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1、 Reference number ISO 15862:2009(E) ISO 2009 INTERNATIONAL STANDARD ISO 15862 First edition 2009-02-01 Space systems Launch-vehicle-to- spacecraft flight environments telemetry data processing Systmes spatiaux Traitement des donnes tlmtriques des environnements de vol entre le lanceur spatial et le
2、vhicule spatial Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=HP Monitoring/1111111164 Not for Resale, 04/08/2009 02:04:49 MDTNo reproduction or networking permitted without license from IHS -,-,- ISO 15862:2009(E) PDF disclaimer This PDF fi
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6、 2009 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 address below or ISOs member body in the
7、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 2009 All rights reserved Copyright International Organization for Standardization Provided by IHS unde
8、r license with ISO Licensee=HP Monitoring/1111111164 Not for Resale, 04/08/2009 02:04:49 MDTNo reproduction or networking permitted without license from IHS -,-,- ISO 15862:2009(E) ISO 2009 All rights reserved iii Foreword ISO (the International Organization for Standardization) is a worldwide feder
9、ation 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 on that commit
10、tee. 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 drafted in accordanc
11、e 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 Standard requires a
12、pproval 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 15862 was prepared by Technical Com
13、mittee ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 14, Space systems and operations. Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=HP Monitoring/1111111164 Not for Resale, 04/08/2009 02:04:49 MDTNo reproduction or networking perm
14、itted without license from IHS -,-,- ISO 15862:2009(E) iv ISO 2009 All rights reserved Introduction This International Standard addresses flight environment measurements, data processing and analysis, and reports of analysis results. If launch vehicle (LV) environmental specifications are exceeded,
15、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, acoustics,
16、 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 envir
17、onment analysis results records all the above information. Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=HP Monitoring/1111111164 Not for Resale, 04/08/2009 02:04:49 MDTNo reproduction or networking permitted without license from IHS -,-,- I
18、NTERNATIONAL STANDARD ISO 15862:2009(E) ISO 2009 All rights reserved 1 Space systems Launch-vehicle-to-spacecraft flight environments telemetry data processing 1 Scope This International Standard provides basic requirements for the measurement of the spacecraft flight environments generated by the l
19、aunch 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 and the content and the form of the flight environment analysis report. Flight
20、 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 and analysing failure causes. This International Standard is applicable to com
21、mercial 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 load case when the engine thrust begins to decrease from current value to zer
22、o 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 motion” of the vehicle. Possible abnormal cut-off is also included. 2.4 load ca
23、se 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 minimum number of data points of measurement fields collected per second Copy
24、right International Organization for Standardization Provided by IHS under license with ISO Licensee=HP Monitoring/1111111164 Not for Resale, 04/08/2009 02:04:49 MDTNo reproduction or networking permitted without license from IHS -,-,- ISO 15862:2009(E) 2 ISO 2009 All rights reserved 2.7 spacecraft-
25、to-launch-vehicle interface SC/LV interface mechanical interface that connects spacecraft (or spacecraft-provided adapter) to launch-vehicle-provided adapter 2.8 separation separations of launch vehicle stages, boosters and other structural elements (e.g. fairing jettison) 2.9 steady-state accelerat
26、ion 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 Abbreviated terms LV launch vehicle PSD power spectral density SC spacecraft SPL sound pressure level SRS shock response spectrum RMS root mean square 4 Fligh
27、t environments, measurement fields and measurement requirements 4.1 Flight environments 4.1.1 General Different types of mechanical environments and 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
28、the exception of gravity applied on the LV centre of gravity. 4.1.3 Low-frequency vibration Low-frequency vibration is the structural response generated 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 l
29、oads at stage separation(s). 4.1.4 High-frequency vibration High-frequency vibration is the structural response generated mainly by the LV engine noise and by the aerodynamic noise. High-frequency vibration reaches the maximum during lift-off, ascent phase and transonic flight. Copyright Internation
30、al Organization for Standardization Provided by IHS under license with ISO Licensee=HP Monitoring/1111111164 Not for Resale, 04/08/2009 02:04:49 MDTNo reproduction or networking permitted without license from IHS -,-,- ISO 15862:2009(E) ISO 2009 All rights reserved 3 4.1.5 Acoustic noise Acoustic no
31、ise is the sound pressure generated mainly by the LV engine noise and 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
32、(s) and SC/LV separation(s). 4.1.7 Steady-state pressure The steady-state 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 pr
33、essure of air is related to the flight trajectory, the shape of the fairing 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 Measur
34、ement fields shall be determined by common agreement between the LV service 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-frequenc
35、y vibration, acoustic noise, shock acceleration, steady-state pressure, 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
36、the two lateral 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. Copyright International Organization for Standardization Provided by IHS under
37、license with ISO Licensee=HP Monitoring/1111111164 Not for Resale, 04/08/2009 02:04:49 MDTNo reproduction or networking permitted without license from IHS -,-,- ISO 15862:2009(E) 4 ISO 2009 All rights reserved 4.3.1.2 Low-frequency vibration As a minimum, low-frequency vibration shall be measured at
38、 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 lateral ort
39、hogonal 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. The
40、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 interface.
41、 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 indicate th
42、e 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. 4.3.
43、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 characteristi
44、cs 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 by agr
45、eement between the SC and LV agencies. Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=HP Monitoring/1111111164 Not for Resale, 04/08/2009 02:04:49 MDTNo reproduction or networking permitted without license from IHS -,-,- ISO 15862:2009(E) ISO
46、 2009 All rights reserved 5 4.4 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, orientation, characteristics of the measurement sensors, ranges of frequencies, sequence o
47、f 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 code, type, location, direction (if applicable), units, measurement range, frequency
48、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 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 p