SIST EN 16603-32:2014

Space engineering - Structural general requirements

ECSS-E-ST-32C (Space engineering – Structural) defines the mechanical engineering requirements for structural engineering.
This Standard specifies the requirements to be considered in all engineering aspects of structures: requirement definition and specification, design, development, verification, production, in­service and eventual disposal.
The Standard applies to all general structural subsystem aspects of space products including: launch vehicles, transfer vehicles, re­entry vehicles, spacecraft, landing probes and rovers, sounding rockets, payloads and instruments, and structural parts of all subsystems.
This Standard may be tailored for the specific characteristics and constraints of a space project in conformance with ECSS S ST-00.

Raumfahrttechnik - Strukturen, allgemeine Anforderungen

Ingénierie spatiale - Structure, exigences générales

Vesoljska tehnika - Konstrukcija, splošne zahteve

Standard ECSS-E-ST-32C (Vesoljska tehnika - Konstrukcija) določa mehanske zahteve za statiko. Ta standard določa zahteve, ki jih je treba upoštevati pri vseh inženirskih vidikih konstrukcij: definicija zahteve in specifikacija, oblikovanje, razvoj, preverjanje ustreznosti, proizvodnja, uporaba in morebitna odstranitev. Standard se uporablja za vse splošne vidike strukturnih podsistemov vesoljskih proizvodov, vključno z: napravami za izstrelitev, transportnimi vozili, povratnimi vozili, vesoljskimi plovili, pristajalnimi sondami in vozili rover, raziskovalnimi raketami, tovori in instrumenti ter strukturnimi deli vseh podsistemov. Ta standard se lahko prilagodi posameznim lastnostim in omejitvam vesoljskega projekta v skladu s standardom ECSS-S-ST-00.

General Information

• Status: Published
• Publication Date: 22-Oct-2014
• ICS: 49.140 - Space systems and operations
• Technical Committee: I13 - Imaginarni 13
• Current Stage: 6060 - National Implementation/Publication (Adopted Project)
• Start Date: 05-Sep-2014
• Due Date: 10-Nov-2014
• Completion Date: 23-Oct-2014
• Mandate: M/496 - Mandate addressed to CEN, CENELEC and ETSI to develop standardisation regarding space industry (Phase 3 of the process)
• Ref Project: EN 16603-32:2014 - Space engineering - Structural general requirements

Relations

• Replaces: SIST EN 14607-2:2005 - Space engineering - Mechanical - Part 2: Structural
• Effective Date: 01-Nov-2014

Standards Content (Sample)

SLOVENSKI STANDARD
01-november-2014
1DGRPHãþD
SIST EN 14607-2:2005
Vesoljska tehnika - Konstrukcija, splošne zahteve
Space engineering - Structural general requirements
Raumfahrttechnik - Strukturen, allgemeine Anforderungen
Ingénierie spatiale - Structure, exigences générales
Ta slovenski standard je istoveten z: EN 16603-32:2014
ICS:
49.140 Vesoljski sistemi in operacije Space systems and
operations
2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.

EUROPEAN STANDARD
EN 16603-32
NORME EUROPÉENNE
EUROPÄISCHE NORM
August 2014
ICS 49.140 Supersedes EN 14607-2:2004
English version
Space engineering - Structural general requirements
Ingénierie spatiale - Structure, exigences générales Raumfahrttechnik - Strukturen, allgemeine Anforderungen
This European Standard was approved by CEN on 1 March 2014.

CEN and CENELEC members are bound to comply with the CEN/CENELEC Internal Regulations which stipulate the conditions for giving
this European Standard the status of a national standard without any alteration. Up-to-date lists and bibliographical references concerning
such national standards may be obtained on application to the CEN-CENELEC Management Centre or to any CEN and CENELEC
member.
This European Standard exists in three official versions (English, French, German). A version in any other language made by translation
under the responsibility of a CEN and CENELEC member into its own language and notified to the CEN-CENELEC Management Centre
has the same status as the official versions.

CEN and CENELEC members are the national standards bodies and national electrotechnical committees of Austria, Belgium, Bulgaria,
Croatia, Cyprus, Czech Republic, Denmark, Estonia, Finland, Former Yugoslav Republic of Macedonia, France, Germany, Greece,
Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania, Slovakia,
Slovenia, Spain, Sweden, Switzerland, Turkey and United Kingdom.

CEN-CENELEC Management Centre:
Avenue Marnix 17, B-1000 Brussels
© 2014 CEN/CENELEC All rights of exploitation in any form and by any means reserved Ref. No. EN 16603-32:2014 E
worldwide for CEN national Members and for CENELEC
Members.
Table of contents
Foreword . 9
1 Scope . 10
2 Normative references . 11
3 Terms, definitions and abbreviated terms . 12
3.1 Terms from other standards . 12
3.2 Terms specific to the present standard . 12
3.3 Abbreviated terms. 18
4 Requirements . 20
4.1 Overview . 20
4.2 Mission . 20
4.2.1 Lifetime . 20
4.2.2 Natural and induced environment . 21
4.2.3 Mechanical environment . 21
4.2.4 Microgravity, audible noise and human induced vibration . 22
4.2.5 Load events . 22
4.2.6 Combined loads . 23
4.2.7 Limit loads . 24
4.2.8 Design limit loads . 24
4.3 Functionality . 24
4.3.1 Overview . 24
4.3.2 Strength . 24
4.3.3 Local yielding . 25
4.3.4 Buckling . 25
4.3.5 Stiffness . 25
4.3.6 Dynamic behaviour . 25
4.3.7 Thermal . 25
4.3.8 Damage tolerance . 26
4.3.9 Tolerances and alignments . 26
4.3.10 Electrical conductivity . 26
4.3.11 Lightning protection . 26
4.3.12 Electromagnetic compatibility . 26
4.3.13 Dimensional stability . 27
4.4 Interface . 27
4.5 Design . 28
4.5.1 Inspectability . 28
4.5.2 Interchangeability . 28
4.5.3 Maintainability . 28
4.5.4 Dismountability . 29
4.5.5 Mass and inertia properties . 29
4.5.6 Material selection . 30
4.5.7 Mechanical parts selection . 30
4.5.8 Material design allowables . 30
4.5.9 Metals . 31
4.5.10 Non-metallic materials . 32
4.5.11 Composite materials . 32
4.5.12 Adhesive materials in bonded joints . 33
4.5.13 Ablation and pyrolysis . 33
4.5.14 Micrometeoroid and debris collision . 33
4.5.15 Venting . 33
4.5.16 Margin of safety (MOS) . 34
4.5.17 Factors of safety (FOS) . 34
4.5.18 Scatter factors . 35
4.6 Verification . 35
4.6.1 Overview . 35
4.6.2 Verification by analysis . 36
4.6.3 Verification by test . 41
4.6.4 Verification of composite structures . 46
4.7 Production and manufacturing . 47
4.7.1 General . 47
4.7.2 Manufacturing process . 47
4.7.3 Manufacturing drawings . 47
4.7.4 Tooling . 47
4.7.5 Assembly . 48
4.7.6 Storage . 48
4.7.7 Cleanliness . 49
4.7.8 Health and safety . 49
4.8 In-service . 49
4.8.1 Ground inspection . 49
4.8.2 In-orbit inspection . 49
4.8.3 Evaluation of damage . 50
4.8.4 Maintenance . 50
4.8.5 Repair . 51
4.9 Data exchange . 52
4.9.1 General . 52
4.9.2 System configuration data . 53
4.9.3 Data exchange between design and structural analysis . 53
4.9.4 Data exchange between structural design and manufacturing . 53
4.9.5 Data exchange with other subsystems . 53
4.9.6 Tests and structural analysis . 54
4.9.7 Structural mathematical models . 54
4.9.8 Data traceability . 54
4.10 Deliverables . 54
Annex A (normative) Computer aided design model description and
delivery (CADMDD) - DRD. 56
A.1 DRD identification . 56
A.1.1 Requirement identification and source document . 56
A.1.2 Purpose and objective . 56
A.2 Expected response . 56
A.2.1 Scope and content . 56
A.2.2 Special remarks . 61
Annex B (normative) Design loads (DL) - DRD . 62
B.1 DRD identification . 62
B.1.1 Requirement identification and source document . 62
B.1.2 Purpose and objective . 62
B.2 Expected response . 62
B.2.1 Scope and content . 62
B.2.2 Special remarks . 65
Annex C (normative) Dimensional stability analysis (DSA) - DRD . 66
C.1 DRD identification . 66
C.1.1 Requirement identification and source document . 66
C.1.2 Purpose and objective . 66
C.2 Expected response . 66
C.2.1 Scope and content . 66
C.2.2 Special remarks . 69
Annex D (normative) Fatigue analysis (FA) - DRD . 70
D.1 DRD identification . 70
D.1.1 Requirement identification and source document . 70
D.1.2 Purpose and objective . 70
D.2 Expected response . 70
D.2.1 Scope and content . 70
D.2.2 Special remarks . 72
Annex E (normative) Fracture control analysis (FCA) - DRD . 73
E.1 DRD identification . 73
E.1.1 Requirement identification and source document . 73
E.1.2 Purpose and objective . 73
E.2 Expected response . 73
E.2.1 Scope and content . 73
E.2.2 Special remarks . 76
Annex F (normative) Fracture control plan - DRD . 77
F.1 DRD identification . 77
F.1.1 Requirement identification and source document . 77
F.1.2 Purpose and objective . 77
F.2 Expected response . 77
F.2.1 Scope and content . 77
F.2.2 Special remarks . 79
Annex G (normative) Fracture control items lists (PFCIL, FCIL and FLLIL) -
DRD . 80
G.1 DRD identification . 80
G.1.1 Requirement identification and source document . 80
G.1.2 Purpose and objective . 80
G.2 Expected response . 80
G.2.1 Scope and content . 80
G.2.2 Special remarks . 81
Annex H (normative) Material and mechanical part allowables (MMPA) -
DRD . 82
H.1 DRD identification . 82
H.1.1 Requirement identification and source document . 82
H.1.2 Purpose and objective . 82
H.2 Expected response . 82
H.2.1 Scope and content . 82
H.2.2 Special remarks . 84
Annex I (normative) Mathematical model description and delivery (MMDD) -
DRD . 85
I.1 DRD identification . 85
I.1.1 Requirement identification and source document . 85
I.1.2 Purpose and objective . 85
I.2 Expected response . 85
I.2.1 Scope and content . 85
I.2.2 Special remarks . 92
Annex J (normative) Modal and dynamic response analysis (MDRA) - DRD . 93
J.1 DRD identification . 93
J.1.1 Requirement identification and source document . 93
J.1.2 Purpose and objective . 93
J.2 Expected response . 94
J.2.1 Scope and content . 94
J.2.2 Special remarks . 96
Annex K (normative) Stress and strength analysis (SSA) - DRD . 97
K.1 DRD identification . 97
K.1.1 Requirement identification and source document . 97
K.1.2 Purpose and objective . 97
K.2 Expected response . 97
K.2.1 Scope and content . 97
K.2.2 Special remarks . 103
Annex L (normative) Structure alignment budget (SAB) - DRD . 105
L.1 DRD identification . 105
L.1.1 Requirement identification and source document . 105
L.1.2 Purpose and objective . 105
L.2 Expected response . 105
L.2.1 Scope and content . 105
L.2.2 Special remarks . 108
Annex M (normative) Structure buckling (SB) - DRD . 109
M.1 DRD identification . 109
M.1.1 Requirement identification and source document . 109
M.1.2 Purpose and objective . 109
M.2 Expected response . 109
M.2.1 Scope and content . 109
M.2.2 Special remarks . 111
Annex N (normative) Structure mass summary (SMS) - DRD . 112
N.1 DRD identification . 112
N.1.1 Requirement identification and source document . 112
N.1.2 Purpose and objective . 112
N.2 Expected response . 112
N.2.1 Scope and content . 112
N.2.2 Special remarks . 114
Annex O (normative) Test-analysis correlation (TAC) - DRD . 115
O.1 DRD identification . 115
O.1.1 Requirement identification and source document . 115
O.1.2 Purpose and objective . 115
O.2 Expected response . 115
O.2.1 Scope and content . 115
O.2.2 Special remarks . 117
Annex P (normative) Test evaluation (TE) - DRD . 118
P.1 DRD identification . 118
P.1.1 Requirement identification and source document . 118
P.1.2 Purpose and objective . 118
P.2 Expected response . 118
P.2.1 Scope and content . 118
P.2.2 Special remarks . 121
Annex Q (normative) Test prediction (TP) - DRD . 122
Q.1 DRD identification . 122
Q.1.1 Requirement identification and source document . 122
Q.1.2 Purpose and objective . 122
Q.2 Expected response . 122
Q.2.1 Scope and content . 122
Q.2.2 Special remarks . 125
Annex R (informative) Document description list . 126
R.1 Computer aided design model description and delivery . 126
R.2 Configuration item data list (document controlled by ECSS-M-ST-40) . 126
R.3 Design definition file (document controlled by ECSS-E-ST-10) . 126
R.4 Design development plan (included in the System engineering plan controlled
by ECSS-E-ST-10) . 126
R.5 Design justification file (document controlled by ECSS-E-ST-10) . 126
R.6 Drawings (document controlled by ISO 128) . 127
R.7 Design loads . 127
R.8 Dimensional stability analysis . 127
R.9 Fatigue analysis . 127
R.10 Fracture control analysis . 127
R.11 Fracture control plan . 127
R.12 Fracture control items lists . 127
R.13 Material and mechanical part allowables . 128
R.14 Mathematical model description and delivery . 128
R.15 Modal and dynamic response analysis . 128
R.16 Stress and strength analysis . 128
R.17 Structure alignment budget . 128
R.18 Structure buckling . 128
R.19 Structure mass summary . 128
R.20 Test-analysis correlation . 128
R.21 Test evaluation . 129
R.22 Test prediction . 129
R.23 Test procedure (document controlled by ECSS-E-ST-10-03) . 129
R.24 Test report (document controlled by ECSS-E-ST-10-03) . 129
R.25 Test specification (document controlled by ECSS-E-ST-10-03) . 129
R.26 Verification plan (document controlled by ECSS-E-ST-10-02) . 129
Annex S (informative) Effective mass definition . 130
Annex T (informative) E-32 discipline documents delivery per review . 133
Bibliography . 135

Foreword
This document (EN 16603-32:2014) has been prepared by Technical Committee
CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN.
This standard (EN 16603-32:2014) originates from ECSS-E-ST-32C Rev. 1.
This European Standard shall be given the status of a national standard, either
by publication of an identical text or by endorsement, at the latest by February
2015, and conflicting national standards shall be withdrawn at the latest by
February 2015.
Attention is drawn to the possibility that some of the elements of this document
may be the subject of patent rights. CEN [and/or CENELEC] shall not be held
responsible for identifying any or all such patent rights.
This document supersedes EN 14607-2:2004.
This document has been developed to cover specifically space systems and has
therefore precedence over any EN covering the same scope but with a wider
domain of applicability (e.g. : aerospace).
According to the CEN-CENELEC Internal Regulations, the national standards
organizations of the following countries are bound to implement this European
Standard: Austria, Belgium, Bulgaria, Croatia, Cyprus, Czech Republic,
Denmark, Estonia, Finland, Former Yugoslav Republic of Macedonia, France,
Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania,
Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania,
Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and the United
Kingdom.
Scope
ECSS-E-ST-32C (Space engineering – Structural) defines the mechanical
engineering requirements for structural engineering.
This Standard specifies the requirements to be considered in all engineering
aspects of structures: requirement definition and specification, design,
development, verification, production, in-service and eventual disposal.
The Standard applies to all general structural subsystem aspects of space
products including: launch vehicles, transfer vehicles, re-entry vehicles,
spacecraft, landing probes and rovers, sounding rockets, payloads and
instruments, and structural parts of all subsystems.
This Standard may be tailored for the specific characteristics and constraints of
a space project in conformance with ECSS-S-ST-00.
Normative references
The following normative documents contain provisions which, through
reference in this text, constitute provisions of this ECSS Standard. For dated
references, subsequent amendments to, or revisions of any of these
publications, do not apply. However, parties to agreements based on this ECSS
Standard are encouraged to investigate the possibility of applying the most
recent editions of the normative documents indicated below. For undated
references the latest edition of the publication referred to applies.

EN reference Reference in text Title
EN 16601-00-01 ECSS-S-ST-00-01 ECSS system– Glossary of terms
EN 16603-32-01 ECSS-E-ST-32-01 Space engineering – Fracture control
EN 16603-32-02
ECSS-E-ST-32-02 Space engineering – Structural design and
verification of pressurized hardware
EN 16603-32-10
ECSS-E-ST-32-10 Space engineering – Reliability based mechanical
factors of safety
EN 16602-70-36 ECSS-Q-ST-70-36 Space product assurance – Material selection for
controlling stress-corrosion cracking
EN 16602-70-37 ECSS-Q-ST-70-37 Space product assurance – Determination of the
susceptibility of metals to stress-corrosion cracking

Terms, definitions and abbreviated terms
3.1 Terms from other standards
For the purpose of this Standard, the terms and definitions from
ECSS-S-ST-00-01 apply.
3.2 Terms specific to the present standard
3.2.1 A-basis design allowable (A-value)
mechanical property value above which at least 99 % of the population of
values is expected to fall, with a confidence level of 95 %
3.2.2 B-basis design allowable (B-value)
mechanical property value above which at least 90 % of the population of
values is expected to fall, with a confidence level of 95 %
3.2.3 buckling
not stable equilibrium of a structure under loads applied statically or
dynamically
NOTE Buckling include snapping of slender beams,
buckling of flat plates, buckling of cylindrical
panels, three dimensionally curved shells, rib
crippling, and skin buckling of a sandwich.
3.2.4 composite material
combination of materials different in composition or form on a macro scale
NOTE 1 Composite materials provide improved
characteristics not obtainable by any of the original
components acting alone
NOTE 2 The constituents retain their identities in the
composite.
NOTE 3 Normally the constituents can be physically
identified, and there is an interface between them.
NOTE 4 Composites include
• fibrous (composed of fibres, usually in a
matrix),
• laminar (layers of materials), and
• hybrid (combinations of any of the above).
NOTE 5 Composites material can be metallic, non-metallic
or a combination thereof.
3.2.5 composite structure
structure fully or partially made of composite materials
3.2.6 contributing loads
loads which decrease the margin of safety.
3.2.7 damage tolerance
capability of a structure to resist failure due to the presence of flaws, cracks, or
other damage for a specified period of usage without inspection or repair.
3.2.8 design allowable
statistically based strength capability with respect to a failure mode
NOTE For example in terms of load resistance, stress
resistance, or strain limit with respect to rupture,
collapse, detrimental deformation.
3.2.9 design factor
factor used in the determination of DLL to account for uncertainties
NOTE Design factor accounts for uncertainties related to
loads, models and project programmatic aspects
(i.e. protoflight approach, uncertainty in launcher
environment, maturity of design, growth potential
and other design considerations).
3.2.10 design limit load (DLL)
limit load multiplied by a design factor
NOTE Design factors are defined in ECSS-E-ST-32-10.
3.2.11 design load (DL)
design limit load or design yield load or design ultimate load
3.2.12 design parameters
physical features which influence the design performances
NOTE According to the nature of the design variables,
different design problems can be identified such
as:
• structural sizing for the dimensioning of beams,
shells;
• shape optimization;
• material selection;
• structural topology.
3.2.13 design ultimate load (DUL)
design limit load multiplied by the ultimate safety factor
3.2.14 design ultimate stress
stress caused by the design ultimate load
NOTE With this definition no relation exists with ultimate
strength.
3.2.15 design yield load (DYL)
design limit load multiplied by the yield safety factor
3.2.16 design yield stress
stress caused by the design yield load
NOTE With this definition no relation exists with yield
strength.
3.2.17 detrimental deformation
structural deformation, deflection or displacement that prevents any portion of
the structure or other system from performing its intended function or that
reduces the probability of successful completion of the mission
3.2.18 dynamic load
time varying load with deterministic or stochastic distribution
3.2.19 effective mass
measure of the mass portion associated to the mode shape with respect to a
reference support point
3.2.20 factor of safety (FOS)
factor by which design limit loads are multiplied in order to account for
uncertainties of the verification methods, and uncertainties in manufacturing
process and material properties
NOTE 1 Factor of safety is synonym of safety factor.
NOTE 2 FS and SF are also recognized abbreviations used
for factor of safety
NOTE 3 The factor of safety is a combination of factors
according to various sources of uncertainties. Its
magnitude is based on proven processes and
verification methods for analyses, tests and
manufacturing. To account for uncertainties of
analysis, higher values of factor of safety are
normally used for verification by analysis only.
Higher values of factors of safety are also used if
higher reliability is desired than was taken in the
limit load determination.
3.2.21 failure
rupture, collapse, degradation, excessive wear or any other phenomenon
resulting in an inability to sustain design limit loads, pressures (e.g. MDP) and
environments
3.2.22 fail-safe structure
structure designed with sufficient redundancy to ensure that the failure of one
structural element does not cause failure of the entire structure
NOTE No factor of safety is applied to design limit loads
in the failure analysis.
3.2.23 flaw
local discontinuity in a structural material
NOTE For example: scratch, notch, crack, void or pores in
case of metallic and homogenous non metallic
material; delamination or porosity in case of
composite material.
3.2.24 generalized mass
mass transformed by the mode shapes into the modal space (i.e. modal
coordinates)
3.2.25 limited service life items
hardware item that requires periodic re-inspection or replacement
3.2.26 limit load (LL)
maximum load(s), which a structure is expected to experience with a given
probability, during the performance of specified missions in specified
environments
3.2.27 maximum design pressure (MDP)
pressure equal to MEOP*Km*Kp
NOTE 1 MDP correspond to design limit loads
NOTE 2 MDP is equal or larger than MEOP.
NOTE 3 Km is a factor which takes into account the
representativity of the mathematical models
predicting MEOP and it is defined by  the entity
defining MEOP (for definition of Km see ECSS-E-
ST-32-10 ‘Factors of safety’).
NOTE 4 Kp is the project factor (for definition of Kp see
ECSS-E-ST-32-10 ‘Factors of safety’)
3.2.28 maximum expected operating pressure (MEOP)
highest pressure that a system or component is expected to experience during
its mission life in association with its applicable environment
NOTE 1 For mission life see definition in 3.2.29.
NOTE 2 MEOP corresponds to limit loads.
NOTE 3 MEOP includes effects of temperature and
acceleration on pressure, maximum relief pressure,
maximum regulator pressure and effects of failures
within the system or its components. The effect of
pressure transient is assessed for each component
of the system and used to define its MEOP.
NOTE 4 MEOP includes effects of failures of an external
system (e.g. spacecraft), as specified by the
customer ,on systems (e.g. propulsion ) or
components.
NOTE 5 MEOP does not include testing factors, which are
included in ECSS-E-ST-32-02 ‘Structural design
and verification of pressurized hardware’ and
ECSS-E-ST-10-03 ‘Verification’.
3.2.29 mission life
life cycle from delivery to disposal
3.2.30 primary structure
part of the structure that carries the main flight loads and defines the overall
stiffness
3.2.31 proof load
load applied during a proof test
3.2.32 proof test
test of flight hardware under the proof load or pressure, to give evidence of
satisfactory workmanship and material quality or to establish the initial crack
sizes in the hardware
3.2.33 random load
vibration load whose instantaneous magnitudes are specified only by
probability distribution functions giving the probable fraction of the total time
that the instantaneous magnitude lies within a specified range
NOTE Random load contains no periodic or
quasi-periodic constituents.
3.2.34 relieving loads
loads which increase the margin of safety
3.2.35 residual stress
stress that remains in a structure after processing, fabrication, assembly, testing
or operation
3.2.36 safe life
fracture control design principle, for which the largest undetected defect that
can exist in the part does not grow to failure when subjected to the cyclic and
sustained loads and environments encountered in the service life
3.2.37 safe life structure
structure designed according to the safe life design principle
3.2.38 scatter factor
factor by which the number of cycles or life time is multiplied in fatigue
analysis, fracture analysis, thermal cycling analysis and test in order to account
for uncertainties in the statistical distribution of loads and cycles
3.2.39 service life
interval beginning with the last item inspection or flaw screening proof test
after manufacturing, and ending with completion of its specified life
3.2.40 secondary structure
structure attached to the primary structure with negligible participation in the
main load transfer and overall stiffness
3.2.41 shock load
special type of transient load, where the load shows significant peaks and the
duration of the load is well below the typical response time of the structure
3.2.42 (quasi) static loads
loads independent of time or which vary slowly, so that the dynamic response
of the structure is not significant
3.2.43 stiffness
ratio between an applied force and the resulting displacement or between an
applied moment and the corresponding rotation
3.2.44 structural design
set of information defining the structure, or the process used to generate it
NOTE Structural design is an iterative process. The
process starts with the conceptual design of
possible alternatives which can be considered to
satisfy the general performance requirements and
are likely to meet the main mission constraints (e.g.
mass, interfaces, operation and cost). The various
concepts are then evaluated according to a set of
prioritised criteria in order to select the designs to
develop in further detail. The main purpose of the
evaluation is to identify the main mission
requirements and to establish whether the selected
concepts meet the requirements. The selected
concepts are evolved and evaluated in more detail
against a comprehensive set of mechanical
requirements and interface constraints which are
“flowed down” from the main mission and
functional requirements.
3.2.45 structure
set of mechanical components or assemblies
...