requirement specification for pressure transducer (hp and...

BC.ASU.SP.00021

Issue 01 of 67

Document Autogenerated from DOORS Module : /BepiColombo Implementation Phase/Level 3 Equipment Specifications/MPB/CPSPressureTransducerSpecificationFinal BC.ASU.SP.00021.PressTrans.Spec01.doc

Requirement Specification for Pressure Transducer (HP and LP)

CI CODE: CI CODE: B3126 (MTM) B3226 (MPO) DRL Refs : NOT REQUIRED

UK EXPORT CONTROL RATING : Not Listed

Rated By : J. Bolter

Prepared by: Date:

Checked by: Date:

Approved by: Date:

Authorised by: Date:

This document is produced under ESA contract, ESA export exemptions may therefore apply. These Technologies may require an export licence if exported from the EU

© Astrium Limited 2008

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.

Astrium Limited, Registered in England and Wales No. 2449259 Registered Office: Gunnels Wood Road, Stevenage, Hertfordshire, SG1 2AS, England

BC.ASU.SP.00021Issue 01

of 67

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.

BC.ASU.SP.00021.PressTrans.Spec01.doc

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CONTENTS 1 SCOPE...................................................................................................................................................... 7 2 APPLICABLE DOCUMENTS .................................................................................................................... 8

2.1 Customer Documentation .................................................................................................................. 8 2.2 Military Standards .............................................................................................................................. 8 2.3 Other Standards................................................................................................................................. 9

3 REQUIREMENTS.................................................................................................................................... 10 3.1 Component Function........................................................................................................................ 10 3.2 Performance..................................................................................................................................... 10

3.2.1 Functional Performance............................................................................................................ 10 3.2.2 Electrical Characteristics........................................................................................................... 12 3.2.3 Operating Requirements........................................................................................................... 15

3.3 Design Criteria ................................................................................................................................. 16 3.3.1 General Design Criteria ............................................................................................................ 16 3.3.2 Proof Pressure .......................................................................................................................... 16 3.3.3 Burst Pressure .......................................................................................................................... 16 3.3.4 Over Pressure Protection.......................................................................................................... 17

3.4 Environmental Conditions ................................................................................................................ 17 3.4.1 Pre-Launch (Including Storage and Transportation) ................................................................ 17 3.4.2 Launch ...................................................................................................................................... 17 3.4.3 Post-Launch.............................................................................................................................. 19

3.5 Physical Characteristics ................................................................................................................... 20 3.5.1 Configuration and Dimensions.................................................................................................. 20 3.5.2 Mass.......................................................................................................................................... 21 3.5.3 Stiffness .................................................................................................................................... 21 3.5.4 Interfaces .................................................................................................................................. 21

3.6 Reliability .......................................................................................................................................... 22 3.6.1 Failure Rate .............................................................................................................................. 22 3.6.2 Items Subject to Wear-Out/Degradation................................................................................... 22

3.7 Maintainability .................................................................................................................................. 22 3.8 Storage............................................................................................................................................. 22

3.8.1 Storage Life............................................................................................................................... 22 3.8.2 Equipment Storage ................................................................................................................... 22

3.9 Transportability................................................................................................................................. 22 3.10 Design and Construction .............................................................................................................. 22

3.10.1 Selection of Specifications and Standards ............................................................................... 22 3.10.2 Materials, Parts and Processing ............................................................................................... 22

3.11 Identification and Marking............................................................................................................. 26 3.12 Serialisation .................................................................................................................................. 26 3.13 Safety............................................................................................................................................ 26

3.13.1 General ..................................................................................................................................... 26 3.13.2 Toxic or Hazardous Materials ................................................................................................... 26 3.13.3 Locking...................................................................................................................................... 26 3.13.4 Explosive Atmosphere .............................................................................................................. 26 3.13.5 Pressure Barriers ...................................................................................................................... 27

4 QUALITY ASSURANCE PROVISIONS .................................................................................................. 28 4.1 General Requirements ..................................................................................................................... 28

4.1.1 Responsibility for Inspection and Test ...................................................................................... 28 4.1.2 Quality Assurance Programme................................................................................................. 28 4.1.3 Surveillance, and Witness of Inspection and Test.................................................................... 28 4.1.4 Pre-production Sample ............................................................................................................. 28 4.1.5 Classification of Inspection and Test ........................................................................................ 28


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4.2 Verification of Compliance ............................................................................................................... 28 4.2.1 General ..................................................................................................................................... 29 4.2.2 Acceptance, Inspection and Test.............................................................................................. 29 4.2.3 Qualification Inspection and Test.............................................................................................. 31

4.3 Test Conditions and Test Equipment............................................................................................... 33 4.3.1 Ambient Conditions................................................................................................................... 33 4.3.2 Test Equipment......................................................................................................................... 33 4.3.3 Tolerance of Test Conditions (Excluding Ambient) .................................................................. 34 4.3.4 Accuracy of Measurement ........................................................................................................ 34 4.3.5 Test Media ................................................................................................................................ 35 4.3.6 Product Test Controls ............................................................................................................... 35

4.4 Test Methods ................................................................................................................................... 35 4.4.1 Inspection/Examination............................................................................................................. 35 4.4.2 Proof Pressure and Output Voltage Limit ................................................................................. 36 4.4.3 Vibration Test............................................................................................................................ 37 4.4.4 External Leakage ...................................................................................................................... 38 4.4.5 Functional Test ......................................................................................................................... 38 4.4.6 Cleanliness Verification............................................................................................................. 38 4.4.7 Burst Test.................................................................................................................................. 39 4.4.8 Constant Acceleration............................................................................................................... 39 4.4.9 Rapid Depressurisation and Re-pressurisation (External) ....................................................... 39 4.4.10 Thermal Tests ........................................................................................................................... 40 4.4.11 Environmental Temperature (Non-Operating) .......................................................................... 41 4.4.12 Life Cycle Test .......................................................................................................................... 41 4.4.13 Slam Start (Propellant LP Unit only) ......................................................................................... 41 4.4.14 EMC/ESD Tests........................................................................................................................ 41 4.4.15 Attitude Sensitivity..................................................................................................................... 44 4.4.16 Burn-in....................................................................................................................................... 44 4.4.17 Insulation Resistance Test........................................................................................................ 44 4.4.18 Input Current Test ..................................................................................................................... 44 4.4.19 Ripple and Noise Test............................................................................................................... 44 4.4.20 Voltage Calibration.................................................................................................................... 45 4.4.21 Output Impedance .................................................................................................................... 45 4.4.22 Warm-Up Time Test.................................................................................................................. 45 4.4.23 Reverse Polarity Test................................................................................................................ 45 4.4.24 Load Impedance Test ............................................................................................................... 45 4.4.25 Shock Test ................................................................................................................................ 45

4.5 Preparation for Delivery, Inspection and Test.................................................................................. 45 4.6 Documentation ................................................................................................................................. 46

5 PREPARATION FOR DELIVERY ........................................................................................................... 47 5.1 Methods of Preservation and Packaging ......................................................................................... 47

5.1.1 Retention of Cleanliness........................................................................................................... 47 5.1.2 Storage ..................................................................................................................................... 47 5.1.3 Protective Coverings................................................................................................................. 47

5.2 Equipment Packaging ...................................................................................................................... 47 5.3 Equipment Container Design ........................................................................................................... 47 5.4 Packing............................................................................................................................................. 48 5.5 Identification Marking for Shipment and Storage............................................................................. 48

6 FIGURES................................................................................................................................................. 49 7 GDIR Applicability Matrix......................................................................................................................... 59


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TABLES

Table 3-1: Random Vibration Requirements............................................................................................... 18 Table 3-2: Sinusoidal Vibration Requirements............................................................................................ 18 Table 3-3: Shock Levels.............................................................................................................................. 19 Table 3-4: Cleanliness Requirements ......................................................................................................... 24 Table 4-1: Acceptance Test Requirements................................................................................................. 30 Table 4-2: Qualification Test Requirements................................................................................................ 32 Table 4-3: Test Tolerances ......................................................................................................................... 34 Table 6-1: CREME Parameters for GCR and Solar Flares......................................................................... 53 Table 6-2: Dose Depth Values corresponding to Figure 6-7....................................................................... 54 Table 6-3: Dose Depth Values corresponding to Figure 6-8....................................................................... 55

FIGURES Figure 6-1: ESD Injection in the Structure Plane.......................................................................................... 49 Figure 6-2: ESD Injection by Cable Coupling............................................................................................... 49 Figure 6-3: Thermal Vacuum Cycle for Qualification.................................................................................... 50 Figure 6-4: Thermal Cycling Acceptance Test ............................................................................................. 51 Figure 6-5: Thermal Cycling Protoqualification Tests................................................................................... 52 Figure 6-6: LET Spectra ............................................................................................................................... 53 Figure 6-7: Geostationary Orbit Dose versus Aluminium Shielding Thickness............................................ 54 Figure 6-8: Geostationary Orbit Dose versus Aluminium Shielding Thickness............................................ 55 Figure 6-9: Line Impedance Stabilisation network ....................................................................................... 56 Figure 6-10: Conducted Emissions: Narrow band......................................................................................... 57 Figure 6-11: In Rush Current.......................................................................................................................... 57 Figure 6-12: Radiated Emissions ................................................................................................................... 58 Figure 6-13: Radiated Susceptibility............................................................................................................... 58


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1 SCOPE

This document specifies the performance, design and test requirement for the High Pressure (HP) and Low Pressure (LP) Transducers for use in the BepiColombo MTM and MPO Combined Propulsion Subsystem (CPS).

Requirements within this document are shown in an italic font. Each requirement is preceded by a summary line that contains the following fields, delimited by '/'.

• Doors Requirement Number

• Created From

• Verification Method

The Doors Requirement Number has the form PTR-xxx where xxx is a unique number assigned consecutively.

The Created From field shows the parent requirement or 'Created' if the requirement is created at this level.

The Verification Method codes are as follows:

• R - Review

• A - Analysis

• I - Inspection

• T - Test

If Tables are considered as part of the requirement they are referenced clearly in the text and inserted after and separated from the requirement Table and are managed as free text attached to the identifier requirement.

The trace to the upper level requirements (Upper Links), shall be managed using the following format:

• AAA-NNN where AAA is a label associated to the upper document and NNN the requirement identifier of this upper level,

• or CREATED keyword if the requirement has no link with upper level.

All document elements not presented in the format explained above are not requirements and will not be verified or tracked.


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2 APPLICABLE DOCUMENTS

The following documents form a part of this specification to the extent specified herein. In the event of conflict between this specification and any of the applicable documents referenced below, this conflict shall be notified to the Customer.

All documents referenced in the specification shall be to the revision stated in the applied Statement of Work.

Throughout this specification Documents are referred to in the text as AD/2.x(y).

2.1 Customer Documentation

a. Product Assurance Requirements For Subcontractors BC.ASD.RS.00018

b. General Design and Interface Requirements BC-ASD-SP-00001

c. Environmental and Test Requirements BC-ASD-SP-00002

d. Interface Drawings:

High Pressure Transducer Interface Drawing

Low Pressure Transducer Interface Drawing

See Note 1

e. Generic Requirements for Radiation Hardness Assurance EUR-SPM-0002-MMT

f. Mechanical Propulsion Bus Specification BC-ASD-SP-00008

g. Statement of Work for Pressure Transducer BC.ASU.SW.00021

h. Radiation Analysis BC.ASD.TN.00027

Note 1:

Interface Control Drawings shall be provided by the Contractor at start of Contract and shall be subject to Customer Approval.

2.2 Military Standards

a. Monomethyl Hydrazine MIL-P-27404B

b. Helium MIL-PRF-27407B

c. Nitrogen MIL-PRF-27401D

d. Freon TF MIL-C-81302B

e. Dissimilar Metals MIL-STD-889B

f. Argon Gas MIL-A-18455C

g. Penetrant Inspection MIL-STD-1512

h. Radiographic Inspection MIL-STD-453


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2.3 Other Standards

a. Mixed Oxides of Nitrogen: MON-1 and MON-3 CDST.GX001.STE

b. Isopropyl Alcohol TT-I-735A

c. Deionised/Demineralised Water NASA-S-0073

d. Contamination and Cleanliness ECSS-Q-70-01A

e. Hydrazine MIL-PRF-26536E

f. Cleanroom and Work Station Requirements Controlled Environment Fed. Std. 209

g. - deleted -

h. Structural Design of Pressurized Hardware ECSS-E-32-02

i. Fracture Control ECSS-E-30-01A

j. CSG Safety Regulations General Rules CSG-RS-10A-CN, Volume 1

k. CSG Safety Regulations Specific Rules - Ground Installations CSG-RS-21A-CN, Volume 2, Part 1

l. CSG Safety Regulations Specific Rules - SpaceCraft CSG-RS-22A-CN, Volume 2, Part 2


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3 REQUIREMENTS

3.1 Component Function

The BepiColumbo MTM and MPO Combined Propulsion System (CPS) will utilise two types of pressure transducer. One type will monitor the high pressure, helium gas pressurant supply and shall be classified High Pressure (HP). The other type will monitor the propellants (Nitrogen Tetroxide, Hydrazine, and Monomethyl Hydrazine) pressure downstream of the propellant tanks and shall be classified Low Pressure (LP).

3.2 Performance

3.2.1 Functional Performance

3.2.1.1 Operating Pressures

Note: Pressures specified in this document are pressures above local ambient, unless otherwise stated.

3.2.1.1.1 Sensing Pressure Range

PTR-41/Created/T,R

HP Unit (Pressurant)

The equipment shall measure pressures from 0 bar absolute to 310 bar absolute. (Transducer Output = 0 Volts at 0 bar abs and 5 volts at 305 bar abs, giving the linear scale factor shown in Section 3.2.1.7).

LP Unit (Propellant)

The equipment shall measure pressures from 0 bar absolute to 20.0 bar absolute. (Transducer Output = 0 Volts at 0 bar abs and 5 volts at 20 bar abs, giving the linear scale factor shown in Section 3.2.1.7).

Note:

Additionally the LP unit shall be capable of measuring pressures up to and including 22.55 bar absolute. (Output voltage > 5 V).

3.2.1.1.2 Operating Pressure Spectrum

PTR-46/Created/T,R

a. Maximum Expected Operating Pressure (MEOP):

i HP Unit 310 bar absolute

ii LP Unit 20 bar absolute

Spacecraft Level Normal System Pressure Event HP Unit LP Unit

b. Pre-Launch (Ground Handling) Vacuum to 414* bar Vacuum to 26.6* bar

c. Launch < 310 bar < 6 bar

d. Post-Launch < MEOP < MEOP

i Earth Escape Manoeuvres

ii Cruise Phase < 125 bar < 20.5 bar

* System Level Proof Pressure


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3.2.1.2 Leakage Rates

PTR-58/Created/T,I

External Leakage

The external leakage shall not exceed 1 x 10-6 scc/s of helium at differential pressures up to 310 bar (HP Unit) and 20.5 bar (LP Unit) above ambient pressure over the specified temperature ranges of Section 3.2.3.2 and Section 3.4. There shall be no liquid leakage. Internal Leakage The pressure sensing chamber shall be designed with absolute sealing to prevent leakage of the sensed medium into the electronics assembly section.

3.2.1.3 Flow Rate

Not Applicable.

3.2.1.4 Pressure Drop

Not Applicable.

3.2.1.5 Attitude Sensitivity

PTR-68/Created/R

The equipment shall comply with the requirements of the specification in any axis.

3.2.1.6 Slam Start Pressure Surge (LP Propellant Unit Only)

PTR-70/Created/T,R

The unit shall meet all the requirements of this specification and shall not suffer damage or calibration 'zero-shift' when subjected to the following: Hydraulic Shock An inlet transient pressure of 150 bar minimum for a duration of 20 ms minimum. Rapid Inlet Pressurisation A rise of inlet pressure from between vacuum and 6 bar to MEOP in 20 ms maximum.

3.2.1.7 Discernibility and Accuracy

PTR-76/Created/T,I,R

The Full Range Output (FRO) of the pressurant (HP) pressure transducer shall be 5.084 VDC and that of Propellant (LP) Pressure Transducers shall be 5 VDC, at the Maximum Expected Operating Pressures stated in Section 3.2.1.1.2a. The equipment shall have the following output characteristics:

HP Unit LP Unit (Pressurant) (Propellant) Linear scale factor: 16.4 mV/bar 250 mV/bar Max lifetime total error band: ± 1.8% FRO ± 1.8% FRO Max total error band during acceptance testing: ± 1.0% FRO ± 1.0% FRO The total error shall include at least the following contributions: Input voltage variation, zero output voltage, non-linearity, DC drift, hysteresis, non-repeatability, thermal zero shift, thermal sensitivity and lifetime ageing effects. The Contractor shall indicate the % FRO attributed to each of the above error contributions. The ± 1.0% FRO max error band requirement also applies to the 22.55 bar absolute case for the LP unit as specified in Section 3.2.1.1.1b. No calibration shall be necessary once the equipment has been integrated into the tubing manifold at spacecraft level.


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3.2.1.8 Warm Up Time

PTR-87/Created/T

The equipment shall be designed for removal of power for extended periods of time and shall operate within specification in not more than 60 seconds after the return of power.

3.2.2 Electrical Characteristics

3.2.2.1 Voltage

PTR-90/Created/T

The equipment shall operate to the requirements of this specification with input voltages in the range 28 ± 4 VDC over the specified temperature range of Section 3.2.3.2 and Section 3.4.

It shall continue to operate correctly after being subjected to any supply voltage up to 32.85 VDC in the case of a power supply failure.

3.2.2.2 Power Consumption/Input Current

PTR-93/Created/T

The equipment shall not draw current in excess of 17 mA at any specified condition.

3.2.2.3 Insulation Resistance

PTR-95/Created/T

The insulation resistance between the case and the other wires shorted together shall be greater than 100 megaohms at 50 VDC.

3.2.2.4 Corona Discharge

PTR-97/Created/T,R

The equipment shall not exhibit corona discharge while operating in an environmental pressure range from sea level atmospheric pressure to a vacuum of 1 x 10-5 mbar.

3.2.2.5 Electrical Bonding

PTR-99/Created/T

The equipment mounting surfaces shall be unpainted and any protective coating shall produce a conductive finish suitable for electrical bonding.

The DC resistance, measured in either direction, between adjacent metallic parts of the equipment housing including connector shell shall be less than 2.5 milliohms.

The equipment shall be capable of being mounted such that the DC resistance, measured in either directions, between any metallic point of the equipment housing and the structure shall be less than 15 milliohms.

3.2.2.6 Electrical Connections

PTR-104/Created/I,R

The equipment shall be designed with an integral electrical connector to the requirements and orientation specified in AD/2.1(d).

Each equipment shall be supplied with a connector saver as specified in AD/2.1(d).


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3.2.2.7 EMC/ESD

3.2.2.7.1 Conducted Emission

PTR-108/Created/T

Conducted current emissions shall be measured into the impedance defined in Figure 6-9 and in the frequency range 50 Hz to 10 MHz. A LISN suitable for a wire return configuration shall be used.

Under these conditions, the current re-injected on the pressure transducer supply line shall be less than the limits given in Figure 6-10.

In-Rush Current

The in-rush current transient into the impedance defined in Figure 6-9 shall not exceed the limit defined in Figure 6-10.

3.2.2.7.2 Conducted Susceptibility

PTR-113/Created/T

The equipment shall continue to operate in accordance with the relevant equipment functional requirements when the interferences defined hereafter are applied to:

a) the power lines:

Sine-wave signal of 120 mVRMS for frequencies between 50 Hz and 10 MHz (equivalent to the voltage ripples emitted by the supply equipment (ADE4) increased by +6 dB). If a susceptibility occurs, the injected level at susceptibility frequency shall be reduced until the requirement is met. The new injected level shall be noted. The emission noise shall be less than 20 mV peak-to-peak (20 MHz bandwidth measurement).

b) the signal output:

Square-wave signal of 40 mV peak-to-peak at 1 MHz. The output shall not be susceptible (no offset, no stress) when the square-wave signal is applied.

3.2.2.7.3 Radiated Emission

PTR-119/Created/T

The electric field, measured at 1m, radiated by the equipment in the range 1 MHz to 47 GHz shall not be greater than the limits defined in Figure 6-10. For non-RF equipment, the radiated emissions shall be imperatively measured up to 1 GHz. The measurements up to 47 GHz shall only be performed, if the levels measured between 500 MHz and 1 GHz are at 10 dB, or less, below the limits specified in the same range of frequency.

As shown in Figure 6-10, the radiated levels are limited to:

• 20 dBµV/m in the following frequency ranges: 400 MHz to 500 MHz, 1575 MHz to 1660.5 MHz, 1930 MHz to 2690 MHz and 5450 MHz to 7075 MHz.

• 30 dBµV/m in the following frequency ranges: 12.75 GHz to 14.5 GHz and 17.3 GHz to 18.1 GHz.

• 40 dBµV/m in the following frequency ranges: 27 GHz to 31 GHz and 42.5 GHz to 47 GHz.

3.2.2.7.4 Radiated Susceptibility

PTR-125/Created/T

The equipment shall continue to operate without degradation of its functional performances when the electric field defined in Figure 6-10 shall be applied on it. This figure can be summarised as:

From 1 MHz to 1 GHz: E(V/m) = 1 V/m (rms) = 0 dBV/m (rms)

From 1 GHz to 30 GHz: E(V/m) = 25 V/m (rms) = 28 dBV/m (rms)

The emission noise shall be less than 20 mV peak-to-peak (20 MHz bandwidth measurement).


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3.2.2.7.5 Electrostatic Discharge

PTR-130/Created/T

The equipment shall continue to operate in accordance with its functional specification when it is submitted to the following conditions:

- Injected current in the plane of test, see Figure 6-1:

Shape 1: triangular shape of 20ns to 50ns duration , 50 A-peak in amplitude and dI/dt > 3.109 A/s for the front edge.

Shape 2: triangular shape of 300 ns to 500 ns duration, 100 A-peak in amplitude and 109 A/s < dI/dt < 2.109 A/s for the front edge.

3.2.2.8 Load Impedance

PTR-137/Created/T

The equipment shall be calibrated with a load of 25 kohms and 50 pF in parallel and shall operate within specification with any load impedance in excess of 10 kohms and capacitance of less than 100 pF.

3.2.2.9 Output Impedance

PTR-139/Created/T

The equipment output impedance shall not exceed 100 ohms.

3.2.2.10 Output Ripple and Noise

PTR-141/Created/T

Less than 23 mV peak to peak at 10 Hz to 100 kHz into 25 kohms.

Note:

The noise level during vibration may exceed the quiescent level by not more than 60 mV peak to peak.

3.2.2.11 Output Voltage Limit

PTR-144/Created/T

The equipment output voltage in any failure mode or overpressurisation condition shall be limited to +7.5 VDC max and -1 VDC min.

3.2.2.12 Reverse Polarity

PTR-146/Created/T

The equipment shall not be damaged by reversal of input voltage polarity.

3.2.2.13 Burn-In (Power Age)

PTR-148/Created/T

The equipment shall meet the requirements of this specification after it has been power aged as a complete assembly for a minimum of 168 hours at 48°C with 32 VDC applied.


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3.2.3 Operating Requirements

3.2.3.1 Operating/Test Fluids

PTR-151/Created/T,R

The equipment shall be designed to operate with the following media:

a. Working Media

HP Unit:

Gaseous Helium [to AD/2.2(b)]

LP Unit:

Gaseous Helium [to AD/2.2(b)]

Monomethyl Hydrazine [to AD/2.2(a)]

Nitrogen Tetroxide [to AD/2.3(a)]

Hydrazine [to AD/2.3(e)]

The equipment shall be compatible with the following media:

b. Test Media

HP and LP units:

Gaseous Nitrogen [to AD/2.2(c)]

*Freon TF [to AD/2.2(d)]

Argon Gas [to AD/2.2(f)]

*Isopropyl Alcohol (IPA) [to AD/2.3(b)]

Deionised/Demineralised water [to AD/2.3(c)]

Other specialist test media may be used subject to the Customer approval i.e. approval of the Contractor's Acceptance Test Procedure.

* The pressurisation of IPA and Freon TF in contact with Titanium or Titanium Alloys to greater than 4 bar gauge is prohibited.

3.2.3.2 Fluid/Equipment Temperature

PTR-166/ET-14785, Derived/R

The equipment shall meet the requirements of this specification when operating within the following ranges of fluid and equipment temperatures:

(1) Within the functioning temperature ranges the equipment shall meet its performance requirements.

(2) Within the non-functioning temperature ranges the equipment shall survive and be able to meet performance requirements when the temperature returns to the functioning range.


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3.2.3.3 Design Life

PTR-170/Created/R

The equipment shall be designed with positive margins of safety to operate and meet the requirements of this specification for a minimum design life stated below after storage as specified in Section 3.8.

• HP Unit (Pressurant)

i. Not less than 6 months,

ii. Duty cycles as specified in Section 3.2.3.4,

iii. 10 years in-orbit (Section 3.2.1.1.2d.ii.) Structural Integrity Requirement.

• LP Unit (Propellant)

i. Not less than 10 years,

ii. Duty cycles as specified in Section 3.2.3.4.

3.2.3.4 Cycle Life

PTR-182/Created/T,R

The equipment shall be designed to continue to meet the requirements of this specification after being subjected to the following minimum duty cycles:

Qualification Level

10000 minimum electrical on/off cycles with supply voltage in the range specified in Section 3.2.2.1.

3.3 Design Criteria

3.3.1 General Design Criteria

PTR-187/Created/R

The equipment shall be designed with positive margins of safety to meet the requirements of this specification prior to exposure, during exposure and after exposure to the environments specified herein, as applicable. Environments experienced during fabrication (see note), transportation and storage shall be controlled so as to be significantly less severe than the environments specified herein.

Note:

Exceptions where the process is an integral part of fabrication are to be approved by the Customer.

3.3.2 Proof Pressure

PTR-190/Created/T

The equipment shall meet all the requirements of this specification after being subjected to a proof pressure of 1.5 x MEOP for the HP unit and 2 X MEOP for the LP unit. (Refer to Section 3.2.1.1.2a. for MEOP).

3.3.3 Burst Pressure

PTR-192/Created/T

The equipment shall withstand without rupture a pressure of 4 x MEOP. (Refer to Section 3.2.1.1.2a. for MEOP).

Rupture of internal elements shall not result in immediate or subsequent external leakage higher than that specified in Section 3.2.1.2a.


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3.3.4 Over Pressure Protection

PTR-195/Created/T

The equipment shall meet all the requirements of this specification after being subjected to 2 x MEOP for the HP unit and 7.5 x MEOP (Refer to Section 3.2.1.6a) for the LP unit. (Refer to Section 3.2.1.1.2a. for MEOP).

3.4 Environmental Conditions

3.4.1 Pre-Launch (Including Storage and Transportation)

PTR-198/Created/T,R

The equipment shall meet the requirements of this specification after being exposed to the following pre-launch environmental conditions.

• The surrounding medium will be Air, Nitrogen, or Helium.

• Relative humidity not in excess of 70%.

• Ambient pressure between sea-level and 15000 m.

• Ambient temperature range from -40°C to +65°C.

3.4.2 Launch

PTR-204/ET-14346, Derived/T,R

The equipment shall meet the requirements of this specification during and after exposure to the following launch environmental conditions.

The surrounding medium will be Air, Nitrogen, or Helium.

Ambient Pressure

Sea Level to 1 x 10-10 torr Pressure gradients of -0.03 bar per second from sea level ambient pressure to vacuum and 0.02 bar per second from vacuum to sea level (STS abort) shall not result in any degradation of the equipment or its performance.

Temperature

Normal operating 0°C to +38°C.

PTR-208/GDI-3673, Derived/T,R

Constant Acceleration

The qualification and proto-qualification levels are identical and equal to ± 125 g applied separately in each of three orthogonal axes as defined in AD/2.1(d).

The equipment shall be pressurised with gaseous helium during testing to the levels stated in Section 4.4.8.


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Random Vibration

The following Table 3-1, describes the random vibration requirements.

Axis Frequency, Hz Qualification, dB/oct or

g²/Hz Acceptance, dB/oct or

g²/Hz

All Axes

20 to 100 100 to 300 300 to 2000

+ 3 dB/oct 2.0 g²/Hz - 6 dB/oct

+ 3 dB/oct 1.0 g²/Hz - 6 dB/oct

Composite 31.82 grms 22.5 grms

Duration 120 sec/axis 60 sec/axis

Notes:

For Qualification, the equipments shall be pressurised with gaseous helium to the levels stated in Section 4.4.3.2.

For Acceptance, the equipments shall be pressurised with gaseous helium to the levels stated in Section 4.4.3.2.

Table 3-1: Random Vibration Requirements [derived from AD/2.1 (c)]


Qualification Sinusoidal Vibration

The following Table 3-2, describes the sinusoidal vibration requirements.

Axis Frequency, Hz Qualification, g or mm 0

to Peak ProtoFlight, g or mm 0 to

Peak

All Axes 5 to 20 20 to 100

15 mm 0 to Peak 24 g

15 mm 0 to Peak 24 g

Sweep Rate 2 octaves/min 4 octaves/min

Duration 1 Sweep Up 1 Sweep Up

Notes:

The equipments shall be pressurised with gaseous helium to the levels stated in Section 4.4.3.3.

Table 3-2: Sinusoidal Vibration Requirements [derived from AD/2.1 (c)]


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Shock

The following Table 3-3 applies for all axes, defined in AD/2.1(d):


Axis Frequency, Hz Shock Level, g

All Axes

100 300 1000 2000 10000

20 300 820 1500 1500

Notes:

The associated amplification factor is Q = 10, in all cases.


Table 3-3: Shock Levels [derived from AD/2.1 (c)]

PTR-261/Created/R

Relative Humidity

Relative humidity up to 70%.

3.4.3 Post-Launch

PTR-264/Created/A,R

The equipment shall operate within the requirements of this specification when exposed to the following environments:

Ambient Pressure

0.1 Torr to 1 x 10-10 Torr

Temperature

See Section 3.2.3.2.

Acceleration

Zero 'g' to 1 'g' in all axes.

PTR-929/Created/A,R

Radiation

Single Event Phenomena

Galactic Cosmic Ray (GCR) and solar flare radiation result in charge deposition inside EEE components, which can induce different kind of Single Event Phenomena (SEP), such as Single Event Upset (SEU), Single Event Latch-up (SEL), Burn-Out (BO), Single Event Gate Rupture (SEGR), Single Hard Error (SHE), Single Event Functional Interrupt (SEFI), Single Event Snapback (SES) and others. Equipment shall be designed to ensure that nominal performance is maintained in the presence of SEP.

The Contractor shall compute the SEP occurrence probability and effects. SEP rate calculations and SEP characterisation are based on Linear Energy Transfer (LET) integral spectra for galactic cosmic


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ray and anomalous large solar flare conditions. Applicable integral spectra for both conditions are given on Figure 6-6. The analysis rules are given in AD/2.1(e).

The weather index M=3 defines an environment for GCR that will not be exceeded for more than 10% of the mission life. M=8 defines the environment during anomalous large solar flare conditions. Each anomalously large solar flare conditions shall be deemed to last for 1 day. At least 4 anomalous large solar flares of 4 days each will be considered over a 15 years life.

Contractors having access to CREME based codes can use the CREME parameters given in Table 6-1. If not, tabulated values are given in AD/2.1(e).

PTR-281/Created/A,R

Mission Dose Depth Curve

The space radiation environment (electrons and protons) as seen by the satellite over the orbital design life (see Figure 6-7) shows that the radiation dose seen by the units and components can be reduced by adequate shielding.

Units used in the spacecraft shall be designed to ensure that any radiation sensitive components have sufficient shielding such that any change in a component parameter resulting from the radiation environment does not degrade the unit performance below the specified limits (as detailed in the Worst Case Analysis of the equipment). The analysis shall demonstrate a margin higher than 20% on top of the predicted cumulated radiation dose given Figure 6-7.

For the preliminary analysis, it shall be assumed that the satellite structure and its major components offers a shielding of at least 0.5 mm omni-directional for equipment mounted inside the satellite. For equipment which cannot meet the above requirement, the Contractor shall ask for Prime Contractor to perform an analysis to define more accurately the shielding offered by the spacecraft. For detailed a procedure refer to AD/2.1(e).

Contractors wishing to perform a more accurate analysis shall require to Prime Contractor the flux spectrum of particles as applicable to the mission.

The total dose curve given in Figure 6-7, corresponds to a 160°W geostationary position, 15 years of lifetime, 4 anomalous large flares (King's model), 1D shell sphere calculation and over 4π steradian. This dose curve has to be used in conjunction with the method 'NORM' for equivalent aluminium shielding computation at unit level [see AD/2.1(e)]. This is the preferred method leading to the most accurate analysis.

Contractors having only sector analysis code using the 'SLANT' method [see AD/2.1(e)], shall use it in conjunction with the solid sphere dose depth curve given in Figure 6-8 and Table 6-3.

The Contractor shall inform the Prime Contractor of the method used since it may affect the satellite aluminium equivalent shielding.

PTR-285/Created/A,R

Deep Dielectric Discharge

Electrostatic discharge can result from charging of dielectric and floating conductors within a spacecraft by energetic electrons (E>2MeV). The Contractor shall identify in its equipment, all the metallic surfaces which are not always referenced to a fixed potential (track of PCB floating in particular equipment configuration, ....).

3.5 Physical Characteristics

3.5.1 Configuration and Dimensions

PTR-289/Created/I,R

The equipment shall comply with the dimensions plus their tolerances and the configuration as defined in Section 3.5.4 and AD/2.1(d).


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3.5.2 Mass


The mass of the equipment shall be the minimum necessary to meet the requirements of this specification, and shall not exceed 286 grams (without connector saver fitted).

3.5.3 Stiffness

PTR-293/Created/T,A,R

The equipment shall have a natural frequency greater than 140 Hz when supported as in the spacecraft.

3.5.4 Interfaces

3.5.4.1 Interface with Propulsion Subsystem

PTR-296/Created/I,R

The equipment shall be designed for connection to titanium pipework by welding. Transition joints shall be supplied by the equipment Contractor as necessary.

Stub tube interface with the propulsion subsystem shall conform to AD/2.1(d).

The equipment shall be capable of being electro-welded into the pipeline system without damage to internal electronic circuitry.

In the case of special handling installation or operating precautions being necessary these shall be included in the Contractor's Handling and Transportation Procedures.

3.5.4.2 Interface with Structure Subsystem

PTR-301/Created/T,A

Interfaces with the structure subsystem are defined in AD/2.1(d).

The external physical configuration, centre of gravity, mechanical interface and all critical dimensions shall be established and controlled according to AD/2.1(d).

3.5.4.3 Interface with Thermal Control Subsystem (TCS)

PTR-304/Created/I,R

The equipment design shall permit the attachment of the following TCS hardware:

• Heaters,

• Temperature Sensors,

• Low emissivity tape or multilayer insulation blanket.

3.5.4.4 Interface with Electrical Distribution Subsystem (EDS) and AOCS

PTR-309/Created/I,R

The equipment shall be fitted with an integral electrical connector to the orientation and requirements of AD/2.1(d).

3.5.4.5 Interface with Ground Support Equipment (GSE)

PTR-311/Created/R

The equipment shall be supplied with a connector saver as specified in AD/2.1(d) and be capable of allowing checks and functional operations at subsystem and equipment level.


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3.6 Reliability

3.6.1 Failure Rate

PTR-314/Created/A,R

The equipment shall meet the requirements of AD/2.1(a) and this specification with a failure rate ≤ 196 x 10-9 failures per hour for function and < 0.6 x 10-9 failures per hour for leakage, at a 60% confidence level.

3.6.2 Items Subject to Wear-Out/Degradation

PTR-316/Created/R

Equipment parts, materials and processes, subject to wear-out or deterioration due to environment, including radiation, application stresses, or inherent physical processes, shall be designed, fabricated, selected, and used to attain performance life requirements.

3.7 Maintainability

PTR-318/Created/R

Each equipment shall be designed to require a minimum of special tools and test equipment to maintain calibration, perform adjustments and accomplish fault identification. No field maintenance, servicing or adjustment shall be required within the specified lifetime.

3.8 Storage

3.8.1 Storage Life

PTR-321/Created/R

All equipment shall meet the requirements of this specification after being stored for a minimum of 8 years total post-delivery ground storage at equipment, subsystem, or spacecraft level.

The equipment shall be capable of storage under the conditions specified in Section 3.4.1.

3.8.2 Equipment Storage

PTR-324/Created/R

The equipment will be stored at equipment, subsystem and spacecraft level under clean conditions, [AD/2.3(f)] Class 100,000 or better.

3.9 Transportability

PTR-326/Created/R

Special packing shall be used as necessary to ensure that transportation methods do not incur design penalties. The equipment shall be transportable by air, ship, or road. Shipment by train is prohibited.

3.10 Design and Construction

3.10.1 Selection of Specifications and Standards

PTR-329/Created/R

All specifications and standards intended for use in the design and construction of the equipment shall be in accordance with the requirements defined in AD/2.1(a) and AD/2.1(b).

3.10.2 Materials, Parts and Processing

PTR-331/Created/R

Each material, part and process shall be controlled by a detailed specification and shall satisfy the applicable requirements of AD/2.1(a).


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3.10.2.1 Dissimilar Metals

PTR-333/Created/R

Contact of dissimilar metals with each other, as defined in AD/2.2(e) shall be avoided wherever possible. Protection against electrolytic corrosion which can result from such contact shall be provided by surface treatment of the metals.

3.10.2.2 Moisture and Fungus Resistance

PTR-335/Created/R

Materials that are nutrients to fungi shall be avoided. Where used, and not hermetically sealed, they shall be treated with a suitable fungicidal agent.

3.10.2.3 Corrosion of Materials

PTR-337/Created/R

a. Stress Corrosion Sensitivity

Metals and alloys which are susceptible to stress corrosion cracking shall not be used. Heat treating of alloys to obtain non-stress-corrosion sensitive conditions is allowed.

b. Corrosion Resistance

Materials shall be corrosion resistant type or suitably treated to resist corrosive effects likely to result from exposure to the environmental conditions specified herein.

Protective coating shall not crack, chip, peel or scale with age when subjected to the environmental extremes specified.

3.10.2.4 Magnetic Materials

PTR-343/Created/R

Magnetic materials shall only be used where necessary for equipment operation. Materials used shall minimise the permanent, induced and transient magnetic fields.

3.10.2.5 Ceramic Materials

PTR-345/Created/R

Ceramic materials or coatings that may crack or break under any combination of operating conditions or environments specified herein shall not be used.

3.10.2.6 Seals

PTR-347/Created/R

Any seals used shall comply with all the applicable requirements of this specification, particularly Section 3.10.2.11 (compatibility) and Section 3.10.2.3 (outgassing).

3.10.2.7 Lubricants and Sealants

PTR-349/Created/R

Lubricants and sealants shall be used only if essential for equipment assembly. Their use shall be minimised and subject to the Customer approval.

3.10.2.8 Standard and Commercial Parts

PTR-351/Created/R

Standard and commercial parts may be used if they do not degrade the reliability of the equipment and are in accordance with the requirements for approved materials and parts.


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3.10.2.9 Finish

PTR-353/Created/R

The surface of the equipment shall be adequately finished to prevent deterioration from exposure to the specified environments that might jeopardise fulfilment of the specified performance. No cadmium of zinc plating shall be used on any components.

3.10.2.10 Contamination and Cleanliness


Contamination

Operation of the equipment shall not result in the release or generation of particles entering the fluid passage or being exhausted externally to the equipment. The interior of the equipment shall be designed and fabricated to facilitate cleaning and prevent the entrapment of contaminants.

Equipment shall contain no chips, slag, particulate matter, oil, grease, liquid or other foreign material.

Each unit shall be verified free of contamination from any approved specialist test media. The Customer shall approve the decontamination process.

Equipment Cleanliness

The equipment shall be assembled under cleanroom conditions, [AD/2.3(f)] Class 100,000 or better.

All equipment shall be measurably clean to equal or better than the levels shown in Table 3-4, below. A sample (as described below) taken after passage through the equipment shall not exceed the listed particle count or distribution. The flushing media shall be either Isopropyl Alcohol per AD/2.3(b) or Deionised, Distilled and Filtered (3 microns absolute) Water per AD/2.3(c).

Flight equipment shall not be subjected to propellant liquids or vapours prior to flight use. Any other liquids shall be removed by flushing with Isopropyl Alcohol per AD/2.3(b), and then purged with Nitrogen AD/2.2(c) and then vacuum dried such that all traces of the liquids are removed.

After all cleaning procedures have been completed, the level of chemical contaminants retained in the equipment shall be such that correct functioning shall not be impaired or compromised throughout the operational lifetime.

Cleanliness Verification Fluid Sample

100 ml of fluid, or 100 ml of fluid per 929 cm2 (1 ft2) of internal surface area, whichever is the greater.

Particle Count, microns Maximum Allowable Count per 100 ml

Over 100 0

51 to 100* 1

26 to 50 5

11 to 25 20

6 to 10 140

5 No silting

Non Volatile Residue (NVR) Less than 1 mg/100 ml

Notes:

* No metallic particles greater than 50 microns.

The equivalent particle size of any particle at its maximum dimension (i.e. fibre length in the case of a fibre).

Table 3-4: Cleanliness Requirements


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3.10.2.11 Fluid Compatibility

PTR-374/Created/R

All equipment shall be compatible with the working media of Section 3.2.3.1a. for the lifetimes quoted in this specification without performance degradation or external leakage. The equipment shall also be compatible with the test media of Section 3.2.3.1b. and any fluids used by the Contractor to test, clean or dry the equipment for periods of exposure of at least 6 months. The equipment shall be compatible with cleanroom air as specified by Section 3.8.

The use of halogenated solvents in contact with titanium alloys is expressly prohibited.

All fluids used shall be agreed by the Customer.

3.10.2.12 Outgassing

PTR-378/Created/R

Outgassing shall comply with the requirements of AD/2.1(a).

3.10.2.13 Interchangeability

PTR-380/Created/I,R

All like parts shall have the same part number. Each equipment item shall be directly interchangeable in form, fit and function with other equipment of the same part number. The performance characteristics shall permit interchange with a minimum of adjustments and recalibrations. The equipment must be of the same qualification status and reliability to meet interchangeability requirements.

3.10.2.14 Workmanship

PTR-382/Created/I,R

Workmanship shall be executed such that the design standard is not degraded or changed. At all points in the manufacture, production, integration, test, handling, storage and transportation, special steps shall be taken to maintain the design standard. The skill level of personnel is to be such that all aspects of workmanship will ensure retention of the high reliability standards, with particular attention to the following:

• Free from blemishes, burrs, and sharp edges.

• Required tolerances on dimensions.

• Compliance with designed radii of fillets.

• Adequate and correct marking of parts and assemblies.

• Thoroughness of cleaning, soldering, welding, brazing, and finishing.

• Freedom from oxidation, cracks, undercuts, lack of fusion, incomplete penetration, and sharp edges.

• Freedom from paints, dyes, and grease.

• Alignment of parts and assemblies, in accordance with specified requirements.

• Interlocking of components and assemblies.


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3.11 Identification and Marking

PTR-399/Created/I,R

Each equipment shall be permanently labelled in accordance with AD/2.1(a), AD/2.1(b), and AD/2.1(d). This to include, but not be limited to, the following:

a. CIDL/CIMI Identification No. and Issue

b. Equipment Title

c. Serial Number

d. Sensing Range

Note: a. and b. are specified by the Customer in AD/2.1(d).

The identification shall be visible when marked on the equipment and its location shall be noted on the top assembly drawings for the equipment.

3.12 Serialisation

PTR-931/Created/I,R

Assemblies and higher level equipment shall be assigned a unique serial number. Serial numbers once assigned shall not be transferred or used again on other items of the same part number. Where equipment contains levels of serialised hardware items, the lower level items shall be traceable through the tiers of serialisation to the end items.

3.13 Safety

3.13.1 General

PTR-404/Created/R

All equipment shall be designed and fabricated with compatible materials in such a manner that all hazards associated with the equipment are eliminated or minimised and controlled.

The equipment shall be designed to comply with the requirements of Section 3.3.

3.13.2 Toxic or Hazardous Materials

PTR-407/Created/R

Where toxic or hazardous materials are used in equipment, that equipment shall bear a label that identifies the hazard source, e.g. 'Warning - this unit contains ...'. In addition the following hazard reduction criteria shall be implemented.

• The provision of warning notes in manufacturing documents.

• Special handling constraints and procedures.

• Scrap disposal controls.

3.13.3 Locking

PTR-412/Created/I,R

Positive locking of screw type hardware used on the equipment shall be achieved by safety wire where possible.

Alternative methods of locking and internal locking shall be approved by the Customer.

3.13.4 Explosive Atmosphere

PTR-415/Created/R

The equipment shall be non-hazardous when operating in an explosive atmosphere and when measuring the pressure of an explosive fluid even when an internal electronic/electrical fault has occurred.


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3.13.5 Pressure Barriers

PTR-417/Created/R

The unit shall provide at least two barriers between the pressurised section and the external environment of the transducer. Each barrier shall be capable of withstanding the full burst differential pressure of the unit..


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4 QUALITY ASSURANCE PROVISIONS

4.1 General Requirements

4.1.1 Responsibility for Inspection and Test

PTR-421/Created/R

Unless otherwise specified in the contract or purchase order, the Contractor is responsible for the performance of all inspection and test requirements as specified herein.

4.1.2 Quality Assurance Programme

PTR-423/Created/R

The Contractor shall have or shall establish and implement a Quality Programme that complies with the requirements of AD/2.1(a). The Contractor's Quality Programme/Plan shall be approved by the Customer.

4.1.3 Surveillance, and Witness of Inspection and Test

PTR-425/Created/I,R

The Customer shall be given access to the Contractor's facilities at all times in order to inspect the Contractor's quality control system and the records specified to be maintained therein. The Contractor shall ensure that appropriate arrangements are made for access to lower tier Vendor's facilities/test houses where critical operations are to be performed.

The Customer (or their nominated representatives) reserve the right to witness, perform, or review the tests or documentation of any of the inspections set forth in the specification where such inspections are deemed necessary to assure that supplies and services conform to prescribed requirements.

The Contractor shall notify the Customer at least 2 weeks and subsequently 48 hours (telex) prior to the commencement of the qualification or acceptance test phases to enable representation by the Customer and witnessing of any or all tests as considered necessary by the Customer.

4.1.4 Pre-production Sample

PTR-429/Created/R

Prior to manufacturing of a new equipment batch, the Contractor shall verify the use of the same materials, techniques, and processes as are applicable to the unit referred to in Section 4.2.3.1.

4.1.5 Classification of Inspection and Test

PTR-431/Created/R

The examination and testing of the equipment shall be classified as follows:

• Qualification Inspection and Testing (Section 4.2.3.2)

• Acceptance Inspection and Test (Section 4.2.2.2)

• Preparation for delivery Inspection and Test (Section 4.5)

4.2 Verification of Compliance

PTR-436/Created/A,R

Compliance with the requirements of Section 3 shall be verified by acceptance inspections and tests, qualification, or analysis as stated in Section 4.2.1. The method of verification of all paragraphs of Section 3 of this specification shall be presented in a Design Verification Matrix Report to a format defined by the Customer.

The Contractor shall provide positive verification from analysis, trials or in service experience, of the MMH, Hydrazine, and NTO compatibility of the equipment to the requirements of Section 3.10.2.11.

At the discretion of the Customer, if the verification of compliance with Section 3.10.2.11 is not conclusive, further testing prior to and as part of Qualification to Section 4.2.3 will be required.


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4.2.1 General

4.2.1.1 Acceptance Inspections and Tests

PTR-441/Created/I,R

The applicable paragraphs of Section 3 shall be verified by performing acceptance inspections and tests in accordance with Section 4.2.2 on each deliverable equipment.

4.2.1.2 Qualification

PTR-443/Created/T,A,R

Qualification of the equipment to meet the requirements of Section 3 may be demonstrated as specified below.

Qualification Inspection and Tests

Design Verification of the equipment shall be established by performing the qualification inspections and tests detailed in Section 4.2.3 on a minimum of one sample of each unit type. These units shall not subsequently be used on a flight spacecraft.

Qualification by Similarity

If the Contractor can demonstrate by analysis that the proposed equipment is similar in design, construction and performance to existing space qualified equipment and that previous qualification covers all or part of the performance and environmental requirements of Section 3, then the Contractor may offer 'Qualification by Similarity' against the relevant requirement(s). Qualification testing may be then omitted subject to Customer approval.

Qualification by Analysis

Where analysis is proposed to demonstrate compliance with any of the requirements of this specification, it is subject to Customer approval.

Qualification by Protoflight Testing

Subject to Customer agreement, delta qualification can be performed using a protoflight qualification philosophy. The testing shall occur at protoflight levels as detailed in this specification. Protoflight units are subsequently acceptable for flight use.

4.2.2 Acceptance, Inspection and Test

4.2.2.1 Test Sample

PTR-454/Created/I,R

Each deliverable unit produced in accordance with this specification, shall be subjected to the acceptance tests specified in Section 4.2.2.2.

Each unit shall be clean prior to entering acceptance testing.


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4.2.2.2 Acceptance Tests Required (Minimum)


Table 4-1 shows the Acceptance, Inspection, and Tests which shall be conducted in the following sequence.

Test Sequence Test Description Section

1. Burn-In Section 4.4.16

2. *Examination and Mass Section 4.4.1

3. Proof Pressure/Output Voltage Limit Section 4.4.2

4. Random Vibration Section 4.4.3.2(b)

5. Insulation Resistance Section 4.4.17

6. Input Current Section 4.4.18

7. Output Ripple and Noise Section 4.4.19

8. Functional Test Section 4.4.5

9. Thermal Cycle Test Section 4.4.20(b)

10 External Leakage Section 4.4.4

11. Voltage Calibration Section 4.4.20

12. Post Acceptance Examination Section 4.4.1.3(h)

13. Cleaning/Cleanliness Verification Section 4.4.6

* May be performed just before final cleaning, Item 13.

Table 4-1: Acceptance Test Requirements

4.2.2.3 Failure Criteria

PTR-460/Created/R

The unit shall exhibit no failure, malfunction or out-of-tolerance performance degradation as a result of acceptance inspections and tests specified in Section 4.2.2.2. Any such occurrence shall be cause for rejection.

4.2.2.4 Acceptance Tests Report

PTR-462/Created/R

Following completion of Acceptance Tests on each unit, a test report shall be prepared evaluating results of tests in accordance with Section 4.6.

4.2.2.5 Test Limitations

PTR-464/Created/T

The Acceptance Inspection and Test shall not degrade the unit performance or expose the Assembly to test levels or conditions which could induce a subsequent failure.


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4.2.2.6 Rejection and Re-Submittal

PTR-466/Created/T

Any failure, malfunction or out-of-specification conditions which occur during the test programmes shall result in immediate stoppage of the test to avoid the possibility of further hazard to equipment or personnel. Testing shall not be recommenced unless the condition has been properly investigated and the proposed recovery and corrective action has been reviewed and approved by the Customer. In the case of a failure requiring replacement or rework, the test programme will be repeated in its entirety except as mutually agreed between the Contractor and the Customer.

4.2.3 Qualification Inspection and Test

4.2.3.1 Test Sample

PTR-469/Created/T

Qualification testing shall be carried out on a unit which has been manufactured in accordance with the requirements of this specification. The unit shall be identical to the units that will be supplied for flight spacecraft.


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4.2.3.2 Qualification Tests Required


As a minimum, the Qualification Inspection and Tests listed in Table 4-2 below shall be conducted in the following sequence:

Test Sequence Test Description Section

1. Acceptance Tests (less Vibration and Thermal Cycle) Section 4.2.2.2

2. Environmental Temperature Section 4.4.11

3. Random Vibration Section 4.4.3.2(a)

4. Sinusoidal Vibration Section 4.4.3.3

5. Constant Acceleration Section 4.4.8

6. Shock Section 4.4.25


8. Slam Start Tests Section 4.4.13

9. Rapid Depressurisation Section 4.4.9

10. Corona and Arcing Section 4.4.20(a)

11. Thermal Vacuum Section 4.4.20(a)

12. EMC/ESD Test Section 4.4.14

13. Output Impedance Section 4.4.21

14. Warm-Up Time Section 4.4.22

15. Reverse Polarity Section 4.4.23

16. Load Impedance Section 4.4.24

17. External Leakage Section 4.4.4


19. Voltage Calibration Section 4.4.20

20. Life Test Section 4.4.12


22. Cleanliness Verification Section 4.4.6

23. Burst Test Section 4.4.7

24. Inspection Section 4.4.1

Note:

Subject to Customer approval individual tests above may be omitted if qualification can be verified by similarity and/or analysis as stated in Section 4.2.1.2b. and c.

The Attitude Sensitivity Test (Section 4.4.15) is performed during each Functional Test (Section 4.4.5).

Table 4-2: Qualification Test Requirements


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4.2.3.3 Failure Criteria

PTR-476/Created/T,R

The unit shall exhibit no failure, malfunction or out of tolerance performance degradation as a result of Qualification inspections and tests specified in Section 4.2.3.2. Any such occurrence shall be cause for rejection and refusal to grant Qualification.

4.2.3.4 Qualification Test Report

PTR-478/Created/R

Following the completion of qualification tests, a test report containing the test results, together with an evaluation and comparison with the requirements, shall be delivered in accordance with Section 4.6.

4.3 Test Conditions and Test Equipment

4.3.1 Ambient Conditions

PTR-483/Created/T,R

Unless otherwise specified herein, all measurements and tests shall be made within the following ambient conditions:

Temperature: 23°C + 5°C

Relative Humidity: 60% maximum

Pressure: 760 + 25 mm mercury

All pressures and temperatures shall be recorded unless specified otherwise.

Whenever these conditions must be closely controlled in order to obtain reproducible results, a reference temperature of 23°C, a relative humidity of 50% and an atmospheric pressure of 760 mm of mercury respectively shall be used, together with whatever tolerances are required to obtain the desired precision of measurement.

4.3.2 Test Equipment

PTR-490/Created/T,R

The apparatus used in conducting tests shall be capable of producing and maintaining the required test conditions as defined in the applicable test procedures.


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4.3.3 Tolerance of Test Conditions (Excluding Ambient)

PTR-2302/ET-115, Derived/T,I,R

All testing shall observe the tolerances stated in Table 4-3.

Parameter Tolerance

Temperature, Maximum -0°C, +3°C

Temperature, Minimum +0°C, -3°C

Pressure For proof and leak tests a tolerance of -0/+0.5 bar applies. For all other pressures not specified directly, a tolerance of ± 2% applies.

Relative Humidity ± 5%

Acceleration +10%, -0%

Sinusoidal Vibration +10%, 0 'g' peak

At low frequencies, the electrodynamic exciter may have an amplitude limitation which prevents achievement of 12.5 mm, zero to peak, and the subsequent 'g' level. Such limitations are acceptable down to a minimum amplitude of 5 mm zero to peak for equipment having resonant frequencies greater than 30 Hz.

Random Power Spectral Density ± 3 dB

Random Overall Acceleration (RMS) Frequencies:

+10%, -0% ± 2%, ± 0.5 Hz below 20 Hz

Time +5%, -0

Acoustic Pressure Force

+ 3, -0 dB in each octave + 5%, -0

Dry Mass ± 1 g (see Section DPT-816)

Shock: 100 Hz to 1 kHz Shock: 1 kHz to 10 kHz

+0, + 3dB +0, + 6dB

Table 4-3: Test Tolerances

4.3.4 Accuracy of Measurement

PTR-512/Created/T,R

The accuracy of all instruments and test equipment used to control or monitor the test parameters, whether located at the Contractor's testing laboratory or at a Contractor's plant shall be verified periodically by calibration, traceable to national standards.

Equipment performance parameters shall be measured to at least the following accuracy:

Sensed Pressure: ± 0.05% of reading (LP Unit)

(Pressure Calibrator): ± 0.1% of reading (HP Unit)

Output Voltage: ± 0.05% of reading


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4.3.5 Test Media

PTR-517/Created/I,R

Helium gas [to AD/2.2(b)]

Nitrogen gas [to AD/2.2(c)]

Isopropyl Alcohol* [to AD/2.3(b)]

Distilled or De-ionised Water [to AD/2.3(c)]

Other specialist test media may be used subject to the Customer approval of the Contractor's acceptance test procedure.

Note:

* Pressurisation of equipment with Isopropyl Alcohol (IPA) in excess of 4 bar gauge is prohibited.

4.3.6 Product Test Controls

PTR-524/Created/R

Controls for item configuration, testing item documentation, non-conformance and failure reporting, the Customer and the Customer's Customer inspection and test surveillance shall be as specified in AD/2.1(a).

4.4 Test Methods

PTR-526/Created/T,R

The following tests shall be carried out in the sequence specified in Section 4.2.2.2 and Section 4.2.3.2.

4.4.1 Inspection/Examination

PTR-528/Created/I,R

The unit shall be inspected by Contractor Quality Assurance for the applicable requirements listed below in accordance with this specification and approved Contractor standards. Mechanical inspection criteria shall be as specified on the applicable drawings.

4.4.1.1 Dimensions

PTR-530/Created/I,R

The unit shall be measured for compliance with the overall dimensions and mounting requirements of AD/2.1(d).

4.4.1.2 Identification and Marking

PTR-532/Created/I,R

The unit shall be inspected for compliance with the marking requirements of Section 3.11.


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4.4.1.3 Materials and Processes


The unit shall be visually inspected and manufacturing records and drawings shall be reviewed to verify that materials and processes used conform to specified requirements. Inspection shall verify the following as a minimum:

• Completeness of product.

• Conformance to drawings or other manufacturing documents.

• Completion of all steps in the manufacturing process and proper certification.

• Workmanship, assembly and fit.

• Materials, parts and finish.

• All welds subject to pressure shall be inspected by an approved method of non-destructive test (NDT) such as X-ray [AD/2.2(h) and AD/2.3(e)], or fluorescent penetrant inspection [AD/2.2(g)], or combination of these methods.

• Inspection methods shall comply with the requirements of AD/2.1(a). Subsequent tests will subject the welds to proof and leak tests.

• There shall be no evidence of nicks, scratches, burrs or any defect (or physical imperfection) which would adversely affect the unit's performance, or compromise cleanliness.

• The unit shall conform to drawing and show no evidence of damage or deformation as a result of the acceptance testing. (The stub tube surfaces and end shall be subject to individual inspection).

4.4.1.4 Physical Measurements

PTR-545/Created/I,R

The following physical measurement shall be performed:

The weight of each unit shall be measured to an accuracy of 0.1%, or ± 1 g whichever provides the greatest accuracy.

The centre of gravity and the moment of inertia of the unit shall be recorded. Alternatively, subject to the Customer approval values of centre of gravity and inertia may be calculated.

4.4.2 Proof Pressure and Output Voltage Limit

PTR-549/Created/T,R

Pressurise the unit with gas (to Section 4.3.5) at ambient temperature to the proof pressure specified in Section 3.3.2 above test ambient. Maintain the pressure for 5 minutes minimum. Following the test, the unit shall meet all the specified requirements and show no evidence of damage or of distortion exceeding 0.2%.

Record the output voltage at zero, 50% of MEOP, MEOP, mid range between MEOP, and proof and at proof pressure on increasing and decreasing pressure. At pressures < MEOP* and > MEOP* voltage output shall meet the requirements of Section 3.2.1.7 and Section 3.2.2.11 respectively.

* 22.55 bar for LP unit.


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4.4.3 Vibration Test

4.4.3.1 General Requirements


A sine vibration survey of 0.2 g, 10 to 2000 Hz shall be conducted in each of the three mutually perpendicular axes prior to and after performing the qualification tests specified. Survey results shall indicate no shift between pre and post vibration surveys attributable to a change in test item or test fixture characteristics. The unit shall meet the stiffness requirement of Section 3.5.3.

Subject to the Customer approval a functional test and leak check may be performed in place of the post-test survey.

The transmissibility and cross-talk of the test fixture shall be determined by a swept sine vibration (as above) or a low level random vibration applied in each of three mutually perpendicular axes. The test fixture shall be sufficiently stiff to be considered rigid for the frequency range up to 2000 Hz (random case) and 100 Hz (sine case).

Axis definition is specified by AD/2.1(d).

4.4.3.2 Random Vibration


Observing the general requirements of Section 4.4.3.1, the unit shall be subjected to random vibration inputs separately along the three orthogonal axes at the following levels.

Qualification

120 seconds per axis at Qualification Levels defined at Section 3.4.2e.i.

Acceptance

60 seconds per axis at Acceptance Levels defined at Section 3.4.2e.ii.

Protoflight Qualification

Following testing, the unit shall be inspected to confirm no physical damage.

During vibration, the unit shall be pressurised as specified below:

Axis Pressure

HP Unit (Pressurant) X, Y, and Z 310 bar

LP Unit (Propellant) X, Y, and Z 6 bar

During each period of vibration the unit shall be monitored for output noise. Noise levels shall be within the requirements of Section 3.2.2.10.


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4.4.3.3 Sinusoidal Vibration


Observing the general requirements of Section 4.4.3.1 the unit shall be vibrated at the levels specified in Section 3.4.2f. The levels shall be applied along each of three orthogonal axes at a sweep rate of 2 octaves/minute for qualification testing. For protoqualification testing the sweep rate shall be 4 octaves/minute.

Following testing the unit shall be inspected to confirm no physical damage.

During vibration the unit shall be pressurised as specified below:

Axis Pressure



During each period of vibration the unit output shall be monitored. Intermittent operation shall not occur.

4.4.4 External Leakage

PTR-581/Created/T,R

The dry unit shall be pressurised with helium at ambient temperature to the 'Internal-External' differential pressure(s) specified in Section 3.2.1.2a. The total external leakage shall not exceed the limit specified in Section 3.2.1.2a.

4.4.5 Functional Test

PTR-583/Created/R

With 28 ± 0.1 VDC supply voltage applied to the unit the output voltage shall be measured as a function of test pressure through the sensing pressure range specified in Section 3.2.1.1.1 (Acceptance testing on the LP unit shall include an additional test point at 22.55 bar absolute). The test shall be carried out for increasing and decreasing pressure.

4.4.6 Cleanliness Verification


The purpose of this test is to verify that the unit still meets the cleanliness requirements of Section 3.10.2.10 after completing any preceding tests. The unit should be clean prior to entering Acceptance or Qualification testing. It should not be subjected to any cleaning procedure immediately prior to this Cleanliness Verification or after any preceding tests (unless otherwise stated).

The units shall be flushed and rinsed to a the Customer approved procedure with the specified quantity of either Freon TF to AD/2.2(d), Isopropyl Alcohol to AD/2.3(b) or Deionised/Demineralised water to AD/2.3(c) filtered to 3 microns absolute.

Each unit shall be verified free from contamination by calibration oil (where applicable). It shall be decontaminated by liquid flushing. The last 100 ml of liquid shall be analysed by a laboratory to show that the oil level is less than 15 ppm.

A 100 ml fluid sample, or 100 ml of fluid per 929 cm2 (1 ft2) of internal surface area, whichever is the greater, shall be used. The effluent shall be withdrawn from the unit for particle count and NVR assessment. The particulate count of the total effluent sample when tested using a procedure approved by the Customer, shall meet the requirements of Section 3.10.2.10.

In the event that the unit fails to meet the specified requirement on the first cleanliness verification test the Contractor shall inform the Customer of the failure and particulate count, and await the Customer approval before subjecting the unit to additional cleaning, cleaning verification tests, or any other tests.


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Following the cleanliness verification test, the unit shall be gas purged and thoroughly dried in vacuum to a the Customer approved procedure to remove all traces of residual liquid.

The unit shall then be protected against contamination in accordance with Section 5.1.1 prior to removal from the contamination controlled area.

4.4.7 Burst Test

PTR-593/Created/T,R

The unit inlet shall be pressurised at ambient temperature to the burst pressure specified in Section 3.3.3 above test ambient. The pressure shall be increased at a uniform rate and the burst pressure shall be maintained for a minimum of 1 min. Rupture of the unit at or below the specified level shall be cause for rejection. Rupture of internal elements shall not result in external leakage higher than that specified in Section 3.2.1.2a.

During the above test, the unit output shall be monitored and shall not exceed the voltage limit specified in Section 3.2.2.11.

4.4.8 Constant Acceleration

PTR-596/GDI-3673, Derived/T,R

The unit shall be subject to the constant acceleration levels specified in Section 3.4.2d., applied separately along each of three orthogonal axes. Test duration shall be 1 minute in each direction (6 minutes total).

As an alternative, sustained acceleration qualification may be achieved by sinusoidal vibration testing (Sine Dwell) at a frequency which is demonstrated by low level sine sweep to be well separated from any equipment resonances. In this case a constant frequency sine input (typical value: 34 Hz) shall be held for one minute after a steady state sine level (20g) has been established, along each of three orthogonal axes.

During testing the unit shall be pressurised as specified below:

Axis Pressure



During each period of acceleration the unit output shall be monitored. Intermittent operation shall not occur.

4.4.9 Rapid Depressurisation and Re-pressurisation (External)

PTR-604/Created/

The unit shall be subjected to external depressurisation and re-pressurisation to the levels and rates specified in Section 3.4.2b. The configuration shall be that applicable to the launch phase with the unit internally pressurised with helium to:

• HP Unit (Pressurant) 310 bar

• LP Unit (Propellant) 6 bar


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4.4.10 Thermal Tests

PTR-608/ET-179, ET-183, Derived/T,R

Thermal Vacuum Test (Qualification)

The unit shall be tested in a thermal vacuum environment having a pressure of 1 x 10-5 torr or less. The test (temperature cycling) shall commence when the pressure falls below 1 x 10-4 torr, and a pressure of 1 x 10-5 torr or less shall be achieved before switch ON of the unit.

The sequence and unit/environmental temperatures for the qualification test are shown in Figure 6-3.

The performance tests, as shown in Figure 6-3, shall include:

Functional Test to Section 4.4.5

Voltage Calibration to Section 4.4.20

External Leakage to Section 4.4.4

Corona Discharge Test

During the initial evacuation of the test chamber the unit shall be pressurised to MEOP with a 32 VDC supply voltage applied and monitored to confirm no corona discharge.

The unit shall be tested in a thermal vacuum environment having a pressure of 1 x 10-5 torr or less. The test (temperature cycling) shall commence when the pressure falls below 1 x 10-4 torr, and a pressure of 1 x 10-5 torr or less shall be achieved before switch ON of the unit.

The sequence and unit/environmental temperatures for the qualification test are shown in Figure 6-3.

The performance tests, as shown in Figure 6-3, shall include:

Functional Test to Section 4.4.5

Voltage Calibration to Section 4.4.20

External Leakage to Section 4.4.4

Corona Discharge Test

During the initial evacuation of the test chamber the unit shall be pressurised to MEOP with a 32 VDC supply voltage applied and monitored to confirm no corona discharge.

Thermal Cycle (Acceptance)

The test conditions shall be as for Section 4.4.20a. except that:

i. Thermal cycling at ambient pressure may be authorised by the Prime Contractor provided that:

• At least 3 identical units at flight standard have already successfully gone through thermal vacuum test.

• The Contractor can demonstrate that this has no (or minor) impact on the accuracy of performance testing.

The equivalence of a specifically configured ambient test should be demonstrated by analysis to achieve all critical temperatures to within +5/-2°C for hot acceptance tests and +2/-5°C for cold acceptance tests in comparison to those expected for vacuum acceptance testing. In addition, in order to avoid a specific corona test for units ON during launch, the Contractor shall demonstrate that the workmanship cannot induce corona sensitivity.

A formal approval from the Prime Contractor is mandatory before the test. In any case the Contractor shall be able to perform acceptance thermal vacuum testing, when requested.


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ii. The sequence and temperatures shall be as shown in Figure 6-4.

iii. Performance tests, as shown in Figure 6-4, maybe limited to the Voltage Calibration Test (to Section 4.4.20).

Thermal Cycle (Protoqualification)

The test conditions shall be as for Section 4.4.20a. except that:

The sequence and temperatures shall be as shown in Figure 6-5.

4.4.11 Environmental Temperature (Non-Operating)

PTR-630/Created/T,R

a. The empty and dry unit shall be mounted in a climatic chamber, and nitrogen at ambient pressure and temperature applied to the inlet and outlet connections. With the chamber at ambient pressure, the chamber temperature shall be raised to +65°C and the relative humidity adjusted to between 70% and 80% RH. This condition shall be maintained for 8 hours.

b. Immediately following Section 4.4.11a., the temperature shall be reduced to -40°C and maintained at this condition for 16 hours.

The unit shall be examined for evidence of deterioration following the completion of a. and b.

4.4.12 Life Cycle Test

PTR-634/Created/T,R

With the unit pressurised to MEOP a minimum of 10,000 electrical power on/off cycles shall be carried out at a input voltage of 32 VDC. At the completion of the test the unit shall continue to meet the requirements of this specification.

4.4.13 Slam Start (Propellant LP Unit only)

PTR-636/Created/T,R

Hydraulic Shock

The low pressure unit shall be pressurised to a minimum of 150 bar above ambient test pressure for a minimum duration of 20 ms. The output voltage shall remain within the limits specified in Section 3.2.2.11 during the test. After the test the unit shall continue to meet all specified requirements. No calibration 'zero shift' shall occur.

Rapid Inlet Pressurisation

The low pressure unit shall be subjected to a hydraulic pressure rise at the inlet from vacuum to MEOP in a time not exceeding 20 ms. The output voltage shall remain within the limits specified in Section 3.2.2.11 during the test. After the test the unit shall continue to meet all specified requirements. No calibration 'zero shift' shall occur.

4.4.14 EMC/ESD Tests

4.4.14.1 Test Sample Loading and Stimulus

PTR-642/Created/T,R

Loading and excitation of the test sample shall be representative of actual flight units and stimulating circuits as representative as practicable. When flight loads or sources are impractical or unavailable the impedance characteristics of such loads and sources shall be simulated.

The simulation shall consist of reactive and resistive elements as necessary to maximise the value of the interference. However, all power supplies shall use Line Impedance Stabilisation Network (LISN), given in Figure 6-9.

If the quantity being measured is current, the test sample load impedance shall be designed so as to exhibit the nominal or larger currents than would be encountered in a flight installation. When the quantity being measured is voltage, the load impedance shall be made larger so as to increase the interference voltage on that particular wire.


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The choice of components to be used for impedance simulation shall be listed in the test plan with the justification.

Typical devices for the impedance simulation of loads current measurements could be for example, bypass capacitors whose reactance value is lower than the value seen in the flight installation. Similarly for voltage measurements, the impedance increasing device could consist of a series inductance whose reactance value is larger than flight loads.

4.4.14.2 General Test Conditions

PTR-648/Created/T,R

The test sample shall be set up with harness that simulates flight harness in shielding, twisting, ground and wiring properties. The EMC test plan shall include a test harness description and shall be submitted to the Customer for approval.

The tests shall be performed in an ambient electromagnetic environment which is at least 6 dB below the lowest level to be measured. Emissions from the attendant test equipment and harnesses are included in the ambient levels.

The tests shall be performed with test samples, unit test equipment (UTE) and harness, on an electrically conductive ground plane. This ground plane shall have a length of a least 2.5 metres and a width greater than 0.5 metres. If a shielded room is used, the ground plane shall be bonded to the room by bonds whose resistance is less than 2.5 mOhm and separated by no more than 2.5 metres. This connection of the ground plane is very important when the UTE has to be located outside the shielded room because of emission in excess of, or susceptibility below, the specified limits.

Interconnecting cable assemblies shall simulate actual usage. Shielded wires shall not be used in the test set-ups unless that have been specified in the intended installation. No overall cable shields are allowed unless used in the actual design.

4.4.14.3 Test Equipment

PTR-653/Created/T,R

The grounding of the EMC measuring equipment shall be implemented in accordance with the details of this section in order to avoid false data introduced by ground loops and minimise the likelihood of shock hazards.

a) The antenna shall be remote from the measuring instruments.

b) The measuring instruments shall be physically grounded by only one connection to the ground plane.

c) The measuring instruments shall be connected to their power supply through an isolation transformer.

Any receiving equipment used shall be capable of measuring sine wave signals with an accuracy of ± 2 dB and broadband (impulse) signals with an accuracy of ± 3 dB. Its frequency accuracy shall be better than ± 2 %.

Any signal source such as signal generator, pulse generator, or power amplifier, may be used provided that it is capable of supplying the necessary modulated and unmodulated power required to develop the susceptibility levels over the frequency range specified and it meets the following requirements, where applicable :

a) Absolute frequency measurement accuracy ± 0.01 %

b) Harmonic content a minimum of 30 dB below fundamental signal level.


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4.4.14.4 Conducted Emission

PTR-662/Created/T,R

The Conducted Emission test shall meet the requirements of Section 3.2.2.7.1.

The voltage and current ripples shall be measured in the time domain with a measuring bandwidth of at least 50 MHz.

4.4.14.5 Conducted Susceptibility

PTR-665/Created/T,R

The test shall be performed as per the requirements of Section 3.2.2.7.2. During the 120 mVRMS conducted susceptibility test, the dwell time at each frequency shall not be less than the time necessary for the equipment to be exercised and to be able to respond. However, the dwell time shall not exceed, as far as possible, 5 seconds at each frequency during the scan. The frequency step size of the signal source shall not exceed 1% of the frequency of the injected signal.

4.4.14.6 Radiated Emissions

PTR-667/Created/T,R

The radiated emission test shall cover the requirements of Section 3.2.2.7.3 and be performed under the following conditions:

• the measurement shall be carried out in a worst case localisation (by detecting the most emissive face) and a worst case polarisation of the antenna,

• distance between antenna and the equipment = 1m,

• the worst case radiated emissions shall be recorded.

Before beginning this test, a leakage detection of the RF connections, cables and test set-up inside the EMC chamber shall be performed to ensure that the equipment's radiated emissions measurement will not be affected by the test set-up. A background measurement shall be performed. This measurement shall be at least 6 dB below the test limit given in Figure 6-10.

4.4.14.7 Radiated Susceptibility

PTR-673/Created/T,R

The radiated susceptibility test shall cover the requirements of Section 3.2.2.7.4 and be performed on the most sensitive face of the equipment. If a susceptibility occurs, the injected electric field at susceptibility frequency shall be reduced until the requirement is met. The new injected level shall be noted.

During the radiated susceptibility test, the dwell time at each frequency shall not be less than the time necessary for the equipment to be exercised and to be able to respond. However, the dwell time shall not exceed, as far as possible, 5 seconds at each frequency during the scan. The frequency step size of the signal source shall not exceed 1% of the frequency of the injected signal.


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4.4.14.8 ESD Test

PTR-676/Created/T,R

The equipment shall continue to operate in accordance with its functional specification when it is submitted to the following conditions:

• equipment mounted on a plane structure of the same nature of that used on the spacecraft.

• bonding and grounding representative of the flight conditions.

• same harness as in the spacecraft (nature - technology - height above structure - separate bundle...).

The test plan shall include a test harness description and shall be submitted for approval by the Customer.

Injected current as described in Section 3.2.2.6. Each shape of injected current shall not be applied more than 10 times.

In case of susceptibility during injection into the structure, ESD cable coupling test, see Figure 6-2, shall be performed (with the same injection waveform), for investigation, to discriminate the coupling path.

ESD testing shall not be carried out on flight equipment (FM or PFM).

4.4.15 Attitude Sensitivity

PTR-685/Created/T,R

The tests to Section 4.4.5 shall be carried out with the axis of the unit in the vertical plane.

The above tests shall be repeated with the axis rotated through first 90° and then 180°. The unit shall meet the requirements of Section 3.2.1.5 in any of the attitudes tested.

4.4.16 Burn-in

PTR-688/Created/T,R

The unit shall be stored for a minimum of 168 h at a temperature of +48°C +2 -0 °C with a voltage of 32 ± 0.02 VDC applied.

4.4.17 Insulation Resistance Test

PTR-690/Created/T,R

A potential of 50 VDC shall be gradually applied between all connector pins, and the unit case and maintained for 1 minute. The resistance shall be measured for conformance to the specified requirements of Section 3.2.2.3.

4.4.18 Input Current Test

PTR-692/Created/T,R

The input current shall be measured with input voltages of 24 and 32 VDC to show conformance with the requirements of Section 3.2.2.2.

4.4.19 Ripple and Noise Test

PTR-694/Created/T,R

With an input voltage of 28 ± 0.1 VDC applied, vary inlet pressure from ambient to MEOP. Measurements of output voltage shall be taken to demonstrate compliance with the ripple and noise limits specified in Section 3.2.2.10.


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4.4.20 Voltage Calibration

PTR-696/Created/T,R

With 24 ± 0.1 VDC applied, carry out the Functional Test specified in Section 4.4.5. Repeat the test with 32 ± 0.1 VDC applied. The test results must show compliance with the requirement of Section 3.2.1.7 at each of the applied voltages. Acceptance test allowable error bands shall be as specified in Section 4.4.5.

4.4.21 Output Impedance

PTR-698/Created/T,R

The output impedance shall be measured and shown to comply with the requirements of Section 3.2.2.9.

4.4.22 Warm-Up Time Test

PTR-700/Created/T,R

With the unit sensing ambient pressure the output voltage shall be recorded. Power shall then be disconnected. After a minimum time of 30 minutes the unit shall be reconnected and the output voltage recorded. The unit shall comply with the warm-up requirements of Section 3.2.1.8. The test shall be repeated with the unit sensing MEOP.

4.4.23 Reverse Polarity Test

PTR-702/Created/T,R

An input voltage of 32 VDC shall be applied to the unit for a minimum of two minutes with the polarity reversed. There shall be no evidence of damage to the unit or degradation of performance.

4.4.24 Load Impedance Test

PTR-704/Created/T,R

The Functional Test to Section 4.4.5 shall be carried out with the unit operating at each of the following Load Impedance.

• 25 kohm with 50 pF in parallel

• 10 kohm with 100 pF in parallel

The test results shall comply with the requirements of Section 3.2.2.8.

4.4.25 Shock Test


The unit shall be subject to the shock levels specified in Section 3.4.2(g), applied separately along each of the three orthogonal axes. These levels are qualification levels, no shock test is required for acceptance. The tolerances of Section 4.3.3(i) shall apply.

During testing the unit shall be pressurised as specified below:

Axis Pressure

HP Unit X, Y and Z 310 bar

LP Unit X, Y and Z 6 bar

Any shock testing shall be followed by a Functional Test, see Section 4.4.5.

4.5 Preparation for Delivery, Inspection and Test

PTR-716/Created/T,R

Examination of preservation, packaging, and marking shall be conducted to assure compliance with the requirements of Section 5 of this specification.


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4.6 Documentation

PTR-718/Created/T,R

The documentation requirements are fully specified in applied Statement of Work and defined in AD/2.1(a), and AD/2.1(b).


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5 PREPARATION FOR DELIVERY

5.1 Methods of Preservation and Packaging

PTR-721/GDI-75, Derived/R

Unless otherwise specified in the contract or purchasing order, equipment procured to this specification shall be packaged, packed and marked for shipment as specified herein.

A copy of the Contractor's handling/transportation and safety procedures shall be included with the equipment in an obvious and readily accessible position to facilitate reference before final stages of unpacking.

5.1.1 Retention of Cleanliness

PTR-724/Created/I,R

After cleaning, and while the unit is still in a controlled clean room area, tube ends are to be capped off or enclosed using antistatic Nylon material conforming to AD/2.3(d) cleaned to Level 1. Material should then be secured in place with clean-room tape to a specification approved by the Customer. Tape shall not touch tube o.d. surface closer than 50 mm from tube end. The unit shall then be bagged using a 2 mil minimum antistatic Nylon inner bag cleaned to Level 1, per AD/2.3(d) and outer bagged with 4 mil minimum Nylon or Polyethylene transparent antistatic material cleaned to Level 2 per AD/2.3(d). Bag ends are to be heat sealed closed; the inner bag shall be evacuated prior to heat sealing. An identification non-shedding tag shall be placed between the inner and outer bags, and shall display the following caution note as a minimum: 'Open in a Contamination Controlled Area Only'. Desiccant and a humidity indicator shall be placed between the inner and outer bags.

5.1.2 Storage

PTR-726/Created/R

The unit shall be capable of being stored for a minimum of that stated in Section 3.8.1 without requiring repair, maintenance or retesting at the end of storage.

5.1.3 Protective Coverings

PTR-728/Created/R

The unit shall be provided with protective covering to prevent contamination during transportation outside clean areas and where necessary to protect against damage in handling, where applicable blanking caps shall be fitted at any venting or sensing ports. Blanking caps shall be labelled and instructions included in the Handling and Transportation Procedures, to 'Remove Before Flight or Test' as applicable.

5.2 Equipment Packaging

PTR-730/Created/R

Each bagged unit shall be inserted into a equipment container. Additional cushioning material shall be used to fill all voids and prevent movement of the unit during handling and shipping.

5.3 Equipment Container Design

PTR-732/Created/R

The equipment container shall be designed and constructed to provide sufficient strength and protection of the equipment during the handling and environmental hazards which may be encountered when transported by common carrier. The inside dimensions of the container shall permit a minimum of 50 mm spacing between any surface of the equipment and inside surface of the container.

The equipment container shall be usable for storage of packaged equipment.


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5.4 Packing

PTR-735/Created/R

Any number of equipment containers shall be loaded into a shipping container. The shipping container shall provide protection for each equipment and equipment container during shipment and handling and shall meet the minimum packaging requirements of the common carrier (if so shipped) for safe transportation at the lowest rate to the point of delivery.

5.5 Identification Marking for Shipment and Storage

PTR-737/Created/I,R

Each unit's intermediate and shipping container shall be labelled, tagged or marked to show at least the following:

• Part Number (CIDL/CIMI) and Issue

• Nomenclature

• Contractor's Part/Serial Number

• Contractor's Name or Trademark

• Quantity or Weight (kg)

• Contractor's Customer Contract Number/Name

• WARNING: 'OPEN ONLY WITH QA/QC SUPERVISION'. (Inner container to be opened in Class 100,000 area only).


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6 FIGURES

High voltage source

Rs Rs

C

0.5 m

10cm

10cm

H=1cm

Current probe

Bonding as rerquired

Metallic plate

Spark gap

R

Equipmentunder test

LISN+

+ -

Towardstest bench

MAT 8814

L=1m

Figure 6-1: ESD Injection in the Structure Plane

Figure 6-2: ESD Injection by Cable Coupling


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TEMPERATUREtS

tS tS tS tS tS tS tS tS tE

tS tS tS tS tS tS tS tS tE

tS

Cycle 1

ONOFF

EXTERNAL PRESSURE (Torr)

Limited Performance TestSwitch unit on at end of low non-functioning temperature plateauAt all times when unit is ON, a selected set of major parameters(current…) are continuously monitored (typically 1 point per minute)For CORONA test, unit ON during pressure drop

TNQ max

TNQ min

10-5

TQ max

TQ min

T Ambient 1

1

1

1

2

2

3

3

1

4

4

Note:

TNQMIN TQMIN TQMAX TNQMAX

HP Unit -65°C -60°C +60°C +65°C

LP Unit -25°C -20°C +60°C +65°C

TNQ Non-functioning qualification temperatures

TQ Functioning qualification temperatures

dT/dt < 2°C per min

tS Minimum stabilised temperature time: 1 hour

tE Minimum stabilised temperature time prior to start performance test: 4 hours

TAMBIENT Ambient Temperature, see Section 4.3.1.

At all times when unit is ON, a selected set of major parameters (current...) are continuously monitored (Typically 1 point per minute).

Figure 6-3: Thermal Vacuum Cycle for Qualification


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TEMPERATUREtS

tS tS tS tE

tS tS tS tE

tS

Cycle 1

ONOFF


Limited Performance TestSwitch unit on at lowest temperature plateauAt all times when unit is ON, a selected set of major parameters(current…) are continuously monitored (typically 1 point per minute)Cycled in vacuum if applicable

10-5

TNA min

TNA max

T Ambient

TA max

TA min

1

1

1

1

1

2

2

3

3

4

4

Note:

TNAMIN TAMIN TAMAX TNAMAX

HP Unit -60 °C -55°C +55°C +60 °C

LP Unit -20 °C -15°C +55°C +60 °C

TNA Non-functioning acceptance temperature

TA Functioning acceptance temperature






Figure 6-4: Thermal Cycling Acceptance Test


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TEMPERATUREtS

tS tS tS tE

tS tS tS tE

tS

Cycle 1

ONOFF


Limited Performance TestSwitch unit on at lowest temperature plateauAt all times when unit is ON, a selected set of major parameters(current…) are continuously monitored (typically 1 point per minute)

10-5

TNP min

TNP max

T Ambient

TP max

TP min

1

1

1

1

1

2

2

3

3

Note:

TNPMIN TPMIN TPMAX TNPMAX

HP Unit -65 °C -60°C +60°C +65 °C

LP Unit -25 °C -20°C +60°C +65 °C

TNP Non-functioning protoflight temperature

TP Functioning protoflight temperature






Figure 6-5: Thermal Cycling Protoqualification Tests


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Heavy ions integral spectra on geosynchronous orbit

1E-111E-101E-091E-081E-071E-061E-051E-041E-031E-021E-011E+001E+011E+021E+031E+041E+051E+061E+07

1E+02 1E+03 1E+04 1E+05

LET (MeV cm2 / g)

F(/m

2/sr

/s)>L

ET

Figure 6-6: LET Spectra

CREME Parameter Solar Flare GCR

Geomagnetic Cut-off Yes Yes

Earth Shadow Yes Yes

Magnetosphere Quiet Quiet

Heavy Ion Atomic Number Range 1 to 92 1 to 92

Weather Index M M = 8 M = 3 (90% Adams Worst Case)

Shielding Thickness 1 g/cm² 1 g/cm²

Table 6-1: CREME Parameters for GCR and Solar Flares


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Figure 6-7: Geostationary Orbit Dose versus Aluminium Shielding Thickness

A1 (mm) Shell Sphere

Dose (rad) A1 (mm) Shell Sphere

Dose (rad) A1 (mm) Shell Sphere

Dose (rad)

0.050 0.495E+09 0.473 0.297E+08 3.484 0.111E+06

0.064 0.406E+09 0.607 0.184E+08 4.472 0.409E+05

0.082 0.325E+09 0.779 0.110E+08 5.740 0.185E+05

0.106 0.254E+09 1.000 0.617E+07 7.368 0.110E+05

0.136 0.193E+09 1.284 0.325E+07 9.457 0.815E+04

0.174 0.142E+09 1.648 0.160E+07 12.139 0.626E+04

0.224 0.101E+09 2.115 0.729E+06 15.582 0.473E+04

0.287 0.695E+08 2.714 0.302E+06 20.000 0.343E+04

0.368 0.461E+08

Table 6-2: Dose Depth Values corresponding to Figure 6-7


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Eurostar Solid Sphere Dose Depth Curve 15 years at 160W (worst case)

1.00E+03

1.00E+04

1.00E+05

1.00E+06

1.00E+07

1.00E+08

1.00E+09

0 2 4 6 8 10 12 14 16 18 20

Depth - mm Aluminium

Tota

l Dos

e -

Rad

s (S

i)

Figure 6-8: Geostationary Orbit Dose versus Aluminium Shielding Thickness

A1 (mm) Solid Sphere dose

(rads) A1 (mm) Solid Sphere dose

(rads) A1 (mm) Solid Sphere dose

(rads)

0.05 9.15E+08 0.473 8.65E+07 3.484 5.61E+05

0.064 7.89E+08 0.607 5.62E+07 4.472 1.86E+05

0.082 6.64E+08 0.779 3.55E+07 5.740 6.12E+04

0.106 5.47E+08 1.000 2.15E+07 7.368 2.44E+04

0.136 4.38E+08 1.284 1.21E+07 9.457 1.35E+04

0.174 3.41E+08 1.648 6.37E+06 12.139 1.07E+04

0.224 2.56E+08 2.115 3.13E+06 15.582 8.58E+03

0.287 1.86E+08 2.714 1.43E+06 20.000 6.80E+03

0.368 1.29E+08

Table 6-3: Dose Depth Values corresponding to Figure 6-8


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-40

-30

-20

-10

0

10

20

30

40

1,E+01 1,E+02 1,E+03 1,E+04 1,E+05 1,E+06 1,E+07

Frequency (Hz)

Z (d

B)

-17 dBΩ

-23 dBΩ

2 4

To Power Source

To Test Sample

5 µH

5 µH

125 mΩ

125 mΩ

25 Ω

25 Ω

80 mF

Figure 6-9: Line Impedance Stabilisation network


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30

40

50

60

70

80

90

100

110

0.01 0.1 1 10 100 1000 10000 100000

Frequency (KHz)

µ

Figure 6-10: Conducted Emissions: Narrow band

0

2

4

6

8

10

12

14

0 1 2 3 4 5 6

Steady State Input Current (A)

Figure 6-11: In Rush Current


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Radiated Emission

0

20

40

60

80

100

120

1 10 100 1000 10000 100000

Fre que ncy (M Hz)

E d

BµV

/m (r

ms)

1: 400 - 500 MHz2: 1575 - 1660,5 MHz3: 1930 - 2690 MHz4: 5450 - 7075 MHz

5: 12,75 - 14,5 GHz6: 17,3 - 18,1 GHz7: 27 - 31 GHz8: 42,5 - 47 GHz

1 2 3 4 5 6 7 8

Figure 6-12: Radiated Emissions

Radiated Susceptibility

0

5

10

15

20

25

30

35

40

1 10 100 1000 10000 100000

Fre que ncy (M H z)

E d

BV

/m (r

ms)

Internal Unit External Unit

Figure 6-13: Radiated Susceptibility


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7 GDIR APPLICABILITY MATRIX

The following table lists the applicable requirements of the GDIR.

It contains, in the first column, the Local ID for each applicable GDIR requirement number.

The second column contains the GDIR Requirement number and the opening text of the requirement.

The third column defines the Applicability Y/N

The final column shows the intended verification method. If no method is shown it shall be assumed that verification is required and the method is TBD.

Req No. Reference Applicability Verif. Method

2.1 Applicable Documents PTR-2612 GDI-3994:

The following documents, of the latest issue, or o ... Y

2.2 Applicable Standards PTR-2614 GDI-3993:

The following documents, of the latest issue, or o ... Y

2.2.1 ECSS 3.1 General Design Requirements PTR-2617 GDI-3287:

All BepiColombo documentation shall use the SI Int ... Y R

3.1.1 Lifetime PTR-2619 GDI-35:

The equipment/subsystem shall meet the requirement ... Y TBD

PTR-2620 GDI-38: Maintenance during storage shall be as limited as ...

Y A

PTR-2621 GDI-37: The MPO equipment/subsystems shall be designed wit ...

Y A

PTR-2622 GDI-51: The MPO equipment/subsystems shall be designed to ...

Y T,A

PTR-2623 GDI-53: The MTM equipment/subsystems shall be designed wit ...

Y T,A

PTR-2624 GDI-48: Where the design margin on nominal lifetime is not ...

Y R,TBC

PTR-2625 GDI-49: The lifetime of items which degrade shall be desig ...

Y R,TBC

3.1.2 Safety and Product Liability PTR-2627 GDI-55:

The subcontractor shall comply to the applicable s ... Y A

3.1.5 Interchangeability PTR-2629 GDI-70:

All spacecraft equipment/subsystems of the same pa ... Y R

3.1.6 Identification & Marking PTR-2631 GDI-72:

The equipment hardware shall be identified with a ... Y I

PTR-2632 GDI-73: The equipment/subsystem identification nameplate s ...

Y I

3.1.7 Accessibility/Maintainability & Ground Testing Requirements

PTR-2634 GDI-82: The design of the equipment/subsystem, the positio ...

Y R


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Req No. Reference Applicability Verif.

Method PTR-2635 GDI-83:

The equipment shall be designed to require a minim ... Y R

PTR-2636 GDI-84: No field maintenance, servicing or adjustment shal ...

Y R

3.1.8 Transportation, Handling and Storage 3.1.8.1 Transport PTR-2639 GDI-77:

The equipment/subsystems shall be transported usin ... Y R

PTR-2640 GDI-78: The equipment/subsystem containers, covers (for op ...

Y R

PTR-2641 GDI-79: The equipment/subsystem transport container shall ...

Y R

PTR-2642 GDI-80: The equipment/subsystem storage container shall be ...

Y R

3.1.8.2 Equipment/Subsystem Packing PTR-2644 GDI-90:

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

PTR-2645 GDI-91: All equipment shall be packaged to ensure that it ...

Y I

PTR-2646 GDI-93: The specified item GSE shall follow as far as appr ...

Y I

3.1.8.3 Container Identification PTR-2648 GDI-95:

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

PTR-2649 GDI-96: In addition to the above, the container shall also ...

Y I

PTR-2650 GDI-2267: Size of company labels on containers shall be agre ...

Y R

3.1.8.4 Handling PTR-2652 GDI-98:

Equipment/subsystem weighing more than 10 kg shall ... Y R

3.1.9 Seals PTR-2654 GDI-100:

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

PTR-2655 GDI-101: Any seals requiring periodic replacement during gr ...

Y R

3.1.10 Lubricants and Sealants PTR-2657 GDI-103:

No lubricants or sealants shall be used without th ... Y R

3.1.11 Radiation Environment PTR-2659 GDI-3289:

The spacecraft equipments/subsystems shall be able ... Y A

PTR-2660 GDI-3292: The equipment/subsystem shall be able to safely wi ...

Y A

PTR-2661 GDI-3594: SEE in terms of transients are depending on applic ...

Y A

PTR-2662 GDI-3595: The subcontractor shall perform a displacement ana ...

Y A

PTR-2663 GDI-3596: With respect to radiation impact, the unit shall b ...

Y A


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Method 3.2 Mechanical Design and Interface Requirements PTR-2665 GDI-105:

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

PTR-2666 GDI-106: Equipment/subsystem shall be compatible with mecha ...

Y R

PTR-2667 GDI-2137: Material selection shall be in accordance with ECS ...

Y R

PTR-2668 GDI-2139: Mechanical parts selection shall be in accordance ...

Y R

PTR-2669 GDI-3980: All reference frames shall be right-handed orthogo ...

Y R

3.2.2 Structural Design 3.2.2.1 General Requirements PTR-2672 GDI-117:

The following failure modes, for equipment/subsyst ... Y A

PTR-2673 GDI-118: For all structural items the following analyses ar ...

Y A

PTR-2674 GDI-119: Dynamic Analysis: The dynamic analysis shall show ...

Y A

PTR-2675 GDI-121: Stress Analysis: For each item a complete stress/s ...

Y A

PTR-2676 GDI-122: No yielding is allowed at proof load/proof pressur ...

Y T

PTR-2677 GDI-2053: The structure shall be of adequate strength to wit ...

Y A

PTR-2678 GDI-2054: Local buckling shall be tolerated only if it is re ...

Y A

PTR-2679 GDI-2055: For composite materials, microbuckling of fibers s ...

Y A

PTR-2680 GDI-123: The equipment/subsystem shall be designed to withs ...

Y A

PTR-2681 GDI-124: For sine and random vibrations, the mechanical siz ...

Y A

PTR-2682 GDI-125: Wherever practical in the design of the primary st ...

Y A

PTR-2683 GDI-126: Redundancy concepts (fail-safe) shall be considere ...

Y A

PTR-2684 GDI-127: Fracture control principles shall be applied where ...

Y A

PTR-2685 GDI-128: In cases where a fail-safe design cannot be implem ...

Y A

PTR-2686 GDI-129: Pressure vessels shall be potential fracture criti ...

Y A

PTR-2687 GDI-130: A sealed container is a pressurized container, com ...

Y A

PTR-2688 GDI-131: Pressure lines, fittings and components shall subj ...

Y T

PTR-2689 GDI-133: All fusion joints shall be 100 %inspected accordin ...

Y I


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Method PTR-2690 GDI-134:

Fasteners used in safe life applications, items fa ... Y A

PTR-2691 GDI-135: Fasteners a. Fasteners shall be classified and ana ...

Y A

PTR-2692 GDI-136: PFCIs shall comply with ECSS-E-30-01A in full. ...

Y A

PTR-2693 GDI-137: Non-metallic flight structural items (composite, g ...

Y T

PTR-2694 GDI-138: For load cases involving thermal and/or moisture d ...

Y A

PTR-2695 GDI-139: Where pressure and/or temperature and/or moisture ...

Y A

PTR-2696 GDI-140: The Flight equipment shall be able to survive 4 ti ...

Y A

3.2.2.2 Mass Properies PTR-2698 GDI-143:

All equipment/subsystem suppliers shall provide eq ... Y R

PTR-2699 GDI-146: The mass of an item must be measured with the foll ...

Y T

3.2.2.3 Centre of Gravity and Moment of Inertia PTR-2701 GDI-148:

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

PTR-2702 GDI-149: The Center of Gravity (CoG) shall be given. w.r.t. ...

Y R

PTR-2703 GDI-150: The Moments of Inertia (MoI) shall be given about ...

Y R

3.2.2.4 Stiffness requirements PTR-2705 GDI-2140:

Minimum natural frequency requirements are imposed ... Y A

PTR-2706 GDI-154: Except otherwise specified, when equipment/subsyst ...

Y T,A

PTR-2707 GDI-155: Modal analysis shall be performed to verify the fr ...

Y T,A

3.2.2.5.1 Ground Operations Loads PTR-2709 GDI-2188:

The units and associated transport containers shal ... Y A

PTR-2710 GDI-2189: Vertical and horizontal loads shall be considered ...

Y A

PTR-2711 GDI-2199: The transportation containers shall be designed to ...

Y A

PTR-2712 GDI-2200: The MGSE design and analysis shall consider a desi ...

Y A

PTR-2713 GDI-3629: During ground transportation the units shall withs ...

Y A

PTR-2714 GDI-3664: All MGSE, containers, transportation and handling ...

Y A

PTR-2715 GDI-3665: Sine and random vibrations: the unit transport con ...

Y A

PTR-2716 GDI-3666: For containers, the shock requirement is a drop of ...

Y T,R


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Method 3.2.2.6 Strength requirements 3.2.2.6.1 Definitions and General Requirements 3.2.2.6.2 Margins of Safety and Factors of Safety PTR-2720 GDI-186:

An uncertainty factor Jf shall be defined to provi ... Y A

PTR-2721 GDI-187: A Qualification Factor of 1.5 shall be used for KQ ...

Y T

PTR-2722 GDI-188: An Acceptance Factor of 1.0 shall be used for KA t ...

Y A

PTR-2723 GDI-189: A Design Factor of 1.5 shall be used for DF to det ...

Y A

PTR-2724 GDI-194: The unit shall be able to withstand, without failu ...

Y A

PTR-2725 GDI-195: Margin of safety (MOS) a. Margins of safety (MOS) ...

Y A

PTR-2726 GDI-197: Minimum Factors of Safety against ultimate for pre ...

Y A

PTR-2727 GDI-198: For combined loads where L(P) is the load due to m ...

Y A

PTR-2728 GDI-207: Conservative friction coefficients regarding minim ...

Y A

PTR-2729 GDI-208: Wherever applicable, for general design of bolts, ...

Y R

PTR-2730 GDI-209: In addition, in case of combined loads due to ther ...

Y A

3.2.3 Design Requirements 3.2.3.1 Mounting Requirements PTR-2733 GDI-219:

The attachment points of the equipment/subsystem s ... Y R

PTR-2734 GDI-3996: The mechanical mounting interface shall be consist ...

Y R

PTR-2735 GDI-220: The number of attachment bolts for an equipment sh ...

Y A

PTR-2736 GDI-221: The interface plane flatness of a equipment/subsys ...

Y I

PTR-2737 GDI-222: The equipment/subsystem bolts type and number shal ...

Y R

PTR-2738 GDI-223: Except otherwise specified, all equipment/subsyste ...

Y R

PTR-2739 GDI-228: Unless special conditions override, the thickness ...

Y R

PTR-2740 GDI-229: Minimum clearance between mechanical parts shall c ...

Y R

PTR-2741 GDI-230: All equipment/subsystems shall be designed allowin ...

Y A

PTR-2742 GDI-2550: The minimum load carrying capability of the insert ...

Y A,R

PTR-2743 GDI-2551: The following typical insert distances along the m ...

Y A,R


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Method 3.2.4 Mechanical / Optical Interface Control Documents PTR-2745 GDI-239:

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

PTR-2746 GDI-240: Interfaces will be subjected to a formal inspectio ...

Y T,I

PTR-2747 GDI-241: The issues of ICDs have to be released as defined ...

Y A

PTR-2748 GDI-242: One of the attachment holes on a equipment/subsyst ...

Y R

PTR-2749 GDI-243: The equipment/subsystem reference frame shall have ...

Y R

PTR-2750 GDI-246: The dimensioning of the attachment hole pattern sh ...

Y A

PTR-2751 GDI-247: Interface Control Drawings shall be provided to AS ...

Y R

3.2.5 Mechanical Mathematical Model Requirements PTR-2753 GDI-253:

Detailed Finite Element Models (FEM) shall be prov ... Y A

PTR-2754 GDI-254: All FE model requirements, checks and formats are ...

Y T

PTR-2755 GDI-2256: Mechanisms shall conform to the spacecraft system ...

Y A,R

3.4 Thermal Design and Interface Requirements 3.4.2 Definition of Temperatures and Terms PTR-2758 GDI-298:

In the frame of BepiColombo, all equipment/subsyst ... Y R

3.4.2.3 Isothermal Equipment/Subsystem PTR-2760 GDI-302:

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

PTR-2761 GDI-303: For radiative equipment/subsystems the temperature ...

Y T,A

PTR-2762 GDI-304: For conductive equipment/subsystems the temperatur ...

Y T,A

PTR-2763 GDI-305: For non-isothermal equipment/subsystems a referenc ...

Y R

3.4.2.4 Temperature Reference Point (TRP) PTR-2765 GDI-307:

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

3.4.3 Thermal Interface Requirements 3.4.3.1 Conductive Interface PTR-2768 GDI-316:

The mounting interface shall comply with the mecha ... Y A

PTR-2769 GDI-2536: An interface filler with a coefficient of friction ...

Y R

3.4.3.2 Radiative Interface PTR-2771 GDI-322:

Equipment/subsystems shall be designed with an emi ... Y R

3.4.3.3 Internal Temperature Monitoring PTR-2773 GDI-324:

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

PTR-2774 GDI-325: The location, type and electrical interface of all ...

Y R


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Method 3.4.5 Thermal Control PTR-2776 GDI-331:

All thermal hardware mounted on the equipment/subs ... Y R

3.4.6 Thermal Interface Control Documents PTR-2778 GDI-333:

All equipment/subsystem thermal interfaces shall b ... Y R

3.4.7 Thermal Mathematical Model Requirements 3.4.7.2 Thermal Interface Modeling PTR-2781 GDI-336:

The Thermal mathematical model shall be provided f ... Y A

PTR-2782 GDI-337: SI units: All units used in thermal models (geomet ...

Y A

3.4.7.3 Thermal Model Correlation PTR-2784 GDI-339:

The detailed thermal model of a equipment/subsyste ... Y T,A

3.4.7.4 Reduced Thermal Model PTR-2786 GDI-341:

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

PTR-2787 GDI-342: The convergence of the thermal models shall be dem ...

Y A

5.1 Mechanical Interface Datasheet PTR-2789 GDI-2760:

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

6.1 Thermal Interface Control Document PTR-2791 GDI-2892:

All unit thermal interfaces shall be described wit ... Y R


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Requirement/Section Cross Reference Page numbers are the pages where the sections start

PTR-41 ............... 3.2.1.1.1...........10 PTR-46 ............... 3.2.1.1.2...........10 PTR-58 ............... 3.2.1.2..............11 PTR-68 ............... 3.2.1.5..............11 PTR-70 ............... 3.2.1.6..............11 PTR-76 ............... 3.2.1.7..............11 PTR-87 ............... 3.2.1.8..............12 PTR-90 ............... 3.2.2.1..............12 PTR-93 ............... 3.2.2.2..............12 PTR-95 ............... 3.2.2.3..............12 PTR-97 ............... 3.2.2.4..............12 PTR-99 ............... 3.2.2.5..............12 PTR-104 ............. 3.2.2.6..............12 PTR-108 ............. 3.2.2.7.1...........13 PTR-113 ............. 3.2.2.7.2...........13 PTR-119 ............. 3.2.2.7.3...........13 PTR-125 ............. 3.2.2.7.4...........13 PTR-130 ............. 3.2.2.7.5...........14 PTR-137 ............. 3.2.2.8..............14 PTR-139 ............. 3.2.2.9..............14 PTR-141 ............. 3.2.2.10............14 PTR-144 ............. 3.2.2.11............14 PTR-146 ............. 3.2.2.12............14 PTR-148 ............. 3.2.2.13............14 PTR-151 ............. 3.2.3.1..............15 PTR-166 ............. 3.2.3.2..............15 PTR-170 ............. 3.2.3.3..............16 PTR-182 ............. 3.2.3.4..............16 PTR-187 ............. 3.3.1.................16 PTR-190 ............. 3.3.2.................16 PTR-192 ............. 3.3.3.................16 PTR-195 ............. 3.3.4.................17 PTR-198 ............. 3.4.1.................17 PTR-204 ............. 3.4.2.................17 PTR-208 ............. 3.4.2.................17 PTR-210 ............. 3.4.2.................17 PTR-239 ............. 3.4.2.................17 PTR-245 ............. 3.4.2.................17 PTR-261 ............. 3.4.2.................17 PTR-264 ............. 3.4.3.................19 PTR-281 ............. 3.4.3.................19 PTR-285 ............. 3.4.3.................19 PTR-289 ............. 3.5.1.................20 PTR-291 ............. 3.5.2.................21 PTR-293 ............. 3.5.3.................21 PTR-296 ............. 3.5.4.1..............21 PTR-301 ............. 3.5.4.2..............21 PTR-304 ............. 3.5.4.3..............21 PTR-309 ............. 3.5.4.4..............21 PTR-311 ............. 3.5.4.5..............21 PTR-314 ............. 3.6.1.................22 PTR-316 ............. 3.6.2.................22 PTR-318 ............. 3.7....................22 PTR-321 ............. 3.8.1.................22 PTR-324 ............. 3.8.2.................22 PTR-326 ............. 3.9....................22 PTR-329 ............. 3.10.1...............22

PTR-331..............3.10.2 .............. 22 PTR-333..............3.10.2.1 ........... 23 PTR-335..............3.10.2.2 ........... 23 PTR-337..............3.10.2.3 ........... 23 PTR-343..............3.10.2.4 ........... 23 PTR-345..............3.10.2.5 ........... 23 PTR-347..............3.10.2.6 ........... 23 PTR-349..............3.10.2.7 ........... 23 PTR-351..............3.10.2.8 ........... 23 PTR-353..............3.10.2.9 ........... 24 PTR-355..............3.10.2.10 ......... 24 PTR-374..............3.10.2.11 ......... 25 PTR-378..............3.10.2.12 ......... 25 PTR-380..............3.10.2.13 ......... 25 PTR-382..............3.10.2.14 ......... 25 PTR-399..............3.11 ................. 26 PTR-404..............3.13.1 .............. 26 PTR-407..............3.13.2 .............. 26 PTR-412..............3.13.3 .............. 26 PTR-415..............3.13.4 .............. 26 PTR-417..............3.13.5 .............. 27 PTR-421..............4.1.1 ................ 28 PTR-423..............4.1.2 ................ 28 PTR-425..............4.1.3 ................ 28 PTR-429..............4.1.4 ................ 28 PTR-431..............4.1.5 ................ 28 PTR-436..............4.2 ................... 28 PTR-441..............4.2.1.1 ............. 29 PTR-443..............4.2.1.2 ............. 29 PTR-454..............4.2.2.1 ............. 29 PTR-457..............4.2.2.2 ............. 30 PTR-460..............4.2.2.3 ............. 30 PTR-462..............4.2.2.4 ............. 30 PTR-464..............4.2.2.5 ............. 30 PTR-466..............4.2.2.6 ............. 31 PTR-469..............4.2.3.1 ............. 31 PTR-471..............4.2.3.2 ............. 32 PTR-476..............4.2.3.3 ............. 33 PTR-478..............4.2.3.4 ............. 33 PTR-483..............4.3.1 ................ 33 PTR-490..............4.3.2 ................ 33 PTR-512..............4.3.4 ................ 34 PTR-517..............4.3.5 ................ 35 PTR-524..............4.3.6 ................ 35 PTR-526..............4.4 ................... 35 PTR-528..............4.4.1 ................ 35 PTR-530..............4.4.1.1 ............. 35 PTR-532..............4.4.1.2 ............. 35 PTR-534..............4.4.1.3 ............. 36 PTR-545..............4.4.1.4 ............. 36 PTR-549..............4.4.2 ................ 36 PTR-554..............4.4.3.1 ............. 37 PTR-559..............4.4.3.2 ............. 37 PTR-573..............4.4.3.3 ............. 38 PTR-581..............4.4.4 ................ 38 PTR-583..............4.4.5 ................ 38 PTR-585..............4.4.6 ................ 38

PTR-593 ............. 4.4.7 .................39 PTR-596 ............. 4.4.8 .................39 PTR-604 ............. 4.4.9 .................39 PTR-608 ............. 4.4.10 ...............40 PTR-630 ............. 4.4.11 ...............41 PTR-634 ............. 4.4.12 ...............41 PTR-636 ............. 4.4.13 ...............41 PTR-642 ............. 4.4.14.1 ............41 PTR-648 ............. 4.4.14.2 ............42 PTR-653 ............. 4.4.14.3 ............42 PTR-662 ............. 4.4.14.4 ............43 PTR-665 ............. 4.4.14.5 ............43 PTR-667 ............. 4.4.14.6 ............43 PTR-673 ............. 4.4.14.7 ............43 PTR-676 ............. 4.4.14.8 ............44 PTR-685 ............. 4.4.15 ...............44 PTR-688 ............. 4.4.16 ...............44 PTR-690 ............. 4.4.17 ...............44 PTR-692 ............. 4.4.18 ...............44 PTR-694 ............. 4.4.19 ...............44 PTR-696 ............. 4.4.20 ...............45 PTR-698 ............. 4.4.21 ...............45 PTR-700 ............. 4.4.22 ...............45 PTR-702 ............. 4.4.23 ...............45 PTR-704 ............. 4.4.24 ...............45 PTR-709 ............. 4.4.25 ...............45 PTR-716 ............. 4.5 ....................45 PTR-718 ............. 4.6 ....................46 PTR-721 ............. 5.1 ....................47 PTR-724 ............. 5.1.1 .................47 PTR-726 ............. 5.1.2 .................47 PTR-728 ............. 5.1.3 .................47 PTR-730 ............. 5.2 ....................47 PTR-732 ............. 5.3 ....................47 PTR-735 ............. 5.4 ....................48 PTR-737 ............. 5.5 ....................48 PTR-929 ............. 3.4.3 .................19 PTR-931 ............. 3.12 ..................26 PTR-2302 ........... 4.3.3 .................34


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