1、BSI Standards PublicationBS EN 16603-35:2014Space engineering Propulsion generalrequirementsBS EN 16603-35:2014 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of EN 16603-35:2014. The UK participation in its preparation was entrusted to TechnicalCommittee ACE/68, Spa
2、ce systems and operations.A list of organizations represented on this committee can be obtained on request to its secretary.This publication does not purport to include all the necessary provisions of a contract. Users are responsible for its correct application. The British Standards Institution 20
3、14. Published by BSI Standards Limited 2014ISBN 978 0 580 83984 9 ICS 49.140 Compliance with a British Standard cannot confer immunity from legal obligations.This British Standard was published under the authority of the Standards Policy and Strategy Committee on 30 September 2014.Amendments issued
4、since publicationDate Text affectedEUROPEAN STANDARD NORME EUROPENNE EUROPISCHE NORM EN 16603-35 September 2014 ICS 49.140 English version Space engineering - Propulsion general requirements Ingnierie spatiale - Exigences gnrales pour la propulsion Raumfahrttechnik - Antrieb, allgemeine Anforderunge
5、n und Grundstze This European Standard was approved by CEN on 23 February 2014. CEN and CENELEC members are bound to comply with the CEN/CENELEC Internal Regulations which stipulate the conditions for giving this European Standard the status of a national standard without any alteration. Up-to-date
6、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 three official versions (English, French, German). A version in any other language made by tr
7、anslation 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 the national standards bodies and national electrotechnical committees of Austria, Belgium,
8、 Bulgaria, Croatia, Cyprus, Czech Republic, Denmark, Estonia, 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, Switzerlan
9、d, 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 Members and for CENELEC Members. Ref. No. EN 16603-35:2014 EBS EN 16603-35:2014Table of contents
10、 Foreword 5 Introduction 6 1 Scope . 7 2 Normative references . 8 3 Terms, definitions and abbreviated terms 9 3.1 Terms defined in other standards . 9 3.2 Terms specific to the present standard . 9 3.2.1 General terms . 9 3.2.2 Definition of masses 20 3.3 Abbreviated terms. 21 3.4 Symbols 23 4 Prop
11、ulsion engineering activities . 25 4.1 Overview 25 4.1.1 Relationship with other standards . 25 4.1.2 Characteristics of propulsion systems . 25 4.2 Mission . 26 4.3 Development 26 4.4 Propulsion system interfaces 27 4.5 Design 28 4.5.1 General . 28 4.5.2 Global performance . 28 4.5.3 Reference enve
12、lope 29 4.5.4 Transients . 31 4.5.5 Sizing 31 4.5.6 Dimensioning 32 4.5.7 Imbalance . 32 4.5.8 Thrust vector control . 33 4.5.9 Contamination and cleanliness 33 4.5.10 Plume effect 34 EN 16603-35:2014BS EN 16603-35:20144.5.11 Leak tightness . 35 4.5.12 Environment 35 4.5.13 Impact of ageing on sizin
13、g and dimensioning 36 4.5.14 Components 36 4.5.15 Monitoring and control system. 38 4.6 Ground support equipment (GSE) 38 4.6.1 General . 38 4.6.2 Mechanical and fluid . 39 4.6.3 Electrical . 39 4.7 Materials . 39 4.8 Verification 39 4.8.1 Verification by analyses 39 4.8.2 Verification by tests . 40
14、 4.9 Production and manufacturing 41 4.9.1 Overview . 41 4.9.2 Tooling and test equipment . 41 4.9.3 Marking . 41 4.9.4 Component manufacturing and assembly . 42 4.10 In-service 42 4.10.1 Operations 42 4.10.2 Propulsion system operability 42 4.11 Deliverables 43 Annex A (normative) Propulsion perfor
15、mance analysis report (AR-P) - DRD 44 Annex B (normative) Gauging analysis report (AR-G) - DRD 48 Annex C (normative) Addendum: Specific propulsion aspects for thermal analysis - DRD . 52 Annex D (normative) Plume analysis report (AR-PI) - DRD . 61 Annex E (normative) Nozzle and discharge flow analy
16、sis report (AR-N) - DRD 65 Annex F (normative) Sloshing analysis report (AR-S) - DRD 69 Annex G (normative) Propulsion transients analysis report (AR-Tr) - DRD . 73 Annex H (normative) Propulsion subsystem or system user manual (UM) - DRD 77 EN 16603-35:2014BS EN 16603-35:2014Annex I (normative) Mat
17、hematical modelling for propulsion analysis (MM-PA) - DRD . 85 Annex J (normative) Addendum: Additional propulsion aspects for mathematical model requirements (MMR) - DRD . 89 Annex K (normative) Addendum: Additional propulsion aspects for mathematical model description and delivery (MMDD) - DRD 91
18、Annex L (normative) Propulsion system instrumentation plan - DRD 93 Annex M (informative) Standards for propellants, pressurants, simulants and cleaning agents 95 Bibliography . 98 Figures Figure 3-1 Burning time 10 Figure 3-2: NPSP . 15 Figure 3-3 Relief flap or floater . 16 Tables Table 4-1 Delive
19、rable DRD . 43 EN 16603-35:2014BS EN 16603-35:2014Foreword This document (EN 16603-35:2014) has been prepared by Technical Committee CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN. This standard (EN 16603-35:2014) originates from ECSS-E-ST-35C Rev. 1. This European Standard shall be g
20、iven the status of a national standard, either by publication of an identical text or by endorsement, at the latest by March 2015, and 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 b
21、e the subject of patent rights. CEN and/or CENELEC shall not be held responsible for identifying any or all such patent rights. 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 s
22、pecifically space systems and has therefore precedence over any EN covering the same scope 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 Europ
23、ean Standard: 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, Netherlands, Norway, Poland, Portugal, Romania, Slovakia, Slov
24、enia, Spain, Sweden, Switzerland, Turkey and the United Kingdom. EN 16603-35:2014BS EN 16603-35:2014Introduction The requirements in this Standard (ECSS-E-ST-35) and in the three space propulsion standards dedicated to particular type of propulsion (ECSS-E-ST-35-01, ECSS-E-ST-35-02 and ECSS-E-ST-35-
25、03) are organized with a typical structure as follows: Functional Constraints Interfaces Design GSE Materials Verification Production and manufacturing Inservice (operation and disposal) Deliverables. All the normative references, terms, definitions, abbreviated terms, symbols and DRDs of the ECSS P
26、ropulsion standards are collected in this ECSS-E-ST-35 standard. The ECSS Propulsion standards structure is as follows. ECSS-E-ST-35 Propulsion general requirements Standards, covering particular type of propulsion ECSS-E-ST-35-01 Liquid and electric propulsion for spacecrafts ECSS-E-ST-35-02 Solid
27、propulsion for spacecrafts and launchers ECSS-E-ST-35-03 Liquid propulsion for launchers. Standard covering particular propulsion aspects ECSS-E-ST-35-06 Cleanliness requirements for spacecraft propulsion hardware ECSS-E-ST-35-10 Compatibility testing for liquid propulsion systems Further informatio
28、n on the use of conventional propellants, pressurants, simulants and cleaning agents is given in Annex M. EN 16603-35:2014BS EN 16603-35:20141 Scope This Standard defines the regulatory aspects that apply to the elements and processes of liquid propulsion for launch vehicles and spacecraft, solid pr
29、opulsion for launch vehicles and spacecraft and electric propulsion for spacecraft. The common requirements for the three types of space propulsion are written in the ECSS-E-ST-35 document. The specific requirements for each type of propulsion are given in ECSS-E-ST-35-01, ECSS-E-ST-35-02 and ECSS-E
30、-ST-35-03. It specifies the activities to be performed in the engineering of these propulsion systems and their applicability. It defines the requirement for the engineering aspects such as functional, physical, environmental, quality factors, operational and verification. Other forms of propulsion
31、(e.g. nuclear, nuclearelectric, solarthermal and hybrid propulsion) are not presently covered in this issue of the Standard. This standard applies to all types of space propulsion systems used in space applications, including: Liquid and electric propulsion for spacecraft. Solid propulsion for launc
32、h vehicles and spacecraft; Liquid propulsion for launch vehicles. This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00. EN 16603-35:2014BS EN 16603-35:20142 Normative references The following normative documents contain prov
33、isions which, through reference in this text, constitute provisions of this ECSS Standard. For dated 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 o
34、f applying the more recent editions of the normative documents indicated below. For undated references, 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 ECSS-E-ST-10 Space engineer
35、ing System engineering general requirements EN 16603-10-02 ECSS-E-ST-10-02 Space engineering Verification EN 16603-35-06 ECSS-E-ST-35-06 Space engineering Cleanliness requirements for spacecraft propulsion hardware EN 16603-31 ECSS-E-ST-31 Space engineering Thermal control general requirements EN 16
36、603-32 ECSS-E-ST-32 Space engineering Structural general requirements EN 16603-35:2014BS EN 16603-35:20143 Terms, definitions and abbreviated terms 3.1 Terms defined in other standards For the purpose of this Standard, the terms and definitions from ECSS-S-ST-00-01 apply. For the purpose of this Sta
37、ndard, the following definitions from ECSS-E-ST-10 apply: technology readiness level (TRL) For the purpose of this Standard, the following definitions from ECSS-E-ST-32 apply: MDP MEOP mission life 3.2 Terms specific to the present standard 3.2.1 General terms 3.2.1.1 ablated thickness removed thick
38、ness of thermal protection material, due to thermal and mechanical loads, during combustion duration NOTE Mathematically called “ea” 3.2.1.2 barbecue mode mode where a stage or spacecraft slowly rotates in space in order to obtain an even temperature distribution under solar radiation 3.2.1.3 beam d
39、ivergence semiangle of a cone, passing through the thruster exit, containing a certain percentage of the current of an ion beam at a certain distance of that thruster exit 3.2.1.4 buffeting fluctuating external aerodynamic loads due to vortex shedding EN 16603-35:2014BS EN 16603-35:20143.2.1.5 burni
40、ng time, tbtime for which the propulsion system delivers a thurst NOTE Figure 3-1 illustrates an arbitrary thrust or pressure history of a rocket propulsion system. An igniter peak can, but need not, be observed. Depending on the application, a time, t0, is defined at which the propulsion system is
41、assumed to deliver a thrust, and a time, te, at which the propulsion system is assumed not to deliver an thrust any more. The burning time is the time interval defined as the difference between the two times: tb=te t0. moment at which t he i gnit i on signal arrives at the ignition syst em t=0 t0 tb
42、 I gni t er peak te p, F Figure 3-1 Burning time 3.2.1.6 characteristic velocity, C* ratio of the product of the throat area of a rocket engine and the total pressure (at the throat) and the propellants mass flow rate NOTE 1 In accordance with this definition, the instantaneous characteristic veloci
43、ty is: mApCtc=* NOTE 2 Instantaneous and overall characteristic velocities are usually referred to as characteristic velocity. NOTE 3 The usual units are m/s. EN 16603-35:2014BS EN 16603-35:20143.2.1.7 characteristic velocity, C* ratio of the time integral of the product of throat area and total pre
44、ssure (at the throat) and the propellants ejected mass during the same time interval NOTE 1 In accordance with this definition, the overall characteristic velocity is: =2121*tttttcmddApCIn many cases t1 is taken to be the ignition time, t0, and t2 is taken to be the time at burnout (te). In that cas
45、e, t2 - t1 = tb and the integral in the denominator equals the ejected mass. NOTE 2 Instantaneous and overall characteristic velocities are usually referred to as characteristic velocity. NOTE 3 The usual units are m/s. 3.2.1.8 charred thickness remaining thermal material thickness after motor opera
46、ting, affected by thermal loads NOTE 1 For example, composition evolution. NOTE 2 Mathematically, it is called “ec” 3.2.1.9 chilldown process of cooling the engine system components before ignition in order to reach specific functional and mechanical criteria (e.g. the propellants proper thermodynam
47、ic state) 3.2.1.10 component smallest individual functional unit considered in a subsystem NOTE For example tanks, valves and regulators. 3.2.1.11 contaminant undesired material present in the propulsion system at any time of its life 3.2.1.12 corridor variation envelope of a time dependent paramete
48、r 3.2.1.13 critical speed speed at which the eigenfrequency of the rotor coincides with an integer multiple of the rotational speed 3.2.1.14 cryopumping condensation of gas on cryogenic fluid (e.g. LH2, LHe ) lines or components, thereby sucking in more gas and thereby preventing normal operation of
49、 cryogenic system EN 16603-35:2014BS EN 16603-35:2014NOTE For example, preventing proper chilldown. 3.2.1.15 deorbiting controlled return to Earth or other celestial body or burnup in the atmosphere of a spacecraft or stage 3.2.1.16 dimensioning process by which the dimensions of an entity (system, subsystem or component) is determined and verified, such that the entity conforms to the entity requirements and can withstand all loads during its mission NOTE Dimensioning is only possible after the sizing process for t
