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1、 Reference number ISO 14303:2002(E) ISO 2002 INTERNATIONAL STANDARD ISO 14303 First edition 2002-10-15 Space systems Launch-vehicle-to- spacecraft interfaces Systmes spatiaux Interfaces entre le lanceur spatial et le vhicule spatial ISO 14303:2002(E) PDF disclaimer This PDF file may contain embedded
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4、 optimized for printing. Every care has been taken to ensure that the file is suitable for use by ISO member bodies. In the unlikely event that a problem relating to it is found, please inform the Central Secretariat at the address given below. ISO 2002 All rights reserved. Unless otherwise specifie
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6、postale 56 CH-1211 Geneva 20 Tel. + 41 22 749 01 11 Fax + 41 22 749 09 47 E-mail copyrightiso.ch Web www.iso.ch Printed in Switzerland ii ISO 2002 All rights reserved -,-,- ISO 14303:2002(E) ISO 2002 All rights reserved iii Contents Page Foreword iv Introduction. v 1 Scope 1 2 Terms and definitions.
7、 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 limitations. 14 9 Verification analysis and documentation. 16 10 Verification tests . 20 11 Spacecraft launch preparation
8、 operations. 23 Annex A (informative) Usable envelopes . 26 Annex B (informative) Physical interface presentations 31 Annex C (informative) Performance presentations. 34 Annex D (informative) Environment presentations. 40 Annex E (informative) Verification 52 ISO 14303:2002(E) iv ISO 2002 All rights
9、 reserved 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 normally carried out through ISO technical committees. Each member body interested in a subject for
10、 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 the work. ISO collaborates closely with the International Electrotechnical Commission (IEC) on a
11、ll matters of electrotechnical standardization. International Standards are drafted in accordance with the rules given in the ISO/IEC Directives, Part 3. The main task of technical committees is to prepare International Standards. Draft International Standards adopted by the technical committees are
12、 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 some of the elements of this International Standard may be the subject of patent rights. ISO shall
13、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, Subcommittee SC 14, Space systems and operations. Annexes A to E of this International Standard are for information only. -,-,- ISO 14303:2002(
14、E) ISO 2002 All rights reserved v Introduction ISO 14303 together with ISO 15863 and ISO 17401 forms a set of International Standards that describes fully the process for communicating information about launch vehicle (LV) to spacecraft (SC) interfaces. Clauses 4 to 8 of this International Standard
15、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. 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
16、. 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. These sections should therefore only be considered if applicable. The annexes give examples of the typical presentation format of the various interfac
17、e parameters, as appropriate. -,-,- -,-,- INTERNATIONAL STANDARD ISO 14303:2002(E) ISO 2002 All rights reserved 1 Space systems Launch-vehicle-to-spacecraft interfaces 1 Scope This International Standard specifies the interfaces between a launch vehicle (LV) and the spacecraft (SC) being launched, t
18、o provide LV and SC organizations with the necessary format for presenting the required technical data on existing and future interfaces. Its intended purpose is to minimize costs and reduce the risks from errors resulting from miscommunication. It does not limit the ability of LV or SC organization
19、s to specify unique requirements. 2 Terms and definitions For the purposes of this International Standard, the following terms and definitions apply. 2.1 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
20、 system LV system launch vehicle and associated launch services supplied by the launch services contractor or subcontractors or both 2.3 separation plane plane where launch vehicle and spacecraft separation occurs 2.4 mating plane interface between the spacecraft, or the spacecraft-provided payload
21、adapter, and the launch vehicle 2.5 payload adapter PLA structure that mates the spacecraft to the launch vehicle, including the SCLV separation system 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 fair
22、ing or carrying structure ISO 14303:2002(E) 2 ISO 2002 All rights reserved 3 Abbreviated terms The following abbreviations are used in this International Standard. ACS Attitude control system CG Centre of gravity CLA Coupled loads analysis EMC Electromagnetic compatibility EMI Electromagnetic interf
23、erence GSE Ground support equipment GTO Geosynchronous transfer orbit ICD Interface control document IRD Interface requirements document 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
24、 Spacecraft processing facility SPM Solid propellant motor SSO Sun synchronous orbit TBD To be determined TM Telecommand 4 Mechanical 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 clau
25、ses 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 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
26、 4.4 shall be used. During final launch processing and launch ascent, the SC shall be contained in a structure provided by the LV contractor. ISO 14303:2002(E) ISO 2002 All rights reserved 3 4.3 SC characteristics 4.3.1 SC fundamental natural frequency The SCs fundamental natural frequency in the lo
27、ngitudinal and lateral axes shall not be less than a value specified by the LV with the SC cantilevered from the mating 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 characteristic
28、s to be used for the LV providers sloshing analysis. 4.4 Usable volume The SC shall be accommodated in the LVs usable 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 betw
29、een the SC and the LV in a dynamic environment. Protrusions outside this usable volume may be allowed by mutual agreement 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
30、 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) LV and PLA coordinate systems and relative angular orientation. b) Physical configuration (including keyway location): 1) material; 2) coating; 3) roughness; 4) flatness and perpendi
31、cularity; 5) stiffness section area (mm2) applicable length (millimetres) inertia (mm4). c) Clampband: 1) geometry; 2) material; 3) roughness; 4) allowable tension (newtons). d) Other mating systems. -,-,- ISO 14303:2002(E) 4 ISO 2002 All rights reserved 4.5.3 SC-supplied PLA The SCLV mating surface
32、 for SC-provided PLA shall be defined by the following. a) LV and PLA coordinate systems and relative angular 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) flatn
33、ess and perpendicularity; 6) stiffness section area (mm2) applicable length (millimetres) inertia (mm4). 4.5.4 Separation actuators Separation actuators (springs or pushrods) shall be characterized by number, location, nominal stroke (millimetres), reduced stroke (millimetres), maximum force (newton
34、s), and energy per unit (joules). 4.6 Umbilical connectors and microswitches The LV side of the interface 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 duri
35、ng SCLV mating. The SC shall have compatible connector halves. All connectors shall be characterized by supplier, number, location and mechanical interface, push-on load per connector (newtons), push-off load per connector (newtons), -,-,- ISO 14303:2002(E) ISO 2002 All rights reserved 5 energy rele
36、ased by each plug (joules), and keying index. 4.7 Fluid connections Fluid connections shall 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
37、 or the carrying structure to the SC after encapsulation if physical access is required 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 cor
38、responding size shall be defined. 5 Electrical interfaces 5.1 General This clause identifies 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 an
39、d SC sides: type and reference designator of connectors; number of pins available to the user; number of connectors; segregation between SC power and pyro-firing circuits; location; shielding; keying index. -,-,- ISO 14303:2002(E) 6 ISO 2002 All rights reserved 5.3 Umbilical links Umbilical links be
40、tween the SC mated with the LV and the SCs electrical ground support equipment (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 con
41、straints number of functions types of function; d) current at umbilical plug 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 optiona
42、l commands generated by the LV and dedicated to the SC shall be listed with a 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 correspondin
43、g electrical circuits may be included. The following characteristics shall be indicated: time and number of commands; voltage (volts); pulse width (hertz); output insulation (ohms); characteristics of current delivered to pyro-charges (amperes); -,-,- ISO 14303:2002(E) ISO 2002 All rights reserved 7
44、 interval between two commands (seconds); insulation between wires and structure (ohms); protection of SC equipment; utilization constraints (inhibits) on the SC side. 5.4.3 Dry loop command A general description of electrical circuits associated with dry loop commands shall be made. Optionally, a s
45、chematic drawing of the corresponding electrical circuits may be included. The following main electrical characteristics shall be indicated: number of commands available on-ground or in-flight; voltage (volts); resistance (ohms); insulation of the onboard circuit; protection on the SC side; utilizat
46、ion constraints on the SC side maximum voltage and current (volts and amperes). 5.4.4 LV-generated SC electrical commands A general description of the electrical circuits associated with LV-generated SC electrical commands shall be made. Optionally, a schematic drawing of the corresponding electrica
47、l circuits may be included. The following main electrical characteristics shall be indicated: number of commands available on-ground or in-flight; output voltage (volts); protection on the SC side; insulation between circuit and structure; Electromagnetic compatibility (EMC) compliance with internat
48、ional specifications; utilization constraints on the SC side. 5.5 Separation status transmission The separation status shall be indicated through the LV telemetry (TM) system modes of transmission available for separation status transmission as determined by microswitch or microswitches, break wires, dry loop, and others. -,