BS ISO 15862-2009 Space systems - Launch-vehicle-to-spacecraft flight environments telemetry data processing《航空系统 航天器的运载火箭飞行环境遥感勘测数据处理》.pdf

《BS ISO 15862-2009 Space systems - Launch-vehicle-to-spacecraft flight environments telemetry data processing《航空系统 航天器的运载火箭飞行环境遥感勘测数据处理》.pdf》由会员分享，可在线阅读，更多相关《BS ISO 15862-2009 Space systems - Launch-vehicle-to-spacecraft flight environments telemetry data processing《航空系统 航天器的运载火箭飞行环境遥感勘测数据处理》.pdf（18页珍藏版）》请在麦多课文档分享上搜索。

1、BS ISO15862:2009ICS 49.140NO COPYING WITHOUT BSI PERMISSION EXCEPT AS PERMITTED BY COPYRIGHT LAWBRITISH STANDARDSpace systems Launch-vehicle-to-spacecraft flightenvironmentstelemetry dataprocessingThis British Standardwas published under theauthority of the StandardsPolicy and StrategyCommittee on 3

2、1 March2009 BSI 2009ISBN 978 0 580 61663 1Amendments/corrigenda issued since publicationDate CommentsBS ISO 15862:2009National forewordThis British Standard is the UK implementation of ISO 15862:2009.The UK participation in its preparation was entrusted to TechnicalCommittee ACE/68/-/2, Space system

3、s and operations - Interfaces,integration and test.A list of organizations represented on this committee can be obtained onrequest to its secretary.This publication does not purport to include all the necessary provisionsof a contract. Users are responsible for its correct application.Compliance wit

4、h a British Standard cannot confer immunityfrom legal obligations.BS ISO 15862:2009Reference numberISO 15862:2009(E)ISO 2009INTERNATIONAL STANDARD ISO15862First edition2009-02-01Space systems Launch-vehicle-to-spacecraft flight environments telemetry data processing Systmes spatiaux Traitement des d

5、onnes tlmtriques des environnements de vol entre le lanceur spatial et le vhicule spatial BS ISO 15862:2009ISO 15862:2009(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

6、typefaces which are embedded are licensed to and installed on the computer performing the editing. In downloading this file, parties accept therein the responsibility of not infringing Adobes licensing policy. The ISO Central Secretariat accepts no liability in this area. Adobe is a trademark of Ado

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8、likely event that a problem relating to it is found, please inform the Central Secretariat at the address given below. COPYRIGHT PROTECTED DOCUMENT ISO 2009 All rights reserved. Unless otherwise specified, no part of this publication may be reproduced or utilized in any form or by any means, electro

9、nic or mechanical, including photocopying and microfilm, without 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

10、 Web www.iso.org Published in Switzerland ii ISO 2009 All rights reservedBS ISO 15862:2009ISO 15862:2009(E) ISO 2009 All rights reserved iiiForeword ISO (the International Organization for Standardization) is a worldwide federation of national standards bodies (ISO member bodies). The work of prepar

11、ing 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 on that committee. International organizations, governmental and non-governmental, in li

12、aison 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 drafted in accordance with the rules given in the ISO/IEC Directives, Part 2. The main task of

13、 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 Standard requires approval by at least 75 % of the member bodies casting a vote. Attention is

14、 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 15862 was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 14, Space s

15、ystems and operations. BS ISO 15862:2009ISO 15862:2009(E) iv ISO 2009 All rights reservedIntroduction This International Standard addresses flight environment measurements, data processing and analysis, and reports of analysis results. If launch vehicle (LV) environmental specifications are exceeded

16、, the LV and spacecraft (SC) agencies can perform an analysis to determine the cause of the problem. Flight environments describe different types of flight mechanical and thermal environments. Measurement fields include parameters characterizing such environments as loads, vibration, shock, acoustic

17、s, steady-state pressure and temperature. Requirements include number, location, range and frequency of measurement devices. Data processing and analysis include data pre-processing, data processing and formats of delivered data. Flight measurement plan formats are provided. The report on flight env

18、ironment analysis results records all the above information. BS ISO 15862:2009INTERNATIONAL STANDARD ISO 15862:2009(E) ISO 2009 All rights reserved 1Space systems Launch-vehicle-to-spacecraft flight environments telemetry data processing 1 Scope This International Standard provides basic requirement

19、s for the measurement of the spacecraft flight environments generated by the launch vehicle, telemetry data processing and formats of analysis reports. This International Standard defines the field and number of measurement parameters, the principles of data processing, the format of delivered data

20、and the content and the form of the flight environment analysis report. Flight telemetry data are used to verify if flight environment conditions exceed pre-flight analyses and environmental test results. In the event of a launch failure, adequate flight environment data can assist in investigating

21、and analysing failure causes. This International Standard is applicable to commercial launch vehicles and related ground processing, no matter which launch vehicle agencies are selected. 2 Terms and definitions For the purposes of this document, the following terms and definitions apply. 2.1 cut-off

22、 load case when the engine thrust begins to decrease from current value to zero 2.2 ground transportation spacecraft transportation at launch site 2.3 lift-off launch vehicle motion when the vehicles contact is terminated with launch pad or other support devices NOTE This is commonly called “first m

23、otion” of the vehicle. Possible abnormal cut-off is also included. 2.4 load case event in spacecraft service life during which essential mechanical environments are expected 2.5 maximum dynamic pressure phase flight phase when dynamic pressure reaches its maximum value 2.6 minimum sampling frequency

24、 minimum number of data points of measurement fields collected per second BS ISO 15862:2009ISO 15862:2009(E) 2 ISO 2009 All rights reserved2.7 spacecraft-to-launch-vehicle interface SC/LV interface mechanical interface that connects spacecraft (or spacecraft-provided adapter) to launch-vehicle-provi

25、ded adapter 2.8 separation separations of launch vehicle stages, boosters and other structural elements (e.g. fairing jettison) 2.9 steady-state acceleration constant acceleration that generates static loads. 2.10 transonic phase flight phase when the Mach number is in the range of 0,8 to 1,2 3 Abbr

26、eviated terms LV launch vehicle PSD power spectral density SC spacecraft SPL sound pressure level SRS shock response spectrum RMS root mean square 4 Flight environments, measurement fields and measurement requirements 4.1 Flight environments 4.1.1 General Different types of mechanical environments a

27、nd thermal environments are described in 4.1.2 to 4.1.8 below. 4.1.2 Quasi-static load The quasi-static load is the resultant of all external forces with the exception of gravity applied on the LV centre of gravity. 4.1.3 Low-frequency vibration Low-frequency vibration is the structural response gen

28、erated mainly by thrust variation of the LV engines at ignition and cut-off, by fluctuation of the pressure during the transonic phase, and by transient loads at stage separation(s). 4.1.4 High-frequency vibration High-frequency vibration is the structural response generated mainly by the LV engine

29、noise and by the aerodynamic noise. High-frequency vibration reaches the maximum during lift-off, ascent phase and transonic flight. BS ISO 15862:2009ISO 15862:2009(E) ISO 2009 All rights reserved 34.1.5 Acoustic noise Acoustic noise is the sound pressure generated mainly by the LV engine noise and

30、by aerodynamics. The maximum fairing internal noise occurs during lift-off, ascent phase and transonic flight. 4.1.6 Shock Shock environment consists of the transient response generated by the LV fairing jettison, stage separation(s) and SC/LV separation(s). 4.1.7 Steady-state pressure The steady-st

31、ate pressure field consists of the instantaneous pressure of air outside the LV and inside the fairing. The fairing internal pressure of air decreases gradually during the LV ascent phase due to air escape. The fairing internal pressure of air is related to the flight trajectory, the shape of the fa

32、iring and the vent configurations. 4.1.8 Thermal The launch phase thermal environment is dependent on the fairing aerodynamic heating, the radiation of the sun and the earth, and the space conditions. 4.2 Measurement fields Measurement fields shall be determined by common agreement between the LV se

33、rvice provider and the SC customer. Unless otherwise specified, the following measurement fields shall be planned and corresponding measurements shall be conducted: steady-state acceleration, low-frequency vibration, high-frequency vibration, acoustic noise, shock acceleration, steady-state pressure

34、, and temperature. 4.3 Measurement requirements 4.3.1 Number and location of measurements 4.3.1.1 Steady-state acceleration As a minimum, steady-state acceleration shall be measured at one location in the LV longitudinal axis and the two lateral orthogonal axes. The measurement location shall be clo

35、se to the SC/LV interface. NOTE In general, this practice is recommended for developmental flights, but is often not required for operational systems. BS ISO 15862:2009ISO 15862:2009(E) 4 ISO 2009 All rights reserved4.3.1.2 Low-frequency vibration As a minimum, low-frequency vibration shall be measu

36、red at one location in the LV longitudinal axis and the two lateral orthogonal axes. The measurement location shall be close to the SC/LV interface. 4.3.1.3 High-frequency vibration As a minimum, high-frequency vibration shall be measured at one location in the LV longitudinal axis and the two later

37、al orthogonal axes. The measurement location shall be close to the SC/LV interface. NOTE In general, this practice is recommended for developmental flights, but is often not required for operational systems. 4.3.1.4 Acoustic noise As a minimum, acoustic sound pressure shall be measured at two points

38、. The measurement location shall be representative of the acoustic field inside the fairing. 4.3.1.5 Shock acceleration As a minimum, shock acceleration shall be measured at one location in the LV longitudinal axis and in one orthogonal axis. The measurement location shall be close to the SC/LV inte

39、rface. NOTE In general, this practice is recommended for developmental flights, but is often not required for operational systems. 4.3.1.6 Steady-state pressure As a minimum, steady-state pressure shall be measured at one location. The measurement location shall be chosen inside the fairing to indic

40、ate the ambient pressure. NOTE In general, this practice is recommended for developmental flights, but is often not required for operational systems. 4.3.1.7 Temperature As a minimum, temperature shall be measured at one location. The measurement location shall be chosen close to the SC/LV interface

41、. 4.3.2 Measurement range selection The range of measurement shall be properly defined by the LV agency. 4.3.3 Frequency range and minimum sampling frequency Frequency ranges and minimum sampling frequency shall be selected to provide representative measurement results for flight environment charact

42、eristics evaluation. Frequency ranges, corresponding measuring tool parameters and minimum sampling frequencies shall be selected to prevent frequency masking phenomena. Frequency ranges and minimum sampling frequencies shall be established in technical specifications and/or in a statement of works

43、by agreement between the SC and LV agencies. BS ISO 15862:2009ISO 15862:2009(E) ISO 2009 All rights reserved 54.4 Flight measurement plan The flight measurement plan shall be properly defined by the LV agency and shall be agreed by the SC customer. It shall include the list, type, location, orientat

44、ion, characteristics of the measurement sensors, ranges of frequencies, sequence of measurement, as well as the minimal sampling frequency of sensors needed to fulfil the measurement requirements. For each measurement sensor, the following are examples to be described in the plan: identification cod

45、e, type, location, direction (if applicable), units, measurement range, frequency range, sampling rate, sensitivity, and accuracy. 5 Data processing and analysis 5.1 Data pre-processing procedure 5.1.1 General The time history of telemetry data shall be examined for data quality. If the signal time

46、history is inconsistent with corresponding parameter physical nature, the signal shall be regarded as invalid. Telemetry malfunction segments shall be identified and excluded from further processing. 5.1.2 Steady-state acceleration, steady-state pressure and temperature Because steady-state accelera

47、tion, steady-state pressure and temperature change slowly along with time, large and unexpected changes of signal for a very short duration shall be regarded as corrupted data points and shall be deleted or replaced with adjacent data points. 5.1.3 Low-frequency vibration, high-frequency vibration,

48、acoustic noise and shock acceleration 5.1.3.1 Data quality identification The time history shall be plotted and examined for data quality. The signal amplitude should be properly evaluated to determine whether the signal is regarded as valid or invalid. BS ISO 15862:2009ISO 15862:2009(E) 6 ISO 2009

49、All rights reserved5.1.3.2 Pseudo-signal identification The pseudo-signal is identified as a random signal with a value significantly greater than the root mean square of the validated signal for a short period. Pseudo-signal shall be discarded. 5.1.3.3 Zero drift elimination Low-frequency vibration, high-frequency vibration, acoustic noise and shock acceleration signals shall be processed to eliminate zero drift. 5.1.3.4 Mean value correction Low-frequency vibration signals shall be processed to corr