1、Dezember 2014DEUTSCHE NORM DIN-Normenausschuss Luft- und Raumfahrt (NL)Preisgruppe 16DIN 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!%;sc“2248064www.din.deDDIN EN 16
2、603-35-02Raumfahrttechnik Feststoffantriebe fr Raumfahrzeuge und Trgerraketen;Englische Fassung EN 16603-35-02:2014Space engineering Solid propulsion for spacecrafts and launchers;English version EN 16603-35-02:2014Ingnierie spatiale Propulsion solide pour satellites et lanceurs;Version anglaise EN
3、16603-35-02:2014Alleinverkauf der Normen durch Beuth Verlag GmbH, 10772 Berlin www.beuth.deGesamtumfang 39 SeitenDIN EN 16603-35-02:2014-12 2 Nationales Vorwort Dieses Dokument (EN 16603-35-02:2014) wurde vom Technischen Komitee CEN/CLC/TC 5 Raumfahrt“ erarbeitet, dessen Sekretariat vom DIN (Deutsch
4、land) 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 16603-35-02:2014) basiert auf ECSS-E-ST-35-02C. Diese
5、s Dokument enthlt unter Bercksichtigung des DIN-Prsidialbeschlusses 1/2004 nur die englische Originalfassung von EN 16603-35-02:2014. Dieses Dokument wurde speziell zur Behandlung von Raumfahrtsystemen erarbeitet und hat daher Vorrang vor jeglicher Europischer Norm, da es denselben Anwendungsbereich
6、 hat, jedoch ber einen greren Geltungsbereich (z. B. Luft- und Raumfahrt) verfgt. DIN EN 16603-35-02:2014-12 3 Nationaler Anhang NA (informativ) Begriffe und Abkrzungen 3 Begriffe und Abkrzungen 3.1 Begriffe aus anderen Normen Fr die Anwendung dieses Dokuments gelten die Begriffe nach ECSS-S-ST-00-0
7、1, ECSS-E-ST-35, ECSS-E-ST-32 und ECSS-E-ST-32-10, insbesondere fr die folgenden Benennungen: ECSS-E-ST-32 MDP grter Bemessungsdruck (en: maximum design pressure) MEOP grter erwarteter Betriebsdruck (en: maximum expected operating pressure) Testfaktoren KA und KQ ECSS-E-ST-35 ea abladierte Dicke (en
8、: ablated thickness) Brenndauer (en: burning time) ec verkohlte Dicke (en: charred thickness) Korridor Hump-Effekt tignZndzeit (en: ignition time) ei Dmmdicke (en: insulation thickness) unbeeintrchtigte Dicke(n) (en: non affected thickness(es) Vorwrmzeit (en: pre-heating time) Feststoffantrieb (en:
9、solid rocket motor) Hauptschubzeit (en: thrust centroid time) DIN EN 16603-35-02:2014-12 4 3.2 Abkrzungen Fr die Anwendung dieses Dokuments gelten die Abkrzungen nach ECSS-S-ST-00-01 und die Folgenden. Abkrzung Bedeutung AIV Montage, Integration und Prfung (en: assembly, integration and verification
10、) COG Schwerkraftzentrum (en: centre of gravity) COM Masseschwerpunkt (en: centre of mass) DLAT Abnahmeprfung unter Werkstoffzerstrung (en: destructive lot acceptance test) EMC elektromagnetische Vertrglichkeit (en: electromagnetic compatibility) EMI elektromagnetische Interferenz (en: electromagnet
11、ic interference) ESD elektromagnetische Entladung (en: electrostatic discharge) GSE Bodendienstgerte (en: ground support equipment) HCl Salzsure MCI Masse, Massezentrum, Trgheit (en: mass, centre of mass, inertia) MDP grter Bemessungsdruck (en: maximum design pressure) MEOP grter erwarteter Betriebs
12、druck (en: maximum expected operating pressure) NDI zerstrungsfreie Prfung (en: non-destructive inspection) OBDH Datenverarbeitung an Bord (en: on-board data handling) SRM Feststoffantrieb (en: solid rocket motor) TBPM durch den Hersteller bereitzustellen (en: to be provided by manufacturer) TBPU du
13、rch den Nutzer bereitzustellen (en: to be provided by user) TM/TC Fernmessung/Fernsteuern (en: telemetry/telecommand) TVC Schubvektorsteuerung (en: thrust vector control) EUROPEAN STANDARD NORME EUROPENNE EUROPISCHE NORM EN 16603-35-02 October 2014 ICS 49.140 English version Space engineering - Soli
14、d propulsion for spacecrafts and launchers Ingnierie spatiale - Propulsion solide pour satellites et 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 CE
15、N/CENELEC Internal 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 Ce
16、ntre 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 translation under the responsibility of a CEN and CENELEC member into its own language and notified to the CEN-CENELEC Management Centre
17、has the same status 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,
18、Hungary, Iceland, Ireland, 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 exploitat
19、ion in any form and by any means reserved worldwide for CEN national Members and for CENELEC Members. Ref. No. EN 16603-35-02:2014 EEN 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
20、other standards 8 3.2 Abbreviated terms. 9 4 Solid propulsion engineering activities 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 centro
21、id time 12 4.3.4 Acoustic noise . 12 4.3.5 Pollution 12 4.3.6 Ejected parts . 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
22、 15 4.5.3 Global performance . 17 4.5.4 Ignition and tail-off . 17 DIN EN 16603-35-02:2014-12 EN 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 .
23、 21 4.9 Production and manufacturing 24 4.10 In-service 26 4.10.1 General . 26 4.10.2 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: Coeff
24、icient values 18 Table 4-2: Test for qualification of solid propulsion systems, subsystems 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: Exam
25、ples of mission dependent verification tests for acceptance 26 DIN EN 16603-35-02:2014-12 EN 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)
26、 originates from ECSS-E-ST-35-02C. This European Standard shall be given the status of a national standard, either by publication of an identical text or by endorsement, at the latest by April 2015, and conflicting national standards shall be withdrawn at the latest by April 2015. Attention is drawn
27、 to the possibility that some of the elements 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
28、 Free 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 organi
29、zations 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, M
30、alta, Netherlands, Norway, Poland, Portugal, Romania, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and the United Kingdom. DIN EN 16603-35-02:2014-12 EN 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 ECS
31、S-E-ST-35, ECSS-E-ST-35-01 and ECSS-E-ST-35-03) are organized 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 ECS
32、S-E-ST-35 series which has the following structure; ECSS-E-ST-35 Propulsion general requirements 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 req
33、uirements for spacecrafts propulsion hardware 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-
34、01, ECSS-E-ST-35-02 and ECSS-E-ST-35-03. DIN EN 16603-35-02:2014-12 EN 16603-35-02:2014 (E) 6 1 Scope 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-
35、ST-35-02 are applied together. This Standard defines the regulatory aspects that apply to the elements 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
36、the requirements for the engineering aspects such as functional, physical, environmental, quality 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 pr
37、esent document. NOTE 2 For SRM with TVC, only moveable nozzle with flexseal are addressed. This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00. DIN EN 16603-35-02:2014-12 EN 16603-35-02:2014 (E) 7 2 Normative references The
38、 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 are
39、 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 of
40、terms EN 16603-20 ECSS-E-ST-20 Space engineering - Electrical and electronic EN 16603-20-07 ECSS-E-ST-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 1
41、6603-32-10 ECSS-E-ST-32-10 Space engineering - Structural factors of safety for spaceflight hardware EN 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 as
42、surance Quality assurance EN 16602-40 ECSS-Q-ST-40 Space product assurance - Safety EN 16602-70 ECSS-Q-ST-70 Space product assurance - Materials, mechanical parts and processes DIN EN 16603-35-02:2014-12 EN 16603-35-02:2014 (E) 8 3 Terms, definition and abbreviated terms 3.1 Terms from other standar
43、ds For the purpose of this Standard, the terms and definitions from ECSS-S-ST-00-01, ECSS-E-ST-35, ECSS-E-ST-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-
44、35 ablated thickness (ea) burning time charred thickness (ec) corridor hump effect ignition time (tign) insulation thickness (ei) non affected thickness(es) pre-heating time solid rocket motor thrust centroid time DIN EN 16603-35-02:2014-12 EN 16603-35-02:2014 (E) 9 3.2 Abbreviated terms For the pur
45、pose of this Standard, the abbreviated terms from ECSS-S-ST-00-01 and the following apply: Abbreviation Meaning AIV assembly, integration and verification COG centre of gravity COM centre of mass DLAT destructive lot acceptance test EMC electromagnetic compatibility EMI electromagnetic interference
46、ESD electrostatic discharge GSE ground support equipment HCl chloride acid MCI mass, centre of mass, inertia MDP 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
47、 to be provided by user TM/TC telemetry/telecommand TVC thrust vector control DIN EN 16603-35-02:2014-12 EN 16603-35-02:2014 (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 soli
48、d propellant contained in a thermally protected case. A nozzle with or without TVC. An ignition system to ignite the 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 deliv
49、er a velocity increment in a fixed direction (with respect to the launcher or spacecraft) or in a variable direction, 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 item, an acceptance firing test cannot be performed with the actual flight mo
