Tiêu chuẩn iso 15864 2004

Microsoft Word C029313e doc Reference number ISO 15864 2004(E) © ISO 2004 INTERNATIONAL STANDARD ISO 15864 First edition 2004 08 15 Space systems — General test methods for space craft, subsystems and[.]

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Reference numberISO 15864:2004(E)

First edition2004-08-15

Space systems — General test methods for space craft, subsystems and units

Systèmes spatiaux — Méthodes d'essai générales pour véhicules spatiaux, sous-systèmes et équipements

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Foreword iv

Introduction v

1 Scope 1

2 Normative references 1

3 Terms, definitions and abbreviated terms 1

3.1 Terms and definitions 1

3.2 Abbreviated terms 2

4 General requirements 3

4.1 Testing philosophy 3

4.2 Tailoring of requirements 3

4.3 Development tests 3

4.4 Qualification tests 4

4.5 Acceptance tests 4

4.6 Proto-flight tests 4

4.7 Prelaunch validation tests 4

4.8 Retest 4

4.9 Test documentation 5

4.10 Tests facilities and other requirements 7

5 Spacecraft system tests 7

5.1 Test items and sequence 7

5.2 Test levels and duration 7

6 Subsystem/unit tests 7

6.1 Test items and sequence 7

6.2 Test levels and duration 7

7 Test requirements 12

7.1 General 12

7.2 Functional test 12

7.3 Electromagnetic compatibility (EMC) test 13

7.4 Magnetic field test 14

7.5 Antenna pattern test 14

7.6 Optical alignment measurement 15

7.7 Physical property measurement 15

7.8 Dynamic balance 16

7.9 Launcher/spacecraft interface test 17

7.10 Static load test 17

7.11 Acceleration test 18

7.12 Modal survey 19

7.13 Sinusoidal vibration test 20

7.14 Random vibration test 21

7.15 Acoustic test 22

7.16 Shock test 23

7.17 Thermal balance test 23

7.18 Thermal vacuum test 24

7.19 Thermal cycle test 26

7.20 Pressure test 26

7.21 Leakage test 28

7.22 Burn-in and wear-in test 28

7.23 Tracking and control system/spacecraft compatibility test 29

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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 15864 was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcommittee

SC 14, Space systems and operations

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Introduction

Throughout this International Standard, the minimum essential criteria are identified by the use of the key word “shall” Recommended criteria are identified by the use of the key word “should”, and while not mandatory are considered to be of primary importance in providing serviceable, economical and practical designs Deviations from the recommended criteria should occur only after careful consideration, extensive testing and thorough service evaluation have shown alternative methods to be satisfactory

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Space systems — General test methods for space craft,

subsystems and units

1 Scope

This International Standard provides the baseline standard on the subject of testing at the system, subsystem and unit levels for applicable unmanned spacecraft programmes It also provides the requirements for documentation associated with testing activities

The acceptance criteria, specifications or procedures, and other detail test requirements applicable to a particular programme are defined in the applicable technical specifications and statement of work When requirements have to be verified by measuring product performance and function under various simulated environments, the method is referred to as “Test” The requirements of this International Standard may be tailored for each specific space programme application

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 14302, Space systems — Electromagnetic compatibility requirements

ISO 14303, Space systems — Launch-vehicle-to-spacecraft interfaces

ISO 14623, Space systems — Pressure vessels and pressurized structures — Design and operation

3 Terms, definitions and abbreviated terms

3.1 Terms and definitions

For the purposes of this document, the following terms and definitions apply

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3.1.4

maximum and minimum predicted temperatures

highest and lowest temperatures that can be expected to occur during the entire life cycle of the subsystem/unit in all operational modes plus an uncertainty factor

EED electroexplosive devices

EMC electromagnetic compatibility

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LBB leak-before-burst

MEOP maximum expected operating pressure

MMA moving mechanical assembly

Performance requirements contained in the contract documentation are compared to performance achieved during testing and provide the basis for judging the capability of the spacecraft to operate as intended Besides verifying performance, test programmes provide the following items:

a) training for personnel in the operation of the spacecraft;

b) incorporation of corrective actions taken for nonconformances;

c) validation of data processing;

d) opportunity to perform calibrations under simulated space conditions;

e) verification of ground hardware compatibility with the spacecraft for operations

Factors that contribute to the provisions of test specifications include experience with similar spacecraft, subsystem and unit; cost considerations; and reliability requirements This International Standard contains range conditions to which the items under test shall be operated and test conditions that shall be used to demonstrate capability

Where practicable, development tests shall be conducted over a range of operating conditions that exceed design limits to identify marginal design features Development tests may be conducted on mock-ups, breadboards, development models or integration models

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4.4 Qualification tests

Qualification tests demonstrate that items meet design requirements and include proper margin The qualification test level shall exceed the maximum predicted levels by a factor of safety or qualification margin; unless otherwise specified, the qualification test duration shall be longer than maximum environment duration with appropriate qualification margin In addition, qualification tests shall validate methods, procedures, facility conditions and ground support test equipment that will be reused for acceptance

4.5 Acceptance tests

Acceptance tests shall demonstrate that the item is free of workmanship defects and integration errors and that its function and performance to the extent practicable can meet stipulated mission requirements Acceptance tests detect latent material or workmanship defects introduced during the manufacturing and assembly process by measuring function and performance parameters Such parameters shall be measured through sequential tests to identify function and performance degradation that is likely to damage mission purposes and to establish a baseline to ensure that no degradation is found in the data history

4.6 Proto-flight tests

It shall be recognized that the proto-flight approach presents a higher risk than the approach in which design margins are demonstrated by the testing of a dedicated nonflight qualification item Moreover, programmatic realities of limited production, tight schedules, and budgetary limits do not always allow the use of dedicated nonflight qualification items In response, several strategies have evolved to minimize the risk created by this situation The higher risk of the proto-flight approach is an example In principle, the proto-flight approach may

be applied at each level of decomposition of the space system

Proto-flight tests shall qualify the design and manufacturing methods of hardware for the purpose of acceptance for flight operations Qualification of design and manufacturing methods is accomplished by imposing environmental levels more severe than environments expected during ground and orbital operations Hardware fatigue is prevented by limiting exposure so not to expend a significant portion of the useful life of the hardware These tests also detect latent material and manufacturing defects and provide experience with each test item's performance under conditions similar to the mission environment

4.7 Prelaunch validation tests

Prelaunch validation tests for spacecraft shall be conducted at the launch site, if they are necessary These tests demonstrate that transportation to and handling at the launch site cause no spacecraft parameter changes and verify that spacecraft and launch vehicle interface and compatibility testing with the Tracking and Control System stay within the stipulated limits as part of launch site operations The tests shall exercise spacecraft within practical limits in order to ensure that all mission requirements can be satisfied

4.8 Retest

4.8.1 General

In principle, there are four situations that may require retest

4.8.2 Retest due to design modification after completion of qualification

Whenever hardware design is modified, the hardware involved shall be retested as necessary, and all documentation pertinent to the design modification shall be revised Depending on the type and extent of the implemented modification, the issue of whether to partially or completely repeat the qualification test sequence shall be evaluated The acceptance test sequence shall be either partially or completely repeated to demonstrate that no new problems have been introduced

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4.8.3 Retest due to nonconformance

If nonconformance occurs during testing activities, necessary action shall be taken in accordance with the test procedure, and the causes of nonconformance shall be identified If nonconformance is caused by the test set-up, test software or failures in test equipment, the test being conducted at the time of the failure may be continued after repair is completed, as long as the nonconformance did not overstress the test items If nonconformance caused in the test items is disposed, initial failure analysis and appropriate corrective action shall be completed before retesting If a failure occurs during the environmental test, the test may be continued as long as the nonconformance does not affect continuity of the test

The details of retesting shall be determined in consideration of the nature of each failure If the units must be substantially redesigned, all previous qualification tests shall be repeated After the redesign of the unit is qualified, all acceptance test programmes shall be repeated

4.8.4 Retest after refurbishment

Former qualification hardware is often refurbished to be used as flight hardware (typically when more than one item of the same hardware is needed) or as a flight spare This approach may be dictated by programme costs and schedule constraint A detailed assessment shall be established by the design and quality engineers to determine the necessary refurbishment to make this hardware flight worthy (e.g replacement of items overstressed or potentially overstressed by qualification testing) After refurbishment, the hardware should be subjected to a partial or complete acceptance test, depending on the extent of refurbishment and disintegration

4.8.5 Retest during and after long-term storage

Tests performed during and after long-term storage depend on the failure modes likely to occur during storage

At minimum, these tests are necessary to validate moving mechanical assemblies, check preloads, ensure lubrication, and validate interfaces and required functional operations

a) a brief background of the applicable project and descriptions of the test items;

b) an overall test philosophy, testing approach, and test objective for each item, including any special tailoring or interpretation of design and testing requirements

4.9.3 Test specifications

Test specifications are documents that define test requirements and associated conditions to be implemented

to properly demonstrate an item’s performance For some tests (e.g sinusoidal vibration), test requirements shall be based on test predictions These documents shall be prepared for each major test activity described

in the test plan activity sheets, with the objective to detail test requirements

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Tests shall be conducted using documented test procedures prepared for performing all required tests in

accordance with test objectives in approved test plans and specifications Test objectives, testing criteria, and

pass-fail criteria shall be stated clearly in the test procedures Test procedures shall cover all operations in

enough detail to eliminate doubt as to execution of any step Test objectives and criteria shall be stated clearly

to relate to design or operations specifications Where appropriate, minimum requirements for valid data and

pass-fail criteria shall be provided at the procedure step level based on analysis using an appropriate

mathematical model Traceability shall be provided from the specifications or requirements to the test

procedures Where practicable, the individual procedure step that satisfies the requirement shall be identified

The test procedure for each item shall include, at minimum, descriptions of the following:

a) identification of test items;

b) criteria, objectives, assumptions and constraints;

c) test set-up;

d) initialization parameters;

e) input data;

f) test instrumentation;

g) expected intermediate test results;

h) output data format;

i) expected output data (by supporting analysis and predictions);

j) minimum requirements for valid data to consider the test successful;

k) pass-fail criteria for evaluating results;

l) safety considerations and hazardous conditions;

m) procedural steps required for successful test and verification signature;

n) personnel involved and relevant responsibility

4.9.5 Test data

Pertinent test data shall be maintained in a quantitative form to permit evaluation of performance under the

various specified test conditions; pass or fail statements alone may be insufficient The test data shall also be

compared across major test sequences for trends or evidence of anomalous behaviour To the extent

practicable, all relevant test measurements and environmental conditions imposed on the units shall be

recorded on computer-compatible electronic media, such as disks, magnetic tape or other suitable means to

facilitate automated accumulation and sorting of data for critical test parameters These records are intended

to be an accumulation of trend data and critical test parameters that shall be examined for out-of-tolerance

values and characteristic signatures during transient and mode switching

4.9.6 Test reports

A summary of the test results shall be documented in test reports Test reports shall detail the degree of

success in meeting the test objectives of the approved test plans and specifications, and shall document test

results, deficiencies, problems encountered, and problem resolutions The test reports shall be provided to the

customer and the launch vehicle side to prove compliance with all requirements

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4.9.7 Test log

Formal test conduct shall be documented in a test log The test log shall identify personnel involved and be time-tagged to permit reconstruction of test events such as start time, stop time, anomalies and any periods of interruption

4.10 Tests facilities and other requirements

4.10.1 General

The spacecraft, subsystem, and unit tests shall be performed using facilities that simulate the environmental exposure within the specified test tolerance and measure the required operational performance All test facilities shall have current and valid calibration; controls to avoid over- or under-testing; proven software operational programmes; and controlled temperature, humidity and cleanliness

4.10.2 Test condition tolerances

Test condition tolerances and measuring precision shall be determined on the basis of the performance of test facilities, and others shall be determined by the design standard Test levels and duration for the design standard should be consistent with the launch environment determined by the launch service providers according to ISO 14303 requirements

4.10.3 Instrumentation

The instruments to be used for tests shall be calibrated periodically to remain accurate, and each instrument shall have an expiration date

5 Spacecraft system tests

5.1 Test items and sequence

Test items and their sequence shall be defined in a verification/test plan and established early in the programme or campaign Table 1 shows all possible tests from which the set of qualification tests (QTs), acceptance tests (ATs), and proto-flight tests (PFTs) is selected A minimum test series shall include all items marked as R

5.2 Test levels and duration

Test levels and duration shall be determined on the basis of the environments to which the system will be exposed, and others shall be determined by the design standard The launch environment shall be determined

by the launch service providers

6 Subsystem/unit tests

6.1 Test items and sequence

The test items and their sequence shall be defined in a verification plan and established early in the programme or campaign The set of QTs may include some or all tests described in Table 2 The set of ATs may include some or all tests described in Table 3 The set of PFTs may include some or all tests described in Table 4

6.2 Test levels and duration

Test levels and duration shall be determined on the basis of the environments to which the subsystem/unit shall be exposed during the service life of the system The system supplier shall derive the maximum predicted values (AT levels and duration) for each subsystem/unit test

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Table 1 — Spacecraft QT, AT, and PFT items and sequence

Minimum test series b

Test Reference paragraph Suggested

Tracking and control

a The test sequence suggested may be modified according to the efficiency of the operation, schedule of test facilities and effects to

detect malfunctions However, the following principles may not be changed:

1) Functional tests shall be conducted at the beginning and end of each environmental test, at minimum

2) The leakage test and alignment check shall be conducted at the beginning and end of the environmental tests, at minimum

b R: required; O: optional; —: not required

c Some cases can be replaced by a combination of analysis and/or modal survey

d Either vibration or acoustic test is recommended, whichever is more appropriate, with the other discretionary

e These tests are mainly applied to subsystem and unit level

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Table 2 — Subsystem/unit QT items and sequence

a The test sequence suggested may be modified according to the efficiency of the operation, schedule of test facilities and effects to detect malfunctions However, the following principles may not be changed:

c Either random vibration or acoustic test is recommended, whichever is more appropriate, with the other discretionary

d Usually, antenna pattern test is performed as part of functional test

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Table 3 — Subsystem/units AT items and sequence

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Table 4 — Subsystem/units PFT items and sequence

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7 Test requirements

7.1 General

Test requirements specified in this section shall apply to all levels of test articles, including spacecraft, subsystems and units, as appropriate Test specifications will be different in imposed levels and duration among models (qualification, flight and proto-flight) Since such quantitative requirements are not specified in the subsection identified by test levels and duration, requirements for each model shall be specified by test specifications accepted by procurement and launch vehicle authorities, as appropriate

7.2 Functional test

7.2.1 Purpose of test

The functional test verifies that the electrical and mechanical performance of the test article meet specification requirements

7.2.2 Test facilities and set-up as basic requirements

Electrical tests shall include application of expected voltages, impedance, frequencies, pulses and wave forms

at the electrical interface of the test article, including all redundant circuits

Mechanical tests shall include application of torques, loads, and motion of mechanisms as appropriate These parameters shall be varied throughout their specification range and the sequence of operation expected in flight Test results shall be used to verify the test article performance with respect to specifications

Functional test shall also include electrical continuity, stability, response time, or other special functional tests related to a particular configuration

7.2.3 Test article configuration

Functional tests shall also be performed while the environment is being imposed, if the test article is expected

to be fully operational in that environment (except for solar panels, antennae, propellant, etc during thermal vacuum test) Simulated thruster valves and batteries shall also be adopted to verify overall compatibility

7.2.4 Monitoring during test

A database of critical parameters shall be established for trend analysis Any unusual or unexpected trends shall be evaluated to determine the existence of drift toward out-of-limit value or incipient failure

7.2.5 Test levels and duration

There are no mandatory requirements

7.2.6 Test condition and guidelines

The hardware configuration for system and subsystem/unit functional testing shall consist of all flight hardware and applicable flight software Through the test article environmental tests, sequential functional tests shall confirm that no degradation has occurred Satisfactory electrical performance shall be demonstrated in all applicable operational modes before, during and after specified environmental exposures During the test, the spacecraft electrical and mechanical subsystems/units shall be in various operational modes appropriate for launch and orbital configurations At that time, all subsystems/units shall be powered, if possible Test requirements for functional tests shall be defined not only for those tests performed before and after environmental tests, but also for functional and performance verification of the items under test

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7.3.2 Test facilities and set-up as basic requirements

Test facilities and set-up shall be prepared for far-field environment and radio frequency (RF) environment, which simulate the actual space environment External RF signals shall be shielded Spurious RF reflected signals shall be minimized Discrimination between spurious and intentional emissions shall be performed for EMC test data evaluation Telemetry/telecommand and RF communication signals shall be tested using airlink configuration

7.3.3 Test article configuration

Two configurations shall be tested — the on-orbit configuration, and the pre-launch through plus-count and separation configuration Electroexplosive devices (EEDs) used to initiate spacecraft functions (such as appendages deployment and separation) shall be replaced by inert EEDs except for bridgewires

7.3.4 Monitoring during test

During EMC tests, power ripple and peak transients shall be measured Selected critical parameters shall be monitored

7.3.5 Test levels and duration

The test programme (emission and susceptibility) shall comply with ISO 14302 requirements Supplementary requirements as necessary to achieve EMC compliance are provided by the product provider’s specifications and interface documents (launch manual, etc.)

7.3.6 Test condition and guidelines

The operation of spacecraft and selection of instrumentation shall be suitable for determining the margin against malfunctions and unacceptable or undesired responses resulting from electromagnetic incompatibilities The test shall demonstrate satisfactory electrical and electronic equipment operation in conjunction with the expected electromagnetic radiation and conduction from other subsystems or units, such

as from other spacecraft elements and the launcher The electromagnetic radiation and conduction from the spacecraft shall not disturb the launcher An electrostatic arc discharge susceptibility test shall be conducted if the spacecraft has the possibility of disturbance that may arise from electrostatic discharge on orbit Inert EEDs shall be installed and monitored during all tests EMC between system and subsystem shall be demonstrated functionally with required margins

7.3.7 Tailoring guide

EMC test shall be performed only once in the test flow for each test article

Tiêu đề	Space Systems — General Test Methods For Space Craft, Subsystems And Units
Trường học	International Organization for Standardization
Chuyên ngành	Space Systems
Thể loại	tiêu chuẩn
Năm xuất bản	2004
Thành phố	Geneva

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