ISO 10786:2025

International
Standard
ISO 10786
Second edition
Space systems — Structural
2025-09
components and assemblies
Systèmes spatiaux — Composants et assemblages de structure
Reference number
© ISO 2025
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ii
Contents Page
Foreword .vi
Introduction .vii
1 Scope . 1
2 Normative references . 1
3 Terms and definitions . 1
4 Symbols and abbreviated terms. 14
5 Tailoring .15
6 Requirements .15
6.1 General . 15
6.2 Design requirements .16
6.2.1 Static strength .16
6.2.2 Buckling strength .16
6.2.3 Margin of safety (MS) .16
6.2.4 Static stiffness .16
6.2.5 Dynamic behaviour .17
6.2.6 Dimensional stability .17
6.2.7 Tolerances and alignments . . .17
6.2.8 Thermal .17
6.2.9 Thermal distortion .17
6.2.10 Interface requirements . . .18
6.2.11 Electromagnetic compatibility .18
6.2.12 Lightning protection .18
6.2.13 Mass and inertia properties .18
6.2.14 Fatigue life .18
6.2.15 Fracture control .18
6.2.16 Impact damage .19
6.2.17 Stress-rupture life .19
6.2.18 Corrosion and stress corrosion control . 20
6.2.19 Outgassing. 20
6.2.20 Meteoroid and orbital debris protection . 20
6.3 Material requirements. 20
6.3.1 Mechanical properties . 20
6.3.2 Metallic materials . 20
6.3.3 Glass and ceramics materials .21
6.3.4 Composite materials . 22
6.3.5 Polymeric materials. 23
6.3.6 Adhesive materials in bonded joints .24
6.4 Manufacturing and interfaces requirements .24
6.4.1 Ensuring quality, reliability and reproducibility of manufacturing process by
production engineering.24
6.4.2 Manufacturing requirements .24
6.4.3 Manufacturing process .24
6.4.4 Integration requirements and procedures . 25
6.5 Quality assurance . 26
6.5.1 General . 26
6.5.2 Inspection . 26
6.5.3 Acceptance proof test . .27
6.6 Traceability .27
6.7 Deliverables .27
6.7.1 Identification of contractual deliverable products .27
6.7.2 Packing, handling, transportation .27
6.7.3 Storage . 28
6.8 In-service requirements . 28

iii
6.8.1 Ground inspection . . 28
6.8.2 In-orbit inspection . 28
6.8.3 Evaluation of damage . 28
6.9 Maintenance requirements . 29
6.9.1 General maintenance requirements . 29
6.9.2 Preventive maintenance . 29
6.9.3 Corrective maintenance . 29
6.10 Repair and refurbishment . 30
7 Verification of general requirements .30
7.1 General . 30
7.2 Verification of design requirements . .31
7.2.1 Introductory remarks for verification of design requirements .31
7.2.2 Verification of static strength .31
7.2.3 Buckling strength verification .32
7.2.4 Margin-of-safety (MS) verification . 33
7.2.5 Stiffness verification . 33
7.2.6 Verification of dynamic behaviour . 33
7.2.7 Dimensional stability verification . 36
7.2.8 Verification of tolerances and alignments and geometric control . 36
7.2.9 Verification of thermal stress . 36
7.2.10 Verification of thermal distortion .37
7.2.11 Verification of interface joints and connections .37
7.2.12 Verification of electromagnetic compatibility (EMC) . 38
7.2.13 Verification of lightning protection . 38
7.2.14 Verification of mass and inertia properties . 38
7.2.15 Verification of fatigue life . 39
7.2.16 Verification of fracture control . 40
7.2.17 Verification of impact damage . 40
7.2.18 Verification of stress-rupture life .41
7.2.19 Verification of corrosion and stress-corrosion cracking control .41
7.2.20 Outgassing verification .41
7.2.21 Verification of meteoroid and orbital debris shielding .41
7.3 Acceptance tests.41
7.3.1 Overview of acceptance tests .41
7.3.2 Non-destructive inspection (NDI) .41
7.3.3 Proof load and/or pressure test .42
7.3.4 Vibration and shock test .42
7.4 Qualification programme (qualification tests) .42
7.4.1 Overview of qualification tests .42
7.4.2 Inspection .43
7.4.3 Proof load and/or pressure tests .43
7.4.4 Vibration and shock tests .43
7.4.5 Qualification load and/or pressure tests .43
8 Special structural items .44
8.1 General . 44
8.2 Special structural items with published standards . 44
8.3 Special structural items without published standards. 44
8.3.1 Overview of the requirements for special structural items . 44
8.3.2 Beryllium structural items .45
8.3.3 Cryo structures and hot structures .45
8.3.4 Sandwich structures .45
9 Documentation requirements .45
9.1 Interface control documents .45
9.2 Applicable (contractual) documents .45
9.3 Analysis reports . 46
9.3.1 General . 46
9.3.2 Stress analysis report . 46

iv
9.3.3 Fatigue or damage tolerance life analysis reports . 46
9.3.4 Fracture/impact damage control plan/report .47
9.3.5 Inspection reports .47
9.3.6 Dynamic analysis .47
10 Data exchange . 47
10.1 Data set requirements .47
10.2 System configuration data . 48
10.3 Data exchange between design and structural analysis . 48
10.4 Data exchange between structural design and manufacturing . 48
10.5 Data exchange with other subsystems . 48
10.6 Tests and structural analysis . 48
10.7 Structural mathematical models. 48
Annex A (informative) Recommended best practices for structural design .50
Annex B (informative) Design requirements verification methods .60
Annex C (informative) Minimum design safety factors .63
Annex D (informative) Margin of safety for combined loads . 67
Bibliography .69

v
Foreword
ISO (the International Organization for Standardization) is a worldwide federation of national standards
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The procedures used to develop this document and those intended for its further maintenance are described
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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 10786:2011), which has been technically
revised.
The main changes are as follows:
— clarification of the Scope;
— updates of the normative references and their citations in the text;
— updates of the terms and definitions to harmonize with the other ISO structural related standards.
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.

vi
Introduction
Structures are the backbones of all spaceflight systems. A structural failure can cause the loss of human
lives for crewed space systems or can jeopardize the intended mission for uncrewed space systems.
The purpose of this document is to establish general requirements for structures in all space flight systems.
It provides the uniform requirements necessary to minimize the duplication of effort and the differences
between approaches taken by the participating nations and their commercial space communities in
developing structures. In addition, the use of agreed-upon standards can facilitate cooperation and
communication among space programmes.
This document, when implemented for a particular space system, ensures high confidence in achieving safe
and reliable operation in all phases of its planned mission.

vii
International Standard ISO 10786:2025(en)
Space systems — Structural components and assemblies
1 Scope
This document establishes requirements for the design, material selection and characterization, fabrication,
testing and inspection of all structural items in space systems, including expendable and reusable launch
vehicles, satellites and their payloads.
This document applies to all structural items, including fracture-critical hardware used in space systems
during all phases of the mission, with the following exceptions: adaptive structures, propulsion systems,
nuclear systems, and thermal protection systems.
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 14623, Space systems - Pressure vessels and pressurized structures — Design and operation
ISO 15864, Space systems — General test methods for spacecraft, subsystems and units
ISO 16126, Space systems — Survivability of unmanned spacecraft against space debris and meteoroid impacts
for the purpose of space debris mitigation
ISO 16454, Space systems — Structural design — Stress analysis requirements
ISO 21347, Space systems — Fracture and damage control
ISO 21648, Space systems — Flywheel module design and testing
ISO 24113, Space systems — Space debris mitigation requirements
ISO 24638, Space systems — Pressure components and pressure system integration
ISO 24917, Space systems — General test requirements for launch vehicles
3 Terms and definitions
For the purposes of this document, the following terms and definitions apply.
ISO and IEC maintain terminology databases for use in standardization at the following addresses:
— ISO Online browsing platform: available at https:// www .iso .org/ obp
— IEC Electropedia: available at https:// www .electropedia .org/

3.1
A-basis allowable
A-basis design allowable
A-value
mechanical strength value above which at least 99 % of the population of values is expected to fall, with a
confidence level (3.13) of 95 %
[SOURCE: ISO 14623:2003, 2.1, modified — The admitted terms "A-basis design allowable" and "A-value"
have been added.]
3.2
acceptance test
required formal test (3.77) conducted on flight hardware to ascertain that the materials (3.39), manufacturing
processes (3.36), and workmanship meet specifications and that the hardware is acceptable for intended usage
[SOURCE: ISO 14623:2003, 2.2, modified — The term and definition have been changed from plural to
singular forms.]
3.3
adaptive structure
autonomous structural system which incorporates sensors, processors, and actuators to enable adaptation
to changing environmental conditions, thereby enhancing safety, stability, vibration damping, acoustic noise
suppression, aerodynamic performance and optimization, pointing accuracy, load redistribution, damage
response, structural integrity, etc.
3.4
allowable load
maximum load that can be accommodated by a material (3.39)/structure (3.75) or a component of a
structural assembly (3.5) without potential rupture, collapse (3.9), or detrimental deformation (3.19) in a
given environment
Note 1 to entry: Commonly, “allowable load” is the load which correspond to the statistically based ultimate strength
(3.80), buckling (3.7) strength, and yield strength (3.86), or strength defined by maximum strain (for ductile materials).
Note 2 to entry: "Allowable stress", or "allowable strain" are similar definition of "allowable load”, which are defined
for potential rupture, collapse, or detrimental deformation, by using other physical properties such as "stress" or
"strain" respectively, instead of "load".
3.5
assembly
combination of parts, components and units that form a functional entity
[SOURCE: ISO 10795:2019, 3.23]
3.6
B-basis allowable
B-basis design allowable
B-value
mechanical strength value above which at least 90 % of the population of values is expected to fall, with a
confidence level (3.13) of 95 %
Note 1 to entry: See also A-basis allowable (3.1).
[SOURCE: ISO 21648:2008, 2.1.4, modified — The admitted terms "B-basis design allowable" and "B-value"
have been added.]
3.7
buckling
failure mode (3.22) in which an infinitesimal increase in the load can lead to sudden collapse (3.9) or
detrimental deformation (3.19) of a structure (3.75)
EXAMPLE Snapping of slender beams, columns, struts and thin-wall shells.

3.8
catastrophic failure
failure which results in the loss of human life, mission or a major ground facility, or long-term detrimental
environmental effects
3.9
collapse
failure mode (3.22) induced by quasi-static loads (3.58) (compression, shear or combined stress) accompanied
by irreversible loss of load-carrying capability
3.10
composite material
combination of materials (3.39) different in composition or form on a macro scale
Note 1 to entry: The constituents retain their identities in the composite.
Note 2 to entry: The constituents can normally be physically identified; and there is an interface between them.
Note 3 to entry: Composites include:
— fibrous (composed of fibres, usually in a matrix),
— laminar (layers of materials), and
— hybrid (combination of fibrous and laminar).
[SOURCE: ISO 16454:2024, 3.6, modified— Note 3 to entry has been added.]
3.11
composite overwrapped pressure vessel
COPV
pressure vessel (3.46) with a fibre-based composite system fully or partially encapsulating a liner
Note 1 to entry: The liner serves as a liquid or gas permeation barrier and may or may not carry substantial pressure
loads. The composite overwraps generally carry pressure and environmental loads.
3.12
composite structure
structural components (3.71) that are made of composite materials (3.10)
3.13
confidence level
value (1 − α) of the probability associated with a confidence interval or a statistical coverage interval
Note 1 to entry: The confidence level, i.e. (1 − α), is often expressed as a percentage.
Note 2 to entry: In some cases, the confidence level is dictated by the needs of the situation. In all other instances, use
of (1 − α) = 0,95 is recommended.
3.14
damage tolerance
ability of a structure (3.75) or a component of a structural assembly (3.5) to resist failure due to the presence
of flaws (3.25) for a specified period of unrepaired usage
[SOURCE: ISO 24638:2021, 3.5, modified — The wording “a material/structure” has been replaced by “a
structure or a component of a structural assembly”.]

3.15
damage tolerance life
safe life
design criterion under which failure due to the presence of flaws (3.25) does not occur in
the expected environment during the service life (3.65)
Note 1 to entry: In this design criterion, a flaw is assumed consistent with the inspection (3.31) process specified and
it is shown that the largest undetected flaw that can exist in the structure (3.75) will not grow to failure in durations
multiplying life factors (3.32) to service lifetimes when subjected to the cyclic and sustained loads in the environments
encountered.
3.16
damage tolerance life
safe life
required period during which a structural item (3.73), even containing the largest undetected
flaw (3.25), is shown by analysis or testing not to fail catastrophically under the expected service load and
environment
3.17
design parameter
physical feature which influences the design performance of the design of structural items (3.73)
Note 1 to entry: According to the nature of the design variables, different design problems can be identified such as:
— structural sizing for the dimensioning of beams, shells, etc.;
— shape optimization;
— material (3.39) selection;
— structural topology.
3.18
design safety factor
safety factor
design factor of safety
factor of safety
multiplying factor to be applied to limit loads (3.33) and/or maximum expected operating pressure (MEOP) (3.41)
Note 1 to entry: The factor is defined in order to account for the statistical variations of loads and structural strength,
and inaccuracies in the knowledge of their statistical distributions.
Note 2 to entry: In this definition, the term, maximum expected operating pressure (MEOP), may be replaced by
maximum design pressure (MDP) (3.40).
[SOURCE: ISO 24638:2021, 3.8, modified — The wording “or maximum design pressure (MDP)“ has been
deleted from the definition; notes 1 and 2 to entry have been added.]
3.19
detrimental deformation
structural deformation, deflection or displacement that prevents any portion of the structure (3.75) or some
other system from performing its intended function or that jeopardizes mission success
[SOURCE: ISO 24638:2021, 3.9]
3.20
development test
test (3.77) to provide information that can be used to check the validity of analytic techniques and assumed
design parameters (3.17), to uncover unexpected system response characteristics, to evaluate design
changes, to determine interface compatibility, to prove qualification (3.56) and acceptance procedures and
techniques, to check manufacturing technology, or to establish accept/reject criteria
[SOURCE: ISO 14623: 2003, 2.20, modified — "may" has been replaced by "can".]

3.21
dynamic load
time-dependent load with deterministic or stochastic variation
3.22
failure mode
manner in which failure occurs
Note 1 to entry: A failure mode may be defined by the function lost or other state transition that occurred.
Note 2 to entry: Structural failure modes include: rupture, collapse (3.9), detrimental deformation (3.19), excessive
wear or any other phenomenon resulting in an inability to sustain loads, pressures and corresponding environments,
or that jeopardizes mission success.
[SOURCE: IEC 60050-192:2015, 192-03-17, modified — Note 2 to entry has been added.]
3.23
fail-safe structure
structural item (3.73) for which it can be shown by analysis or test (3.77) that, as a result of structural
redundancy, the structure (3.75) remaining after the failure of any element of the structural item can sustain
the redistributed limit loads (3.33) with an ultimate design safety factor (3.18) of 1,0
Note 1 to entry: For this entry, it is possible to verify that the structural item can withstand the fatigue induced by cyclic
loads for all the mission life for multi-mission applications, without damage tolerance life (3.16) verification (3.82).
[SOURCE: ISO 21347:2005, 3.10, modified – The term “safety factor” has been replaced by “design safety
factor”; note 1 to entry has been restated.]
3.24
fatigue life
number of cycles of stress or strain of a specified character that a given structure (3.75) or component of
a structural assembly (3.5) can sustain [without the presence of flaw (3.25)] before failure of a specified
nature can occur
3.25
flaw
local discontinuity in a structural material (3.39)
EXAMPLE Crack, cut, scratch, void, delamination disbond, impact damage and other kinds of mechanical damage.
3.26
fracture control
application of design philosophy, analysis methods, manufacturing technology, verification (3.82)
methodology, quality assurance, including non-destructive evaluation (NDE) and operating procedures
to prevent premature structural failure caused by the presence and/or propagation of flaws (3.25) during
fabrication, testing, transportation, handling and service events such as launch, in-orbit operation and return
3.27
fracture-critical item
fracture-critical part
structural part whose failure due to the presence of a flaw (3.25) would result in a catastrophic hazard
3.28
full-scale article
full-size test (3.77) article which represents the whole flight structure (3.75) or a part of the flight structure
with representative loading and boundary conditions

3.29
hydrogen embrittlement
reduction in the ductility or mechanical properties such as strength, toughness of a metal resulting from the
absorption of hydrogen into a metal
Note 1 to entry: Mechanical environmental failure due to the hydrogen embrittlement usually occurs in combination
with residual or applied tensile stresses.
3.30
human vibration
vibration transmitted to and/or induced by the crew members
3.31
inspection
determination of conformity to specified requirements
Note 1 to entry: If the result of an inspection shows conformity, it can be used for purposes of verification (3.82).
Note 2 to entry: The result of an inspection can show conformity or nonconformity or a degree of conformity.
[SOURCE: ISO 9000:2015, 3.11.7]
3.32
life factor
factor by which the service life (3.65) is multiplied to obtain total fatigue life (3.24) or damage tolerance life (3.16)
Note 1 to entry: Life factor is often referred to as a scatter factor (3.63) that is normally used to account for the scatter
of a material’s (3.39) fatigue or crack growth rate data.
Note 2 to entry: It can also account for the dispersion of loading spectra parameters and other uncertainties, when
appropriate.
[SOURCE: ISO 21648:2008, 2.1.24, modified —Note 1 to entry has been separated to note 1 to entry and note
2 to entry.]
3.33
limit load
design limit load
maximum load, or combination of loads, which a structure (3.75) or a component in a structural assembly
(3.5) is expected to experience during its service life (3.65) in association with the applicable operating
environments
Note 1 to entry: Load is a generic term for thermal load, pressure, external mechanical load (force, moment, or enforced
displacement) or internal mechanical load [residual stress (3.61), pretension, or inertial load].
Note 2 to entry: The corresponding stress or strain is called limit stress or limit strain.
[SOURCE: ISO 24638:2021, 3.13, modified— “maximum expected load” has been replaced by “maximum load”.]
3.34
loading case
combined loading case
particular condition of single (or combined) mechanical load, pressure and temperature that can occur for some
structural components (3.71) or a structural assembly (3.5) (at the same time) during their service life (3.65)

3.35
loading spectrum
load spectrum
loads spectrum
representation of the cumulative loading levels and associated cycles anticipated for the structure (3.75)
or component of a structural assembly (3.5) according to its service life (3.65) under all expected operating
environments
Note 1 to entry: Significant transportation, test (3.77), and handling loads are included in this definition.
Note 2 to entry: Also referred as “service life spectrum” or “load history”.
[SOURCE: ISO 24638:2021, 3.15, modified— The admitted terms “load spectrum” and “loads spectrum” have
been added; note 2 to entry has been added.]
3.36
manufacturing process
set of interrelated or interacting activities or operations performed upon material (3.39) to convert it from
the raw material or a semi-finished state to a state of further completion
[SOURCE: ISO 15531-1:2004, 3.6.25, modified — The wording “structured set of activities or operations”
has been replaced by “set of interrelated or interacting activities or operations”; note 1 to entry has been
deleted.]
3.37
margin of safety
MS
parameter to express the margin of structural load carrying capability for the loads derived from multiplying
the design safety factor (3.18) to loading cases (3.34) defined as limit loads (3.33)
Note 1 to entr
...