iTeh StandardsiTeh Standards
EURUSD
Your shopping cart is empty.
ISO

ISO/TR 20891:2020

(Main)

Space systems — Space batteries — Guidelines for in-flight health assessment of lithium-ion batteries

Space systems — Space batteries — Guidelines for in-flight health assessment of lithium-ion batteries

This document provides detailed information on the various methods of assessing the health status of lithium-ion space batteries in flight and makes recommendations to battery suppliers, spacecraft manufacturers and operators to ease this assessment.

Systèmes spatiaux - Batteries spatiales - lignes directrices pour l'évaluation en vol de la santé des batteries lithium-ion

General Information

Status
Published
Publication Date
21-Oct-2020
ICS
49.140 - Space systems and operations
Technical Committee
ISO/TC 20/SC 14 - Space systems and operations
Drafting Committee
ISO/TC 20/SC 14/WG 1 - Design engineering and production
Current Stage
9020 - International Standard under periodical review
Start Date
15-Apr-2024
Completion Date
15-Apr-2024
Ref Project

Buy Standard

ISO/TR 20891:2020 - Space systems -- Space batteries -- Guidelines for in-flight health assessment of lithium-ion batteriesISO/TR 20891:2020 - Space systems -- Space batteries -- Guidelines for in-flight health assessment of lithium-ion batteries
PreviousNext
Technical report
ISO/TR 20891:2020 - Space systems -- Space batteries -- Guidelines for in-flight health assessment of lithium-ion batteries
English language
54 pages
sale 15% off
Preview
sale 15% off
Preview

Standards Content (Sample)

TECHNICAL ISO/TR
REPORT 20891
First edition
2020-10
Space systems — Space batteries
— Guidelines for in-flight health
assessment of lithium-ion batteries
Systèmes spatiaux - Batteries spatiales - lignes directrices pour
l'évaluation en vol de la santé des batteries lithium-ion
Reference number
ISO/TR 20891:2020(E)
©
ISO 2020

---------------------- Page: 1 ----------------------
ISO/TR 20891:2020(E)

COPYRIGHT PROTECTED DOCUMENT
© ISO 2020
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
CP 401 • Ch. de Blandonnet 8
CH-1214 Vernier, Geneva
Phone: +41 22 749 01 11
Email: copyright@iso.org
Website: www.iso.org
Published in Switzerland
ii © ISO 2020 – All rights reserved

---------------------- Page: 2 ----------------------
ISO/TR 20891:2020(E)

Contents Page
Foreword .iv
Introduction .v
1 Scope . 1
2 Normative references . 1
3 Terms, definitions and abbreviated terms . 1
3.1 Term and definitions . 1
3.2 Abbreviated terms . 1
4 Overview . 2
4.1 General . 2
4.2 Battery capacity . 4
4.3 Battery impedance . . 4
4.3.1 General. 4
4.3.2 Electrochemical impedance spectroscopy (EIS) . 5
4.4 Battery internal resistance . 8
5 Specificities of spacecraft telemetry and resulting limitations .11
5.1 General .11
5.2 Signal digitization .11
5.3 Temperature .12
5.4 Voltage .
...

Questions, Comments and Discussion

Ask us and Technical Secretary will try to provide an answer. You can facilitate discussion about the standard in here.

This May Also Interest You

ISO
ISO 14953:2024(Main)
Space systems — Structural design — Determination of loading levels for static qualification testing of launch vehicles

This document specifies a procedure for determining the loading level of a qualification test of a launch vehicle structure and takes into account all the minimum allowable strength characteristics necessary for these structures.

  • Standard
    6 pages
    English language
    sale 15% off
ISO
ISO 17520:2024(Main)
Space environment (natural and artificial) — Cosmic ray and solar energetic particle penetration inward the magnetosphere — Method of determination of the effective vertical cut-off rigidity

This document describes the effective vertical cut-off rigidities of charged particles for near-Earth space and establishes principal requirements for their calculation based on different models of Earth’s geomagnetic field.[1] The techniques are useful for determination of penetrating into the Earth's magnetosphere by charged particle fluxes, as well as for test and estimations of the impact on spacecrafts and other equipment in the near-Earth space.

  • Standard
    14 pages
    English language
    sale 15% off
ISO
ISO 16454:2024(Main)
Space systems — Structural design — Stress analysis requirements

This document provides requirements for the determination of maximum stress and corresponding margin of safety under loading and defines criteria for static strength failure modes, such as rupture, collapse and detrimental yielding. This document does not cover critical-conditions-induced fatigue, creep and crack growths. Notwithstanding these limitations in scope, the results of stress calculations based on the requirements of this document are applicable to other critical condition analysis. This document is applicable to the determination of the stress/strain distribution and margins of safety in launch vehicles and spacecraft load-bearing elements design. Liquid propellant engine structures, solid propellant engine nozzles and the solid propellant itself are not covered, but liquid propellant tanks, pressure vessels and solid propellant cases are within the scope of this document. In accordance with the requirements of this document, the models, methods and procedures for stress calculation can also be applicable to the displacements and deformation calculation, as well as the calculation of loads, applied to substructures and structural elements under consideration. When this document is applied, it is assumed that temperature distribution has been determined and is used as input data.

  • Standard
    14 pages
    English language
    sale 15% off
ISO
ISO 27852:2024(Main)
Space systems — Estimation of orbit lifetime

This document describes a process for the long-duration orbit lifetime prediction of orbit lifetime for spacecraft, launch vehicles, upper stages and associated debris in LEO-crossing orbits after mission phase (including any mission lifetime extensions). The document also clarifies: a) modelling approaches and resources for solar and geomagnetic activity modelling; b) resources for atmosphere model selection; c) approaches for spacecraft ballistic coefficient estimation.

  • Standard
    48 pages
    English language
    sale 15% off
ISO
ISO 17546:2024(Main)
Space systems — Lithium ion battery for space vehicles — Design and verification requirements

This document specifies design and minimum verification requirements for lithium-ion batteries from the perspectives of performance, safety and logistics. This document is applicable to battery assemblies for space vehicles and component cells of batteries, which are critical devices to be harmonized with standards and regulations for other industries. In addition, this document is applicable to component cells which are not designed for space vehicles but can be used in space.

  • Standard
    55 pages
    English language
    sale 15% off
ISO
ISO 26900:2024(Main)
Space data and information transfer systems — Orbit data messages

This document specifies four standard message formats for use in transferring spacecraft orbit information between space agencies and commercial or governmental spacecraft operators: The Orbit Parameter Message (OPM), the Orbit Mean-Elements Message (OMM), the Orbit Ephemeris Message (OEM), and the Orbit Comprehensive Message (OCM). Such exchanges are used for: a) pre-flight planning for tracking or navigation support; b) scheduling tracking support; c) carrying out tracking operations (sometimes called metric predicts); d) performing orbit comparisons; e) carrying out navigation operations such as orbit propagation and orbit reconstruction; f) assessing mutual physical and electromagnetic interference among satellites orbiting the same celestial body (primarily Earth, Moon, and Mars at present); g) performing orbit conjunction (collision avoidance) studies; and h) developing and executing collaborative maneuvers to mitigate interference or enhance mutual operations. This document includes sets of requirements and criteria that the message formats have been designed to meet. For exchanges in which these requirements do not capture the needs of the participating agencies and satellite operators, another mechanism may be selected. This document is an international standard published under the auspices of CCSDS and International Standards Organization (ISO) Technical Committee 20, Subcommittee 13, developed jointly and in concert with the ISO TC20/SC14. As such, this CCSDS standard is also properly labeled as ISO 26900. The recommended Orbit Data Message format is ASCII (reference REF R_ISO_IEC_8859_1_1998 \h [4] 08D0C9EA79F9BACE118C8200AA004BA90B02000000080000001600000052005F00490053004F005F004900450043005F0038003800350039005F0031005F0031003900390038000000 ). This document describes both ‘Keyword = Value Notation’ (KVN) as well as Extensible Markup Language (XML) (reference REF R_505x0b3XMLSpecificationforNavigationDa \h[5] 08D0C9EA79F9BACE118C8200AA004BA90B02000000080000002800000052005F00350030003500780030006200330058004D004C00530070006500630069006600690063006100740069006F006E0066006F0072004E0061007600690067006100740069006F006E0044000000 ) formatted messages. Selection of KVN or XML format should be mutually agreed between message exchange partners. NOTE – As currently specified, an OPM, OMM, or OEM file is to represent orbit data for a single spacecraft, and the OCM is to represent orbit data for either a single spacecraft or single parent spacecraft of a parent/child spacecraft deployment scenario. It is possible that the architecture may support multiple spacecraft per file; this could be considered in the future.

  • Standard
    225 pages
    English language
    sale 15% off
ISO
ISO/TS 6434:2024(Main)
Space systems — Design, testing and operation of a large constellation of spacecraft

This document provides requirements that are either unique or particularly relevant to large constellations of spacecraft operating in the LEO protected region throughout their life cycle, including planning, designing, testing, operating and disposal activities. The requirements in this document are applicable to large constellation owners. While some are directly applicable to the constellation owners, others are allocated to the manufactures or operators under the responsibility of the constellation owners.

  • Technical specification
    10 pages
    English language
    sale 15% off
ISO
ISO 16192:2024(Main)
Space systems — Lessons learned — Principles and guidelines

This document specifies lessons learned principles and guidelines that are applicable in all space project activities (management, technical, quality, cost and schedule). The application of this document is intended to be included in the supplier quality management system, but can be tailored in individual contracts as agreed by the customer and supplier, depending on: — the content of each project (size, technological level and novelty, particular organization, participants, etc.); — the interest and usefulness of the related information. The lessons learned information can result from any situation which can be encountered in similar contexts for future projects, i.e.: — undesirable experiences to be avoided; — strategies, rules, principles of design, validation, tests and operations proved to be successful or necessary. This document neither endorses nor recommends the transmission of company proprietary information to external entities as part of a lessons learned process. Implementing a formal lessons learned process as outlined in this document makes it possible to capture and benefit from this information. The lessons learned activity is an important contribution to the processing of the preventive and corrective actions specified in ISO 9001, ISO 17666, ISO 14620-1 and ISO 23460. This document also provides lessons learned processes and suggested lessons learned forms.

  • Standard
    13 pages
    English language
    sale 15% off
ISO
ISO 14300-1:2023(Main)
Space systems — Programme management — Part 1: Structuring of a project

This document specifies the space programme/project management requirements, applicable through a top-down approach in a contractual relationship between customers and suppliers.

  • Standard
    34 pages
    English language
    sale 15% off
ISO
ISO 14300-2:2023(Main)
Space systems — Programme management — Part 2: Product assurance

This document defines the product assurance (PA) policy, objectives, principles, and requirements for the establishment and implementation of PA programmes for space programmes covering mission definition, design, development, production and operations of space products, including disposal. The PA discipline covers: PA management, quality assurance, safety assurance, dependability (reliability, availability and maintainability), assurance of software and hardware products, as well as parts (including electrical, electromechanical and electronic components, and mechanical parts), materials and processes assurance. This document defines their respective objectives, policies, and principles to achieve the stated overall PA objectives throughout the complete life cycle of the products. This document applies to space products.

  • Standard
    10 pages
    English language
    sale 15% off