BS EN 16603-60-30-2015 Space engineering Satellite AOCS requirements《航天工程 卫星AOCS要求》.pdf

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1、BSI Standards PublicationBS EN 16603-60-30:2015Space engineering SatelliteAOCS requirementsBS EN 16603-60-30:2015 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of EN16603-60-30:2015.The UK participation in its preparation was entrusted to TechnicalCommittee ACE/68,

2、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 Standards Institution 20

3、15. Published by BSI Standards Limited 2015ISBN 978 0 580 86645 6ICS 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 2015.Amendments/corrigenda

4、issued since publicationDate T e x t a f f e c t e dBS EN 16603-60-30:2015EUROPEAN STANDARD NORME EUROPENNE EUROPISCHE NORM EN 16603-60-30 September 2015 ICS 49.140 English version Space engineering - Satellite AOCS requirements Ingnierie spatiale - Exigences pour le systme de contrle dattitude et d

5、orbite dun satellite Raumfahrttechnik - Anforderungen an Satelliten-AOCS This European Standard was approved by CEN on 16 November 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 o

6、f 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 (English, Fr

7、ench, 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 bodies and

8、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, Portuga

9、l, Romania, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and United Kingdom. CEN-CENELEC Management Centre: Avenue Marnix 17, B-1000 Brussels 2015 CEN/CENELEC All rights of exploitation in any form and by any means reserved worldwide for CEN national Members and for CENELEC Members. Ref. N

10、o. EN 16603-60-30:2015 EBS EN 16603-60-30:2015EN 16603-60-30:2015 (E) 2 Table of contents European 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 Terms specific to the present Standard . 8 3.3 Abbrev

11、iated terms. 11 3.4 Nomenclature . 12 4 Principles 13 4.1 Purpose and applicability 13 4.2 Tailoring 13 4.3 Relation between AOCS level and higher level requirements . 14 5 Requirements 15 5.1 Functional and FDIR requirements . 15 5.1.1 General functional requirements . 15 5.1.2 Fault management req

12、uirements . 20 5.1.3 Propulsion related functional requirements . 21 5.2 Operational requirements . 22 5.2.1 Requirements for ground telecommand 22 5.2.2 Requirements for telemetry . 24 5.2.3 Requirements for autonomous operations . 25 5.2.4 Requirement for calibration operations 25 5.2.5 Requiremen

13、ts related to the satellite database 26 5.3 Performance requirements . 26 5.3.1 Flight domain 26 5.3.2 Normal mode 26 BS EN 16603-60-30:2015EN 16603-60-30:2015 (E) 3 5.3.3 Orbit knowledge and control 29 5.3.4 Attitude agility 31 5.3.5 Performances outages 31 5.3.6 Acquisition and safe mode 32 5.3.7

14、Performance budgets 32 5.4 Verification requirements 33 5.4.1 Scope 33 5.4.2 Overview . 33 5.4.3 Verification facilities . 34 5.4.4 AOCS design and performance verification . 36 5.4.5 AOCS hardware/software verification 37 5.4.6 Verification at satellite level . 37 5.4.7 AOCS-ground interface verifi

15、cation . 38 5.4.8 In-flight verification 38 5.5 Documentation requirements 39 5.5.1 Overview . 39 5.5.2 Required documentation . 39 Annex A (normative) Design Definition File (DDF) for AOCS - DRD . 40 Annex B (normative) Design Justification File (DJF) for AOCS-DRD . 42 Annex C (normative) AOCS Algo

16、rithms and Functional Description - DRD 44 Annex D (normative) Verification Plan (VP) for AOCS - DRD 46 Annex E (normative) User Manual (UM) for AOCS - DRD 48 Annex F (informative) AOCS Documentation delivery by Phase 50 Bibliography . 51 Tables Table F-1 : Typical AOCS documentation. 50 BS EN 16603

17、-60-30:2015EN 16603-60-30:2015 (E) 4 European foreword This document (EN 16603-60-30:2015) has been prepared by Technical Committee CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN. This standard (EN 16603-60-30:2015) originates from ECSS-E-ST-60-30C. This European Standard shall be giv

18、en the status of a national standard, either by publication of an identical text or by endorsement, at the latest by March 2016, and conflicting national standards shall be withdrawn at the latest by March 2016. Attention is drawn to the possibility that some of the elements of this document may be

19、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 been developed to cover spe

20、cifically 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 to implement this Europea

21、n 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, Romania, Slovakia, Sloven

22、ia, Spain, Sweden, Switzerland, Turkey and the United Kingdom. BS EN 16603-60-30:2015EN 16603-60-30:2015 (E) 5 Introduction The Attitude and Orbit Control System (AOCS) requirements for the development of space programmes are typically part of the Project Requirements Document. The level of complete

23、ness and the level of detail vary very much from project to project. This Standard provides a baseline for the AOCS requirements which are used in the specification and the validation process. The Standard is intended to be used for each programme as an input for writing the Project Requirements Doc

24、ument. It includes all subjects related to AOCS: Functional and FDIR requirements Operational requirements Performance requirements Verification requirements Documentation requirements BS EN 16603-60-30:2015EN 16603-60-30:2015 (E) 6 1 Scope This Standard specifies a baseline for the attitude and orb

25、it control system requirements to be used in the Project Requirements Document for space applications. Project requirements documents are included in business agreements, which are agreed between the parties and binding them, at any level of space programmes, as described in ECSS-S-ST-00. This Stand

26、ard deals with the attitude and orbit control systems developed as part of a satellite space project. The classical attitude and orbit control systems considered here include the following functions: Attitude estimation Attitude guidance Attitude control Orbit control Orbit estimation, called Naviga

27、tion in this document, can be part of the function for missions which explicitly require this function Acquisition and maintenance of a safe attitude in emergency cases and return to nominal mission upon command The present Standard does not cover missions that include the following functions: Real-

28、time on-board trajectory guidance and control Real-time on-board relative position estimation and control Example of such missions are rendezvous, formation flying, launch vehicles and interplanetary vehicles. Although the present document does not cover the above mentioned types of mission, it can

29、be used as a reference document for them. This standard may be tailored for the specific characteristic and constraints of a space project in conformance with ECSS-S-ST-00. BS EN 16603-60-30:2015EN 16603-60-30:2015 (E) 7 2 Normative references The following normative documents contain provisions whi

30、ch, 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 the possibility of applyin

31、g 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 terms EN 16603-10 ECSS-E-ST-10 Space engineering - S

32、ystem engineering general requirements EN 16603-10-03 ECSS-E-ST-10-03 Space engineering - Testing EN 16603-60-10 ECSS-E-ST-60-10 Space engineering - Control performances EN 16603-70-11 ECSS-E-ST-70-11 Space engineering - Space segment operability BS EN 16603-60-30:2015EN 16603-60-30:2015 (E) 8 3 Ter

33、ms definitions and abbreviated terms 3.1 Terms from other standards For the purpose of this Standard, the terms and definitions from ECSS-ST-00-01, ECSS-E-ST-10 and ECSS-E-ST-60-10 apply. In particular, the following terms are used in the present Standard, with the definition given in the ECSS-E-ST-

34、60-10: Absolute knowledge error (AKE) Absolute performance error (APE) Relative knowledge error (RKE) Relative performance error (RPE) Robustness 3.2 Terms specific to the present Standard The definitions given in this clause are specific to the present Standard and are applicable for the understand

35、ing of the requirements. Other names or definitions may be used however during the development of space programmes. 3.2.1 attitude and orbit control system (AOCS) functional chain of a satellite which encompasses attitude and orbit sensors, attitude estimation and guidance, attitude and orbit contro

36、l algorithms, attitude and orbit control actuators NOTE 1 The AOCS can include an orbit estimation function usually called Navigation. NOTE 2 The AOCS can include additional items such as AOCS dedicated computer and AOCS application software, depending on satellite architecture. BS EN 16603-60-30:20

37、15EN 16603-60-30:2015 (E) 9 3.2.2 AOCS mode state of the AOCS for which a dedicated set of equipment and algorithms is used to fulfil operational objectives and requirements 3.2.3 AOCS functional simulator fully numerical simulator used to verify the AOCS design, algorithms, parameters and performan

38、ces NOTE The AOCS functional simulator can be a collection of unitary numerical simulators, provided that a full coverage of the verification is ensured. 3.2.4 avionics test bench facility dedicated to the validation of the avionics and its constituents NOTE 1 The avionics content and definition can

39、 vary from one programme to another. It includes as a minimum the platform on-board computer and platform software, the Data Handling functions, the AOCS sensors and actuators. NOTE 2 This facility includes numerical models and/or real hardware representative of flight units. The avionics test bench

40、 is used to validate the AOCS behaviour in real-time conditions, including hardware-software interfaces. 3.2.5 AOCS end-to-end tests tests defined to validate complete AOCS loops on the satellite, including all the real components such as hardware, software and wiring NOTE End-to-end tests can be pe

41、rformed in open loop or closed loop. 3.2.6 flight dynamics (FD) functionalities performed on ground in support of on-board AOCS/GNC NOTE Examples include orbit manoeuvres computation, guidance, AOCS/GNC TC generation and ephemerides. 3.2.7 guidance navigation and control functions (GNC) functions in

42、 charge of targeted orbit and attitude computation, attitude and orbit determination, attitude and orbit control NOTE GNC versus AOCS: the term AOCS is commonly used when the orbit guidance is not performed on board, which is the case for standard LEO, MEO and GEO missions. GNC is commonly used for

43、the on-board segment, when the satellite position is controlled in closed loop, for instance in case of rendezvous BS EN 16603-60-30:2015EN 16603-60-30:2015 (E) 10 and formation flying. The GNC term can be also used for the whole function, distributed between on-board and ground systems. 3.2.8 sensi

44、tivity analysis identification of the parameters which impact the AOCS performance, and assessment of their individual contribution to this performance NOTE 1 Only the dominating contributors are of interest. These contributors can include: Noise, bias and misalignment, for the AOCS sensors and actu

45、ators Satellite mass properties Satellite configuration variation, e.g. solar array position, sensors and actuators configuration Measurements outages Environmental conditions External and internal disturbances NOTE 2 The AOCS performance can be for instance: Pointing accuracy Duration of a manoeuvr

46、e Fuel consumption NOTE 3 The objective is to have an order of magnitude of the contribution, and this can be achieved by analysis, simulation or test. 3.2.9 worst case analysis deterministic analysis to identify a set of parameters, disturbances and initial conditions, which, when combined at some

47、given values within their nominal operational range, define a worst case situation or scenario for the evaluation of AOCS performances NOTE 1 The parameter variations and disturbances are as defined for the sensitivity analysis, and their selection can rely on a sensitivity analysis. NOTE 2 The init

48、ial conditions can be for instance: Angular rates Initial angular momentum Sun, Earth or planetary positions Orbit parameters NOTE 3 The worst case scenarios depend on the considered AOCS performance. 3.2.10 tranquilization phase phase following an attitude manoeuvre, or possibly an orbit correction

49、 manoeuvre, during which the full attitude performance is not yet achieved BS EN 16603-60-30:2015EN 16603-60-30:2015 (E) 11 3.3 Abbreviated terms The following abbreviated terms are defined and used within this document: Abbreviation Meaning AOCS attitude and orbit control system AKE absolute knowledge error APE absolute performance error ATB avionics test bench CDR critical design review CoM centre of mass DDF design definition file DJF design justification file DRD document requirements definition ECEF Earth centred