BS ISO 14303-2002 Space systems - Launch-vehicle-to-spacecraft interfaces《航天系统 航天运载工具与航天器的接口》.pdf

1、BRITISH STANDARD BS ISO 14303:2002 Space systems Launch-vehicle-to- spacecraft interfaces ICS 49.140 BS ISO 14303:2002 This British Standard, having been prepared under the direction of the Engineering Sector Policy and Strategy Committee, was published under the authority of the Standards Policy an

2、d Strategy Committee on 14 November 2002 BSI 14 November 2002 ISBN 0 580 40740 3 National foreword This British Standard reproduces verbatim ISO 14303:2002 and implements it as the UK national standard. The UK participation in its preparation was entrusted to Technical Committee ACE/68, Space system

3、s and operations, which has the responsibility to: A list of organizations represented on this committee can be obtained on request to its secretary. Cross-references The British Standards which implement international publications referred to in this document may be found in the BSI Catalogue under

4、 the section entitled “International Standards Correspondence Index”, or by using the “Search” facility of the BSI Electronic Catalogue or of British Standards Online. This publication does not purport to include all the necessary provisions of a contract. Users are responsible for its correct appli

5、cation. Compliance with a British Standard does not of itself confer immunity from legal obligations. aid enquirers to understand the text; present to the responsible international/European committee any enquiries on the interpretation, or proposals for change, and keep the UK interests informed; mo

6、nitor related international and European developments and promulgate them in the UK. Summary of pages This document comprises a front cover, an inside front cover, the ISO title page, pages ii to v, a blank page, pages 1 to 53 and a back cover. The BSI copyright date displayed in this document indic

7、ates when the document was last issued. Amendments issued since publication Amd. No. Date Comments Reference number ISO 14303:2002(E)INTERNATIONAL STANDARD ISO 14303 First edition 2002-10-15 Space systems Launch-vehicle-to- spacecraft interfaces Systmes spatiaux Interfaces entre le lanceur spatial e

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13、002(E) I SO 2002 All irthgs ersedevr iiiContents Page Foreword iv Introduction. v 1 Scope 1 2 Terms and definitions. 1 3 Symbols and abbreviated terms 2 4 Mechanical interfaces. 2 5 Electrical interfaces 5 6 RF/electromagnetic interface. 8 7 Mission performance 9 8 Induced environment and load limit

14、ations. 14 9 Verification analysis and documentation . 16 10 Verification tests . 20 11 Spacecraft launch preparation operations. 23 Annex A (informative) Usable envelopes . 26 Annex B (informative) Physical interface presentations 31 Annex C (informative) Performance presentations. 34 Annex D (info

15、rmative) Environment presentations. 40 Annex E (informative) Verification 52 BSISO14303:2002iiiIS:30341 O2002(E) vi I SO 2002 All irthgs ersedevrForeword ISO (the International Organization for Standardization) is a worldwide federation of national standards bodies (ISO member bodies). The work of p

16、reparing International Standards is normally carried out through ISO technical committees. Each member body interested in a subject for which a technical committee has been established has the right to be represented on that committee. International organizations, governmental and non-governmental,

17、in liaison with ISO, also take part in the work. ISO collaborates closely with the International Electrotechnical Commission (IEC) on all matters of electrotechnical standardization. International Standards are drafted in accordance with the rules given in the ISO/IEC Directives, Part 3. The main ta

18、sk of technical committees is to prepare International Standards. Draft International Standards adopted by the technical committees are circulated to the member bodies for voting. Publication as an International Standard requires approval by at least 75 % of the member bodies casting a vote. Attenti

19、on is drawn to the possibility that some of the elements of this International Standard may be the subject of patent rights. ISO shall not be held responsible for identifying any or all such patent rights. ISO 14303 was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcommi

20、ttee SC 14, Space systems and operations. Annexes A to E of this International Standard are for information only. BSISO14303:2002ivIS:30341 O2002(E) I SO 2002 All irthgs ersedevr vIntroduction ISO 14303 together with ISO 15863 and ISO 17401 forms a set of International Standards that describes fully

21、 the process for communicating information about launch vehicle (LV) to spacecraft (SC) interfaces. Clauses 4 to 8 of this International Standard identify the parameters of an LVSC interface, while clauses 9 and 10 define the methodology for verification of the interface by analyses, testing or both

22、. Clause 11 defines the operations performed on the SC to prepare it for launch and the joint operations performed until it is installed on the LV. Some sections of this document may refer to elements of the LV or SC, or elements of both, that are not applicable to their design characteristics. Thes

23、e sections should therefore only be considered if applicable. The annexes give examples of the typical presentation format of the various interface parameters, as appropriate. BSISO14303:2002vINTENRATIONAL TSANDADR IS:30341 O2002(E)I SO 2002 All irthgs ersedevr 1Space systems Launch-vehicle-to-space

24、craft interfaces 1 Scope This International Standard specifies the interfaces between a launch vehicle (LV) and the spacecraft (SC) being launched, to provide LV and SC organizations with the necessary format for presenting the required technical data on existing and future interfaces. Its intended

25、purpose is to minimize costs and reduce the risks from errors resulting from miscommunication. It does not limit the ability of LV or SC organizations to specify unique requirements. 2 Terms and definitions For the purposes of this International Standard, the following terms and definitions apply. 2

26、.1 spacecraft system SC system spacecraft bus, payload and all items supplied by the SC contractor in support of the launch effort 2.2 launch vehicle system LV system launch vehicle and associated launch services supplied by the launch services contractor or subcontractors or both 2.3 separation pla

27、ne plane where launch vehicle and spacecraft separation occurs 2.4 mating plane interface between the spacecraft, or the spacecraft-provided payload adapter, and the launch vehicle 2.5 payload adapter PLA structure that mates the spacecraft to the launch vehicle, including the SCLV separation system

28、 NOTE The PLA is a part of the LV and does not separate with the SC. 2.6 usable volume volume available to the payload within the launch-vehicle fairing or carrying structure BSISO14303:20021IS:30341 O2002(E) 2 I SO 2002 All irthgs ersedevr 3 Abbreviated terms The following abbreviations are used in

29、 this International Standard. ACS Attitude control system CG Centre of gravity CLA Coupled loads analysis EMC Electromagnetic compatibility EMI Electromagnetic interference GSE Ground support equipment GTO Geosynchronous transfer orbit ICD Interface control document IRD Interface requirements docume

30、nt LEO Low Earth orbit LV Launch vehicle LVS Launch vehicle system MEO Medium Earth orbit PLA Payload adapter PLF Payload fairing RF Radio frequency SC Spacecraft SPF Spacecraft processing facility SPM Solid propellant motor SSO Sun synchronous orbit TBD To be determined TM Telecommand 4 Mechanical

31、interfaces 4.1 General This clause identifies the mechanical interfaces between the SC and the LV. The methodology for verifying these interfaces is discussed in clauses 9 and10. 4.2 Mechanical configurations The SC shall be mated to the LV by a payload adapter (PLA). If the LV provides the PLA, it

32、shall include a pyrotechnically activated separation system. If the SC provides its own separation system, then a static bolted interface to the LV in accordance with 4.4 shall be used. During final launch processing and launch ascent, the SC shall be contained in a structure provided by the LV cont

33、ractor. BSISO14303:20022IS:30341 O2002(E) I SO 2002 All irthgs ersedevr 34.3 SC characteristics 4.3.1 SC fundamental natural frequency The SCs fundamental natural frequency in the longitudinal and lateral axes shall not be less than a value specified by the LV with the SC cantilevered from the matin

34、g plane. 4.3.2 SC mass properties The SC-CG location, and the inertia properties for the x, y and z axes, shall be defined, and shall include the SC propellant-tanking characteristics to be used for the LV providers sloshing analysis. 4.4 Usable volume The SC shall be accommodated in the LVs usable

35、volume, as characterized in annex A, without interference. The static envelope of the SC shall not exceed the usable volume, in order to ensure that there is no physical contact between the SC and the LV in a dynamic environment. Protrusions outside this usable volume may be allowed by mutual agreem

36、ent between SC and LV contractors. 4.5 PLA interface 4.5.1 General The LVSC interface shall be characterized by the following elements, for each PLA type as shown in annex B, Figures B.1 and B.2. 4.5.2 LV-supplied PLA The SCLV mating surface for LV supplied PLA shall be defined by the following. a)

37、LV and PLA coordinate systems and relative angular orientation. b) Physical configuration (including keyway location): 1) material; 2) coating; 3) roughness; 4) flatness and perpendicularity; 5) stiffness section area (mm 2 ) applicable length (millimetres) inertia (mm 4 ). c) Clampband: 1) geometry

38、; 2) material; 3) roughness; 4) allowable tension (newtons). d) Other mating systems. BSISO14303:20023IS:30341 O2002(E) 4 I SO 2002 All irthgs ersedevr 4.5.3 SC-supplied PLA The SCLV mating surface for SC-provided PLA shall be defined by the following. a) LV and PLA coordinate systems and relative a

39、ngular orientation. b) Physical configuration: 1) description of bolted interfaces (number, size, location of holes, type of bolts and torque value); 2) material; 3) coating; 4) roughness; 5) flatness and perpendicularity; 6) stiffness section area (mm 2 ) applicable length (millimetres) inertia (mm

40、 4 ). 4.5.4 Separation actuators Separation actuators (springs or pushrods) shall be characterized by number, location, nominal stroke (millimetres), reduced stroke (millimetres), maximum force (newtons), and energy per unit (joules). 4.6 Umbilical connectors and microswitches The LV side of the int

41、erface shall have electrical connectors for electrical power and signals in accordance with clause 5. The LV connectors shall be adjustable in two planes to provide for alignment of the connectors during SCLV mating. The SC shall have compatible connector halves. All connectors shall be characterize

42、d by supplier, number, location and mechanical interface, push-on load per connector (newtons), push-off load per connector (newtons), BSISO14303:20024IS:30341 O2002(E) I SO 2002 All irthgs ersedevr 5 energy released by each plug (joules), and keying index. 4.7 Fluid connections Fluid connections sh

43、all be defined to indicate location, size, fluid (gas or liquid) and flowrate, material, operating characteristics, and functional usage. 4.8 Encapsulated SC access The LV shall provide access through the fairing or the carrying structure to the SC after encapsulation if physical access is required

44、by the SC contractor. A drawing shall be made with developed views of fairings and dual launch structures indicating authorized areas for access doors. The maximum number of doors authorized per SC with their corresponding size shall be defined. 5 Electrical interfaces 5.1 General This clause identi

45、fies the parameters required to define electrical interfaces (power and signal) between the SC and LV. 5.2 Umbilical connectors Umbilical connectors shall be defined by the following characteristics for the LV and SC sides: type and reference designator of connectors; number of pins available to the

46、 user; number of connectors; segregation between SC power and pyro-firing circuits; location; shielding; keying index. BSISO14303:20025IS:30341 O2002(E) 6 I SO 2002 All irthgs ersedevr 5.3 Umbilical links Umbilical links between the SC mated with the LV and the SCs electrical ground support equipmen

47、t (GSE) shall be described as follows: a) number and type of links; b) limitations maximum voltage (volts) maximum current (amperes) power (watts) maximum one-way resistance or voltage drop (ohms or volts); c) operating constraints number of functions types of function; d) current at umbilical plug

48、extraction; e) conformance certification end-to-end resistance (ohms) line to ground insulation line-to-line insulation; f) insertion of components. 5.4 Electrical commands dedicated to SC 5.4.1 General Standard and optional commands generated by the LV and dedicated to the SC shall be listed with a

49、 description of the related characteristics. 5.4.2 Pyrotechnic commands A general description of the electrical circuit associated with pyrotechnic commands shall be made. Optionally, a schematic drawing of the corresponding electrical circuits may be included. The following characteristics shall be indicated: time and number of commands; voltage (