1、BSI Standards PublicationBS EN 16603-35-01:2014Space engineering Liquidand electric propulsion forspacecraftBS EN 16603-35-01:2014 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of EN 16603-35-01:2014. It supersedes BS EN 14607-5-1:2004 which is withdrawn.The UK part
2、icipation in its preparation was entrusted to T e c h n i c a lCommittee ACE/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 necessaryprovisions of a contract. User
3、s are responsible for its correctapplication. The British Standards Institution 2014.Published by BSI Standards Limited 2014ISBN 978 0 580 83987 0 ICS 49.140 Compliance with a British Standard cannot confer immunity from legal obligations.This British Standard was published under the authority of th
4、eStandards Policy and Strategy Committee on 30 September 2014.Amendments issued since publicationDate T e x t a f f e c t e dEUROPEAN STANDARDNORME EUROPENNEEUROPISCHE NORMEN 16603-35-01 September 2014 ICS 49.140 Supersedes EN 14607-5-1:2004 English version Space engineering - Liquid and electric pr
5、opulsion for spacecraft Ingnierie spatiale - Propulsion liquide et lectrique pour satellites Raumfahrttechnik - 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 Interna
6、l Regulations which stipulate the conditions for giving this 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 CE
7、N and CENELEC member.This European Standard exists in three 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 statu
8、s as the official versions.CEN and CENELEC members are the 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, Ir
9、eland, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, 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
10、by any means reservedworldwide for CEN national Members and for CENELEC Members. Ref. No. EN 16603-35-01:2014 E BS EN 16603-35-01:2014Table 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 A
11、bbreviated terms. 9 4 Liquid propulsion systems for spacecraft . 10 4.1 Overview 10 4.2 Functional . 10 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
12、 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 Selection . 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 EN 16603-35-01:20
13、14BS EN 16603-35-01:20144.5.10 Pressure vessels . 20 4.5.11 Propellant tanks 20 4.5.12 Blow-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 4.5.1
14、9 Ground support equipment (GSE) . 24 4.6 Verification 25 4.6.1 General . 25 4.6.2 Verification 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 .
15、33 4.8.1 General . 33 4.8.2 Operations on ground . 34 4.8.3 Tank operation 34 4.8.4 Disposal 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 Gener
16、al . 38 5.3.2 Thermal fluxes 38 5.3.3 Thruster plume effects 39 5.3.4 High frequency current loops 39 5.3.5 Electromagnetic compatibility 39 5.3.6 Spacecraft charging 39 EN 16603-35-01:2014BS EN 16603-35-01:20145.4 Interfaces 40 5.4.1 Interface with the spacecraft . 40 5.4.2 Interface with the power
17、 bus . 40 5.5 Design 41 5.5.1 General . 41 5.5.2 Selection . 42 5.5.3 Sizing 43 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.
18、11 Blow-down ratio 47 5.5.12 Thrusters . 47 5.5.13 Thrust-vector control . 50 5.5.14 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
19、 5.6.1 General . 53 5.6.2 Verification by analysis 54 5.6.3 Verification by test . 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:
20、Component failure modes 18 EN 16603-35-01:2014BS EN 16603-35-01:2014Foreword 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
21、 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 elements of
22、 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 supersedes EN 14607-5-1:2004. This document has been prepared under a mandate given to CEN by the European Commission and the European Fre
23、e Trade Association. 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 (e.g. : aerospace). According to the CEN-CENELEC Internal Regulations, the national standards organizati
24、ons 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 Macedonia, France, Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta
25、, Netherlands, Norway, Poland, Portugal, Romania, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and the United Kingdom. EN 16603-35-01:2014BS EN 16603-35-01:2014Introduction The ECSS Propulsion standards structure is as follows. ECSS-E-ST-35 Propulsion general requirements Standards, coveri
26、ng 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 propulsion for launchers Standard covering particular propulsion aspects ECSS-E-ST-35-06 Cleanliness requirements for
27、spacecraft propulsion hardware ECSS-E-ST-35-10 Compatibility testing for liquid propulsion systems EN 16603-35-01:2014BS EN 16603-35-01:20141 Scope This Standard defines the regulatory aspects applicable to elements and processes for liquid, including cold gas, and electrical propulsion for spacecra
28、ft. It specifies the activities to be performed in the engineering of such propulsion systems, their applicability, and defines the requirements for the engineering aspects: functional, interfaces, environmental, design, quality factors, operational and verification. General requirements applying to
29、 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 in conformance with ECSS-S-ST-00. EN 16603-35-01:2014BS EN 16603-35-01:20142 Normative references The following normative documen
30、ts 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 are encouraged to investigate t
31、he 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 16601-01 ECSS-S-ST-00-01 ECSS system Glossary of terms EN 16603-10 ECSS-E-ST-10 S
32、pace 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 Space engineering Spacecraft changing EN 16603-20-07 ECSS-E-ST-20-07 Space engineering Electromagnetic compatibility EN 16603-31 ECSS-E-ST-31 S
33、pace 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 engineering Propulsion general requirements EN 16602-30 ECSS-Q-ST-30 Space product assurance Dependability EN 16603-35-01:2014BS EN 16603-35
34、-01:20143 Terms, definitions and 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-ST-00-01 apply. EN 16603-
35、35-01:2014BS EN 16603-35-01:20144 Liquid propulsion systems for spacecraft 4.1 Overview Liquid propulsion systems for spacecraft provide the forces and torques for orbit transfer, orbit maintenance and attitude control. For manoeuvrable spacecraft, capsules and transport vehicles, they provide in ad
36、dition the forces and torques for rendez-vous and docking. Apart from what is specific for propellant combustion, liquid propulsion criteria 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 i
37、n ECSS-E-ST-70. 4.2 Functional 4.2.1 Mission a. The propulsion system shall conform to the spacecraft mission requirements including: 1. Ground operations NOTE For example: functional control, testing, propellant, simulant loading and spacecraft transportation. 2. Pre-launch and launch activities NO
38、TE For example: integration, storage, ageing and transport. 3. In-orbit operations. NOTE For example: orbit transfer, orbit maintenance and attitude control) and the complete in-orbit life. EN 16603-35-01:2014BS EN 16603-35-01:20144.2.2 Functions a. The propulsion system shall provide the total impu
39、lse, minimum impulse bit, thrust levels and torques required by the AOCS. b. The following aspects shall be defined: 1. Thruster 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 impuls
40、e bit 6. Impulse reproducibility 7. Total impulse 8. Cycle life 9. Mission life 10. Reliability level 11. Thrust noise 12. 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
41、For example: quasi-static loads, vibrations, transportation. 2. thermal loads; 3. electrical loads. 4.3 Constraints 4.3.1 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 perturbat
42、ions, e.g. during possible observations or experiments; protect sensitive equipments; design adequate tank PMD. EN 16603-35-01:2014BS EN 16603-35-01:20144.3.2 Pressure vessels and pressurized components a. Support structures of pressure vessels and pressurized components shall allow deformations of
43、the vessels due to pressure or temperature changes and cycles to occur without causing stresses that exceed acceptable 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.
44、Thruster surroundings shall conform to the radiative and conductive heat fluxes rejected by the thrusters. 4.3.5 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 specifie
45、d at spacecraft level. c. The generation of perturbing torques, forces, thermal gradients, contamination and 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 repo
46、rt 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 l
47、ine thermal control. 3. Power NOTE For example: valve drivers, pressure transducers, thermistors, heaters and thermocouples. 4. Electromagnetic compatibility 5. Pyrotechnics NOTE For example: pyrotechnic valves. EN 16603-35-01:2014BS EN 16603-35-01:20146. Mechanisms NOTE For example: valves, regulat
48、ors, actuators and actuation system. 7. AOCS, OBDH and TM/TC. NOTE For example: commanding, handling of data for status and health monitoring and failure detection. b. Interfaces shall be defined: 1. For ground tests and loading activities, with the propulsion GSE. 2. For safety and prelaunch operat
49、ion with the launcher authorities. 4.5 Design 4.5.1 General 4.5.1.1 Architecture a. The propulsion system architecture shall apply the requirements in ECSS-Q-ST-30. b. The propulsion system architecture shall provide evidence that fail safe, redundancy, reliability and safety requirements are met. 4.5.1.2 Replacement of parts a. For replacement of parts during development, testing and mission life pre-launch activities ECSS-E-ST-35, requirements 4.5.1c, d and e. shall be applied. 4.5.1.3 Water-hammer effect a. A water-hammer effects analysis sh
