EN 16603-35-03-2014 en Space engineering - Liquid propulsion for launchers《航天工程 发射器的液态推动》.pdf

1、BSI Standards PublicationBS EN 16603-35-03:2014Space engineering Liquidpropulsion for launchersBS EN 16603-35-03:2014 BRITISH STANDARDNational forewordThis British Standard is the UK implementation ofEN 16603-35-03:2014.The UK participation in its preparation was entrusted to Technical Committee ACE

2、/68, Space 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 Instit

3、ution 2014.Published by BSI Standards Limited 2014ISBN 978 0 580 83988 7 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

4、issued since publicationDate T e x t a f f e c t e dEUROPEAN STANDARD NORME EUROPENNE EUROPISCHE NORM EN 16603-35-03 September 2014 ICS 49.140 English version Space engineering - Liquid propulsion for launchers Ingnierie spatiale - Propulsion liquide pour lanceurs Raumfahrttechnik - Flssigantriebe f

5、r Trgerraketen 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 l

6、ists 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 tra

7、nslation 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, Switzerland

9、, 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 16603-35-03:2014 EBS EN 16603-35-03:2014Table of con

10、tents Foreword 4 Introduction 5 1 Scope . 6 2 Normative references . 7 3 Terms, definitions and abbreviated terms 8 3.1 Terms from other standards 8 3.2 Abbreviated terms. 8 4 Overview of a liquid propulsion system . 9 5 Functional . 11 5.1 Overview 11 5.2 Mission . 11 5.3 Functions 11 6 Constraints

11、 12 6.1 Acceleration 12 6.2 Geometrical constraints 12 6.3 Electrical constraints . 12 6.4 Safety . 12 7 Development . 13 7.1 Overview 13 7.2 Development logic 13 8 Interfaces . 16 8.1 Overview 16 8.2 General . 16 9 Design 17 9.1 General . 17 9.2 Specification . 17 9.3 Propulsion system selection .

12、17 EN 16603-35-03:2014BS EN 16603-35-03:20149.3.1 Overview . 17 9.3.2 System selection . 17 9.3.3 Propellant selection . 18 9.3.4 Engine selection 18 9.3.5 Selection of the TVC system . 18 9.4 Propulsive system detailed design 19 9.4.1 Overview . 19 9.4.2 General . 19 9.4.3 Filling and draining syst

13、em 19 9.4.4 Propellant tanks and management 20 9.4.5 Propellant feed system 23 9.5 Liquid engines 24 9.5.1 General . 24 9.5.2 Performance . 25 9.5.3 Functional system analysis . 25 9.5.4 Thrust chamber assembly (TCA) . 29 9.5.5 Gas generator and pre-burner . 36 9.5.6 Turbomachinery subsystem 36 9.5.

14、7 Control and monitoring systems 38 9.5.8 Auxiliary functions supplied by the stage . 40 9.5.9 Components 41 9.6 Mechanical design 44 10 Ground support equipment . 48 11 Materials 49 12 Verification 50 13 Production and manufacturing . 51 14 In-service . 52 14.1 General . 52 14.2 Operation 52 15 Del

15、iverables 53 Bibliography . 54 EN 16603-35-03:2014BS EN 16603-35-03:2014Foreword This document (EN 16603-35-03:2014) has been prepared by Technical Committee CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN. This standard (EN 16603-35-03:2014) originates from ECSS-E-ST-35-03C. This Euro

16、pean 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, and conflicting national standards shall be withdrawn at the latest by March 2015. Attention is drawn to the possibility that some of the element

17、s 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 document has been prepared under a mandate given to CEN by the European Commission and the European Free Trade Association. This document has b

18、een developed to cover specifically 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

19、 to implement this European 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,

20、 Romania, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and the United Kingdom. EN 16603-35-03:2014BS EN 16603-35-03:2014Introduction The requirements in this Standard ECSS-E-ST-35-03 (and in the 3 other space propulsion standards ECSS-E-ST-35, ECSS-E-ST-35-01 and ECSS-E-ST-35-02) are organ

21、ized with a typical structure as follows: functional; constraints; development; interfaces; design; GSE; materials; verification; production and manufacturing; in-service (operation and disposal); deliverables. This standard forms parts of ECSS-E-ST-35 series which has the following structure; ECSS-

22、E-ST-35 Propulsion general requirements ECSS-E-ST-35-01 Liquid and electric propulsion for spacecrafts ECSS-E-ST-35-02 Solid propulsion for spacecrafts and launchers ECSS-E-ST-35-03 Liquid propulsion for launchers ECSS-E-ST-35-06 Cleanliness requirements for spacecraft propulsion components, subsyst

23、ems, and systems ECSS-E-ST-35-10 Compatibility testing for liquid propulsion components, subsystems, and systems ECSS-E-ST-35 contains all the normative references, terms, definitions, abbreviated terms, symbols and DRD that are applicable for ECSS-E-ST-35, ECSS-E-ST-35-01, ECSS-E-ST-35-02 and ECSS-

24、E-ST-35-03. In the use of this standard, the term propulsion system is intended to be read and interpreted only and specifically for liquid prolusion system. EN 16603-35-03:2014BS EN 16603-35-03:20141 Scope General requirements applying to all type of Propulsion Systems Engineering are defined in EC

25、SS-E-ST-35. For Liquid propulsion for launchers activities within a space project the standards ECSS-E-ST-35 and ECSS-E-ST-35-03 are applied together. This Standard defines the specific regulatory aspects that apply to the elements and processes of liquid propulsion for launch vehicles. It specifies

26、 the activities to be performed in the engineering of these propulsion systems and their applicability. It defines the requirements for the engineering aspects such as functional, physical, environmental, quality factors, operational and verification. Other forms of propulsion (e.g. nuclear, nuclear

27、-electric, solar-thermal and hybrid propulsion) are not presently covered in this issue of the Standard. This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00. EN 16603-35-03:2014BS EN 16603-35-03:20142 Normative references T

28、he following normative documents contain provisions 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 ar

29、e encouraged to investigate the possibility of 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 o

30、f terms EN 16603-10 ECSS-E-ST-10 Space engineering - System engineering general requirements EN 16603-10-02 ECSS-E-ST-10-02 Space engineering - Verification EN 16603-10-06 ECSS-E-ST-10-06 Space engineering - Technical requirements specification EN 16603-32 ECSS-E-ST-32 Space engineering - Structural

31、 general requirements EN 16603-32-02 ECSS-E-ST-32-01 Space engineering - Fracture control EN 16603-32-02 ECSS-E-ST-32-02 Space engineering - Structural design and verification of pressurized hardware EN 16603-32-10 ECSS-E-ST-32-10 Space engineering - Structural factors of safety for spaceflight hard

32、ware EN 16603-35 ECSS-E-ST-35 Space engineering - Propulsion general requirements EN 16602-70 ECSS-Q-ST-70 Space product assurance - Materials, mechanical parts and processes ISO 15389:2001 Space systems - Flight-to-ground umbilicals EN 16603-35-03:2014BS EN 16603-35-03:20143 Terms, definitions and

33、abbreviated terms 3.1 Terms from other standards For the purpose of this Standard, the terms and definitions from ECSS-S-ST-00-01 and ECSS-E-ST-35 apply. 3.2 Abbreviated terms For the purpose of this Standard, the abbreviated terms from ECSS-S-ST-00-01, ECSS-E-ST-35 and the following apply: Abbrevia

34、tion Meaning LPS liquid propulsion system EN 16603-35-03:2014BS EN 16603-35-03:20144 Overview of a liquid propulsion system Main functions of a liquid propulsion system are: To provide thrust To provide thrust vector control To provide multiple burn capability if necessary To supply pressurized gas

35、for auxiliary functions (e.g. roll control, stage orientation ) To supply fluid for pneumatic control (e.g. Helium) To provide thrust for propellant settling To provide information concerning its status (e.g. measurement) The liquid propulsion system generally consists in: the engine the tank the fe

36、ed system the pressurisation system the command system the TVC auxiliary systems such as the anti-POGO device, roll control system The typical life of a liquid propulsion system is the following: Manufacturing and assembly Acceptance test (if any) Storage and transport Launcher integration Pre-launc

37、h activities (e.g. flushing, leak tightness checks) Tanks filling Main stage Chill down (for cryogenic liquid propulsion system) Launch chronology (including launch-abort activities) EN 16603-35-03:2014BS EN 16603-35-03:2014 Lift-off Chill-down (for cryogenic liquid propulsion upper stages) Boost ph

38、ases Stage separation Ballistic phase Passivation De-orbiting, reaching a graveyard orbit, or both NOTE The way how to write the technical specification is given in ECSS-E-ST-10-06. EN 16603-35-03:2014BS EN 16603-35-03:20145 Functional 5.1 Overview The general functional specification coming from mi

39、ssion optimisation at system level provides values for: Thrust Isp Burning time The additional functional requirements are: thrust level versus time (throttling) propellant budget management (e.g. mixture ratio variation) TVC (e.g. maximum angle, acceleration, response time) start-up and shutdown tr

40、ansient requirements (e.g. duration, impulse scatter) auxiliary power to be delivered to the launcher (e.g. electrical and fluids) re-startability propellant depletion 5.2 Mission a. ECSS-E-ST-35 clause 4.2 shall apply. 5.3 Functions a. The technical specification shall provide the values of thrust,

41、 Isp and burning time with their deviations. EN 16603-35-03:2014BS EN 16603-35-03:20146 Constraints 6.1 Acceleration a. Accelerations in the axial and lateral directions, assessed at launch vehicle level, shall be specified as an input for the propulsion system. NOTE The acceleration has an impact o

42、n the: functioning of the vortex suppression devices in the tank outlets; pressure at the pump inlets; flow pattern in the tank; mechanical loads. 6.2 Geometrical constraints a. The dimensioning of the liquid propulsion system and its components shall conform to the overall launch vehicle dimensions

43、, interfaces between stages, ground infrastructure and requirements for transportation. 6.3 Electrical constraints a. The design of the prop system shall be such that the electrical continuity is ensured. 6.4 Safety a. The design of the liquid propulsion system shall conform to the safety requiremen

44、ts of the launch system. NOTE For Example, ground safety requirements, flight safety requirements. EN 16603-35-03:2014BS EN 16603-35-03:20147 Development 7.1 Overview The phases of development for a liquid propulsion system are as follows: definition of system and subsystem requirements conforming t

45、o mission requirements establishment of the general concepts trade-off of various concepts preliminary design risk analysis of the preliminary design and trade-off of various options detailed design and definition manufacturing and assembly of components, subsystems. integration of subsystem and sys

46、tem testing of: components, subsystems, engines, and system (functional stage). selection of the design to be qualified qualification process review of first article 7.2 Development logic a. The development logic shall include a requirement verification plan in conformance with ECSS-E-ST-10-02 verif

47、ication plan. NOTE Example of verification methods are analyses, tests. EN 16603-35-03:2014BS EN 16603-35-03:2014b. The development logic shall be structured into phases with a goal assigned to each phase. c. Mathematical models shall be implemented during the preliminary design phase and used for s

48、ystem trade-off analysis. NOTE 1 See clause 9.3. NOTE 2 Preliminary design phase is Phase B of ECSS-M-ST-10. d. Mathematical models shall be updated using component and subsystem results at milestones agreed by the customer. e. Mathematical models shall be validated using test results. f. Mathematic

49、al models shall be used to determine the design margins. g. The development logic shall list the activities that are submitted to cross-check. NOTE See ECSS-E-ST-35 clause 4.8.1. h. The sequence of development activities shall include components and subsystem tests prior to system tests. i. The development logic shall mention the difficulties and critical activities of the development. NOTE In particular major develo