1、Space systems Cube satellites (CubeSats)BS ISO 17770:2017BSI Standards PublicationWB11885_BSI_StandardCovs_2013_AW.indd 1 15/05/2013 15:06 ISO 2017Space systems Cube satellites (CubeSats)Systmes spatiaux Satellites cubiques (CubeSats)INTERNATIONAL STANDARDISO17770First edition2017-06Reference number
2、ISO 17770:2017(E)National forewordThis British Standard is the UK implementation of ISO 17770:2017.The UK participation in its preparation was entrusted to Technical Committee ACE/68, Space systems and operations.A list of organizations represented on this committee can be obtained on request to its
3、 secretary.This publication does not purport to include all the necessary provisions of a contract. Users are responsible for its correct application. The British Standards Institution 2017 Published by BSI Standards Limited 2017ISBN 978 0 580 87091 0ICS 49.140Compliance with a British Standard cann
4、ot confer immunity from legal obligations.This British Standard was published under the authority of the Standards Policy and Strategy Committee on 31 July 2017.Amendments/corrigenda issued since publicationDate Text affectedBRITISH STANDARDBS ISO 17770:2017 ISO 2017Space systems Cube satellites (Cu
5、beSats)Systmes spatiaux Satellites cubiques (CubeSats)INTERNATIONAL STANDARDISO17770First edition2017-06Reference numberISO 17770:2017(E)BS ISO 17770:2017ISO 17770:2017(E)ii ISO 2017 All rights reservedCOPYRIGHT PROTECTED DOCUMENT ISO 2017, Published in SwitzerlandAll rights reserved. Unless otherwi
6、se specified, no part of this publication may be reproduced or utilized otherwise in any form or by any means, electronic or mechanical, including photocopying, or posting on the internet or an intranet, without prior written permission. Permission can be requested from either ISO at the address bel
7、ow or ISOs member body in the country of the requester.ISO copyright officeCh. de Blandonnet 8 CP 401CH-1214 Vernier, Geneva, SwitzerlandTel. +41 22 749 01 11Fax +41 22 749 09 47copyrightiso.orgwww.iso.orgBS ISO 17770:2017ISO 17770:2017(E)ii ISO 2017 All rights reservedCOPYRIGHT PROTECTED DOCUMENT I
8、SO 2017, Published in SwitzerlandAll rights reserved. Unless otherwise specified, no part of this publication may be reproduced or utilized otherwise in any form or by any means, electronic or mechanical, including photocopying, or posting on the internet or an intranet, without prior written permis
9、sion. Permission can be requested from either ISO at the address below or ISOs member body in the country of the requester.ISO copyright officeCh. de Blandonnet 8 CP 401CH-1214 Vernier, Geneva, SwitzerlandTel. +41 22 749 01 11Fax +41 22 749 09 47copyrightiso.orgwww.iso.orgISO 17770:2017(E)Foreword i
10、vIntroduction v1 Scope . 12 Normative references 13 Terms and definitions . 14 Abbreviated terms 25 CubeSat requirements 25.1 General requirements . 25.2 CubeSat mechanical requirements: External dimensions . 35.3 CubeSat mechanical requirements: Mass 55.4 CubeSat mechanical requirements: Materials
11、. 55.5 Electrical requirements . 65.6 Operational requirements . 66 Interface to the launch vehicle: The CubeSat Deployer 76.1 Enclosure . 76.2 Interface 76.3 Mass 76.4 Modularity 76.5 Parts attachment . 76.6 Release from the Deployer 77 CubeSat and Deployer assurance/quality verification . 77.1 Gen
12、eral . 77.2 Random vibration . 87.3 Thermal/Vacuum bakeout 87.4 Shock 87.5 Visual inspection . 8Bibliography 9 ISO 2017 All rights reserved iiiContents PageBS ISO 17770:2017ISO 17770:2017(E)ForewordISO (the International Organization for Standardization) is a worldwide federation of national standar
13、ds 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 which a technical committee has been established has the right to be represented on that committee. International organi
14、zations, governmental and non-governmental, 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.The procedures used to develop this document and those intended for its fu
15、rther maintenance are described in the ISO/IEC Directives, Part 1. In particular the different approval criteria needed for the different types of ISO documents should be noted. This document was drafted in accordance with the editorial rules of the ISO/IEC Directives, Part 2 (see www .iso .org/ dir
16、ectives).Attention is drawn to the possibility that some 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. Details of any patent rights identified during the development of the document will be in th
17、e Introduction and/or on the ISO list of patent declarations received (see www .iso .org/ patents).Any trade name used in this document is information given for the convenience of users and does not constitute an endorsement.For an explanation on the voluntary nature of standards, the meaning of ISO
18、 specific terms and expressions related to conformity assessment, as well as information about ISOs adherence to the World Trade Organization (WTO) principles in the Technical Barriers to Trade (TBT) see the following URL: www .iso .org/ iso/ foreword .html.This document was prepared by Technical Co
19、mmittee ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 14, Space systems and operations.iv ISO 2017 All rights reservedBS ISO 17770:2017ISO 17770:2017(E)ForewordISO (the International Organization for Standardization) is a worldwide federation of national standards bodies (ISO member bodies
20、). The work of preparing 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 no
21、n-governmental, 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.The procedures used to develop this document and those intended for its further maintenance are descri
22、bed in the ISO/IEC Directives, Part 1. In particular the different approval criteria needed for the different types of ISO documents should be noted. This document was drafted in accordance with the editorial rules of the ISO/IEC Directives, Part 2 (see www .iso .org/ directives).Attention is drawn
23、to the possibility that some 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. Details of any patent rights identified during the development of the document will be in the Introduction and/or on the
24、 ISO list of patent declarations received (see www .iso .org/ patents).Any trade name used in this document is information given for the convenience of users and does not constitute an endorsement.For an explanation on the voluntary nature of standards, the meaning of ISO specific terms and expressi
25、ons related to conformity assessment, as well as information about ISOs adherence to the World Trade Organization (WTO) principles in the Technical Barriers to Trade (TBT) see the following URL: www .iso .org/ iso/ foreword .html.This document was prepared by Technical Committee ISO/TC 20, Aircraft
26、and space vehicles, Subcommittee SC 14, Space systems and operations.iv ISO 2017 All rights reserved ISO 17770:2017(E)IntroductionRecent years have seen an increase in the number of student satellites developed at universities around the world. To date, most university satellites require several yea
27、rs to develop and significant financial resources, making them prohibitive for small programs. New technological developments in small low-power electronics make smaller, lower-cost satellites feasible.The CubeSat program has developed a picosatellite standard that significantly reduces the cost and
28、 development time of picosatellites with a specific form factor. In addition, CubeSats can serve as platforms for in-space experimentation, as well as a means of space-qualifying future small-satellite hardware.The CubeSat Standard is an evolution of the picosatellites developed for Stanfords OPAL m
29、ission. CubeSats are constrained to a 100 mm cube (not including deployment interface rails) with a mass of one kilogram or less. Led by Stanford Universitys Space Systems Development Lab (SSDL), the CubeSat project is developed jointly by universities and industry worldwide. Within this internation
30、al community CubeSat developments at the California Polytechnic State University (CalPoly) have been twofold: first, develop the standardized launcher-interface/deployer mechanism for CubeSats, and second, demonstrate the feasibility of developing a working CubeSat using low-cost, commercial off-the
31、-shelf components. The project involves a multidisciplinary team of software, aerospace, manufacturing, electrical, and mechanical engineering undergraduate students.In recent years, more sophisticated capabilities have been demonstrated in CubeSats by major space corporations and major space custom
32、ers. CubeSat concepts for inclusion in Mars exploration are in development. Entire companies have been established to solely support the global CubeSat marketplace. ISO 2017 All rights reserved vBS ISO 17770:2017BS ISO 17770:2017Space systems Cube satellites (CubeSats)1 ScopeThis document addresses
33、CubeSats, CubeSat Deployer and related verification of assurance/quality terms and metrics.This document defines a unique class of picosatellite, the CubeSat. CubeSats are ideal as space development projects for universities around the world. In addition to their significant role in educating space
34、scientists and engineers, CubeSats provide a low-cost platform for testing and space qualification of the next generation of small payloads in space. A key component of the project is the development of a standard CubeSat Deployer.This Deployer is capable of releasing a number of CubeSats as seconda
35、ry payloads on a wide range of launchers. The standard Deployer requires all CubeSats to conform to common physical requirements, and share a standard Deployer interface. CubeSat development time and cost can be significantly reduced by the development of standards that are shared by a large number
36、of spacecraft.Normative control of the CubeSat design, qualification and acceptance testing is generally applied from other small satellite specific standards with the exception of CubeSat/Deployer launch environment test.2 Normative referencesThe following documents are referred to in the text in s
37、uch a way that some or all of their content constitutes requirements 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 14620-1, Space systems Safety requirements Part 1:
38、 System safetyISO 24113, Space systems Space debris mitigation requirements3 Terms and definitions3.1CubeSatpicosatellite measuring 100 mm cubic and weighing 1,33 kg or less Note 1 to entry: Variations on the basic form factor are also considered CubeSats.3.2deployerencloses CubeSats within a confin
39、ed volume with a lid at one side that closes the ejection port during the launch phase Note 1 to entry: It is capable of carrying one or multiple standard CubeSats and serves as the interface between the CubeSats and launch vehicle.3.3P-PODPoly Picosatellite Orbital Deployerexample of a CubeSat Depl
40、oyer Note 1 to entry: In recognition of the original design by the California Polytechnic State University Cal Poly.Note 2 to entry: The P-POD is Cal Polys standardized CubeSat deployment system. It is capable of carrying three standard CubeSats.INTERNATIONAL STANDARD ISO 17770:2017(E) ISO 2017 All
41、rights reserved 1BS ISO 17770:2017ISO 17770:2017(E)3.4single CubeSatsingle 100 mm CubeSat Note 1 to entry: Singe CubeSat is also described as “1U”.3.5triple CubeSatcommon three CubeSat configuration, where it is three CubeSats long connected along the longitudinal axis Note 1 to entry: Triple CubeSa
42、t is also described as “3U”.4 Abbreviated termsCVCM Collected Volatile Condensable MassFCC Federal Communication CommissionIARU International Amateur Radio UnionLV Launch VehicleP/N Part NumberP-POD Poly Picosatellite Orbital DeployerRBF Remove Before FlightRF Radio FrequencySTD StandardTML Total Ma
43、ss LossU Used with a number e.g. 1U (see 3.4), 3U (see 3.5) to denote CubeSat units5 CubeSat requirements5.1 General requirements5.1.1 All parts shall remain attached to the CubeSat during the launch phase, ejection, and operation to ensure safety (see ISO 14620-1). No additional space debris shall
44、be created (see ISO 24113).5.1.2 Pyrotechnics shall not be permitted.5.1.3 Propulsion systems shall have at least three inhibits to activation.5.1.4 Total stored chemical energy shall not exceed 100 Watt-hours.5.1.5 CubeSat materials shall satisfy the following out-gassing criterion to prevent conta
45、mination of other spacecraft during integration, testing and launch.NOTE A list of NASA approved out-gassing materials can be found at h t t p:/ outgassing .nasa .gov.5.1.5.1 Total Mass Loss (TML) shall be 1,0 %.2 ISO 2017 All rights reservedBS ISO 17770:2017ISO 17770:2017(E)3.4single CubeSatsingle
46、100 mm CubeSat Note 1 to entry: Singe CubeSat is also described as “1U”.3.5triple CubeSatcommon three CubeSat configuration, where it is three CubeSats long connected along the longitudinal axis Note 1 to entry: Triple CubeSat is also described as “3U”.4 Abbreviated termsCVCM Collected Volatile Cond
47、ensable MassFCC Federal Communication CommissionIARU International Amateur Radio UnionLV Launch VehicleP/N Part NumberP-POD Poly Picosatellite Orbital DeployerRBF Remove Before FlightRF Radio FrequencySTD StandardTML Total Mass LossU Used with a number e.g. 1U (see 3.4), 3U (see 3.5) to denote CubeS
48、at units5 CubeSat requirements5.1 General requirements5.1.1 All parts shall remain attached to the CubeSat during the launch phase, ejection, and operation to ensure safety (see ISO 14620-1). No additional space debris shall be created (see ISO 24113).5.1.2 Pyrotechnics shall not be permitted.5.1.3
49、Propulsion systems shall have at least three inhibits to activation.5.1.4 Total stored chemical energy shall not exceed 100 Watt-hours.5.1.5 CubeSat materials shall satisfy the following out-gassing criterion to prevent contamination of other spacecraft during integration, testing and launch.NOTE A list of NASA approved out-gassing materials can be found at h t t p:/ outgassing .nasa .gov.5.1.5.1 Total Mass Loss (TML) shall be 1,0 %.2 ISO 2017 All rights reserved ISO 17770:2017(E)5.1.5.2 Collected Volatile Condens
