BS ISO 15864-2004 Space systems - General test methods for space craft subsystems and units《航天系统 航空器、子系统和部件的一般试验方法》.pdf

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1、BRITISH STANDARD AEROSPACE SERIES BS ISO 15864:2004 Space systems General test methods for space craft, subsystems and units ICS 49.140 BS ISO 15864:2004 This British Standard was published under the authority of the Standards Policy and S t r a t e g y C o m m i t t e e o n 20 August 2004 BSI 20 Au

2、gust 2004 ISBN 0 580 44319 1 National foreword This British Standard reproduces verbatim ISO 15864:2004 and implements it as the UK national standard. The UK participation in its preparation was entrusted by Technical Committee ACE/68, Space systems and operations, to Subcommittee ACE/68/-/2, Interf

3、aces, integration and test, which has the responsibility to: A list of organizations represented on this subcommittee can be obtained on request to its secretary. Cross-references The British Standards which implement international publications referred to in this document may be found in the BSI Ca

4、talogue under the section entitled “International Standards Correspondence Index”, or by using the “Search” facility of the BSI Electronic Catalogue or of British Standards Online. This publication does not purport to include all the necessary provisions of a contract. Users are responsible for its

5、correct application. Compliance with a British Standard does not of itself confer immunity from legal obligations. aid enquirers to understand the text; present to the responsible international/European committee any enquiries on the interpretation, or proposals for change, and keep the UK interests

6、 informed; monitor related international and European developments and promulgate them in the UK. Summary of pages This document comprises a front cover, an inside front cover, the ISO title page, pages ii to v, a blank page, pages 1 to 30, an inside back cover and a back cover. The BSI copyright no

7、tice displayed in this document indicates when the document was last issued. Amendments issued since publication Amd. No. Date Comments Reference number ISO 15864:2004(E)INTERNATIONAL STANDARD ISO 15864 First edition 2004-08-15 Space systems General test methods for space craft, subsystems and units

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13、i BSISO15864:2004 iiiContents Page Foreword iv Introduction v 1 Scope 1 2 Normative references. 1 3 Terms, definitions and abbreviated terms 1 3.1 Terms and definitions. 1 3.2 Abbreviated terms. 2 4 General requirements. 3 4.1 Testing philosophy. 3 4.2 Tailoring of requirements. 3 4.3 Development te

14、sts 3 4.4 Qualification tests. 4 4.5 Acceptance tests. 4 4.6 Proto-flight tests. 4 4.7 Prelaunch validation tests 4 4.8 Retest. 4 4.9 Test documentation 5 4.10 Tests facilities and other requirements 7 5 Spacecraft system tests. 7 5.1 Test items and sequence . 7 5.2 Test levels and duration. 7 6 Sub

15、system/unit tests 7 6.1 Test items and sequence . 7 6.2 Test levels and duration. 7 7 Test requirements. 12 7.1 General. 12 7.2 Functional test. 12 7.3 Electromagnetic compatibility (EMC) test 13 7.4 Magnetic field test. 14 7.5 Antenna pattern test . 14 7.6 Optical alignment measurement . 15 7.7 Phy

16、sical property measurement . 15 7.8 Dynamic balance. 16 7.9 Launcher/spacecraft interface test . 17 7.10 Static load test. 17 7.11 Acceleration test. 18 7.12 Modal survey. 19 7.13 Sinusoidal vibration test 20 7.14 Random vibration test 21 7.15 Acoustic test 22 7.16 Shock test 23 7.17 Thermal balance

17、 test 23 7.18 Thermal vacuum test 24 7.19 Thermal cycle test. 26 7.20 Pressure test. 26 7.21 Leakage test 28 7.22 Burn-in and wear-in test. 28 7.23 Tracking and control system/spacecraft compatibility test . 29 BSISO15864:2004iv Foreword ISO (the International Organization for Standardization) is a

18、worldwide federation of national standards bodies (ISO member bodies). The work of preparing International Standards is normally carried out through ISO technical committees. Each member body interested in a subject for which a technical committee has been established has the right to be represented

19、 on that committee. International organizations, governmental and non-governmental, in liaison with ISO, also take part in the work. ISO collaborates closely with the International Electrotechnical Commission (IEC) on all matters of electrotechnical standardization. International Standards are draft

20、ed in accordance with the rules given in the ISO/IEC Directives, Part 2. The main task of technical committees is to prepare International Standards. Draft International Standards adopted by the technical committees are circulated to the member bodies for voting. Publication as an International Stan

21、dard requires approval by at least 75 % of the member bodies casting a vote. Attention is drawn to the possibility that some of the elements of this document may be the subject of patent rights. ISO shall not be held responsible for identifying any or all such patent rights. ISO 15864 was prepared b

22、y Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 14, Space systems and operations. BSISO15864:2004 vIntroduction Throughout this International Standard, the minimum essential criteria are identified by the use of the key word “shall”. Recommended criteria are identified

23、by the use of the key word “should”, and while not mandatory are considered to be of primary importance in providing serviceable, economical and practical designs. Deviations from the recommended criteria should occur only after careful consideration, extensive testing and thorough service evaluatio

24、n have shown alternative methods to be satisfactory. BSISO15864:2004 I SO 4002 All irthgs ersedevr 1Space systems General test methods for space craft, subsystems and units 1 Scope This International Standard provides the baseline standard on the subject of testing at the system, subsystem and unit

25、levels for applicable unmanned spacecraft programmes. It also provides the requirements for documentation associated with testing activities. The acceptance criteria, specifications or procedures, and other detail test requirements applicable to a particular programme are defined in the applicable t

26、echnical specifications and statement of work. When requirements have to be verified by measuring product performance and function under various simulated environments, the method is referred to as “Test”. The requirements of this International Standard may be tailored for each specific space progra

27、mme application. 2 Normative references The following referenced documents are indispensable for the application of this document. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced document (including any amendments) applies. ISO 14302

28、, Space systems Electromagnetic compatibility requirements ISO 14303, Space systems Launch-vehicle-to-spacecraft interfaces ISO 14623, Space systems Pressure vessels and pressurized structures Design and operation 3 Terms, definitions and abbreviated terms 3.1 Terms and definitions For the purposes

29、of this document, the following terms and definitions apply. 3.1.1 development model representative of spacecraft, subsystem or unit dedicated to increase confidence in design and subjected to development tests 3.1.2 flight model spacecraft, subsystem or unit model dedicated to be launched and opera

30、ted in orbit and subjected to acceptance testing 3.1.3 limit load maximum predicted load or combination of loads that a structure may experience during its service life in association with the applicable operating environments BSISO15864:20042 3.1.4 maximum and minimum predicted temperatures highest

31、 and lowest temperatures that can be expected to occur during the entire life cycle of the subsystem/unit in all operational modes plus an uncertainty factor 3.1.5 operational modes modes for spacecraft, subsystems and units that include all combinations of operational configurations that can occur

32、during service life EXAMPLE Power on or power off, the main or redundant system is selected. 3.1.6 proto-flight model model that is subjected to the qualification levels and acceptance duration 3.1.7 qualification model spacecraft, subsystem, or unit dedicated to qualifying the design of flight mode

33、l and subjected to qualification testing 3.1.8 quasi-static load load with magnitude and direction that are independent of time; or load that varies slowly and in which dynamic response of the structure is insignificant NOTE This load can be induced by steady wind, aerodynamic forces, thrust (consta

34、nt or wind slow variations), maneuvers and spin stabilization. 3.1.9 spacecraft vehicle of an integrated set of subsystems and units capable of supporting an operational role in space 3.1.10 subsystem assembly of functionally related units 3.1.11 test article spacecraft, subsystem or unit on which a

35、 test is conducted 3.1.12 test facility location (including equipment, fixture and instrumentation) capable of performing a test 3.1.13 unit lowest level of hardware assembly for which acceptance and qualification tests are required 3.2 Abbreviated terms AT acceptance test CG center of gravity EED e

36、lectroexplosive devices EMC electromagnetic compatibility BSISO15864:2004I SO 4002 All irthgs ersedevr 3LBB leak-before-burst MEOP maximum expected operating pressure MMA moving mechanical assembly PFT proto-flight test QT qualification test RF radio frequency 4 General requirements 4.1 Testing phil

37、osophy In principle, testing is one verification method that ensures that the spacecraft meets all design, performance and product assurance requirements. This International Standard contains provisions for qualification and acceptance testing, or proto-flight testing (PFT). It assumes that hardware

38、 development is complete. Performance requirements contained in the contract documentation are compared to performance achieved during testing and provide the basis for judging the capability of the spacecraft to operate as intended. Besides verifying performance, test programmes provide the followi

39、ng items: a) training for personnel in the operation of the spacecraft; b) incorporation of corrective actions taken for nonconformances; c) validation of data processing; d) opportunity to perform calibrations under simulated space conditions; e) verification of ground hardware compatibility with t

40、he spacecraft for operations. Factors that contribute to the provisions of test specifications include experience with similar spacecraft, subsystem and unit; cost considerations; and reliability requirements. This International Standard contains range conditions to which the items under test shall

41、be operated and test conditions that shall be used to demonstrate capability. 4.2 Tailoring of requirements The test requirements may be tailored to fulfill the objectives of individual tests. Tailoring parameters shall be determined by negotiations among the customer, spacecraft manufacturer and la

42、unch service provider. 4.3 Development tests Development tests support design feasibility and assist in evolution of design. Development tests are necessary to validate new design concepts and the application of proven concepts and techniques to a new configuration. Development tests are used to con

43、firm structural and performance margins, manufacturability, test simplification, maintainability, reliability, lifetime prediction and compatibility with safety. Therefore, requirements for development testing depend on the maturity of the design used and the operational requirements of the specific

44、 project. By its nature, development testing cannot be reduced to a standardized set of procedures. Where practicable, development tests shall be conducted over a range of operating conditions that exceed design limits to identify marginal design features. Development tests may be conducted on mock-

45、ups, breadboards, development models or integration models. BSISO15864:20044 4.4 Qualification tests Qualification tests demonstrate that items meet design requirements and include proper margin. The qualification test level shall exceed the maximum predicted levels by a factor of safety or qualific

46、ation margin; unless otherwise specified, the qualification test duration shall be longer than maximum environment duration with appropriate qualification margin. In addition, qualification tests shall validate methods, procedures, facility conditions and ground support test equipment that will be r

47、eused for acceptance. 4.5 Acceptance tests Acceptance tests shall demonstrate that the item is free of workmanship defects and integration errors and that its function and performance to the extent practicable can meet stipulated mission requirements. Acceptance tests detect latent material or workm

48、anship defects introduced during the manufacturing and assembly process by measuring function and performance parameters. Such parameters shall be measured through sequential tests to identify function and performance degradation that is likely to damage mission purposes and to establish a baseline

49、to ensure that no degradation is found in the data history. 4.6 Proto-flight tests It shall be recognized that the proto-flight approach presents a higher risk than the approach in which design margins are demonstrated by the testing of a dedicated nonflight qualification item. Moreover, programmatic realities of limited production, tight schedules, and budgetary limits do not always allow the use of dedicated nonflight qualification items. In response, s