ISO 10784-1-2011 Space systems - Early operations - Part 1 Spacecraft initialization and commissioning《航天系统 早期运行 第1部分 宇宙飞船的初始化和调试》.pdf

《ISO 10784-1-2011 Space systems - Early operations - Part 1 Spacecraft initialization and commissioning《航天系统 早期运行 第1部分 宇宙飞船的初始化和调试》.pdf》由会员分享，可在线阅读，更多相关《ISO 10784-1-2011 Space systems - Early operations - Part 1 Spacecraft initialization and commissioning《航天系统 早期运行 第1部分 宇宙飞船的初始化和调试》.pdf（16页珍藏版）》请在麦多课文档分享上搜索。

1、Space systems Early operations Part 1: Spacecraft initialization and commissioning Systmes spatiaux Oprations initiales Partie 1: Initialisation et prise en mains du vhicule spatial ISO 2011 Reference number ISO 10784-1:2011(E) First edition 2011-12-01 ISO 10784-1 INTERNATIONAL STANDARDISO 10784-1:2

2、011(E)COPYRIGHT PROTECTED DOCUMENT ISO 2011 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, without permission in writing from either ISO at the add

3、ress 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 2011 All rights reservedISO 10784-1:2011(E) ISO 2011 All rights

4、reserved iii Contents 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 Introduction clause of an initialization plan or commissioning report . 2 4.1 General . 2 4.2 Overall se

5、quence of initialization events 2 4.3 Overall relations of commissioning functions 2 4.4 Orbital-debris considerations in spacecraft initialization and commissioning . 2 5 Objectives of spacecraft initialization and commissioning . 3 5.1 General . 3 5.2 Spacecraft initialization and commissioning st

6、rategy matrix . 3 6 Spacecraft configuration for spacecraft initialization and commissioning 5 6.1 General . 5 6.2 Identification and general configuration . 5 6.3 Deviations from the planned configuration 5 6.4 Functional configuration . 5 7 Spacecraft initialization plan 5 7.1 General . 5 7.2 Spac

7、ecraft configuration . 6 7.3 Initialization constraints and limitations . 6 8 Spacecraft commissioning report 6 8.1 General . 6 8.2 Approach and methodology . 6 8.3 Event flow 6 8.4 Supporting analyses . 6 8.5 Input parameters, tolerances, and limits 7 8.6 Instrumentation 7 8.7 Success criteria . 7

8、8.8 Evaluation of results . 7 8.9 Deviations 7 8.10 Conclusion 7 Bibliography . 8Foreword 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

9、 ISO technical committees. 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 collaborate

10、s closely with the International 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

11、. Draft International Standards 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

12、 document may be the subject of patent rights. ISO shall not be held responsible for identifying any or all such patent rights. ISO 10784-1 was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 14, Space systems and operations. ISO 10784 consists of the followin

13、g parts, under the general title Space systems Early operations: Part 1: Spacecraft initialization and commissioning Part 2: Initialization plan Part 3: Commissioning report ISO 10784-1:2011(E)iv ISO 2011 All rights reservedIntroduction The three parts of ISO 10784 provide spacecraft (SC) manufactur

14、ers and operators with a specific form and format for writing SC initialization plans and commissioning reports required to configure and verify the SC to perform normal mission operations. Often, SC manufacturers and operators have defined these plans and reports uniquely for each programme, or reg

15、ional, national and corporate organizations have unique initialization plans and commissioning reports. The three parts of ISO 10784 aim at establishing a common language and form for SC stakeholders. The use of one form and format will simplify stakeholder understanding of initialization and commis

16、sioning activities. ISO 10784-1:2011(E) ISO 2011 All rights reserved vINTERNATIONAL STANDARD ISO 10784-1:2011(E) Space systems Early operations Part 1: Spacecraft initialization and commissioning 1 Scope A general definition of initialization is that it begins at separation of the spacecraft (SC) fr

17、om the launcher. In some cases, a more exact definition will be that initialization begins in flight, upon planned change in mode or state of the SC from the launch configuration. Commissioning is completed when the SC, including its payload, is certified for initial mission operations. Prior to cer

18、tification for mission operations, the SC is described as a test article in the three parts of ISO 10784. ISO 10784 does not include a requirement for contingency plans, but does include a statement of the need for contingency planning. This part of ISO 10784 outlines general descriptive information

19、 for SC initialization and commissioning as might be appropriate for programme management, project engineering or programme test documentation. Since the SC is considered a test article at this phase of its operational life, ISO 17566 is used as a normative reference in constructing the initializati

20、on plan and the commissioning report. It provides SC manufacturers, SC operators and other stakeholders with a common language and form to verify and document spacecraft initialization and commissioning prior to normal SC mission operations. 2 Normative references The following referenced documents

21、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 10784-3:2011, Space systems Early operations Part 3: Commissioning report ISO 17

22、566, Space systems General test documentation ISO 24113:2011, Space systems Space debris mitigation requirements 3 Terms, definitions and abbreviated terms 3.1 Terms and definitions For the purposes of this document, the following terms and definitions apply. 3.1.1 commissioning certification of a s

23、pacecraft as ready for mission operations 3.1.2 early operations period from initialization to commissioning for mission operations 3.1.3 initialization initial functional and operational checkout of a spacecraft following separation from the launch vehicle ISO 2011 All rights reserved 13.2 Abbrevia

24、ted terms LV launch vehicle PL payload SC spacecraft 4 Introduction clause of an initialization plan or commissioning report 4.1 General The introduction clause of an initialization plan or commissioning report shall provide general information about the technical content of the initialization plan

25、and the commissioning report. It shall include a brief description of the initialization sequence. The overall initialization objective shall be described, and the criteria for the SC certification shall be stated. 4.2 Overall sequence of initialization events This subclause of the introductory clau

26、se shall summarize the overall sequence of functional and operational sequences conducted to demonstrate the initial operational status of the spacecraft with respect to the operational environment and shall explain how the test in question fits into this sequence. The starting mode of the spacecraf

27、t shall be the same as the launch mode. The ending mode of the spacecraft shall be the initial operational mode. 4.3 Overall relations of commissioning functions This subclause shall summarize the minimum overall relations and status of spacecraft functions demonstrated to verify the initial operati

28、onal capability of the system. 4.4 Orbital-debris considerations in spacecraft initialization and commissioning 4.4.1 General Orbital-debris generation is a major consideration during spacecraft initialization and will impose limitations. It is possible that limitations might be placed on both the s

29、pacecraft and the launch vehicle in this phase. 4.4.2 Hardware retention Hardware retention requirements relevant during spacecraft initialization shall be addressed (see ISO 24113:2011, Subclause 6.1). 4.4.3 Avoiding damage This subclause shall summarize the retention measures taken to avoid the re

30、lease of hardware into space (see ISO 24113:2011, Subclause 6.1). Failure to control separation of space objects might result in later contact with, and damage to, the spacecraft. 4.4.4 Collision avoidance This subclause shall summarize the measures taken for avoiding collisions. Collision avoidance

31、 recommendations relevant during spacecraft initialization are contained in the IADC Space Debris Mitigation Guidelines, Revision 1 (September 2007), Subclause 5.4. ISO 10784-1:2011(E)2 ISO 2011 All rights reserved4.4.5 Conjunction analysis This subclause shall summarize the conjunction analysis per

32、formed for the purpose of collision avoidance. Conjunction analysis recommendations relevant during spacecraft initialization are contained in the IADC Space Debris Mitigation Guidelines, Revision 1 (September 2007), Subclause 5.4. 5 Objectives of spacecraft initialization and commissioning 5.1 Gene

33、ral This clause shall detail the general and specific objectives in the context of the spacecraft and payload initialization. A minimum set of objectives for successful initialization shall be identified. It is possible to conceive of simple spacecraft and missions and more complex spacecraft and mi

34、ssions. The user determines the number of operational phases for their unique programme. For example, a multi-phase mission to another planet might have an initialization and commissioning strategy matrix for the spacecraft initial earth orbit, another for the interplanetary phase and a third for in

35、sertion into orbit around the target planet. 5.2 Spacecraft initialization and commissioning strategy matrix The strategy matrix shall define the strategies that will be used to demonstrate compliance with the SC operators requirements related to the spacecraft in general and the payload in particul

36、ar. The required format for the strategy matrix is shown below with a notional sequence of events. Table 1 Initialization and commissioning strategy matrix Event Time Operational requirement SC or PL procedure Prerequisites or constraints Notes Pre-launch Pre-1 Apply power to SC Pre-2 Load SC proces

37、sor with flight softwarePre-3 Upload separation orbit dataOrbit data should be in Earth-centred, Earth-fixed (ECEF) coordinates Pre-4 Upload contact informationUpload at least three days of contact information Pre-5 Verify count of commands on SC processorPre-6 Verify that SC battery is fully charge

38、dPre-7 Safe SC and PL for launch Verify LAUNCH modePre-8 Remove power from SCUnpowered launch Post-launch 1 Separation (S) Record LV separation time and separation orbit dataRetrieve from launch service provider as soon after launch as possible ISO 10784-1:2011(E) ISO 2011 All rights reserved 3Event

39、 Time Operational requirement SC or PL procedure Prerequisites or constraints Notes 2 S+00h05m00 s Determine time of expected initial contact3 Turn on SC processor and load flight software Triggered by LV separation switch4 Start communications queue for initial transmitter turn-on Triggered by LV s

40、eparation switch5 Ensure safe separation from LV6 Damp SC velocity and rotation rates sufficiently for solar-array deployment Triggered by LV separation switch7 Deploy solar arrays Triggered by LV separation switch8 Ensure operation of SC power supply Point solar array towards sun Triggered by LV se

41、paration switch9 Verify proper operation of all SC subsystems Electrical power system Verify that power sufficient SC overhead of ground station10 Verify proper operation of all SC subsystems Attitude determination and control system Verify that solar array pointing at sun and that orbit data correc

42、t and propagating SC overhead of ground station11 Verify proper operation of all SC subsystems Flight software Verify that clock correct SC overhead of ground station12 Verify proper operation of all SC subsystems Telemetry, tracking and commanding Verify that commands being received in real time an

43、d being stored; verify command count and increment Verify that telemetry and other data being received in real time and being stored Download stored state of health of SC SC overhead of ground stationISO 10784-1:2011(E)Table 1 (continued) 4 ISO 2011 All rights reservedEvent Time Operational requirem

44、ent SC or PL procedure Prerequisites or constraints Notes 13 Verify proper operation of all SC subsystems Thermal All components within allowed temperature range SC overhead of ground station14 Control SC in OPERATIONAL mode SC overhead of ground station15 Verify functionality of PLSC overhead of gr

45、ound station Might be similar to SC verification sequence 16 Calibrate PL SC in OPERATIONAL mode17 Control PL in OPERATIONAL mode6 Spacecraft configuration for spacecraft initialization and commissioning 6.1 General This clause shall define how the spacecraft configuration, including the correspondi

46、ng reference frame definition and mass properties, and relevant figures or references to relevant drawings, are described. When necessary, the description shall document how the configuration supports the overall initialization objectives. 6.2 Identification and general configuration All major space

47、craft subsystems shall be listed in a configuration matrix. Changes in the configuration matrix shall be made to reflect initialization events in the initialization and commissioning strategy matrix. 6.3 Deviations from the planned configuration Deviations of the general test article configuration f

48、rom the flight configuration that are critical for the qualification of the SC with respect to the launch environment shall be identified (see ISO 10784-3:2011, Subclause 8.2). The qualification logic with respect to the overall system qualification of those items that are not in the flight standard

49、 category shall be explained. 6.4 Functional configuration The state of the physical systems of the SC shall be described and compared to the expected SC launch configuration. Any change of functional configuration in the course of the initialization sequence shall be mentioned. The functional configuration addresses the operational mode of the SC and the state of the major electrical systems, including, but not limited to, radio-electrical, pyrotechnic, attitude control and thermal subsystems. 7 Spac