BS ISO 16679-2015 Space systems Relative motion analysis elements after LV SC separation《空间系统 LV SC分离后的相对涌动分析元素》.pdf

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1、BSI Standards PublicationBS ISO 16679:2015Space systems Relativemotion analysis elements afterLV/SC separationBS ISO 16679:2015 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of ISO 16679:2015.The UK participation in its preparation was entrusted to TechnicalCommitte

2、e ACE/68, Space systems and operations.A list of organizations represented on this committee can beobtained on request to its secretary.This publication does not purport to include all the necessaryprovisions of a contract. Users are responsible for its correctapplication. The British Standards Inst

3、itution 2015.Published by BSI Standards Limited 2015ISBN 978 0 580 82565 1ICS 49.140Compliance with a British Standard cannot confer immunity fromlegal obligations.This British Standard was published under the authority of theStandards Policy and Strategy Committee on 31 October 2015.Amendments/corr

4、igenda issued since publicationDate T e x t a f f e c t e dBS ISO 16679:2015 ISO 2015Space systems Relative motion analysis elements after LV/SC separationSystmes spatiaux lments danalyse de mouvement relatif aprs sparation du LV/SCINTERNATIONAL STANDARDISO16679First edition2015-09-01Reference numbe

5、rISO 16679:2015(E)BS ISO 16679:2015ISO 16679:2015(E)ii ISO 2015 All rights reservedCOPYRIGHT PROTECTED DOCUMENT ISO 2015, Published in SwitzerlandAll rights reserved. Unless otherwise specified, no part of this publication may be reproduced or utilized otherwise in any form or by any means, electron

6、ic or mechanical, including photocopying, or posting on the internet or an intranet, without prior written permission. Permission can be requested from either ISO at the address below or ISOs member body in the country of the requester.ISO copyright officeCh. de Blandonnet 8 CP 401CH-1214 Vernier, G

7、eneva, SwitzerlandTel. +41 22 749 01 11Fax +41 22 749 09 47copyrightiso.orgwww.iso.orgBS ISO 16679:2015ISO 16679:2015(E)Foreword ivIntroduction v1 Scope . 12 Normative reference . 13 Terms and definitions . 14 Abbreviated terms 15 Input for analysis . 26 General process . 27 Analysis principle 28 An

8、alysis method 38.1 General . 38.2 Astrodynamics modelling 38.3 Deviation analysis and identification 38.4 Relative motion simulation 38.4.1 Relative motion analysis period . 38.4.2 Deviation . 38.4.3 Relative position calculation 48.4.4 Deviation margin of relative position 48.5 Safety evaluation .

9、49 Analysis output . 4Annex A (informative) Relative motion analysis model . 5Annex B (informative) Typical combination of deviations 6Annex C (informative) Coordinate reference frames and variables 7Annex D (informative) */*-*Preliminary (Final) relative motion analysis report after separation . 8B

10、ibliography .10 ISO 2015 All rights reserved iiiContents PageBS ISO 16679:2015ISO 16679:2015(E)ForewordISO (the International Organization for Standardization) is a worldwide federation of national standards bodies (ISO member bodies). The work of preparing International Standards is normally carrie

11、d 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 on that committee. International organizations, governmental and non-governmental, in liaison with ISO, also take part in the work. IS

12、O collaborates closely with the International Electrotechnical Commission (IEC) on all matters of electrotechnical standardization.The procedures used to develop this document and those intended for its further maintenance are described in the ISO/IEC Directives, Part 1. In particular the different

13、approval criteria needed for the different types of ISO documents should be noted. This document was drafted in accordance with the editorial rules of the ISO/IEC Directives, Part 2 (see www.iso.org/directives). Attention is drawn to the possibility that some of the elements of this document may be

14、the subject of patent rights. ISO shall not be held responsible for identifying any or all such patent rights. Details of any patent rights identified during the development of the document will be in the Introduction and/or on the ISO list of patent declarations received (see www.iso.org/patents).

15、Any trade name used in this document is information given for the convenience of users and does not constitute an endorsement.For an explanation on the meaning of ISO specific terms and expressions related to conformity assessment, as well as information about ISOs adherence to the WTO principles in

16、 the Technical Barriers to Trade (TBT) see the following URL: Foreword - Supplementary informationThe committee responsible for this document is ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 14, Space systems and operations.iv ISO 2015 All rights reservedBS ISO 16679:2015ISO 16679:2015(E)I

17、ntroductionRelative motion analysis predicts the relative distance after launch vehicle (LV) and spacecraft (SC) separation. The analysis result offers support to the mission design and operation.This International Standard provides LV and SC operators and manufacturers with specific elements and pr

18、ocedures for performing relative motion analysis after LV and SC separation. The intent is to regulate a common basis and offer a direction. ISO 2015 All rights reserved vBS ISO 16679:2015BS ISO 16679:2015Space systems Relative motion analysis elements after LV/SC separation1 ScopeThis International

19、 Standard provides relative motion analysis elements after LV/SC separation, including analysis input, analysis principle, analysis method and analysis output. It is applicable to the mission design and verification for the prediction of relative motion after LV/SC separation.This International Stan

20、dard focuses on the relative motion between the objects involved in one launch mission. It does not cover the issues about the collision avoidance between newly launched objects and on-orbit ones.2 Normative referenceThe following documents, in whole or in part, are normatively referenced in this do

21、cument and are indispensable for its application. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced document (including any amendments) applies.ISO 14303, Space systems Launch-vehicle-to-spacecraft interfaces3 Terms and definitionsFor

22、the purposes of this document, the terms and definitions given in ISO 14303 and the following apply.3.1LV/S C s ep a r at ionevent of disconnection between LV/SC under the control of LV3.2relative motion analysisanalysis to predict the relative distance of spacecraft(s) to objects (end stage of LV a

23、nd others generated during the separation) after the LV/SC separation3.3separation velocityrelative speed to LV when separation is completed instantly4 Abbreviated termsLV launch vehicleSC spacecraftICD interface control documentRMS root mean squareINTERNATIONAL STANDARD ISO 16679:2015(E) ISO 2015 A

24、ll rights reserved 1BS ISO 16679:2015ISO 16679:2015(E)5 Input for analysisThe following information shall be included as analysis input.a) Theoretical velocity, position, attitude of LV and (each) spacecraft at the separation moment, which shall be presented in pre-determined coordinate system. Velo

25、city and position vectors shall be offered in the format as Vx, Vy, Vz, X, Y, Z. The potential reference frames are offered in Annex C.b) Separation velocity, mass and inertia characteristics of separation bodies.c) Deviations of LV and separation parts mass, thrust, impulse, moment-inertial charact

26、eristics (optional), tailed-effect, etc.d) Manoeuvres or other operations which shall affect LV end-stage orbit, related parameters and sequences.e) Manoeuvres or other operations which shall affect SC orbit, related parameters and sequences (optional).6 General processIn actual flight, relative mot

27、ion after LV/SC separation is affected by many factors, including certain operations, deviations, mission profile, etc. on both sides. However, in order to simplify collaborations in applications of launch services, LV and SC parties shall perform the following processes:a) LV conducts relative moti

28、on analysis without taking into account SC manoeuvre, attitude control, etc. into account,b) SC evaluates it does not collide with LV orbital stage or other SC (for multi-SC launch mission) after separation due to its manoeuvre, attitude control, etc., based on the result of LV relative motion analy

29、sis.The general process is described in Figure 1, where Party A represents LV and Party B represents SC.The final safety evaluation should be performed based upon LVs and SCs analysis. If necessary input can be offered, the aforementioned processes a) and b) can be incorporated.Party BParty AAstrody

30、namicsmodellingDeviation analysis deviation analysis and identification; relative motion simulation; safety evaluation.8.2 Astrodynamics modellingThe astrodynamics modelling can be achieved in different coordinate systems. One alternative centroid motion model in an Earth-fixed coordinate system is

31、offered in Annex A for information. Motion analysis of different objects should be conducted in the same coordinate system.Gravity, atmosphere force models and related parameters shall be dealt in accordance with the trajectory/orbit calculation.8.3 Deviation analysis and identificationTheoretical p

32、arameters shall be applied in normal analysis while deviation status shall be considered to cover the deviations existing in actual flight. The possible deviations have to be included and necessary items have to be identified for the relative motion analysis.Typical deviations for LV shall include t

33、he following: separation velocity; separation attitude (pitch, yaw); mass of orbital stage; other factors, de-orbit thrust, de-orbit attitude control precision, etc.8.4 Relative motion simulation8.4.1 Relative motion analysis periodRelative motion analysis period should be a period of time agreed up

34、on with the SC contractor. It should be no less than one orbit period.8.4.2 DeviationDeviation trajectory calculations are performed to support the analysis on minimum relative distance between orbital stage and spacecraft. Generally, deviations can be generated in 3 typical manners: margin status,

35、typical combination of deviations, (note that Annex B offers a combination matrix for information) and combination of deviations generated by random sampling method. ISO 2015 All rights reserved 3BS ISO 16679:2015ISO 16679:2015(E)8.4.3 Relative position calculationRelative position calculation shall

36、 be performed using the steps below.a) Calculate the orbits of spacecraft.b) Calculate the deviation trajectory of orbital stage (or other objects generated during separations), according to the choice of deviations.c) Calculate relative positions, via subtractions of spacecrafts orbit and certain d

37、eviation trajectories of orbital stage.8.4.4 Deviation margin of relative positionDeviation margin of relative position depends on the result obtained in 8.4.3 and varies from different deviation choice.a) Margin status: deviation margin equals subtraction of spacecrafts orbit and margin status devi

38、ation trajectory of orbital stage.b) Typical combination of deviations: deviation margin equals subtraction of normal result and deviation obtained via RMS method.c) Combination of deviations generated by random sampling method: deviation margin equals (m-) that was obtained via statistics method an

39、d represent mean value and standard deviation respectively.8.5 Safety evaluationThe minimum relative distance shall be obtained on the base of 8.4.4.The safety evaluation shall be performed according to the minimum safety distance agreed upon with the SC contractor, or the data from similar success

40、flight cases.The determination of minimum safety distance shall take the following factors into account: dimensions of LV orbital stage; dimensions of SC; margin of clearance and spacing.9 Analysis outputThe output shall include the relative motion analysis result between LV and SC during analysis p

41、eriod, and general requirements shall include the following:a) data shall be expressed in international unit;b) present the illustration containing distance versus time curves;c) conclusion.Annex D presents a relative motion analysis template for information.4 ISO 2015 All rights reservedBS ISO 1667

42、9:2015ISO 16679:2015(E)Annex A (informative) Relative motion analysis modelCentroid motion formulae are to be built for all objects involved respectively, including SC, LV and other components generated during the separation(s). Numerical simulations will be conducted taking the data at separation p

43、oint as the initial value to predict the relative motion for objects in the analysis period.The coordinate system can be selected according to specific requirements, and be confirmed between parties.The basic motion formulae under Earth-fixed coordinate systems are presented for reference,dotnospdot

44、nospdotnospdotnospdotnospdotnospVVVWWWgggaxyzxyzxyz=+ccxcyczexeyezxyzaaaaaaaa+ =dotnospdotnospdotnospXYZVVVxyz(A.1)wheredotnospdotnospdotnospWWWzxy()is the acceleration vector caused by manoeuvre;gggxyz()is the earth gravity acceleration vector;aaacx cy cz()is the Coriolis acceleration vector;aaaex

45、ey ez()is the centrifugal acceleration vector,aaaxyz()is the perturbation acceleration vector;VVVxyz()is the velocity vector;VVVxyz()is the position vector. ISO 2015 All rights reserved 5BS ISO 16679:2015ISO 16679:2015(E)Annex B (informative) Typical combination of deviationsA typical combination ma

46、trix is listed as shown in Table B.1, different choice of positive and negative are distributed.Table B.1 Typical combination of deviationsDev.Max. Sep. VelMin. Sep. VelMax. Sep. att. (pitch)Min. Sep. att. (pitch)Max. Sep. att. (yaw)Min. Sep. att. (yaw)Sep. Vel + Mass of orbital stage + De-orbit thr

47、ust+ De-orbit att. (pitch) + De-orbit att. (yaw) + Sep. att. (pitch) + - Sep. att. (yaw) + 6 ISO 2015 All rights reservedBS ISO 16679:2015ISO 16679:2015(E)Annex C (informative) Coordinate reference frames and variablesPotential coordinate reference frames and variables applied are as follows: Earth-

48、centred, Earth-fixed (ECEF) Orthogonal system from the centre of the Earth with vertical axis through the geographic North Pole and horizontal axis fixed at 90 longitude. Body-fixed Reference frame affixed to a designated satellite with vertical axis in the nadir direction. J2000 x toward mean verna

49、l equinox, z along Earths mean rotational axis on 1 Jan 2000, 12:00:00.00 UTC. Perigee Orbital Centered on the centre of the Earth, but in the orbital plane of a designated satellite. x toward perigee, y toward the motion direction at perigee. Launch centred earth-fixed A earth-fixed orthogonal system from the launch point with vertical axis pointing up