DIN EN 16603-35-01-2014 Space engineering - Liquid and electric propulsion for spacecraft English version EN 16603-35-01 2014《航天工程 航天器液体和电力推进器 英文版本EN 16603-35-01-2014》.pdf

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1、November 2014DEUTSCHE NORM DIN-Normenausschuss Luft- und Raumfahrt (NL)Preisgruppe 22DIN Deutsches Institut fr Normung e. V. Jede Art der Vervielfltigung, auch auszugsweise, nur mit Genehmigung des DIN Deutsches Institut fr Normung e. V., Berlin, gestattet.ICS 49.140!%;M5“2244218www.din.deDDIN EN 16

2、603-35-01Raumfahrttechnik Flssige und elektrische Antriebe von Raumfahrzeugen;Englische Fassung EN 16603-35-01:2014Space engineering Liquid and electric propulsion for spacecraft;English version EN 16603-35-01:2014Ingnierie spatiale Propulsion liquide et lectrique pour satellites;Version anglaise EN

3、 16603-35-01:2014Alleinverkauf der Normen durch Beuth Verlag GmbH, 10772 BerlinErsatz frDIN EN 14607-5-1:2006-12www.beuth.deGesamtumfang 61 SeitenDIN EN 16603-35-01:2014-11 2 Nationales Vorwort Dieses Dokument (EN 16603-35-01:2014) wurde vom Technischen Komitee CEN/CLC/TC 5 Raumfahrt“ erarbeitet, de

4、ssen Sekretariat vom DIN (Deutschland) gehalten wird. Das zustndige deutsche Normungsgremium ist der Arbeitsausschuss NA 131-10-01 AA Interoperabilitt von Informations-, Kommunikations- und Navigationssystemen“ im DIN-Normenausschuss Luft- und Raumfahrt (NL). Dieses Dokument (EN 16603-35-01:2014) ba

5、siert auf ECSS-E-ST-35-01C. Dieses Dokument ersetzt DIN EN 14607-5-1:2006-12. Dieses Dokument enthlt unter Bercksichtigung des DIN-Prsidialbeschlusses 1/2004 nur die englische Originalfassung von EN 16603-35-01:2014. Dieses Dokument wurde speziell zur Behandlung von Raumfahrtsystemen erarbeitet und

6、hat daher Vorrang vor jeglicher Europischer Norm, da es denselben Anwendungsbereich hat, jedoch ber einen greren Geltungsbereich (z. B. Luft- und Raumfahrt) verfgt. nderungen Gegenber DIN EN 14607-5-1:2006-12 wurden folgende nderungen vorgenommen: a) Norm-Nummer gendert; b) keinerlei nderungen des T

7、extes. Frhere Ausgaben DIN EN 14607-5-1: 2006-12 Nationaler Anhang NA (informativ) Begriffe 3 Begriffe und Abkrzungen 3.1 Begriffe aus anderen Normen Fr die Anwendung dieses Dokuments gelten die Begriffe nach ECSS-S-ST-00-01 und nach ECSS-E-ST-35. 3.2 Abkrzungen Fr die Anwendung dieses Dokuments gel

8、ten die Abkrzungen nach ECSS-S-ST-00-01. EUROPEAN STANDARD NORME EUROPENNE EUROPISCHE NORM EN 16603-35-01 September 2014 ICS 49.140 English version Space engineering - Liquid and electric propulsion for spacecraft Ingnierie spatiale - Propulsion liquide et lectrique pour satellites Raumfahrttechnik

9、- Flssige und elektrische Antriebe von Raumfahrzeugen 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 standa

10、rd 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 three official versions (English, French, German). A ve

11、rsion 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 the national standards bodies and national electrotec

12、hnical 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, Netherlands, Norway, Poland, Portugal, Romania, Slovaki

13、a, 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 Members and for CENELEC Members. Ref. No. EN 16603-35-01:2

14、014 EEN 16603-35-01:2014 (E) 2 Table of contents Foreword 5 Introduction 6 1 Scope . 7 2 Normative references . 8 3 Terms, definitions and abbreviated terms 9 3.1 Terms from other standards 9 3.2 Abbreviated terms. 9 4 Liquid propulsion systems for spacecraft . 10 4.1 Overview 10 4.2 Functional . 10

15、 4.2.1 Mission 10 4.2.2 Functions 11 4.3 Constraints . 11 4.3.1 Accelerations 11 4.3.2 Pressure vessels and pressurized components 12 4.3.3 Induced and environmental temperatures . 12 4.3.4 Thermal fluxes 12 4.3.5 Thruster plume effects 12 4.4 Interfaces 12 4.5 Design 13 4.5.1 General . 13 4.5.2 Sel

16、ection . 14 4.5.3 Sizing 15 4.5.4 Design development . 16 4.5.5 Contamination . 17 4.5.6 Draining 17 4.5.7 Risk of explosion . 18 4.5.8 Components guidelines . 18 4.5.9 Filters 20 DIN EN 16603-35-01:2014-11 EN 16603-35-01:2014 (E) 3 4.5.10 Pressure vessels . 20 4.5.11 Propellant tanks 20 4.5.12 Blow

17、-down ratio 22 4.5.13 Flow calibration . 22 4.5.14 Thrusters . 22 4.5.15 Thrust-vector control (TVC) . 23 4.5.16 Pyrotechnic devices 24 4.5.17 Mass imbalance 24 4.5.18 Monitoring and failure detection 24 4.5.19 Ground support equipment (GSE) . 24 4.6 Verification 25 4.6.1 General . 25 4.6.2 Verifica

18、tion by analysis 26 4.6.3 Verification by test . 28 4.6.4 Data exchange for models 33 4.7 Quality factors . 33 4.7.1 Reliability 33 4.7.2 Production and manufacturing process . 33 4.8 Operation and disposal . 33 4.8.1 General . 33 4.8.2 Operations on ground . 34 4.8.3 Tank operation 34 4.8.4 Disposa

19、l 34 4.9 Supporting documents 35 5 Electric propulsion systems for spacecraft . 36 5.1 Overview 36 5.2 Functional . 37 5.2.1 Mission 37 5.2.2 Function 37 5.2.3 Performance . 37 5.3 Constraints . 38 5.3.1 General . 38 5.3.2 Thermal fluxes 38 5.3.3 Thruster plume effects 39 5.3.4 High frequency curren

20、t loops 39 5.3.5 Electromagnetic compatibility 39 5.3.6 Spacecraft charging 39 DIN EN 16603-35-01:2014-11 EN 16603-35-01:2014 (E) 4 5.4 Interfaces 40 5.4.1 Interface with the spacecraft . 40 5.4.2 Interface with the power bus . 40 5.5 Design 41 5.5.1 General . 41 5.5.2 Selection . 42 5.5.3 Sizing 43

21、 5.5.4 Design development . 44 5.5.5 Contamination . 44 5.5.6 Propellant protection . 45 5.5.7 Components guidelines . 45 5.5.8 Propellant management assembly 45 5.5.9 Pressure vessels . 46 5.5.10 Propellant tanks 47 5.5.11 Blow-down ratio 47 5.5.12 Thrusters . 47 5.5.13 Thrust-vector control . 50 5

22、.5.14 Power supply, control and processing subsystem . 50 5.5.15 Electrical design 51 5.5.16 Pyrotechnic devices 52 5.5.17 Monitoring and failure detection 52 5.5.18 Ground support equipment (GSE) . 53 5.6 Verification 53 5.6.1 General . 53 5.6.2 Verification by analysis 54 5.6.3 Verification by tes

23、t . 55 5.6.4 Data exchange for models 57 5.7 Quality factors . 57 5.7.1 Reliability 57 5.7.2 Production and manufacturing 57 5.8 Operation and disposal . 57 5.9 Supporting documents 58 Bibliography . 59 Tables Table 4-1: Component failure modes 18 DIN EN 16603-35-01:2014-11 EN 16603-35-01:2014 (E) 5

24、 Foreword This document (EN 16603-35-01:2014) has been prepared by Technical Committee CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN. This standard (EN 16603-35-01:2014) originates from ECSS-E-ST-35-01C. This European Standard shall be given the status of a national standard, either

25、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 be the subject of patent rights. CEN and/or CENE

26、LEC shall not be held responsible for identifying any or all such patent rights. This document supersedes EN 14607-5-1:2004. This document has been developed to cover specifically space systems and has therefore precedence over any EN covering the same scope but with a wider domain of applicability

27、(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, Estonia, Finland, Former Yugoslav Republic of Ma

28、cedonia, 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. DIN EN 16603-35-01:2014-11 EN 16603-35-01:2014 (E) 6 Introduction T

29、he 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 propulsion for spacecrafts and launchers ECSS-E-ST-35-03 Liquid pr

30、opulsion 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 DIN EN 16603-35-01:2014-11 EN 16603-35-01:2014 (E) 7 1 Scope This Standard defines th

31、e regulatory aspects applicable to elements and processes for liquid, including cold gas, and electrical propulsion for spacecraft. It specifies the activities to be performed in the engineering of such propulsion systems, their applicability, and defines the requirements for the engineering aspects

32、: functional, interfaces, environmental, design, quality factors, operational and verification. General requirements applying to all type of Propulsion Systems Engineering are defined in ECSS-E-ST-35. This standard may be tailored for the specific characteristics and constraints of a space project i

33、n conformance with ECSS-S-ST-00. DIN EN 16603-35-01:2014-11 EN 16603-35-01:2014 (E) 8 2 Normative references The following normative documents contain provisions which, through reference in this text, constitute provisions of this ECSS Standard. For dated references, subsequent amendments to, or rev

34、ision 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 references, the latest edition of the publication re

35、ferred to applies. EN reference Reference in text Title EN 16601-01 ECSS-S-ST-00-01 ECSS system Glossary of terms EN 16603-10 ECSS-E-ST-10 Space engineering System engineering general requirements EN 16603-20 ECSS-E-ST-20 Space engineering Electrical and electronic EN 16603-20-06 ECSS-E-ST-20-06 Spa

36、ce engineering Spacecraft changing EN 16603-20-07 ECSS-E-ST-20-07 Space engineering Electromagnetic compatibility EN 16603-31 ECSS-E-ST-31 Space engineering Thermal control general requirements EN 16603-32 ECSS-E-ST-32 Space engineering Structural general requirements EN 16603-35 ECSS-E-ST-35 Space

37、engineering Propulsion general requirements EN 16602-30 ECSS-Q-ST-30 Space product assurance Dependability DIN EN 16603-35-01:2014-11 EN 16603-35-01:2014 (E) 9 3 Terms, definitions and abbreviated terms 3.1 Terms from other standards For the purpose of this Standard, the terms and definitions from E

38、CSS-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-ST-00-01 apply. DIN EN 16603-35-01:2014-11 EN 16603-35-01:2014 (E) 10 4 Liquid propulsion systems for spacecraft 4.1 Overview Liquid propulsion systems for spacecraft provid

39、e the forces and torques for orbit transfer, orbit maintenance and attitude control. For manoeuvrable spacecraft, capsules and transport vehicles, they provide in addition the forces and torques for rendez-vous and docking. Apart from what is specific for propellant combustion, liquid propulsion cri

40、teria are also applicable to cold gas propulsion systems. The present clause 4 covers also the design and use of propulsion ground support equipment (GSE), defined in ECSS-E-ST-70. 4.2 Functional 4.2.1 Mission a. The propulsion system shall conform to the spacecraft mission requirements including: 1

41、. Ground operations NOTE For example: functional control, testing, propellant, simulant loading and spacecraft transportation. 2. Pre-launch and launch activities NOTE For example: integration, storage, ageing and transport. 3. In-orbit operations. NOTE For example: orbit transfer, orbit maintenance

42、 and attitude control) and the complete in-orbit life. DIN EN 16603-35-01:2014-11 EN 16603-35-01:2014 (E) 11 4.2.2 Functions a. The propulsion system shall provide the total impulse, minimum impulse bit, thrust levels and torques required by the AOCS. b. The following aspects shall be defined: 1. Th

43、ruster firing modes NOTE For example: steady state, off-modulation, pulse mode. 2. Thrust level and orientation 3. Thrust-vector control 4. Thrust centroid time 5. Minimum impulse bit 6. Impulse reproducibility 7. Total impulse 8. Cycle life 9. Mission life 10. Reliability level 11. Thrust noise 12.

44、 Propellant gauging. c. The propulsion system shall fulfil its functions while subjected to the specified external loads during its mission, including: 1. mechanical loads; NOTE For example: quasi-static loads, vibrations, transportation. 2. thermal loads; 3. electrical loads. 4.3 Constraints 4.3.1

45、Accelerations a. Limits on acceleration levels, induced or experienced by the propulsion system, shall be specified at spacecraft level. NOTE This is in order to: avoid perturbations, e.g. during possible observations or experiments; protect sensitive equipments; design adequate tank PMD. DIN EN 166

46、03-35-01:2014-11 EN 16603-35-01:2014 (E) 12 4.3.2 Pressure vessels and pressurized components a. Support structures of pressure vessels and pressurized components shall allow deformations of the vessels due to pressure or temperature changes and cycles to occur without causing stresses that exceed a

47、cceptable limits. 4.3.3 Induced and environmental temperatures a. The non-operating and operating temperature limitations of the propulsion system shall be specified. 4.3.4 Thermal fluxes a. Thruster surroundings shall conform to the radiative and conductive heat fluxes rejected by the thrusters. 4.

48、3.5 Thruster plume effects a. Elements of the spacecraft sensitive to plume effects shall be identified. b. The allowed plume effects on elements identified in clause 4.3.5a shall be specified at spacecraft level. c. The generation of perturbing torques, forces, thermal gradients, contamination and

49、erosion of surfaces, due to plume effects, shall be defined and documented accordingly. d. The plume analysis specified in 4.3.5c shall be reported in conformance with the Plume analysis report DRD in ECSS-E-ST-35. 4.4 Interfaces a. The liquid propulsion system shall conform to its specified spacecraft interfaces, including: 1. Structure NOTE For example: inserts, tank support structure and vibration levels. 2. Thermal NOTE For example: conduction, radiation levels, tank, thruster and line thermal control. 3. P