BS ISO 24917-2010 Space systems General test requirements for launch vehicles《空间系统 运载火箭用一般试验要求》.pdf

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1、raising standards worldwideNO COPYING WITHOUT BSI PERMISSION EXCEPT AS PERMITTED BY COPYRIGHT LAWBSI Standards PublicationBS ISO 24917:2010Space systems Generaltest requirements for launchvehiclesBS ISO 24917:2010 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of ISO

2、 24917:2010.The UK participation in its preparation was entrusted to TechnicalCommittee ACE/68/-/2, Space systems and operations - Interfaces,integration and test.A list of organizations represented on this committee can beobtained on request to its secretary.This publication does not purport to inc

3、lude all the necessaryprovisions of a contract. Users are responsible for its correctapplication. BSI 2010ISBN 978 0 580 65004 8ICS 49.140Compliance with a British Standard cannot confer immunity fromlegal obligations.This British Standard was published under the authority of theStandards Policy and

4、 Strategy Committee on 31 December 2010.Amendments issued since publicationDate Text affectedBS ISO 24917:2010Reference numberISO 24917:2010(E)ISO 2010INTERNATIONAL STANDARD ISO24917First edition2010-10-15Space systems General test requirements for launch vehicles Systmes spatiaux Exigences gnrales

5、dessai pour vhicules lanceurs BS ISO 24917:2010ISO 24917:2010(E) PDF disclaimer This PDF file may contain embedded typefaces. In accordance with Adobes licensing policy, this file may be printed or viewed but shall not be edited unless the typefaces which are embedded are licensed to and installed o

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8、inform the Central Secretariat at the address given below. COPYRIGHT PROTECTED DOCUMENT ISO 2010 All rights reserved. Unless otherwise specified, no part of this publication may be reproduced or utilized in any form or by any means, electronic or mechanical, including photocopying and microfilm, wit

9、hout permission in writing from either ISO at the address below or ISOs member body in the country of the requester. ISO copyright office Case postale 56 CH-1211 Geneva 20 Tel. + 41 22 749 01 11 Fax + 41 22 749 09 47 E-mail copyrightiso.org Web www.iso.org Published in Switzerland ii ISO 2010 All ri

10、ghts reservedBS ISO 24917:2010ISO 24917:2010(E) ISO 2010 All rights reserved iiiContents Page Foreword iv Introduction.v 1 Scope1 2 Normative references1 3 Terms and definitions .1 4 Abbreviated terms .5 5 Testing philosophy6 5.1 Objectives, tasks and principles of launch vehicle and rocket unit exp

11、erimental optimization .6 5.2 LV and rocket unit test types during their development.10 6 Test type and programme requirements.12 6.1 Test object and type requirements12 6.2 General requirements to ground test programme and individual test programme .25 6.3 General test object requirements 28 7 Crit

12、eria 28 8 Reporting28 Annex A (informative) Manufacturing stage, item categories and test categories 29 Annex B (informative) Requirements applicability matrix 30 Annex C (informative) Typical test report contents 31 Annex D (informative) Typical test programme contents .32 Bibliography35 BS ISO 249

13、17:2010ISO 24917:2010(E) iv ISO 2010 All rights reservedForeword ISO (the International Organization for Standardization) is a worldwide federation of national standards bodies (ISO member bodies). The work of preparing International Standards is normally carried out through ISO technical committees

14、. Each member body interested in a subject for which a technical committee has been established has the right to be represented on that committee. International organizations, governmental and non-governmental, in liaison with ISO, also take part in the work. ISO collaborates closely with the Intern

15、ational Electrotechnical Commission (IEC) on all matters of electrotechnical standardization. International Standards are drafted 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 Sta

16、ndards adopted by the technical committees are circulated to the member bodies for voting. Publication as an International Standard 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 subj

17、ect of patent rights. ISO shall not be held responsible for identifying any or all such patent rights. ISO 24917 was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 14, Space systems and operations. BS ISO 24917:2010ISO 24917:2010(E) ISO 2010 All rights reserv

18、ed vIntroduction This International Standard provides space launch vehicle customers, contractors and manufacturers with general requirements for test types and programmes for space launch vehicles and rocket units (modules) to be used in the documentation associated with their test activity. This I

19、nternational Standard is intended to help reduce the development time and cost of space launch vehicles and rocket units, and to enhance their quality and reliability through the use of common, optimized and approved requirements in the space launch vehicle test scope and organization. BS ISO 24917:

20、2010BS ISO 24917:2010INTERNATIONAL STANDARD ISO 24917:2010(E) ISO 2010 All rights reserved 1Space systems General test requirements for launch vehicles 1 Scope This International Standard establishes general test requirements for launch vehicles equipped with liquid-propellant engines, launched from

21、 stationary ground-, sea- and air-based launchers, in all phases of their development. 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

22、 the referenced document (including any amendments) applies. ISO 14302, Space systems Electromagnetic compatibility requirements ISO 14303, Space systems Launch-vehicle-to-spacecraft interfaces 3 Terms and definitions For the purposes of this document, the following terms and definitions apply. 3.1

23、space-rocket complex set of a space vehicle or space launch vehicles with functionally interconnected means and the constructions intended for transportation, storage, maintenance service, preparation, launching and flight control of space launch vehicles on a trajectory of launching of payload 3.2

24、space rocket space launch vehicle plus space nose section integration 3.3 space launch vehicle component of the space rocket designed for payload injection in a pre-assigned trajectory or orbit 3.4 rocket unit space launch vehicle stage including the upper stage vehicle, body, propulsion system, con

25、trol systems or control system elements, rocket units separation aids and telemetry hardware 3.5 upper stage vehicle upper stage of flight vehicle capable of injecting a space vehicle or vehicles into their orbit from the sub-orbital trajectory that resulted from operation of a launch vehicle BS ISO

26、 24917:2010ISO 24917:2010(E) 2 ISO 2010 All rights reserved3.6 space nose section set of a space vehicle with fairing and adapter and upper stage vehicle NOTE Upper stage vehicle can be absent. 3.7 fairing technical device intended for protection of a space vehicle or of a space nose section from ex

27、ternal influences at transportation of the space launch vehicle on a launcher and on a start of the space launch vehicle and on a trajectory of launching into an orbit of a space vehicle 3.8 integration site equipment and facility designed for launch vehicle storage, assembly, testing, preparation,

28、maintenance, servicing and preparation for transportation to the launch pad ISO/TR 17400:2003, definition 3.1 3.9 launch pad equipment and facility designed to provide for the pre-launch and launch operations of spacecraft ISO/TR 17400:2003, definition 3.3 3.10 launch pad for space launch vehicle de

29、vice intended to maintain the space launch vehicle in readiness for launch, and for the launch itself 3.11 technical project on development of a product initial document establishing a complex of technical requirements to created products, and to the contents, volume and terms of performance of desi

30、gn experiment works as well 3.12 technical specification specification expressing technical requirements for designing and developing the solution to be implemented NOTE The technical specification evolves from the functional specification and defines the technical requirements for the selected solu

31、tion as part of a business agreement. ISO 21351:2005, definition 3.1.11 3.13 requirement need or expectation that is stated, generally implied or obligatory NOTE 1 “Generally implied” means that it is custom or common practice for the organization, its customers and other interested parties that the

32、 need or expectation under consideration is implied. NOTE 2 A qualifier can be used to denote a specific type of requirement, e.g. product requirement, quality management requirement, customer requirement. NOTE 3 A specified requirement is one which is stated, for example, in a document. NOTE 4 Requ

33、irements can be generated by different interested parties. ISO 9000:2005, definition 3.1.2 BS ISO 24917:2010ISO 24917:2010(E) ISO 2010 All rights reserved 33.14 interface control document ICD document of launcher and fairing/payload which defines all physical, electrical and mechanical interfaces be

34、tween the payload and the launch vehicle hardware and software, and interfaces between payload and support equipment and space site facilities, systems and hardware used for spacecraft launch preparation 3.15 test formal process of exercising or putting to trial a system or item by manual or automat

35、ic means to identify differences between specified, expected and actual results 3.16 test conditions combination of effects of factors, or object operation conditions, or both, during the test 3.17 test metrological provision establishment and application of scientific and organizational basis, tech

36、nical means, rules and standards necessary for achieving the measurement unity demanded, precision, completeness, operativeness and the reliability of parameters control and technical characteristics of items 3.18 ground test programme organizational-methodological document obligatory for execution,

37、 which specifies the test object and objectives, types, sequence and scope of conducted experiments, order, conditions, place, time and support of test, test reporting, as well as responsibility for test support and conduct 3.19 reliability assurance programme programme document specifying a set of

38、requirements and measures aimed at providing and controlling the satisfaction of requirements established for the statement of work for a space launch vehicle and its components reliability during their development 3.20 space launch vehicle (unit) experimental optimization operations of modelling un

39、its, mock-ups, test prototypes in order to assure operation of items in accordance with statement of work, definition their efficiency margins 3.21 safety assurance programme programme document which establishes a set of requirements and measures aimed at assuring that all safety risks associated wi

40、th the space launch vehicle design, development, manufacture and use are accordingly identified, assessed, minimized, controlled and accepted 3.22 telemetry measurement programme programme document establishing the composition of telemetry measurement hardware born set on space launch vehicle, launc

41、h pad and positioned along the flight route necessary for satisfying the measurement requirements as well as places and orientation of sensors arrangement and their characteristics, frequency bands, minimal frequency of sensor polling 3.23 flight test tests in real conditions of functioning and perf

42、ormance of target tasks BS ISO 24917:2010ISO 24917:2010(E) 4 ISO 2010 All rights reserved3.24 test prototype of rocket and space technology item item produced in the research and development process applying the newly developed working engineering and technological documentation for test verificatio

43、n of the conformity of its parameters and characteristics with the requirements specified in statement of work to research and development and correctness of adopted technical solutions 3.25 test mock-up (model) structurally, or physically, or structurally and physically similar item presenting a si

44、mplified reproduction of a test object or its part intended for test 3.26 structural model model representing the structural flight characteristics 3.27 electrical model model representing the electrical flight characteristics 3.28 test object item under test 3.29 test type classified test grouping

45、identified according to a certain attribute 3.30 preliminary (development) tests check test of test object prototypes conducted with the purpose of evaluating their conformity with the statement of work requirements and determining their readiness for flight test NOTE Items are subjected to developm

46、ent tests as required, in order to minimize design risk, to demonstrate manufacturing feasibility, to establish packaging designs, to demonstrate electrical and mechanical performance and to demonstrate the capability to withstand environmental stress, including storage, transportation, extreme comb

47、ined environments and launch base operations 3.31 qualification tests required formal contractual tests used to demonstrate that the design, manufacturing, and assembly have resulted in hardware designs conforming to specification requirements ISO 14623:2003, definition 2.52 3.32 acceptance tests re

48、quired formal tests conducted on flight hardware to ascertain that the materials, manufacturing processes and workmanship meet specifications and that the hardware is acceptable for intended usage ISO 14623:2003, definition 2.2 3.33 operational tests tests conducted at the launch vehicle site in an

49、operational environment, with the equipment in its operational configuration BS ISO 24917:2010ISO 24917:2010(E) ISO 2010 All rights reserved 53.34 service (guarantee) life period starting at the completion of fabrication and continuing through all acceptance testing, maintenance, handling, storage, transportation, pre-launch testing, all phases of launch, orbital operations, disposal, re-entry or recovery from orbit 3.35 critical unit unit whose failure can affect the system operation sufficiently to cause the failure