HEERRSSSCCCHHHEEELLL /// PPPLLLAANNNCCCKKKemits.sso.esa.int/emits-doc/ALCATEL/RF mockup_SPEC_Iss1.pdf · RF MOCK-UP & TESTS REQUIREMENT SPECIFICATION ISSUE : 1.0 Page : 4/28 Référence

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RF MOCK-UP & TESTS REQUIREMENT SPECIFICATIONISSUE : 1.0 Page : 1/28

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RF MOCK-UP & TESTSREQUIREMENTS SPECIFICATION

H-P-1-ASPI-SP-0297

Product Code: 00000

HERSCHEL / PLANCK TEAM Date Signature

Rédigé par/Written by

Vérifié par/Verified by



Approbation/Approved

Entité Emettrice : Alcatel Space - Cannes(détentrice de l’original) :

HHHEEERRRSSSCCCHHHEEELLL /// PPPLLLAAANNNCCCKKK

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ENREGISTREMENT DES EVOLUTIONS / CHANGE RECORDS

ISSUE DATE § : DESCRIPTION DES EVOLUTIONS§ : CHANGE RECORD

REDACTEURAUTHOR

1.0 26/6/2002 All / 1st issue O.F

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TABLE OF CONTENTS

1. SCOPE 6

1.1 Applicable documents 7

1.2 REFERENCE DOCUMENTS 7

1.3 Acronyms, symbols and abbreviations 8

2. SYSTEM DESCRIPTION AND DEFINITION 9

2.1 SYSTEM DESCRIPTION 9

2.2 Co-ordinate System 10

2.3 DEFINITIONs 132.3.1 General 132.3.2 TTC coverage and Antennas types 132.3.3 TTC subsystem architecture 14

2.4 Antennas definition 162.4.1 Technology 162.4.2 Gain 162.4.3 Frequency 172.4.4 Polarisation 172.4.5 VSWR 172.4.6 Antennas configuration on RF mock-up 172.4.7 Dimensions 18

2.5 RF MOCK UP REQUIREMENTS 19

2.6 Tests requirements 212.6.1 Test objective 212.6.2 List of required tests 212.6.3 Tests report 222.6.4 Test environment 222.6.5 Test set-up characterisation 232.6.6 Pass/fail criteria 23

3. PRODUCT ASSURANCE / FLIGHT HARDWARE CONSTRAINTS 24

3.1 METHOD OF PRESERVATION AND PACKAGING 24

3.2 PACKAGING 24

3.3 TRANSPORT 24

3.4 PACKAGING, PACKING, HANDLING AND STORAGE PROCEDURES 25

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3.5 MARKING FOR S HIPMENT 25

3.6 DELIVERY DOCUMENTATION 25

3.7 Annex 1 Satellite overviews with major dimensions 26

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1. SCOPE

This document establishes the technical requirements for the design and manufacturing of two satellites mock-ups,for Herschel and Planck satellites, and for the verification of the RF patterns of the wide coverage TTC antennas to bemounted on-board.

Alcatel is the Prime for both satellites, whereas ALENIA Spazio is the Service Module (SVM) provider, which includesall antennas as part of the TTC subsystem.

These tests on RF-mock-up take part of the overall RF performance verification at both SVM and satellite levels.The outcomes of this test campaign will be reviewed at the system Qualification review (QR), planned in December2004 (tbc).

This verification is split as follows :1) Analysis by GTD on a software with a modelling of the Satellite Structure and of the antennas patterns

interferences.2) RF patterns measurement on Satellites mock-ups with the flight antennas3) Verification of peak gain and of gain measurement

The same kind of X-band frequency antennas will be used on both satellites, low gain antennas (LGA); they will befurnished by the Customer as CFEs, to be returned at the end of RF tests. Note that flight hardware will be used.

A complete measurement of overall RF patterns, shall be performed on both satellites mock-ups.

The materials used to build these mock-ups shall obviously be RF representative of those actually used on theSatellites.The Contractor shall, on top of the mock-ups design and manufacturing, provide the adequate test facilities toperform the required RF patterns measurements, in X-band frequency.

The reason for using mock-ups instead of using the actual satellites is to save time on the schedule by anticipatingthis task but also because of the easiness of handling mock-ups in place of the actual satellites.

The RF mock-ups specified in this document shall be designed to withstand a possible activity outdoor or in ananechoid chamber with all associated cleanliness constraints.It is not needed, unless specified otherwise, to deliver these mock-ups but they will in any case become the Customerproperty.

Applicable requirements to the RF mock-up and tests are identified by RFMCK_T# followed by a number

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1.1 Applicable documents

The following documents form a part of this specification. They shall be basically applied in their totality, unlessdedicated restrictions or deviations are explicitly specified in the present document.In case of conflict between an applicable document and this specification, this specification shall have precedence.Any discrepancy shall be notified to the attention of CUSTOMER for clarification and resolution.

System Support Specifications

AD# Requirement Designation Reference

AD01 Herschel Mechanical ICD (MICD) ASPI document N°TBD

AD02 Planck Mechanical ICD (MICD) ASPI document N°TBD

AD03 N/A

AD04 N/A

AD05 PA Requirements for Subcontractors H-P-1-ASPI-SP-0028

AD06 LGA Design description => TB Provided by Antennasupplier

AD07 N/A

AD08 LGA IDS => TB Provided by Antennasupplier

ESA Specifications

N/A

1.2 REFERENCE DOCUMENTS

RD# Requirement Designation Reference

RD01 SVM configuration report H-P-RP-AI-0003

RD02 System GTD analysis report ASPI document N°TBD

RD03 SVM Materials list ASPI document N°TBD

RD04 RF mock-ups and tests statement of work H-P-1-ASPI-SW-0298

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1.3 Acronyms, symbols and abbreviations

Acronyms Definitions

BW BandwidthCDMU Control and Data Management UnitCFE Customer Furnished EquipmentDB Digital Bi-Level statusDR Digital Relay statusEF Electronic FuseEGSE Electrical Ground Support EquipmentEPC Electric Power ConditionerES Electronic SwitchFDIR Failure Detection, Isolation, and RecoveryGDIR General Design and Interface RequirementGTD Geometrical Theory of DiffractionHW HardwareI/F InterfaceI/P Input Port (hardware interface)ICD Interface Control DocumentIDS Interface Data SheetLLC Low Level CommandML 16 Memory Load command (ML 16)PSA Part Stress AnalysisSW SoftwareTC TeleCommandTM TeleMetryVSWR Voltage Stationary Wave RatioWCA Worst Case Analysis

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2. SYSTEM DESCRIPTION AND DEFINITION

2.1 SYSTEM DESCRIPTION

HERSCHEL and Planck are two scientific spacecrafts. The two programmes are developed by the European SpaceAgency under the Science Programme Committee approval.

Herschel MissionHerschel is a Far Infra-Red and Submillimeter Telescope (formerly called Far Infrared and Submillimetre Telescope orFIRST).Its observation domain opens a window over the thermal emission of very cold objects such as interstellar orcircumstellar dust and gas clouds, and over the brightest molecular and atomic emission bands of gas at « low »temperature (that is lower than a few hundreds of Kelvin).

Planck MissionPlanck is a spinning spacecraft carrying a millimeter and sub-millimeter telescope. It is named after the physicist MaxPlanck (1858-1947). The spacecraft is dedicated to the measure of the fine cosmic background temperaturefluctuation.

Mission commonalitiesThe two spacecrafts are developed as a single project. They share indeed a large number of characteristics.The two core SVM platforms are similar.

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2.2 Co-ordinate System

The RF mock-ups shall both use the same coordinate systems described here below.

HERSCHELSatellite overview

Figure 2.2.1 : Herschel satellite axis system

SVM viewThe Herschel SVM reference axis system (OSVM, XSVM, YSVM, ZSVM) is a right-handed Cartesian system, defined asfollows:

− the origin (OSVM) is the intersection of the longitudinal ARIANE-launcher axis with the launcher/satelliteseparation plane

− the XSVM-axis coincides with the longitudinal axis of the launcher (same orientation)− the ZSVM-axis, together with the XSVM-axis, defines that plane where (nominally) the sun will lie; the ZSVM-axis

positive direction is sun-orientedthe YSVM-axis completes the right-handed orthogonal reference frame.

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Figure 2.2.2 : Herschel SVM reference axis systemNota : the antennas type and size presented on this sketch are purely indicative and not representative of the actualantennas

Antennas accomodation:− the two LGA antennas (LGA1/main & LGA2/redundant) are located on the +Z and - Z panels, respectively

PLANCKSatellite Overview

Figure 2.2.3 : Planck Satellite axis system

SVM viewThe Planck SVM reference axis system (OSVM, XSVM, YSVM, ZSVM) is a right-handed Cartesian system, defined as follows:

− the origin (OSVM) is the intersection of the longitudinal ARIANE-launcher axis with the launcher-to-S/Cseparation plane

− the XSVM-axis coincides with the longitudinal axis of the launcher (same orientation)

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− the ZSVM-axis is perpendicular to the XSVM axis and is nominally perpendicular to a short panel of the SVMoctagonal box (for information, the ZSVM-axis lies in the symmetry plane of the telescope, with its positivedirection oriented towards the concave side of the telescope primary-mirror)

− the YSVM-axis completes the right-handed orthogonal reference frame.

Figure 2.2.4 : Planck SVM reference axis systemNota : the antennas type and size presented on this sketch are purely indicative and not representative of the actualantennasAntennas accomodation :

− the main LGA (LGA1) is accommodated inside the Central Cone, oriented toward -X, through the SolarArray (in the -Y+Z sector).

− the two redundant Low Gain Antennae (LGA2 & LGA3) are accommodated on the +Y and the -Y panel,respectively

Nota : as per SOW §6, the Customer will provide CATA files of both satellites as inputs for the RF mock-upsmanufacturing drawings.

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2.3 DEFINITIONs

2.3.1 General

2.3.1.1 Mission phases

For each satellite the Mission is split in a Launch phase, a Transfer phase and then, in an alternate way, a Scienceobservation mode (only the TC Receivers are ON) and a Data Transmission mode. As well an Emergency / Survivalmode is foreseen.During all mission phases the Spacecraft shall be able to receive telecommands and transmithousekeeping data in any attitude and orbit position , i.e. omni-directional coverage shallbe provided.

2.3.1.2 Satellites orbit and attitude

Herschel and Planck operate at the « L2 » Lagrange point of the Earth-Moon and Sun system. This point lays about1.5 million Km out in the Sun to Earth alignment. The spacecrafts indeed oscillate around the L2 ideal position with aLissajou orbit.They are permanently within a few degree of the Earth and Sun axis, and are so permanently lighted (no eclipse).Herschel is a three axis stabilised satellite, with the +Z axis permanently pointed toward the Sun.Planck is a spinned satellite with the –X axis (Spin axis actually) permanently pointed toward the Sun.

2.3.2 TTC coverage and Antennas types

The targetted TTC omni coverage is implemented by a set of LGA on each satellite. Each satellite having a differentorbit and attitude with respect to the Sun and the Earth, the number of antennas and locations is slightly different onPlanck and Herschel.

The purpose of the low gain antennas (LGA) is to provide an omnidirectionnal coverage on both Satellites, whateverthe Satellite attitude is, in all phases of the mission (Launch, Transfer, Operational or Survival Orbit).The individual pattern of this antenna is of hemispherical type (see section §2.4.2.1).Planck : three LGAs are foreseen, one main (-X) and two redundant antennas (+/-Z). If the Satellite Attitude isnominal, then the main LGA only is used. During Launch, Transfer or Survival modes, also the redundant Antennasmight also be used. The redundant LGAs on Planck actually have their patterns significantly impacted by the SVMstructure, the PLM structure and the Solar Array panel.For that reason the system GTD analysis has lead to an optimised inclination of these LGAs with respect to the SVMpanels :

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Figure 2.3.2.1-a : : Planck redundant LGAs accomodation

Figure 2.3.2.1-b : Planck redundant LGA inclination angle

Herschel : two LGAs are foreseen, one main (on +Z) and one redundant (on –Z). If the Satellite attitude isnominal, then only the main LGA will be used.

2.3.3 TTC subsystem architecture

The following picture shows the RF distribution network with all switches and possible paths from and to allon-board antennas.

Interferences with :-PLM structure-SVM structure-Solar Array

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Tx/Rx 1

Tx/Rx 23dBHybridCoupler

Dip

4 PortSwitch

4 PortSwitches

4 PortSwitch

TransferSwitch

UP

DOWN

RFDN

Transponders

SW 1

SW3 SW 4

SW 5 SW6

TWTA

EPC

TWTA

EPC

MGA

LGA 1

LGA 2

LGA 3

Coupler

Dip

UP

DOWN

4 PortSwitch

SW2

Coupler

Figure 2.3.3: RF distribution network architecture

On each Satellite, the LGA can be equally used for TC receive and TM transmit function. The LGA 1 isconsidered as the nominal LGA used in TM/TC under nominal attitude of the Satellite. LGA 2 (and LGA 3on Planck) are used in case of attitude loss or any critical orientation of the spacecraft.Hence, the targetted omni-directionnal coverage is obtained by conjonction of all LGAs on each Satellite.

Actually, the measurement main objective on the RF Mock-up is to perform a simultaneous measurement of PlanckLGA2 and LGA3 antennas, coupled with a representative set of waveguides and coupler (CFE as per SOW).

PLANCKspecific

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2.4 Antennas definition

2.4.1 Technology

The LGA is a passive antenna with waveguide feeders (WR112 Waveguide flange).The H/P concept is to use either Horn antennas or waveguide fed helix antennas (TBC after Antenna Contractorselection)

2.4.2 Gain

The following LGA gain patterns have been specified

ϕ

θ

Zant

Yant

XantFigure : 2.4.2 : LGA angles reference system

The plan (Xant, Yant) is parallel to the mounting plan of the antenna. Yant is the Antenna axis.The minimum LGA gain to be met over the up-link and down-link bandwidths for each ϕ in [0°;360°] shall be: for 0 ≤ θ ≤ 90° GTx/Rx ≥ -3 dBi

Herebelow are shown the targeted coverages from all three LGAs on Planck and from the two LGAs on Herschel :

Figure 2.4.2.-a : Planck LGAs’ patterns Figure 2.4.2.-b : Herschel LGAs’ patterns

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2.4.3 Frequency

The Antennas will operate at X-band and the uplink/downlink signals will be in the range 7190-7235 MHz fortelecommands and 8450-8500 MHz for telemetry as follows:

HERSCHEL PLANCKUPLIINK (TC) 7207.8483 MHz

[3 MHz allocated BW]7196.3580 MHz

[3 MHz allocated BW]

DOWNLINK (TM) 8468.5 MHz[7 MHz allocated BW]

8455.0 MHz[7 MHz allocated BW]

2.4.4 Polarisation

The Antennas will be circularly polarised with an axial ratio better than 4dB for the LGA and better than 1.5dB forthe MGA, both over the specified gain pattern.The selection between RHCP and LHCP will be made at Antennas PDR by ESA/ESOC (september 2002 tbc).

2.4.5 VSWR

The specified VSWR is better than 1.25 :1.

2.4.6 Antennas configuration on RF mock-up

A preliminary waveguide routing on the SVM is shown on next picture.

Figure 2.4.6 : preliminary waveguides routing on SVM

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2.4.7 Dimensions

Refer to LGA IDS (AD08)

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2.5 RF MOCK UP REQUIREMENTS

Mock-up RF interfaces[RFMCK_T#1] The implementation on the mock-up shall use the same interfaces as those used on the spacecraft. Allconnections shall be made with standard wave guide WR112 flange.[RFMCK_T#2]On Planck Mock-up, a representative flight set of waveguides from LGA2, LGA3 and the ending coupler(see figures 2.3.3 and 2.4.6) will be provided as CFE and shall be used by the Contractor in order to accesssimultaneously both LGA2 and LGA3.

Mock-up Antennas I/F brackets[RFMCK_T#3]Dedicated support brackets shall be designed and manufactured or procured to be compliantwith flight HW in order to accommodate the antennas in the required positionaccording to SVM configuration (RD 1).

Mock-up representativity[RFMCK_T#4]For both mock-ups, the external shape shall be fully representative to the actual satellites to allows a validmeasurement of the RF patterns degradation due to reflections and diffraction on the structure of the satellite. Thispoint is of the highest importance for Planck in particular. Anyway in some areas the mock-up can be simplified w.r.t.the actual satellite. The Contractor is invited to make various trade-offs, in that respect, and the final mock-up levelof details and representativity will be discussed and agreed with the Customer.

DesignCATIA file of both satellites will be provided by the Customer, and will have to be used by the Contractor. Potentialsimplification of the mock-up design/shape compared to the actual satellites design will be subject to the Customerapproval. Final agreement shall be reached at the MRR.

Mock up design accuracy[RFMCK_T#5]For large items like SVM structure, Solar array panel, Telescopes, the required accuracy in the manufacturing w.r.t.the actual Satellite dimensions is of 1cm worst case.For small items, like ACMS (Attitude Control and Measurement System) and RCS (Reaction Control Subsystem) dummies locatedclose to the antennas, and the antenna themselves, the accuracy shall be of 5mm worst case.

LGAs alignment requirements[RFMCK_T#6]The Planck redundant LGAs 2 & 3 shall be inclined as specified in AD02 with an accuracy better than 0.5° (tbc).

Materials[RFMCK_T#7]Full freedom is left to the Contractor to use any kind of material to manufacture each mock-up, considering that theMock-up could be exposed to an external storage. For RF reflectivity purpose, it is explicitely required to cover eachMock-up entirely with an Alu film if the structural material is not metallic.

Bonding[RFMCK_T#8]The bonding resistance between any adjacent metallic structure parts shall be lower than 5 mOhm (to beverified after mock-up assembly).

Antennas access[RFMCK_T#9]As a specific pre-requisite, on PLANCK, a simultaneous feeding of the redundant LGAs2&3 shall be done during thetests. To that aim, a representative set of waveguides (with the ending coupler) will be provided by the customer with

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the actual length foreseen on the actual satellite. See figure 2.4.8, as a typical routing to be implemented on thePLANCK mock-up between LGA2 and LGA3.Therefore the mock-up Contractor shall foresee the inner integration of the PLANCK LGA waveguide network, withthe same routing as the actual one use on the satellite.This will allow to perform an overall pattern measurement of LGA2 and LGA3.

MOCK-UP Storage conditions[RFMCK_T#10]In case the RF tests are performed in an anechoid chamber (in-door test) then the mock-up shall be stored in thesame cleanliness environment (class 100 000) in order to foresee additional tests before the end of the Contract,upon Customer request.If the RF tests are performed on an outdoor test range, then the mock-up shall be foreseen to withstand an externalstorage till the end of the Contract without any degradation of the materials.

MGSE and mounting I/F[RFMCK_T#11]All features needed to adapt the mock-up to the test facilities or to the transport means, are part of theContractor deliverables, and associate mock-up design constraints shall be taken into account.

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2.6 Tests requirements

2.6.1 Test objective

This section describes the Far field tests requirements to measure the Herschel and Planck X band antennascoverages.The purpose of these measurements is to verify the omni-directional coverage of the LGA set on each satellite.These tests will allow :1) to measure the TTC RF antennae coverage and identify all interferences with the spacecraft2) to validate the LGA patterns modellings (RD-2) and the gain assumptions used in the TTC link budgets

2.6.2 List of required tests

As a minimum, the following measurements shall be conducted:

PLANCK[RFMCK_T#12]LGA nominal (LGA1,-X)1) Full gain and phase coverage over 4Pi Steradian with identification of peak gain and min gain• 1a) Rx frequency• 1b) Tx frequency2) Iso-level contours at 11 different levels with the following gains : -2dBi, -2.2dBi, -2.4dBi, -2.6dBi, -2.8dBi, -

3.0dBi, -3.2dBi, -3.4dBi, -3.6dBi, -3.8dBi, -4dBi• 2a) Rx frequency• 2b) Tx frequency

[RFMCK_T#13]Redundant LGAs2&3 measured simultaneously (+/-Z)1) Full gain and phase coverage over 4Pi Steradian with identification of peak gain and min gain• 1a) Rx frequency• 1b) Tx frequency2) Azimuthal gain cuts (co&cross-polarisations) at 0°, 22.5°, 45°; 90°, -22.5°, -45°, -90° elevation angles (elevation

w.r.t. XSVM )• 2a) LGA2&LGA3 / Rx frequency• 2b) LGA2&LGA3 / Tx frequency

3) Elevation gain cuts (co&cross-polarisations) at 0°, 45°, 90°, 135°, 180°azimuthal angles (angle shift wrt X/Y SVMplan)

• 2a) LGA2&LGA3 / Rx frequency• 2b) LGA2&LGA3 / Tx frequency

HERSCHEL[RFMCK_T#14]LGA nominal (LGA1,+Z)1) Full gain and phase coverage over 4Pi Steradian with identification of peak gain and min gain• 1a) Rx frequency• 1b) Tx frequency2) Iso-level contours at 11 different levels with the following gains : -2dBi, -2.2dBi, -2.4dBi, -2.6dBi, -2.8dBi, -

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[RFMCK_T#15]Redundant LGA (LGA2, -Z)3) Full gain and phase coverage over 4Pi Steradian with identification of peak gain and min gain• 1a) Rx frequency• 1b) Tx frequency4) Iso-level contours at 11 different levels with the following gains : -2dBi, -2.2dBi, -2.4dBi, -2.6dBi, -2.8dBi, -


[RFMCK_T#16]For each test configuration a calibration of the measuring antenna with a standard gain horn shall be performed.

[RFMCK_T#17]The steps (resolution) in elevation and azimuth angles will be established by the Contractor, based on each Antennaindividual gain pattern (depending on each antenna characteristics and available data from the antenna supplier).By default, a resolution of 0.1° in azimuth and elevation is required to the Contractor, and the steps in the patternsmeasurement shall be of 1° azimuth and 2° elevation.

[RFMCK_T#18]The measurement accuracy for gain shall be better than 0.05dB and better than 0.5° for the phase.

The exhaustive list of tests will be agreed with the Contractor at the TRR.

Power handlingThe Antennas are designed to withstand a maximum RF power of 30W.[RFMCK_T#19]This level shall not be exceeded during tests.

2.6.3 Tests report

[RFMCK_T#20]On PLANCK after the separate measurements, on LGA1 and LGA2&3, an analytical merging of theoverall gain coverage shall be performed. On HERSCHEL mock-up, a merging of the two patterns (measuredseparately) shall also be made.[RFMCK_T#21]Based on these results a correlation with the system GTD modelling (RD-2) outcomes shall be made bythe Contractor, with support of both the SVM Contractor and the Customer (ASPI). An engineering support is explicitlyrequired here from the Contractor during this evaluation of the results compared to the modelling.[RFMCK_T#22]All measured patterns shall be provided under TICRA / GRASP 8 format and also in paper copy.

2.6.4 Test environment

[RFMCK_T#23]The Contractor shall propose a suitable test environment (Anechoid chamber or outdoor test range) for far-fieldpattern measurement at X-band frequency.[RFMCK_T#24]It shall however be kept in mind that in case of an external test range, the Contractor shall take all necessary actionsto protect the Customer CFEs(Flight Hardware) against any kind of damage and against contamination exceedingthe Class 100 000 cleanliness requirements .

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2.6.5 Test set-up characterisation

[RFMCK_T#25]All necessary calibrations of the test range shall be performed by the Contractor prior to anymeasurement.[RFMCK_T#26]The alignment of the Antenna under test w.r.t. the Test range antenna shall be better than 0.1°.[RFMCK_T#27]Also the isotropic reference level (“quiet zone”) of the test range volume shall be determined.

2.6.6 Pass/fail criteria

[RFMCK_T#28] The measured patterns on each mock-up shall be “clean” enough to allow a proper post processingof the results, in particular the correlation with System predicted patterns. Any noisy pattern due to poor test set-uppreparation or calibration, or due to disturbing environment during the measurements will be rejected and shall beredone by the Contractor.[RFMCK_T#29] The measured peak gain of each LGA shall be in line with the predicted one in the System analysis,within the test facilities measurement accuracy. Any deviation shall be justified and if not agreed by the Customer,the measurement shall then be repeated.[RFMCK_T#30] The ISO-gain curves shall be in line with the predicted ones at system level, within the test facilitiesmeasurement accuracy. If not the case, justification shall be provided by the Contractor, and if case of Customerdecision, the measurement shall be repeated.

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3. PRODUCT ASSURANCE / FLIGHT HARDWARE CONSTRAINTS

PA requirements are given in AD-5.

All Customer provided items (CFEs), Antennas, waveguides and Coupler, will be flight hardware, therefore anyhandling and operations on this hardware shall be done according to dedicated procedures to be established by thecontractor and approved by ASPI. In particular a close following of the rules defined here after is required.

3.1 METHOD OF PRESERVATION AND PACKAGING

a) Preservation of articles or materials subject to deterioration, corrosion, contamination or other physicaldamage through exposure of air, moisture or other elements during tests, storage and any interimstorage or transportation cycle, shall be carried out by the Contractor in a suitable method.

b) Painted surface shall be wrapped with cardboard, paper foam sheet or other suitable protectivecovering.

c) Precision surfaces shall be coated with non-water soluble anticorrosion coatings.

c) Special requirements and precautions will be documented in supplementary instructions or will appearin the packaging procedure or handling instructions as appropriate.

d) Suitable precautionary markings shall be applied giving fragility and attitude advisories.

3.2 PACKAGING

a) The units shall be preserved and packaged to avoid material performance degradation.

b) Packaging shall ensure that transportation method does not impose design penalties.c) Materials used for packaging shall be fully compatible with the equipment to be delivered

3.3 TRANSPORT

a) Appropriate container shall be used for packing, transportation and handling in order to preventdeterioration, corrosion or damage of the items that are packaged.

b) Container must be designed in such a manner that the deliverable items will not suffer any damageunder the environment found at Contractor test facilities and during transportation from Contractor'splants to Test facilitie's ones. Definition of the above mentioned environment is Contractorresponsibility.

c) Shipment of critical equipment that are sensitive to shock or acceleration shall include instrumentsthat record acceleration along three axes.

d) Additional instrumentation for monitoring or recording other in-transit environments (e.g.temperature, vibration, humidity, etc.) shall be used, if necessary.

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Nota : adequate transport container will be provided with each Antenna. However it is a Contractor’s task tomaintain these containers in a way to re-use them till the end of the test campaign, including the antennasshipment back to the Satellite Prime (ASPI).The RF mock-up container (if needed) is under Contractor’s full responsibility.

3.4 PACKAGING, PACKING, HANDLING AND STORAGE PROCEDURES

Detailed procedures and instructions describing Antennas packaging, packing, handling and storage will beprovided by the SVM Contractor or the Antenna Supplier, and shall be strictly followed by the Contractor.Prior to ship back the antennas, after RF mock-up tests, the Packaging shall be done in class 100.000 clean roomunder Quality Assurance people.Regarding the Mock-up, all constraints and procedures shall be properly documented by the Contractor in therelevant documentation (see DRL from RD_4).

Antennas protective meansEach Antenna will be provided without any Radome.[RFMCK_T#31] A Protective Radome shall be provided for Cleanliness purpose in case of outdoor Test range

3.5 MARKING FOR SHIPMENT

a) Interior and exterior containers shall be marked and labelled including precautionary markingnecessary to ensure safety of personnel and facilities.

b) Marking shall also comply with applicable requirements governing and labelling of hazardousmaterials.

c) Packaging with reuse capability shall be identified with the words "Reusable Container - do not destroy- retain for reuse".

d) In additional special labels are to be affixed to specific P.A. requirements / cautions (e.g. opening cleanroom only, Static charge sensitive item, Critical Item, etc.).

3.6 DELIVERY DOCUMENTATION

For each antenna, the corresponding EIDP will be provided by the Antenna supplier of the SVM contractor. This EIDPwill have to be filled in by the Contractor and return with the hardware at the end of the RF test campaign.For each mock-up, an End Item Data Package shall be prepared and provided with the hardware. The content shallbe in line with the SOW (RD 4).

REFERENCE :

DATE :

H-P-1-ASPI-SP-0297

26/06/2002





3.7 Annex 1 Satellite overviews with major dimensions

REFERENCE :

DATE :

H-P-1-ASPI-SP-0297

26/06/2002





REFERENCE :

DATE :

H-P-1-ASPI-SP-0297

26/06/2002





END OF DOCUMENT

Documents

HEERRSSSCCCHHHEEELLL /// PPPLLLAANNNCCCKKKemits.sso.esa.int/emits-doc/ALCATEL/RF mockup_SPEC_Iss1.pdf · RF MOCK-UP & TESTS REQUIREMENT SPECIFICATION ISSUE : 1.0 Page : 4/28 Référence