ISO 10786:2011
(Main)Space systems — Structural components and assemblies
Space systems — Structural components and assemblies
ISO 10786:2011 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. When implemented for a particular space system, it will assure high confidence in achieving safe and reliable operation in all phases of its planned mission. ISO 10786:2011 applies specifically to all structural items, including fracture-critical hardware used in space systems during all phases of the mission, with the following exceptions: adaptive structures, engines and thermal protection systems.
Systèmes spatiaux — Composants et assemblages de structure
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Standards Content (Sample)
INTERNATIONAL ISO
STANDARD 10786
First edition
2011-07-15
Space systems — Structural components
and assemblies
Systèmes spatiaux — Composants et assemblages de structure
Reference number
©
ISO 2011
© ISO 2011
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ii © ISO 2011 – All rights reserved
Contents Page
Foreword .iv
Introduction.v
1 Scope.1
2 Normative references.1
3 Terms and definitions .2
4 Symbols and abbreviated terms .11
5 Tailoring.13
6 Requirements.13
6.1 General .13
6.2 Design requirements.13
6.3 Material requirements .18
6.4 Manufacturing and interfaces requirements .21
6.5 Quality assurance.23
6.6 Traceability.25
6.7 Deliverables .25
6.8 In-service requirements.26
6.9 Maintenance requirements.26
6.10 Repair and refurbishment.28
7 Verification of general requirements.28
7.1 General .28
7.2 Verification of design requirements .29
7.3 Acceptance tests .39
7.4 Qualification progamme (qualification tests) .40
8 Special structural items.42
8.1 General .42
8.2 Special structural items with published standards .42
8.3 Special structural items without published standards.42
9 Documentation requirements.43
9.1 Interface control documents .43
9.2 Applicable (contractual) documents .44
9.3 Analysis reports .44
10 Data exchange .46
10.1 Data set requirements.46
10.2 System configuration data .46
10.3 Data exchange between design and structural analysis.46
10.4 Data exchange between structural design and manufacturing.46
10.5 Data exchange with other subsystems.47
10.6 Tests and structural analysis.47
10.7 Structural mathematical models.47
Annex A (informative) Recommended best practices for structural design .48
Annex B (informative) Design requirements verification methods.58
Annex C (informative) Design requirements verification methods.61
Annex D (informative) Margin of safety for combined loads.64
Bibliography.65
Foreword
ISO (the International Organization for Standardization) is a worldwide federation of national standards 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 organizations, 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.
International Standards are drafted in accordance with the rules given in the ISO/IEC Directives, Part 2.
The main task of technical committees is to prepare International Standards. Draft International Standards
adopted by the technical committees are circulated to the member bodies for voting. Publication as an
International Standard requires approval by at least 75 % of the member bodies casting a vote.
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.
ISO 10786 was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcommittee
SC 14, Space systems and operations.
iv © ISO 2011 – All rights reserved
Introduction
Structures are the backbones of all spaceflight systems. A structural failure could cause the loss of human
lives for manned space systems or could jeopardize the intended mission for unmanned space systems.
Currently, there is no International Standard that covers all the aspects that can be used for spaceflight
structural items such as spacecraft platforms, interstage adaptors, launch vehicle buses and rocket motor
cases.
The purpose of this International Standard is to establish general requirements for structures. 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 will facilitate cooperation and communication among space
progammes.
INTERNATIONAL STANDARD ISO 10786:2011(E)
Space systems — Structural components and assemblies
1 Scope
This International Standard 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 International Standard, when implemented for a particular
space system, will assure high confidence in achieving safe and reliable operation in all phases of its planned
mission.
This International Standard applies specifically to all structural items, including fracture-critical hardware used
in space systems during all phases of the mission, with the following exceptions: adaptive structures, engines
and thermal protection systems.
2 Normative references
The following referenced documents are indispensable for the application 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 14622:2000, Space systems —Structural design — Loads and induced environment
ISO 14623:2003, Space systems — Pressure vessels and pressurized structures — Design and operation
ISO 14953:2000, Space systems — Structural design — Determination of loading levels for static qualification
testing of launch vehicles
ISO 14954:2005, Space systems — Dynamic and static analysis — Exchange of mathematical models
ISO 15864:2004, Space systems — General test methods for space craft, subsystems and units
ISO 16454:2007, Space systems — Structural design — Stress analysis requirements
ISO 21347:2005, Space systems — Fracture and damage control
ISO 21648:2008, Space systems – Flywheel module design and testing
ISO 22010:2007, Space systems — Mass properties control
ISO 24638:2008, Space systems — Pressure components and pressure system integration
ISO 24917:2010, Space systems — General test requirements for launch vehicles
MIL-STD-1540, Revision D Test Requirements for Space Vehicles
3 Terms and definitions
For the purposes of this document, the following terms and definitions apply.
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 of 95 %
[ISO 16454:2007]
3.2
acceptance test
required formal test conducted on flight hardware to ascertain that the materials, manufacturing processes,
and workmanship meet specifications and that the hardware is acceptable for intended usage
[ISO 14623:2003]
3.3
adaptive structures
autonomous structural systems which incorporate 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 structure or a component of a structural assembly without
potential rupture, collapse, or detrimental deformation in a given environment
NOTE 1 “Allowable loads” commonly correspond to the statistically based ultimate strength, buckling strength, and
yield strength, or maximum strain (for ductile materials).
NOTE 2 “Allowable load” is often referred to as just “allowable”.
3.5
assembly
combination of parts, components and units which forms a functional entity
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 of 95 %
[ISO 16454:2007]
3.7
buckling
failure mode in which an infinitesimal increase in the load could lead to sudden collapse or detrimental
deformation of a structure
EXAMPLE Snapping of slender beams, columns, struts and thin-wall shells.
2 © ISO 2011 – All rights reserved
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 induced by quasi-static loads (compression, shear or combined stress) accompanied by
irreversible loss of load-carrying capability
3.10
composite material
combination of materials different in composition or form on a macro scale
NOTE 1 The constituents retain their identities in the composite.
NOTE 2 The constituents can normally be physically identified, and there is an interface between them.
[ISO 16454:2007]
EXAMPLE Composites include
⎯ fibrous (composed of fibres, usually in a matrix),
⎯ laminar (layers
...
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