Contact number (where applicable)

Quantity or weight (kg)

Any recommendation necessary for the protection of the unit.

# *


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The supplier shall ensure that the items to be shipped from his plant are inspected beforerelease and found to be complete, adequately preserved and packaged, correctly marked andaccompanied by all the required documents.

# *


Unit accompanying documentation shall include the EIDP and, attached to the outside of theshipping container, the handling and packing or unpacking procedure and any relevant safetyprocedures.

# *


The supplier shall make provisions for the prevention of damage to items during transportation.

# *


Blanking caps shall be labelled and instructions included in the handling and transportationprocedures to “remove before flight or test” as applicable.

# *


All unit shall be packaged to ensure that it is sealed in a dry atmosphere using non-contaminating materials.

# *


The packing of all unit shall be such that:

Pre-cleaned unit first placed in a bag and sealed within the bag

Protected unit then placed in a second bag with a dehydrating agent and a label stating“open in a contamination controlled environment”

Second bag also sealed

Sealing of both bags performed in clean room conditions, complying with ISO-8 rules at leastfor the first bag, and a dry atmosphere


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Double packaged unit placed in a container protected against all risks of degradation duringtransportation and storage.

Shock and humidity indicators corresponding to adequate definition of measurement range,axes and redundancy level.

# *


Any seals used shall comply with all the applicable requirements of this specification,particularly regarding propellant and simulated propellant compatibility and out-gassing.

# *


Any seals requiring periodic replacement during ground activities, and especially prior to launch,shall be identified to the Customer.

# *


The unit supplier shall provide any procedures and special tooling required for replacement ofseals.

# *

3.14 Debris

Space debris mitigation for Agency projects [ND-47] and European code of conduct for Spacedebris mitigation [ND-48] are applicable, tailored for MTG and reflected as such within thisspecification.


The satellite, instruments, subsystems, platfom and units design and integration shall ensurethat no objects become detached from the satellite during routine deployment and operations,including use of pyrotechnic functions.

# Parents : [SA-DEB-410]*

Note: Any deviation is subject to approval by the Prime Contractor.


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The MTG satellite shall be designed such that the end-of-life measures of disposal andpassivation, can be fulfilled through satellite commanding within a maximum 2 month period.

# Parents : [SA-DEB-420]*

Note: Passivation means to eliminate all stored energy on board of the MTG satellite, e.g.depressurization of He tanks.

3.15 Optical design and interface requirements

3.15.1 General optical design


For each optical surface, the physical dimension shall be oversized along both axes with regardto the useful optical dimension.

# *


The over sizing of the optical surface dimension shall be determined and justified by thesupplier taking into account manufacturing and alignment inaccuracies and all instabilities.

# *

3.15.2 Materials


Glass types and material quality shall be selected to comply with the performance requirementin terms of spectral transmittance and spatial environment.

# *


Glass selection and related optical configuration optimisation shall be performed in accordancewith the environment requirements as defined in Satellite Environmental Design & TestsRequirements Specification [AD-36C].

# *


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100173569N-10


The use of stain sensitive glasses shall be prohibited.

# *


The use of optical cements shall be prohibited.

# *


If use of optical cements is nevertheless necessary, the Contractor shall demonstrate theirqualification to the MTG requirements (ageing, thermal cycles, radiation dose, etc…) andmention their use for other space programs.

# *

3.15.3 Coatings


Coating shall be designed such that performance, as measured at operational conditions onground, are maintained in the space environment within its required limits.

# *


Thermo-optical properties of the coatings shall be compatible with the thermal control designrequirements.

# *


Particular attention shall be paid to the selection of the materials and processes to avoidsensitivity of these coatings to water desorption in vacuum environment, especially for the multilayer coatings, if any.

# *


High efficiency anti-reflective coatings shall be applied to all free refractive surfaces.

# *


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Sensitivity of coatings to polarisation effects associated to the incidence angle shall bedetermined and validated.

# *

3.15.4 Performances


The optical performance of the unit shall be verifiable on ground under ambient pressure andEarth gravity conditions, unless otherwise explicitly specified in the relevant unit specification.

# *


Instrument alignment shall be maintained between the clean room conditions and theoperational space environment.

# *

Note 1: Residual defocus or misalignment induced by ambient air or gravity conditions isacceptable as long as the applicable parameter has been quantified.

Note 2 : Residual amplitudes will be anticipated, quantified and correlated.

Note 3 : The deviation between two different configurations (i.e. from 1g to 0g) will be evaluatedwith an associated accuracy which will be included in the global budget.

3.15.5 Optical interface requirements


For the relevant spectral range and environmental conditions, the unit supplier shall provide theoptical interface data within a unit optical interface control data sheet clearly indicatinginformation as defined below:

General optical data parameter values

Pupil

Entrance pupil distance vs. first optical surface

Exit pupil distance vs. last optical surface

Entrance pupil size

Exit pupil size


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Object/image

Object location vs. first optical surface

Image location vs. first optical surface

Object height / object FoV

Image height / image FoV

Transmission and wavefront errors

Image flip

Polarisation

Input polarisation

Input polarisation orientation

Output polarisation

Output polarisation orientation

Note : distance between 2 surfaces has to be calculated on optical axis for assymetric design.

Table 3-1 Optical data interface control data sheet

# *


The free mechanical aperture of optical surfaces shall be oversized with respect to the minimumclear aperture by at least 2 mm along both axes to avoid any stray light reflection on themechanical parts.

# *

Note: The minimum clear aperture is determined according to the input beam characteristics,specified FOV, pupil (dimensions, location and decentring if any), alignment and long termstability.


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In addition to specific requirements mentioned in the relevant unit specification, any unit shall bedesigned to minimise internal stray light.

# *

3.15.6 Optical mathematical model requirements


The unit supplier shall provide all BRDF data on optical surface and mechanical structures(barrels, baffles ...) of the unit.

# *


The unit supplier shall use an optical model for numerical simulation of the unit.

# *


The optical model shall be established using the complete set of latest specifications andtolerances that are available about the unit.

# *


The optical model shall include not only the actual optical elements but also intermediate imageplanes, intermediate pupil imaging planes wherever applicable.

# *


The numerical model shall be developed on Code V ® or ZEEMAX ®, or using a softwareproviding a simple export capability into one of these two software packages.

# *


The numerical model shall be used for the evaluation of the unit optical performance.

# *


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100173569N-10


Actual glass characteristics as measured by the glass supplier shall be included in thenumerical model.

# *


Performance analyses shall take into account the diffraction effects, misalignments andmanufacturing tolerances, launch effects, on-flight (zero gravity, radiations, vacuum ...), as wellas lifetime and storage effects.

# *


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100173569N-10

4. LIST OF REQUIREMENTS INCLUDING TBC / TBD

Erreur ! Aucune entrée d'index n'a été trouvée.

END OF DOCUMENT

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