Space Systems — Mechanism design and verification

This document establishes requirements for the design, material selection and characterization, fabrication, testing and inspection of all space mechanisms on spacecraft and payloads to meet the mission performance requirements. This document does not cover the requirements for mechanisms on expendable and reusable launch vehicles. Applicability of the requirements contained in this document to launch vehicle mechanisms is a decision left to the individual launch vehicle project. This document applies specifically to all moving mechanisms used in spacecraft during all phases of the mission, with the exception of engines and thermal protection systems.

Systèmes spacieux — Conception et vérification des mécanismes

General Information

Status
Published
Publication Date
19-Apr-2022
Current Stage
6060 - International Standard published
Start Date
20-Apr-2022
Due Date
24-Jan-2022
Completion Date
20-Apr-2022
Ref Project
Standard
ISO 23835:2022 - Space Systems — Mechanism design and verification Released:4/20/2022
English language
32 pages
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Standards Content (Sample)


INTERNATIONAL ISO
STANDARD 23835
First edition
2022-04
Space Systems — Mechanism design
and verification
Systèmes spacieux — Conception et vérification des mécanismes
Reference number
© ISO 2022
All rights reserved. Unless otherwise specified, or required in the context of its implementation, 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 below
or ISO’s member body in the country of the requester.
ISO copyright office
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Phone: +41 22 749 01 11
Email: copyright@iso.org
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Published in Switzerland
ii
Contents Page
Foreword .v
Introduction . vi
1 Scope . 1
2 Normative references . 1
3 Terms and definitions . 1
4 Fundamental requirements . 4
4.1 System performance . 4
4.2 Mission . 4
4.3 Function . 4
5 Design requirements .4
5.1 Interfaces . 4
5.2 Environmental design . 5
5.2.1 General . 5
5.2.2 Ground environment . 5
5.2.3 Launch vehicle flight environment . 5
5.2.4 Orbital environment. 5
5.3 Parts and materials . 5
5.3.1 General . 5
5.3.2 Requirements for parts . 6
5.3.3 Requirements for materials . 6
5.4 Mechanism design . 6
5.4.1 Accuracy control design . 6
5.4.2 Driving capability design . 7
5.4.3 Design life . 7
5.4.4 Tribology . 7
5.4.5 Major mechanical components . 8
5.4.6 Other requirements . 8
5.5 Structural design . 9
5.5.1 General requirements related to structural design . 9
5.5.2 Allowable mechanical properties of structural materials . 9
5.5.3 Margin of safety . 9
5.5.4 Stiffness design . 9
5.6 Thermal design . 9
5.7 Electrical design . 9
5.7.1 Electrical design . 9
5.7.2 Electrical wires . . 10
5.7.3 Electric connectors . 10
5.7.4 Insulation . 10
5.7.5 Grounding . 10
5.7.6 Deformation of wiring . 10
5.8 General requirements . 10
5.8.1 Safety . 10
5.8.2 Dependability . 10
5.8.3 Quality assurance . 11
5.8.4 Configuration . 11
5.8.5 Redundancy . 11
5.8.6 Operability . 11
5.8.7 Maintainability . 11
5.8.8 Interchangeability . 11
5.8.9 Fool-proof design . 11
5.8.10 Other requirements .12
6 Verification .12
iii
6.1 General .12
6.2 Verification by analysis . 12
6.2.1 General .12
6.2.2 Identification of worst-case conditions . .13
6.2.3 Thermal analysis . 13
6.2.4 Structural analysis .13
6.2.5 Function and performance analysis . 13
6.2.6 Analysis of torque/force margin . 14
6.2.7 Shock generation and susceptibility . 14
6.2.8 Generated disturbance . 14
6.2.9 Lubrication analysis . 14
6.2.10 Life analysis . 14
6.2.11 Magnetic or electromagnetic analysis . 14
6.2.12 Radiation analysis . 14
6.2.13 Electrical parts stress analysis . 14
6.3 Verification by test . 15
6.3.1 General .15
6.3.2 Development tests .15
6.3.3 Qualification tests . 15
6.3.4 Acceptance tests . 16
6.3.5 Life test . 17
Annex A (informative
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