1、BSI Standards PublicationBS EN 16603-35-02:2014Space engineering Solidpropulsion for spacecrafts andlaunchersBS EN 16603-35-02:2014 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of EN16603-35-02:2014.The UK participation in its preparation was entrusted to Technical
2、Committee 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 correctapplication. The British Standa
3、rds Institution 2014. Published by BSI StandardsLimited 2014ISBN 978 0 580 83989 4ICS 49.140Compliance with a British Standard cannot confer immunity fromlegal obligations.This British Standard was published under the authority of theStandards Policy and Strategy Committee on 30 September 2014.Amend
4、ments issued since publicationDate Text affectedBS EN 16603-35-02:2014EUROPEAN STANDARD NORME EUROPENNE EUROPISCHE NORM EN 16603-35-02 September 2014 ICS 49.140 English version Space engineering - Solid propulsion for spacecrafts and launchers Ingnierie spatiale - Propulsion solide pour satellites e
5、t lanceurs Raumfahrttechnik - Feststoffantriebe fr Raumfahrzeuge und 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
6、 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 three official versions (En
7、glish, 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 the national standards bo
8、dies 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, Netherlands, Norway, Poland
9、, 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 Members and for CENELEC Member
10、s. Ref. No. EN 16603-35-02:2014 EBS EN 16603-35-02:2014EN 16603-35-02:2014 (E) 2 Table of contents Foreword 4 Introduction 5 1 Scope . 6 2 Normative references . 7 3 Terms, definition and abbreviated terms 8 3.1 Terms from other standards 8 3.2 Abbreviated terms. 9 4 Solid propulsion engineering act
11、ivities 10 4.1 Overview 10 4.2 Functional . 10 4.2.1 Mission 10 4.2.2 Functions 10 4.3 Constraints . 12 4.3.1 Dynamic phenomena 12 4.3.2 External loads during the life cycle of the propulsion system . 12 4.3.3 Thrust centroid time 12 4.3.4 Acoustic noise . 12 4.3.5 Pollution 12 4.3.6 Ejected parts .
12、 13 4.3.7 Safety 13 4.4 Interfaces 13 4.4.1 General . 13 4.4.2 Induced and environmental temperature . 14 4.4.3 General environment . 14 4.5 Design 14 4.5.1 Overview . 14 4.5.2 Propulsion system selection and design process 15 4.5.3 Global performance . 17 4.5.4 Ignition and tail-off . 17 BS EN 1660
13、3-35-02:2014EN 16603-35-02:2014 (E) 3 4.5.5 Solid rocket motor components . 18 4.6 Ground support equipment (GSE) 20 4.7 Materials . 21 4.8 Verification 21 4.8.1 Verification by analysis 21 4.8.2 Verification by test . 21 4.9 Production and manufacturing 24 4.10 In-service 26 4.10.1 General . 26 4.1
14、0.2 In-flight operations. 26 4.11 Deliverables 27 Annex A (normative) Dynamic analysis report (AR-DY) - DRD 28 Annex B (normative) Material Safety Data Sheet (AR-MSDS) - DRD 32 Bibliography . 35 Tables Table 4-1: Coefficient values 18 Table 4-2: Test for qualification of solid propulsion systems, su
15、bsystems and components . 22 Table 4-3: Examples of mission dependent verification tests for qualification . 24 Table 4-4: Test for acceptance of solid propulsion systems, subsystems and components . 25 Table 4-5: Examples of mission dependent verification tests for acceptance 26 BS EN 16603-35-02:2
16、014EN 16603-35-02:2014 (E) 4 Foreword This document (EN 16603-35-02:2014) has been prepared by Technical Committee CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN. This standard (EN 16603-35-02:2014) originates from ECSS-E-ST-35-02C. This European Standard shall be given the status of
17、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 be the subject of pa
18、tent 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 specifically space s
19、ystems 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 European Standard: Austr
20、ia, 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, Slovenia, Spain, Sweden
21、, Switzerland, Turkey and the United Kingdom. BS EN 16603-35-02:2014EN 16603-35-02:2014 (E) 5 Introduction The requirements in this Standard ECSS-E-ST-35-02C (and in the 3 other space propulsion standards ECSS-E-ST-35, ECSS-E-ST-35-01 and ECSS-E-ST-35-03) are organized with a typical structure as fo
22、llows: 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-E-ST-35 Propulsion general requirem
23、ents ECSS-E-ST-35-01 Liquid and electric propulsion for spacecraft ECSS-E-ST-35-02 Solid propulsion for spacecraft and launchers ECSS-E-ST-35-03 Liquid propulsion for launchers ECSS-E-ST-35-06 Cleanliness requirements for spacecrafts propulsion hardware ECSS-E-ST-35-10 Compatibility testing for liqu
24、id 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-E-ST-35-03. BS EN 16603-35-02:2014EN 16603-35-02:2014 (E) 6 1 S
25、cope General requirements applying to all type of Propulsion Systems Engineering are defined in ECSS-E-ST-35. For solid propulsion activities within a space project the standards ECSS-E-ST-35 and ECSS-E-ST-35-02 are applied together. This Standard defines the regulatory aspects that apply to the ele
26、ments and processes of solid propulsion for launch vehicles and spacecraft. It specifies 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
27、 factors, operational, and verification. NOTE 1 Some solid propulsion systems use hot gas valves, for thrust or pressure modulation. The requirements applicable to these systems are not covered by the present document. NOTE 2 For SRM with TVC, only moveable nozzle with flexseal are addressed. This s
28、tandard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00. BS EN 16603-35-02:2014EN 16603-35-02:2014 (E) 7 2 Normative references The following normative documents contain provisions which, through reference in this text, constitute pr
29、ovisions 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 of applying the more recent editions of the normative docum
30、ents 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 16603-20 ECSS-E-ST-20 Space engineering - Electrical and electronic EN 16603-20-07 ECSS-E-ST-
31、20-07 Space engineering - Electromagnetic compatibility EN 16603-32 ECSS-E-ST-32 Space engineering - Structural general requirements EN 16603-32-08 ECSS-E-ST-32-08 Space engineering - Materials EN 16603-32-10 ECSS-E-ST-32-10 Space engineering - Structural factors of safety for spaceflight hardware E
32、N 16603-33-11 ECSS-E-ST-33-11 Space engineering - Explosive systems and devices EN 16603-35 ECSS-E-ST-35 Space engineering - Propulsion general requirements 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
33、-ST-70 Space product assurance - Materials, mechanical parts and processes BS EN 16603-35-02:2014EN 16603-35-02:2014 (E) 8 3 Terms, definition 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, ECSS-E-ST-35, ECSS-E-S
34、T-32, and ECSS-E-ST-32-10 apply, in particular for the following terms: ECSS-E-ST-32 maximum design pressure (MDP) maximum expected operating pressure (MEOP) test factors (KA and KQ) ECSS-E-ST-35 ablated thickness (ea) burning time charred thickness (ec) corridor hump effect ignition time (tign) ins
35、ulation thickness (ei) non affected thickness(es) pre-heating time solid rocket motor thrust centroid time BS EN 16603-35-02:2014EN 16603-35-02:2014 (E) 9 3.2 Abbreviated terms For the purpose of this Standard, the abbreviated terms from ECSS-S-ST-00-01 and the following apply: Abbreviation Meaning
36、AIV assembly, integration and verification COG centre of gravity COM centre of mass DLAT destructive lot acceptance test EMC electromagnetic compatibility EMI electromagnetic interference ESD electrostatic discharge GSE ground support equipment HCl chloride acid MCI mass, centre of mass, inertia MDP
37、 maximum design pressure MEOP maximum expected operating pressure NDI non-destructive inspection OBDH on-board data handling SRM solid rocket motor TBPM to be provided by manufacturer TBPU to be provided by user TM/TC telemetry/telecommand TVC thrust vector control BS EN 16603-35-02:2014EN 16603-35-
38、02:2014 (E) 10 4 Solid propulsion engineering activities 4.1 Overview A solid propulsion system comprises the following main subsystems: The gas generating system consisting of a solid propellant contained in a thermally protected case. A nozzle with or without TVC. An ignition system to ignite the
39、solid propellant. This document applies to large and small systems; the latter usually have some different requirements to the large systems. Solid propulsion systems can either deliver a velocity increment in a fixed direction (with respect to the launcher or spacecraft) or in a variable direction,
40、 depending on whether TVC is present or not. Most solid propulsion systems use a single nozzle and roll control is usually provided by a separate system. Solid propulsion systems are “one-shot” systems and do not need a lot of preparation before use. Because a solid propellant motor is a one shot it
41、em, an acceptance firing test cannot be performed with the actual flight motor. 4.2 Functional 4.2.1 Mission a. ECSS-E-ST-35 clause 4.2 mission shall apply. 4.2.2 Functions 4.2.2.1 Steady state a. The propulsion system shall: 1. conform to the interfaces (see “interfaces” clause 4.4), 2. provide the
42、 specified total impulse, a thrust profile (nominal and dispersion) versus time. BS EN 16603-35-02:2014EN 16603-35-02:2014 (E) 11 b. The overall thrust profile shall be defined, taking into account the following launcher or spacecraft system constraints: 1. the general loads on the launcher or space
43、craft (due to aerodynamics, thermal fluxes and guidance or attitude control), 2. the induced accelerations. c. To conform to 4.2.2.1a and 4.2.2.1b, the following aspects shall be covered: 1. thrust level and orientation versus time; 2. burning time; 3. total impulse; 4. reliability level. 4.2.2.2 Tr
44、ansients a. The initial and final transient thrusts shall conform to the lift-off and separation constraints and requirements. 4.2.2.3 End-of-flight mass a. The mass of the motor shall conform to the system requirements. NOTE The “end-of-flight” mass of solid motors strongly depends on the internal
45、ballistics, functional parameters and the applied technologies. 4.2.2.4 First stage a. The first stage configuration and thrust profile shall be thoroughly analysed and a trade-off made against system constraints and requirements. 4.2.2.5 Electrical a. The propulsion system shall have electrical con
46、tinuity, including grounding and bonding. 4.2.2.6 Thrust orientation a. The propulsion system shall provide TVC or a thrust in a fixed orientation (with respect to the launcher or spacecraft) according to the system requirements. BS EN 16603-35-02:2014EN 16603-35-02:2014 (E) 12 4.3 Constraints 4.3.1
47、 Dynamic phenomena a. Pressure or thrust oscillation levels vs frequency range shall be specified at system and subsystem level. b. Pressure or thrust oscillation vs frequency range shall be characterised. c. The maximum allowable dynamic mechanical loads induced by the solid rocket motor during tra
48、nsient phases shall be specified vs frequency. NOTE For example shock during ignition and pressure wave. d. The dynamic mechanical loads induced by the solid rocket motor during transient phases shall be characterised. e. The Report for dynamic phenomena shall be delivered in conformance with the DR
49、D of Annex A. 4.3.2 External loads during the life cycle of the propulsion system a. All external loads, static and dynamic (including mechanical, thermal, electrical, magnetic, humidity and radiation) shall be specified as input for the design. 4.3.3 Thrust centroid time a. For solid thrusters that provide thrust impulsion, the thrust centroid time shall be characterized. NOTE Examples of solid thrusters: separation or braking rockets, control systems. 4.3.4 Acoustic noise a. The acoustic noise generated by the motor operating in the a
