BS EN 16603-31-2014 Space engineering Thermal control general requirements《航天工程 热控制的通用要求》.pdf

1、BSI Standards PublicationBS EN 16603-31:2014Space engineering Thermalcontrol general requirementsBS EN 16603-31:2014 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of EN 16603-31:2014.It supersedes BS EN 14607-1:2004 which is withdrawn.The UK participation in its pre

2、paration was entrusted to TechnicalCommittee 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 cor

3、rectapplication. The British Standards Institution 2014. Published by BSI StandardsLimited 2014ISBN 978 0 580 84091 3ICS 49.140Compliance with a British Standard cannot confer immunity fromlegal obligations.This British Standard was published under the authority of theStandards Policy and Strategy C

4、ommittee on 30 September 2014.Amendments issued since publicationDate Text affectedBS EN 16603-31:2014EUROPEAN STANDARD NORME EUROPENNE EUROPISCHE NORM EN 16603-31 September 2014 ICS 49.140 Supersedes EN 14607-1:2004 English version Space engineering - Thermal control general requirements Ingnierie

5、spatiale - Contrle thermique, exigences gnrales Raumfahrttechnik - Thermalkontrolle, allgemeine Andorderungen This European Standard was approved by CEN on 1 March 2014. CEN and CENELEC members are bound to comply with the CEN/CENELEC Internal Regulations which stipulate the conditions for giving th

6、is European Standard the status of a national standard without any alteration. Up-to-date lists and bibliographical references concerning such national standards may be obtained on application to the CEN-CENELEC Management Centre or to any CEN and CENELEC member. This European Standard exists in thr

7、ee official versions (English, French, German). A version in any other language made by translation under the responsibility of a CEN and CENELEC member into its own language and notified to the CEN-CENELEC Management Centre has the same status as the official versions. CEN and CENELEC members are t

8、he national standards bodies and national electrotechnical committees of Austria, Belgium, Bulgaria, Croatia, Cyprus, Czech Republic, Denmark, Estonia, Finland, Former Yugoslav Republic of Macedonia, France, Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Net

9、herlands, Norway, Poland, Portugal, Romania, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and United Kingdom. CEN-CENELEC Management Centre: Avenue Marnix 17, B-1000 Brussels 2014 CEN/CENELEC All rights of exploitation in any form and by any means reserved worldwide for CEN national Member

10、s and for CENELEC Members. Ref. No. EN 16603-31:2014 E BS EN 16603-31:2014EN 16603-31:2014 (E) 2 Table of contents Foreword 5 1 Scope . 6 2 Normative references . 7 3 Terms, definitions and abbreviated terms 8 3.1 Terms from other standards 8 3.2 Terms specific to the present standard . 8 3.3 Abbrev

11、iated terms. 19 4 Requirements 21 4.1 Mission . 21 4.1.1 General . 21 4.1.2 Ground and pre-launch . 21 4.1.3 Launch and ascent 21 4.1.4 Planetary orbital phases 22 4.1.5 Interplanetary phases 22 4.1.6 Planetary natural environment 22 4.1.7 Docking, docked and separation phases . 22 4.1.8 Descent, en

12、try and landing 23 4.1.9 Post-landing phases 23 4.2 Performance . 23 4.2.1 General . 23 4.2.2 High temperature range 24 4.2.3 Cryogenic temperature range 24 4.2.4 Functionality 25 4.3 Requirements towards other subsystems . 25 4.3.1 General . 25 4.3.2 Mechanical 25 4.3.3 Electrical . 26 4.3.4 AOCS 2

13、6 4.3.5 TM/TC . 27 BS EN 16603-31:2014EN 16603-31:2014 (E) 3 4.3.6 OBDH and S/W . 27 4.3.7 Launcher . 27 4.3.8 GSE 28 4.3.9 ECLS 28 4.4 Design 28 4.4.1 General . 28 4.4.2 Budget allocation 29 4.4.3 Parts, materials and processes (PMP) 29 4.4.4 EEE components 29 4.4.5 Lifetime . 29 4.4.6 Predictabili

14、ty and testability . 29 4.4.7 Flexibility . 29 4.4.8 Integration and accessibility 29 4.4.9 Reliability 30 4.4.10 Interchangeability 30 4.4.11 Maintenance . 30 4.4.12 Safety 30 4.4.13 Availability . 30 4.5 Verification 30 4.5.1 Overview . 30 4.5.2 Verification requirements specific to TCS 30 4.5.3 T

15、hermal balance test (TBT) . 32 4.6 Production and manufacturing 34 4.6.1 Procurement . 34 4.6.2 Manufacturing process 35 4.6.3 Quality management . 35 4.6.4 Cleanliness and Contamination . 35 4.6.5 Integration . 36 4.6.6 Identification and Marking . 36 4.6.7 Packaging, handling, transportation 36 4.

16、6.8 Storage . 36 4.6.9 Repair . 36 4.7 In-service requirements 36 4.8 Product assurance 37 4.9 Deliverables 37 4.9.1 General . 37 4.9.2 Hardware 37 BS EN 16603-31:2014EN 16603-31:2014 (E) 4 4.9.3 Documentation 37 4.9.4 Mathematical models 39 5 Document requirements definitions (DRD) list 40 Bibliogr

17、aphy . 64 Figures Figure 3-1: Temperature definitions for thermal control system (TCS) 9 Figure 3-2: Temperature definitions for unit thermal design 16 Figure 4-1: Product exchange between the system, TCS and the supplier or manufacturer 38 Tables Table 5-1: ECSS-E-ST-31 DRD list 41 Table G-1 : Defi

18、nitions and requirements for the cryogenic temperature range used in this Standard 62 Table H-1 : Definitions and requirements for the high temperature range used in this Standard 63 BS EN 16603-31:2014EN 16603-31:2014 (E) 5 Foreword This document (EN 16603-31:2014) has been prepared by Technical Co

19、mmittee CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN. This standard (EN 16603-31:2014) originates from ECSS-E-ST-31C. This European Standard shall be given the status of a national standard, either by publication of an identical text or by endorsement, at the latest by March 2015, a

20、nd conflicting national standards shall be withdrawn at the latest by March 2015. Attention is drawn to the possibility that some of the elements of this document may be the subject of patent rights. CEN and/or CENELEC shall not be held responsible for identifying any or all such patent rights. This

21、 document supersedes EN 14607-1:2004. This document has been prepared under a mandate given to CEN by the European Commission and the European Free Trade Association. This document has been developed to cover specifically space systems and has therefore precedence over any EN covering the same scope

22、 but with a wider domain of applicability (e.g. : aerospace). According to the CEN-CENELEC Internal Regulations, the national standards organizations of the following countries are bound to implement this European Standard: Austria, Belgium, Bulgaria, Croatia, Cyprus, Czech Republic, Denmark, Estoni

23、a, Finland, Former Yugoslav Republic of Macedonia, France, Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and the United Kingdom. BS EN 16603-31:2014EN 166

24、03-31:2014 (E) 6 1 Scope ECSS-E-ST-31 defines requirements for the discipline of thermal engineering. This Standard defines the requirements for the definition, analysis, design, manufacture, verification and in-service operation of thermal control subsystems of spacecraft and other space products.

25、For this Standard, the complete temperature scale is divided into three ranges: Cryogenic temperature range Conventional temperature range High temperature range. The requirements of this Standard are applicable to the complete temperature scale. However, where applicable, requirements are stated to

26、 be applicable only for the cryogenic or high temperature range. References to these specific requirements have been summarized in Annex G and Annex H. This standard is applicable to all flight hardware of space projects, including spacecraft and launchers. This standard may be tailored for the spec

27、ific characteristic and constrains of a space project in conformance with ECSS-S-ST-00. BS EN 16603-31:2014EN 16603-31:2014 (E) 7 2 Normative references The following normative documents contain provisions which, through reference in this text, constitute provisions of this ECSS Standard. For dated

28、references, subsequent amendments to, or revision of any of these publications do not apply, However, parties to agreements based on this ECSS Standard are encouraged to investigate the possibility of applying the more recent editions of the normative documents indicated below. For undated reference

29、s, the latest edition of the publication referred to applies. EN reference Reference in text Title EN 16601-00-01 ECSS-S-ST-00-01 ECSS system Glossary of terms EN 16603-10-02 ECSS-E-ST-10-02 Space engineering Verification EN 16603-10-03 ECSS-E-ST-10-03 Space engineering Testing EN 16603-10-04 ECSS-E

30、-ST-10-04 Space engineering Space environment EN 16601-40 ECSS-M-ST-40 Space project management Configuration and information management EN 16602-20 ECSS-Q-ST-20 Space product assurance Quality assurance EN 16602-40 ECSS-Q-ST-40 Space product assurance Safety EN 16602-70 ECSS-Q-ST-70 Space product a

31、ssurance Materials, mechanical parts and processes EN 16602-70-01 ECSS-Q-ST-70-01 Space product assurance Cleanliness and contamination control BS EN 16603-31:2014EN 16603-31:2014 (E) 8 3 Terms, definitions and abbreviated terms 3.1 Terms from other standards For the purpose of this Standard, the te

32、rms and definitions from ECSS-ST-00-01 apply, in particular for the following terms: acceptance test (system level) assembly item part For the purpose of this Standard, the following terms and definitions from ECSS-E-ST-10-03 apply: temperature cycle 3.2 Terms specific to the present standard 3.2.1

33、General 3.2.1.1 acceptance margin contingency agreed between system authority and TCS to account for unpredictable TCS-related events NOTE The acceptance margin is the difference between the upper or lower acceptance temperature and the upper or lower design temperature (for both operating and non -

34、operating mode). See Figure 3-1. BS EN 16603-31:2014EN 16603-31:2014 (E) 9 Figure 3-1: Temperature definitions for thermal control system (TCS) 3.2.1.2 acceptance temperature range temperature range obtained from the qualification temperature range after subtraction of qualification margins specifie

35、d for the operating and non-operating mode and the switch-on condition of a unit NOTE 1 The acceptance temperature range is the extreme temperature range that a unit can reach, but never exceed, during all envisaged mission phases (based on worst case assumptions). See Figure 3-1. NOTE 2 Temperature

36、 range used during acceptance tests to verify specified requirements and workmanship 3.2.1.3 calculated temperature range temperature range obtained by analysis or other means for the operating and non-operating mode and the minimum switch-on condition of a unit, based on worst case considerations (

37、i.e. an appropriate combination of external fluxes, materials properties and unit dissipation profiles to describe hot and cold conditions) excluding failure cases NOTE See Figure 3-1. The calculated temperature range plus any uncertainties is limited to the specified design temperature range. Durin

38、g the course of a project these uncertainties change from initial estimates into a value determined by analysis. 3.2.1.4 climatic test test conducted to demonstrate the capability of an item to operate satisfactorily or to survive without degradation under specific environmental conditions at predef

39、ined hot and cold temperatures, temperature gradients and temperature variations BS EN 16603-31:2014EN 16603-31:2014 (E) 10 NOTE Examples of environmental conditions are: pressure, humidity and composition of atmosphere. 3.2.1.5 thermal component piece of thermal hardware which by further subdivisio

40、n loses its functionality, but is not necessarily destroyed 3.2.1.6 correlation correspondence between analytical predictions and test results 3.2.1.7 design temperature range temperature range specified for the operating and non-operating mode and the switch-on condition of a unit, obtained by subt

41、racting acceptance margins from the acceptance temperature range NOTE 1 Temperature range representing the temperature requirement for the TCS design activities. NOTE 2 The terms “operating temperature range” or “operational temperature range” should not be used for the design temperature range. The

42、 term “operating or non-operating temperature limits” is acceptable. 3.2.1.8 geometrical mathematical model (GMM) mathematical model in which an item and its surroundings are represented by radiation exchanging surfaces characterised by their thermo-optical properties NOTE The GMM generates the abso

43、rbed environmental heat fluxes and the radiative couplings between the surfaces. 3.2.1.9 heat dissipation thermal energy divided by time produced by a source 3.2.1.10 heat flux thermal energy (heat) divided by time and unit area perpendicular to the flow path NOTE Heat flux is also referred to as he

44、at flow rate density. 3.2.1.11 heat leak unwanted heat exchange between a thermally protected item and the environment NOTE The heat leak can be a heat gain or a heat loss depending of the environmental temperature 3.2.1.12 heat lift transfer of a specified heat flow rate from a lower to a higher te

45、mperature NOTE For example: Heat pump. BS EN 16603-31:2014EN 16603-31:2014 (E) 11 3.2.1.13 heat storage capability to store heat at a defined temperature or within a defined temperature range NOTE For example: Heat storage can be performed by sensible heat, latent heat as a PCM, by heat conversion i

46、nto chemical energy. 3.2.1.14 induced environment set of environmental conditions for a given item created by the operation or movement of the item itself NOTE For example: Set of loading conditions due to atmospheric flight. 3.2.1.15 infrared test thermal test method in which the solar and planetar

47、y radiation and aerodynamic heating are simulated by locally heating the spacecraft surface to the predicted input level using infrared techniques NOTE For example: Infrared lamps and heaters. 3.2.1.16 minimum switch-on temperature minimum temperature at which a unit can be switched from the non-ope

48、rating mode to the operating mode and functions nominally when the unit temperature is brought back to the relevant operating mode temperatures NOTE Also referred to as start-up temperature. 3.2.1.17 natural environment set of environmental conditions defined by the external physical surrounding for

49、 a certain mission NOTE For example: Heat flux by sun and planet, gas composition and pressure of planet atmosphere. 3.2.1.18 predicted temperature range temperature range obtained from the calculated temperature range increased by the uncertainties NOTE See Figure 3-1 3.2.1.19 qualification margin contingency approved by the system authority to account for any unexpected events NOTE For temperatures, the qualification margin is the difference between the upper or lower qualification temperature and the upper or lower acceptance temperature (for operating a