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BS EN 16603-10-03:2014

BS EN 16603-10-03:2014

$215.11

Space engineering. Testing

Published By Publication Date Number of Pages
BSI 2014 132
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This standard addresses the requirements for performing verification by testing of space segment elements and space segment equipment on ground prior to launch. The document is applicable for tests performed on qualification models, flight models (tested at acceptance level) and protoflight models.

The standard provides:

  • Requirements for test programme and test management,

  • Requirements for retesting,

  • Requirements for redundancy testing,

  • Requirements for environmental tests,

  • General requirements for functional and performance tests,

    NOTE Specific requirements for functional and performance tests are not part of this standard since they are defined in the specific project documentation.

  • Requirements for qualification, acceptance, and protoflight testing including qualification, acceptance, and proto-fight models’ test margins and duration,

  • Requirements for test factors, test condition, test tolerances, and test accuracies,

  • General requirements for development tests pertinent to the start of the qualification test programme,

    NOTE Development tests are specific and are addressed in various engineering discipline standards.

  • Content of the necessary documentation for testing activities (e.g. DRD).

Due to the specific aspects of the following types of test, this Standard does not address:

  • Space system testing (i.e. testing above space segment element), in particular the system validation test,

  • In-orbit testing,

  • Testing of space segment subsystems,

    NOTE Tests of space segment subsystems are often limited to functional tests that, in some case, are run on dedicated models. If relevant, qualification tests for space segment subsystems are assumed to be covered in the relevant discipline standards.

  • Testing of hardware below space segment equipment levels (including assembly, parts, and components),

  • Testing of stand-alone software,

    NOTE For verification of flight or ground software, ECSS-E-ST-40 and ECSS-Q-ST-80 apply.

  • Qualification testing of two-phase heat transport equipment,

    NOTE For qualification testing of two-phase heat transport equipment, ECSS-E-ST-31-02 applies.

  • Tests of launcher segment, subsystem and equipment, and launch facilities,

  • Tests of facilities and ground support equipment,

  • Tests of ground segment.

This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00. Annex D gives guidelines for performing this tailoring.

PDF Catalog

PDF Pages PDF Title
10 1 Scope
12 2 Normative references
14 3 Terms, definitions and abbreviated terms
3.1 Terms from other standards
20 3.2 Terms specific to the present standard
26 3.3 Abbreviated terms
29 4 General requirements
4.1 Test programme
4.2 Development test prior qualification
30 4.3 Test management
4.3.1 General
4.3.2 Test reviews
4.3.2.1 Test programme
31 4.3.2.2 Test readiness review (TRR)
32 4.3.2.3 Post test review (PTR)
33 4.3.2.4 Test review board (TRB)
34 4.3.3 Test documentation
4.3.3.1 General
4.3.3.2 Assembly, integration and test plan (AITP)
4.3.3.3 Test specification (TSPE)
4.3.3.4 Test procedure (TPRO)
35 4.3.3.5 Test report (TRPT)
4.3.4 Anomaly or failure during testing
4.3.5 Test data
4.4 Test conditions, tolerances, and accuracies
4.4.1 Test conditions
36 4.4.2 Test tolerances
38 4.4.3 Test accuracies
40 4.5 Test objectives
4.5.1 General requirements
4.5.2 Qualification testing
41 4.5.3 Acceptance testing
4.5.4 Protoflight testing
4.5.4.1 Overview
4.5.4.2 Requirements
42 4.6 Retesting
4.6.1 Overview
4.6.2 Implementation of a design modification after completion of qualification
4.6.3 Storage after protoflight or acceptance testing
43 4.6.4 Space segment element or equipment to be re-flown
44 4.6.5 Flight use of qualification Space segment element or equipment
45 5 Space segment equipment test requirements
5.1 General requirements
47 5.2 Qualification tests requirements
55 5.3 Acceptance test requirements
61 5.4 Protoflight test requirements
68 5.5 Space segment equipment test programme implementation requirements
5.5.1 General tests
5.5.1.1 Functional and performance tests
69 5.5.1.2 Humidity test
70 5.5.1.3 Life test
71 5.5.1.4 Burn-in test
5.5.2 Mechanical tests
5.5.2.1 Physical properties measurements
5.5.2.2 Acceleration test (static, spin or transient)
72 5.5.2.3 Random vibration test
5.5.2.4 Acoustic test
73 5.5.2.5 Sinusoidal vibration test
5.5.2.6 Shock test
74 5.5.2.7 Micro-vibration generated environment test
5.5.2.8 Micro-vibration susceptibility test
5.5.3 Structural integrity tests
5.5.3.1 Leak test
5.5.3.2 Proof pressure test
75 5.5.3.3 Pressure cycling test
5.5.3.4 Design burst pressure test
5.5.3.5 Burst test
5.5.4 Thermal tests
5.5.4.1 Requirements applicable to thermal vacuum and thermal ambient tests
76 5.5.4.2 Requirements applicable to thermal vacuum test
77 5.5.4.3 Requirements applicable to thermal ambient test
5.5.5 Electrical/RF tests
5.5.5.1 EMC test
78 5.5.5.2 Magnetic test
5.5.5.3 ESD test
5.5.5.4 Passive intermodulation test
5.5.5.5 Multipaction test
5.5.5.6 Corona and arc discharge test
5.5.6 Mission specific test
5.5.6.1 Audible noise test
80 6 Space segment element test requirements
6.1 General requirements
81 6.2 Qualification test requirements
88 6.3 Acceptance test requirements
93 6.4 Protoflight test requirements
100 6.5 Space segment elements test programme implementation requirements
6.5.1 General tests
6.5.1.1 Optical alignment measurement
6.5.1.2 Functional tests
102 6.5.1.3 Performance test
6.5.1.4 Mission test
103 6.5.1.5 Polarity test
104 6.5.1.6 Launcher interface test
6.5.2 Mechanical tests
6.5.2.1 Physical properties measurements
105 6.5.2.2 Modal survey test
6.5.2.3 Static load test
6.5.2.4 Spin test
6.5.2.5 Transient test
106 6.5.2.6 Acoustic test
6.5.2.7 Random vibration test
107 6.5.2.8 Sinusoidal vibration test
108 6.5.2.9 Shock test
109 6.5.2.10 Micro-vibration susceptibility test
6.5.3 Structural integrity tests
6.5.3.1 Proof pressure test
6.5.3.2 Pressure cycling test
110 6.5.3.3 Design burst pressure test
6.5.3.4 Leak test
6.5.4 Thermal tests
6.5.4.1 Requirements applicable to thermal vacuum and thermal ambient tests
111 6.5.4.2 Requirements applicable to thermal vacuum test
112 6.5.4.3 Requirements applicable to thermal ambient test
6.5.4.4 Thermal balance test
6.5.5 Electromagnetic tests
6.5.5.1 General
6.5.5.2 Electromagnetic compatibility test
113 6.5.5.3 Electromagnetic auto-compatibility test
6.5.5.4 Passive intermodulation test
6.5.5.5 Magnetic field measurements
6.5.6 Mission specific tests
6.5.6.1 Aero-thermodynamic test
6.5.7 Crewed mission specific tests
6.5.7.1 Micro-vibration emission test
114 6.5.7.2 Human factor engineering (HFE) test
6.5.7.3 Toxic off gassing test
6.5.7.4 Audible noise test
115 7 Pre-launch testing

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BS EN 16603-10-03:2014
$215.11