ISO 16126:2024
(Main)Space systems — Survivability of unmanned spacecraft against space debris and meteoroid impacts for the purpose of space debris mitigation
Space systems — Survivability of unmanned spacecraft against space debris and meteoroid impacts for the purpose of space debris mitigation
This document defines requirements and procedures for analysing the risk that an unmanned spacecraft fails as a result of a space debris or meteoroid impact.
Systèmes spatiaux — Titre manque
General Information
Relations
Standards Content (Sample)
International
Standard
ISO 16126
Second edition
Space systems — Survivability of
2024-12
unmanned spacecraft against space
debris and meteoroid impacts
for the purpose of space debris
mitigation
Reference number
© ISO 2024
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ii
Contents Page
Foreword .iv
Introduction .v
1 Scope . 1
2 Normative references . 1
3 Terms and definitions . 1
4 Symbols and abbreviated terms. 2
4.1 Symbols .2
4.2 Abbreviated terms .5
5 Requirements for impact risk analysis . 5
5.1 General .5
5.2 Failure probability thresholds .6
5.3 Failure probability analysis .6
6 Impact risk analysis procedure for case 1 . 6
7 Impact risk analysis procedures for case 2 . 10
7.1 General .10
7.2 Case 2a .10
7.3 Case 2b .14
Annex A (informative) Procedure for an impact risk analysis during phase A . 17
Annex B (informative) Methods and models for analysing the impact risk from small SD/M .18
Annex C (informative) Ballistic limit equations .29
Annex D (informative) Guidance for implementing impact protection on a spacecraft .43
Annex E (informative) Examples of advanced shielding for unmanned spacecraft .50
Annex F (informative) Typical environmental constraints for shield materials .56
Bibliography .57
iii
Foreword
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This document was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcommittee
SC 14, Space systems and operations.
This second edition cancels and replaces the first edition (ISO 16126:2014), which has been technically
revised.
The main changes are as follows:
— the provision of new impact risk analysis requirements and procedures aimed specifically at satisfying
the high-level impact risk requirements defined in the top-level International Standard on space debris
mitigation, ISO 24113;
— the provision of new informative annexes to assist in the implementation of the impact risk analysis
procedures.
Any feedback or questions on this document should be directed to the user’s national standards body. A
complete listing of these bodies can be found at www.iso.org/members.html.
iv
Introduction
The purpose of this document is to help satisfy two of the high-level requirements defined in the top-level
International Standard on space debris mitigation, ISO 24113. Specifically, this document aims to maximise
the survival of critical equipment required to perform post-mission disposal of an unmanned spacecraft,
and to limit the possibility of an impact-induced break-up of the spacecraft. The analysis procedures in this
document are consistent with those defined in References [1] and [2].
In principle, this document can also be used to assess the impact survivability of an unmanned spacecraft in
support of other mission objectives. However, careful adaptation of the document can be necessary if put to
such use.
This document is part of a set of International Standards that collectively aim to reduce the growth of space
debris by ensuring that spacecraft are designed, operated, and disposed of in a manner that prevents them
from generating space debris throughout their orbital lifetime. All of the primary space debris mitigation
requirements are contained in ISO 24113. The remaining International Standards, of which this is one,
provide supporting methods and procedures to enable compliance with the primary requirements.
v
International Standard ISO 16126:2024(en)
Space systems — Survivability of unmanned spacecraft
against space debris and meteoroid impacts for the purpose
of space debris mitigation
1 Scope
This document defines requirements and procedures for analysing the risk that an unmanned spacecraft
fails as a result of a space debris or meteoroid impact.
2 Normative references
The following documents are referred to in the text in such 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 24113, Space systems — Space debris mitigation requirements
3 Terms and definitions
For the purposes of this document, the terms and definitions given in ISO 24113 and the following apply.
ISO and IEC maintain terminology databases for use in standardization at the following addresses:
— IEC Electropedia: available at https:// www .electropedia .org/
— ISO Online browsing platform: available at https:// www .iso .org/ obp
3.1
ballistic limit
threshold of impact-induced failure of a structure
Note 1 to entry: A common failure threshold is the critical size of an impacting particle at which perforation occurs.
However, depending on the characteristics of the item being hit, failure thresholds other than perforation are also
possible.
3.2
catastrophic break-up
event that completely destroys an object and generates space debris
3.3
critical equipment
item(s) on a spacecraft whose failure would prevent the completion of one or more essential functions, such
as post-mission disposal
3.4
high-energy SD/M
space debris or meteoroid object whose impact kinetic energy exceeds the threshold necessary to cause the
catastrophic break-up (3.2) of a spacecraft
Note 1 to entry: The threshold is usually expressed in terms of the kinetic energy of an SD/M impact relative to the
mass of the spacecraft, i.e. an energy-to-mass ratio (EMR). A typical value for the EMR threshold is 40 J/g.
3.5
project lifecycle
phases of a project from mission analysis through to disposal
Note 1 to entry: The phases of a project are summarised in Table 1. A more detailed description can be found in
[3]
ISO 14300-1 .
Table 1 — Summary of the phases of a project
Phase Description
Pre-phase A Mission analysis
Phase A Feasibility
Phase B Definition
Phase C Development
Phase D Production
Phase E Utilization
Phase F Disposal
3.6
small SD/M
space debris or meteoroid object whose size does not exceed one centimetre in its largest dimension
Note 1 to entry: This threshold is defined for two reasons. First, in impact risk analysis models it is difficult to
characterise accurately the penetrative damage inside a spacecraft from an SD/M impactor larger than one centimetre
in size. Second, it is difficult for current shielding technology to protect a spacecraft against an SD/M impactor larger
than one centimetre in size.
4 Symbols and abbreviated terms
4.1 Symbols
A power law term
B power law term
C speed of sound of the material in a target wall (km/s)
D constant value
d critical diameter of an impactor at the threshold of failure of a wall, panel or shield (cm)
c
d diameter of largest fragment in an in-line cloud ejection cone (cm)
LF
d diameter of impacting particle or projectile (cm)
p
G constant value
H Brinell hardness of the material in a target wall
K factor that combines the material properties of a target
K factor that combines the material properties of a CFRP target
CFRP
K factor that distinguishes between different types of impact damage failure
f
K factor that combines the material properties of a target
K factor that combines the material properties of a target
K factor that combines the material properties of a target
K factor that combines the material properties of a target
3D
K factor that combines the material properties of a target
3S
K factor that combines the material properties of a target
k factor that distinguishes between different types of impact damage failure
L adjustable coefficient to separate the ruptured and non-ruptured data points in an RLE
L adjustable coefficient to separate the ruptured and non-ruptured data points in an RLE
L adjustable coefficient to separate the ruptured and non-ruptured da
...
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