1、 g49g50g3g38g50g51g60g44g49g42g3g58g44g55g43g50g56g55g3g37g54g44g3g51g40g53g48g44g54g54g44g50g49g3g40g59g38g40g51g55g3g36g54g3g51g40g53g48g44g55g55g40g39g3g37g60g3g38g50g51g60g53g44g42g43g55g3g47g36g58control document ICS 49.140Space systems Spacecraft-to-launch-vehicle interface BRITISH STANDARDBS
2、ISO 15863:2003BS ISO 15863:2003This British Standard was published under the authority of the Standards Policy and Strategy Committee on 30 January 2006 BSI 30 January 2006ISBN 0 580 47413 5The British Standards which implement international publications referred to in this document may be found in
3、the BSI Catalogue under 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
4、 for its correct application. Compliance with a British Standard does not of itself confer immunity from legal obligations.Summary of pagesThis document comprises a front cover, an inside front cover, the ISO title page, pages ii to v, a blank page, pages 1 to 28, an inside back cover and a back cov
5、er.The BSI copyright notice displayed in this document indicates when the document was last issued.Amendments issued since publicationAmd. No. Date CommentsA list of organizations represented on this committee can be obtained on request to its secretary.Cross-referencesenquiries on the interpretatio
6、n, or proposals for change, and keep UK interests informed; monitor related international and European developments and promulgate them in the UK.National forewordThis British Standard reproduces verbatim ISO 15863:2003 and implements it as the UK national standard.The UK participation in its prepar
7、ation was entrusted to Technical Committee ACE/68, Space systems and operations, which has the responsibility to: aid enquirers to understand the text; present to the responsible international/European committee any Reference numberISO 15863:2003(E)INTERNATIONAL STANDARD ISO15863First edition2003-11
8、-01Space systems Spacecraft-to-launch-vehicle interface control document Systmes spatiaux Document de contrle des interfaces entre le vhicule spatial et le lanceur spatial BS ISO 15863:2003ii iiiContents Page Foreword iv Introduction v 1 Scope 1 2 Normative references . 1 3 Terms, definitions and ab
9、breviated terms 1 4 Applicable and reference documentation 1 5 Spacecraft mission characteristics. 2 6 Mechanical interfaces. 3 7 Electrical interface 6 8 RF and electromagnetic interfaces . 10 9 Launch vehicle and spacecraft mission characteristics 14 10 Verification analyses for induced environmen
10、t. 19 11 Verification tests . 21 12 Launch range operations Facilities and support 22 BS ISO 15863:2003iv Foreword ISO (the International Organization for Standardization) is a worldwide federation of national standards bodies (ISO member bodies). The work of preparing International Standards is nor
11、mally 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, in liaison with ISO, also take part in
12、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 2. The main task of technical committees is to prepar
13、e 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. Attention is drawn to the possibility that som
14、e of the elements of this document may be the subject of patent rights. ISO shall not be held responsible for identifying any or all such patent rights. ISO 15863 was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 14, Space systems and operations. BS ISO 1586
15、3:2003vIntroduction This International Standard defines the basic rules for writing an interface control document (ICD) between spacecraft (SC) and launch vehicle (LV) organizations. The necessity of writing this International Standard was expressed by the communication spacecraft community, which i
16、s faced with an increasing number of launch vehicle agencies, with the objective of reducing workload and costs. The application of this International Standard will permit to control the compatibility of SC with various LV systems reducing thereby the risk of discovering incompatibilities late in th
17、e launch-preparation process. LV and SC organizations may include additional topics if required. Some sections of this International Standard may refer to elements that are not applicable to the LV, SC or launch range characteristics, in which case they should be ignored. For most items, except when
18、 specified, the information can be provided in SC or LV drawings and in tabular or narrative format with figures. BS ISO 15863:2003blank1Space systems Spacecraft-to-launch-vehicle interface control document 1 Scope The purpose of this International Standard is to provide spacecraft (SC) and launch v
19、ehicle (LV) organizations with the general format for presenting the interface control document (ICD) that verifies and controls the compatibility between SC and LV for a dedicated mission. This International Standard addresses the definition of the mission, the compatibility of the SC with the LV e
20、nvironment, including all mechanical, electrical, radio frequency, and electromagnetic aspects related to SC to LV and SC to launch range interfaces, verification analyses and tests for the induced environment, and the necessary facilities and support for launch range operations. 2 Normative referen
21、ces The following referenced documents are indispensable for the application of this document. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced document (including any amendments) applies. ISO 14303, Space systems Launch-vehicle-to-sp
22、acecraft interfaces 3 Terms, definitions and abbreviated terms 3.1 Terms and definitions For the purposes of this document, the terms and definitions given in ISO 14303 apply. 3.2 Abbreviated terms EMC electromagnetic compatibility EIRP effective isotropically radiated power ICD interface control do
23、cument LV launch vehicle RF radio frequency SC spacecraft 4 Applicable and reference documentation 4.1 Applicable documents The list of documents that are contractually binding and require a waiver or a formal agreement for any modification shall be provided. This list shall include the applicable L
24、V users manual. BS ISO 15863:20032 4.2 Reference documents The list of documents that form the necessary database for the LV and the SC contractors in the course of the launch preparation shall be provided. Typically, the list shall include the documentation related to the various analyses and test
25、programs specific to the mission. 4.3 Safety submission sheets The list of safety submission sheets and corresponding current status shall be provided. 4.4 Waivers The list of applicable waivers and corresponding current status shall be provided. In case of conflict between the above-listed document
26、ation and the ICD, the latter shall take precedence. 5 Spacecraft mission characteristics 5.1 General This chapter of the ICD is optional. It is for reference and information only and does not establish interface definitions or requirements. 5.2 Mission description The purpose of the SC mission and
27、its orbital characteristics shall be described. An in-orbit view of the SC should be included. General aspects of the mission such as ground network, coverage zones and lifetime may be addressed. 5.3 Spacecraft description 5.3.1 Spacecraft bus description The general characteristics of the SC bus in
28、cluding appendages shall be described. The following items may be addressed: platform type and heritage (if applicable); overall structure; fixed and deployable appendages; attitude and orbit control system. 5.3.2 Spacecraft payload description The payload equipment and its purpose shall be describe
29、d. The following items may be addressed: antennas and associated frequency bands; transmission characteristics; transponder type and number; electrical power. BS ISO 15863:200336 Mechanical interfaces 6.1 General This chapter of the ICD shall provide the specific characteristics and parameters that
30、establish the mechanical interface between the SC and the LV. The information can be provided in SC or LV drawings and in tabular or narrative format with figures. 6.2 Mechanical configuration The LV and SC reference axes and relative rotational orientation shall be described. Drawings of the SC and
31、 adapter assembly within the payload compartment, which show and define the location of all interface components, shall be provided. 6.3 Spacecraft fundamental frequencies The minimum allowable SC fundamental frequencies in axial and lateral directions shall be specified. 6.4 Usable volume Drawings
32、that show the allowable usable volume within the payload compartment shall be provided. The usable volume is determined by the physical clearances that are based on the static clearances and dynamic deflections of the fairing and SC. Critical clearance information including detailed views of protrus
33、ion areas with associated dimensions shall be provided. 6.5 SCLV adapter interface 6.5.1 General All of the characteristics of the physical and geometric interface for both the SC and the LV shall be described. 6.5.2 Payload adapter description (optional) The following general characteristics of the
34、 payload adapter shall be described: type; material; geometrical shape; diameter of upper and lower interface rings; mass properties of equipped adapter. 6.5.3 Interface ring characteristics Drawings showing side sections of the LV and SC interface rings with detailed dimensions and tolerances shall
35、 be provided. The following characteristics shall be specified: a) material; b) Youngs modulus; BS ISO 15863:20034 c) coating: surfaces in contact, other surfaces; d) roughness; e) flatness/perpendicularity; f) stiffness: applicable length, section area, inertia. These requirements are also applicab
36、le to a bolted interface between the LV and the SC adapter when the SC provides the adapter. 6.5.4 Separation system characteristics Drawings showing the separation-system actuator mechanism shall be provided. The following characteristics shall be specified: number; location; nominal stroke; reduce
37、d stroke; maximum force; energy per unit. 6.5.5 SC mating system description 6.5.5.1 General The SC mating and release system shall be described, including system characteristics and material properties as listed below. When the SC contractor provides the adapter, the corresponding separation shock
38、spectrum at the LV-SC interface plane shall be shown (see 10.2.7). 6.5.5.2 Clampband system The following characteristics shall be specified: a) coating: surface in contact with adapter and SC, other surfaces; b) roughness; BS ISO 15863:20035c) tension: ground or test configuration, flight configura
39、tion. 6.5.5.3 Pyrotechnic bolts The following characteristics shall be specified: number; location; diameter; length; mass (of separated hardware); pre-load. 6.5.6 Mating-system installation The orientation of the mating system with respect to the adapter frame shall be defined. 6.6 Connectors and m
40、icroswitches The connector interface shall be defined. The following characteristics shall be considered: a) supplier and part number; b) quantity; c) location and mechanical interface: angular position, radial position, height from separation plane; d) push-on and push-off loads; e) energy released
41、; f) separation force; g) keying index. 6.7 Purges and fluid-connection interface The SC purge and fluid-connection interface shall be defined. The following characteristics shall be considered: a) location and mechanical interface: angular position, radial position, height from separation plane; BS
42、 ISO 15863:20036 b) push-on and push-off loads; c) energy released; d) separation force. 6.8 Encapsulated SC access 6.8.1 SC-access requirements SC items to be accessed and purpose of access needed shall be listed and referenced to the SC coordinate system. 6.8.2 Access configuration Information tha
43、t shows the location and configuration of the required SC physical access openings in the payload compartment shall be provided, including the following indications: payload compartment relevant dimensions; location of centre of door (s) referenced to the LV axes; dimensions of door(s). 7 Electrical
44、 interface 7.1 Umbilical wiring diagram Detailed drawings of the SC-to-LV and SC-to-ground facilities wiring diagram shall be provided. 7.2 Umbilical connectors Organizations responsible for providing connector elements shall be identified. Umbilical connectors shall be described for both the LV and
45、 the SC sides. The distinction shall be made between SC servicing and SC pyrotechnic functions that are maintained on separate LV-SC connectors. Example figures of connectors shall be included. Connector characteristics shall be defined as follows: supplier; part number; number of pins available to
46、user; polarizing key orientation; insert clocking; location (see also 6.6); backshell shielding requirement; harness shielding requirement. BS ISO 15863:200377.3 Umbilical wiring links Umbilical links between the SC and the LV and between the SC and the electrical checkout equipment plugs shall be d
47、escribed with the following characteristic, for each connector and each connector pin: pin number; function(s); wire type; twisting and shielding; maximum voltage (in volts); maximum current (in amperes); end-to-end resistance (in ohms); line start; line end; maximum voltage at separation (if applic
48、able); maximum current at separation (if applicable); signal type; signal frequency. The LV contractor shall define and conduct verification tests of the end-to-end, line-to-ground and line-to-line isolation resistance. 7.4 Electrical commands dedicated to spacecraft 7.4.1 Pyrotechnic commands The S
49、C contractor shall provide a schematic of the SC electrical circuits related to pyrotechnic commands. Pyrotechnic commands shall be described with the following characteristics: command identification; number of redundant commands; time of command initiation; minimum time interval between commands (in milliseconds); pulse width (in milliseconds); voltage (in volts); minimum all-fire current (i
