ISO 4358:2023

Test methods for civil multi-copter unmanned aircraft system

This document specifies test methods for civil electric multi-copter unmanned aircraft systems (UAS). This document is intended to be a general standard for testing the overall UAS functionality with the support of subsystems. It is applicable to the category of civil electric multi-copter UAS with maximum take-off mass (MTOM) level I to level V according to ISO 21895. The configuration control and subsystem (e.g. energy system and flight control system tests) test methods are out of the scope of this document. In addition, test methods for operations in snow and icing conditions are not included either, manufacturers have procedures identified to cope with flight in those conditions.

Méthodes d'essai pour les multicoptères civils télépilotés

General Information

• Status: Published
• Publication Date: 03-May-2023
• ICS: 49.020 - Aircraft and space vehicles in general
• Technical Committee: ISO/TC 20/SC 16 - Unmanned aircraft systems
• Drafting Committee: ISO/TC 20/SC 16/WG 5 - Testing and evaluation
• Current Stage: 6060 - International Standard published
• Start Date: 04-May-2023
• Due Date: 04-Feb-2023
• Completion Date: 04-May-2023

Standards Content (Sample)

INTERNATIONAL ISO
STANDARD 4358
First edition
2023-05
Test methods for civil multi-copter
unmanned aircraft system
Méthodes d'essai pour les multicoptères civils télépilotés
Reference number
ISO 4358:2023(E)
© ISO 2023

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ISO 4358:2023(E)
COPYRIGHT PROTECTED DOCUMENT
© ISO 2023
All rights reserved. Unless otherwise specified, or required in the context of its implementation, no part of this publication may
be reproduced or utilized otherwise in any form or by any means, electronic or mechanical, including photocopying, or posting on
the internet or an intranet, without prior written permission. Permission can be requested from either ISO at the address below
or ISO’s member body in the country of the requester.
ISO copyright office
CP 401 • Ch. de Blandonnet 8
CH-1214 Vernier, Geneva
Phone: [phone]
Email: [e-mail]
Website: www.iso.org
Published in Switzerland
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ISO 4358:2023(E)
Contents Page
Foreword .v
Introduction . vi
1 Scope . 1
2 Normative references . 1
3 Terms and definitions . 1
4 General principles . 1
4.1 Test purpose . 1
4.2 Test conditions and requirements . 2
4.2.1 Technical document . 2
4.2.2 Test article . . 2
4.2.3 Equipment and instruments . 2
4.2.4 Personnel requirements . 2
4.3 Test environmental requirements . 2
4.4 Test interruption and recovery. 2
4.5 Test outline . 3
4.6 Test report . 3
5 Test methods . 3
5.1 Test item . 3
5.2 Basic inspection . 5
5.2.1 Completeness . 5
5.2.2 Appearance . 5
5.2.3 Size . 5
5.2.4 Weight and centre of gravity . 5
5.2.5 Moving and rotating parts check . 5
5.2.6 Connectors . 6
5.3 Functional inspection and testing . 6
5.3.1 Identification . 6
5.3.2 Route loading . 6
5.3.3 Self-test . 6
5.3.4 Information display . 6
5.3.5 Data record . 6
5.3.6 Return to home . 6
5.3.7 Automatic obstacle avoidance . 7
5.3.8 Typical failure protection . 7
5.3.9 Take-off/launch and landing/recovery . 7
5.3.10 Warning . 7
5.3.11 Locking and starting of the motor . 7
5.3.12 Control mode switching . 7
5.4 Flight performance test . 8
5.4.1 Maximum take-off weight . 8
5.4.2 Maximum flight range . 8
5.4.3 Maximum flight altitude . 8
5.4.4 Maximum horizontal flight speed. 9
5.4.5 Maximum steady climb rate . 9
5.4.6 Altitude hold performance . 9
5.4.7 Speed hold performance . 10
5.4.8 Flight endurance . 10
5.4.9 Fixed-point hovering . .12
5.4.10 Positioning navigation .12
5.4.11 Trajectory tracking accuracy .12
5.4.12 Capability of wind resistance . 13
5.5 Navigation system test . 13
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ISO 4358:2023(E)
5.5.1 Static attitude accuracy.13
5.5.2 Static positioning accuracy . 13
5.6 Data link system test .13
5.6.1 Remote control distance and telemetry distance .13
5.6.2 Information transmission distance . 14
5.7 Environmental test . 14
5.7.1 High temperature . 14
5.7.2 Low temperature .15
5.7.3 Rainfall . 16
5.7.4 Humidity and heat. 16
5.7.5 Vibration . 16
5.7.6 Shock . 16
5.8 Electromagnetic compatibility. 16
5.8.1 General principles . 16
5.8.2 Emission test . 17
5.8.3 Immunity . 18
Annex A (informative) Test procedure of remote control and telemetry distance .24
Bibliography .26
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ISO 4358:2023(E)
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.
The procedures used to develop this document and those intended for its further maintenance are
described in the ISO/IEC Directives, Part 1. In particular, the different approval criteria needed for the
different types of ISO documents should be noted. This document was drafted in accordance with the
editorial rules of the ISO/IEC Directives, Part 2 (see www.iso.org/directives).
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. Details of
any patent rights identified during the development of the document will be in the Introduction and/or
on the ISO list of patent declarations received (see www.iso.org/patents).
Any trade name used in this document is information given for the convenience of users and does not
constitute an endorsement.
For an explanation of the voluntary nature of standards, the meaning of ISO specific terms and
expressions related to conformity assessment, as well as information about ISO's adherence to
the World Trade Organization (WTO) principles in the Technical Barriers to Trade (TBT), see
www.iso.org/iso/foreword.html.
This document was prepared by Technical ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 16,
Unmanned aircraft systems.
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.
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ISO 4358:2023(E)
Introduction
Multi-copter unmanned aircraft system (UAS) is the most popular UAS in the market at the time of
publication of this document, but the quality of products can vary significantly. However, it is difficult
to evaluate the function and performance of these products as there is no unified standard test method
and means to evaluate and test the multi-copter UAS. Therefore, the development of test method
standards for civil multi-copter UAS is intended to provide a basis for product testing, in order to
improve the product quality of the multi-copter UAS as a whole.
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INTERNATIONAL STANDARD ISO 4358:2023(E)
Test methods for civil multi-copter unmanned aircraft
system
1 Scope
This document specifies test methods for civil electric multi-copter unmanned aircraft systems (UAS).
This document is intended to be a general standard for testing the overall UAS functionality with the
support of subsystems.
It is applicable to the category of civil electric multi-copter UAS with maximum take-off mass (MTOM)
level I to level V according to ISO 21895. The configuration control and subsystem (e.g. energy system
and flight control system tests) test methods are out of the scope of this document. In addition, test
methods for operations in snow and icing conditions are not included either, manufacturers have
procedures identified to cope with flight in those conditions.
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 21384-4, Unmanned aircraft systems — Part 4: Vocabulary
ISO 21895, Categorization and classification of civil unmanned aircraft systems
3 Terms and definitions
For the purposes of this document, the terms and definitions given in ISO 21384-4, ISO 21895 and the
following 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
mission profile
specified mission to be performed, including the event and the environment sequence that the test
article experiences
3.2
multi-copter UAS
rotorcraft lifted by two or more power-driven rotors on a substantially vertical axis, capable of
hovering, taking off and landing vertically
4 General principles
4.1 Test purpose
The purpose of the test is to:
a) check whether the functionality, performance of the UAS meets the design requirements;
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ISO 4358:2023(E)
b) make recommendations on design modifications and whether to conduct supplementary tests.
4.2 Test conditions and requirements
4.2.1 Technical document
The following documents should be prepared before the test:
a) the design documents, figures and interface file which are relevant to the test;
b) operator’s manual;
c) test plan
4.2.2 Test article
The test article shall fulfil the following requirements.
a) The test article shall conform to the product manuals.
b) The number of test article shall meet the test requirements.
c) The test article shall have quality inspection certificates such as the enterprise qualification
certificate.
4.2.3 Equipment and instruments
Test instruments and equipment (including special equipment and auxiliary equipment) shall be
verified and calibrated, and shall be qualified within the flight test limitations and within the validity
period. All the test instruments used should meet the expected use requirements; and its measurement
uncertainty or maximum allowable error should be less than the agreed allowable error range of the
measured parameter. For test process management, refer to ISO/IEC 17025.
4.2.4 Personnel requirements
Testers shall be able to operate the test article and the test equipment proficiently. Testers shall have
the corresponding competence and qualification, if required.
4.3 Test environmental requirements
Unless otherwise specified, all tests shall be performed by measuring and recording test conditions,
including temperature, relative humidity, atmosphere pressure and wind speed.
4.4 Test interruption and recovery
Test interruption and recovery methods are specified as follows.
a) The test is terminated on one of the following conditions.
1) Key indicator(s) of the test article is (are) unqualified.
2) The test article cannot work normally due to a malfunction and cannot be repaired.
b) When the following situations occur during the test, supplementary tests should be carried out as
appropriate.
1) Individual test article failed, the cause has been identified and corrected.
2) The original design or test article configuration was changed.
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ISO 4358:2023(E)
3) The test article is replaced with the components or devices that affect the technical
performance.
4.5 Test outline
The test plan shall include but not limited to the following:
a) mission profile description;
b) test purpose;
c) test time and location;
d) the number and technical status of the test article and test auxiliary;
e) test article, test classification methods;
f) test requirements;
g) test interruption and recovery;
h) acceptance criteria;
i) test organization;
j) test support;
k) test safety;
m) appendix (e.g. template of data record, collection of formulae).
4.6 Test report
The test report shall include but not limited to the following:
a) serial ID of the test article and pictures of the test article overview and the key components;
b) test general introduction;
c) test item, and necessary specification;
d) test acceptance criteria;
e) test safety (procedures and limitation, etc.);
f) test results;
g) main problems that have occurred in the test and the corresponding treatments;
h) conclusion;
i) issues and suggestions;
i) appendix (e.g. test data histories).
5 Test methods
5.1 Test item
UAS test items are shown in Table 1.
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ISO 4358:2023(E)
Table 1 — Test item information table
No. Test items Subclause number
1 Completeness 5.2.1
2 Appearance 5.2.2
3 Size 5.2.3
Basic
inspection
4 Weight and centre of gravity 5.2.4
5 Moving and rotating parts check 5.2.5
6 Connectors 5.2.6
7 Identification 5.3.1
8 Route loading 5.3.2
8 Self-test 5.3.3
10 Information display 5.3.4
11 Data record 5.3.5
Functional
12 Return to home 5.3.6
inspection and
13 Automatic obstacle avoidance 5.3.7
testing
14 Typical failure protection 5.3.8
15 Take-off/launch and landing/recovery 5.3.9
16 Warning 5.3.10
17 Locking and starting of motor 5.3.11
18 Control mode switching 5.3.12
19 Maximum take-off mass 5.4.1
20 Maximum flight range 5.4.2
21 Maximum flight altitude 5.4.3
22 Maximum horizontal flight speed 5.4.4
23 Maximum steady climb rate 5.4.5
24 Altitude hold performance 5.4.6
Flight performance
test
25 Speed hold performance 5.4.7
26 Flight endurance 5.4.8
27 Fixed-point hovering 5.4.9
28 Positioning navigation 5.4.10
29 Trajectory tracking accuracy 5.4.11
30 Capability of wind resistance 5.4.12
31 Static attitude accuracy 5.5.1
Navigation system
test
32 Static positioning accuracy 5.5.2
33 Remote control distance and telemetry distance 5.6.1
Data link system
test
34 Information transmission distance 5.6.2
35 High temperature 5.7.1
36 Low temperature 5.7.2
37 Rainfall 5.7.3
Environmental
test
38 Humidity and heat 5.7.4
39 Vibration 5.7.5
40 Shock 5.7.6
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ISO 4358:2023(E)
TTabablele 1 1 ((ccoonnttiinnueuedd))
No. Test items Subclause number
41 Conductive emission 5.8.2.1
42 Radiation emission 5.8.2.2
Radiated, radio-frequency, electromagnetic field
43 5.8.3.1
immunity
44 Power frequency magnetic field immunity 5.8.3.2
Electromagnetic
45 compatibility Electrostatic discharge immunity 5.8.3.3
test
46 Electrical fast transient/burst immunity 5.8.3.4
47 Surge immunity 5.8.3.5
Immunity to conducted disturbances, induced by
48 5.8.3.6
radio-frequency fields
49 Voltage sag and short supply Interruption 5.8.3.7
5.2 Basic inspection
5.2.1 Completeness
Visual inspection should be adopted for completeness checking. The test article shall be inspected and
recorded item by item by following product lists.
5.2.2 Appearance
Visual inspection shall be applied for appearance checking. The inspected items generally include:
a) the uniformity of equipment coating, the correctness and clarity of product identities (brand, size,
type, model, weight, etc.), and the robustness of stickers (no curl or erase);
b) the completeness of label or mark for connectors, switches, control sticks;
c) damages such as cracks, scratches, corrosions.
5.2.3 Size
The characteristic size of UA and its components (e.g. length, width, height, wheelbase, propeller/rotor
radius) shall be measured and recorded referring to product specifications with size error range.
5.2.4 Weight and centre of gravity
The weight of the UA and its components shall be measured. The centre of gravity shall be within the
allowable range specified by the manufacturer. Measurement methods generally include the following.
a) Mass measurement tools shall be employed for measuring the weight of the UA and its components
(unit: gram). The measurement should include conditions in which the UA is equipped with different
mission loads.
b) The position of centre of gravity is estimated; and it shall be checked with the designed position.
c) Tests shall be performed with the most critical centre of gravity.
5.2.5 Moving and rotating parts check
Visual inspection shall be employed for checking moving parts such as switches, buttons, foldable arms
and control surfaces; and for rotating parts of the vertical lifting elements (hub, blades, blade dumpers,
pitch control mechanism, and all other parts that rotate with the assembly). Mechanical movement
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ISO 4358:2023(E)
is supposed to be smooth and reliable, without the occurrence of looseness, stagnation, shortage,
deformation, etc.
5.2.6 Connectors
Connectors of the UAS shall be inspected according to indicators; results shall be recorded accordingly.
Inspected items are specified by the manufacturer and may generally include:
a) fool-proofing and locking design, in-place indication;
b) operating friendliness, firm installation and connection robustness;
c) protective design for exposed connecters;
d) skewed, retracted and damaged pins;
e) non-sparking design of power connectors.
5.3 Functional inspection and testing
5.3.1 Identification
While in flight, the identification function of UAS shall be inspected through UAS surveillance system
or a simulated surveillance system. The checked items include:
a) the accuracy of current flight data;
b) whether the identification of UAS and operator meet the requirements of the authority;
c) whether the reporting frequency meets the requirement of the authority.
5.3.2 Route loading
A route of typical flight mission shall be loaded to the UA prior to flight. In this loading process, the
status report shall be examined. Then, how the UA follows the route shall be investigated.
5.3.3 Self-test
Once the power of UAS is engaged, visual inspection shall be used to check the voice or light indications
of self-test results.
5.3.4 Information display
When UAS is powered on at the ground, the display of remote pilot station shall be examined through
visual inspection. Inspected contents should be checked according to the manufacturer's specification.
5.3.5 Data record
The UAS shall be flown in a typical flight mission. After the flight, the recorded data should be read and
inspected. The check items include the integrity of recorded data, the correctness of flight data and
mission data. Both onboard and remote pilot station data record shall be tested.
5.3.6 Return to home
The activation and the manual intervention for abandoning mission shall be checked to confirm that it
can be performed according to the manufacturer's intention.
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ISO 4358:2023(E)
5.3.7 Automatic obstacle avoidance
For UA with obstacle avoidance function, within the range of automatic obstacle avoidance specified
by the manufacturer, the UA shall be manipulated to fly towards obstacles at the speed specified by
the manufacturer until the distance is less than the safety distance specified by the manufacturer.
Inspection should be made that whether the UA can avoid collision. Then, the UA shall be kept away
from obstacles and the capability of regaining aircraft control should be inspected. Obstacles can be
wall, glass, utility pole, power line, etc.
5.3.8 Typical failure protection
For different failure situations, visual inspection shall be m
...

FINAL
INTERNATIONAL ISO/FDIS
DRAFT
STANDARD 4358
ISO/TC 20/SC 16
Test methods for civil multi-copter
Secretariat: ANSI
unmanned aircraft system
Voting begins on:
2023-01-30
Voting terminates on:
2023-03-27
RECIPIENTS OF THIS DRAFT ARE INVITED TO
SUBMIT, WITH THEIR COMMENTS, NOTIFICATION
OF ANY RELEVANT PATENT RIGHTS OF WHICH
THEY ARE AWARE AND TO PROVIDE SUPPOR TING
DOCUMENTATION.
IN ADDITION TO THEIR EVALUATION AS
Reference number
BEING ACCEPTABLE FOR INDUSTRIAL, TECHNO-
ISO/FDIS 4358:2023(E)
LOGICAL, COMMERCIAL AND USER PURPOSES,
DRAFT INTERNATIONAL STANDARDS MAY ON
OCCASION HAVE TO BE CONSIDERED IN THE
LIGHT OF THEIR POTENTIAL TO BECOME STAN-
DARDS TO WHICH REFERENCE MAY BE MADE IN
NATIONAL REGULATIONS. © ISO 2023

---------------------- Page: 1 ----------------------
ISO/FDIS 4358:2023(E)
FINAL
INTERNATIONAL ISO/FDIS
DRAFT
STANDARD 4358
ISO/TC 20/SC 16
Test methods for civil multi-copter
Secretariat: ANSI
unmanned aircraft system
Voting begins on:
Voting terminates on:
COPYRIGHT PROTECTED DOCUMENT
© ISO 2023
All rights reserved. Unless otherwise specified, or required in the context of its implementation, no part of this publication may
be reproduced or utilized otherwise in any form or by any means, electronic or mechanical, including photocopying, or posting on
the internet or an intranet, without prior written permission. Permission can be requested from either ISO at the address below
or ISO’s member body in the country of the requester.
RECIPIENTS OF THIS DRAFT ARE INVITED TO
ISO copyright office
SUBMIT, WITH THEIR COMMENTS, NOTIFICATION
OF ANY RELEVANT PATENT RIGHTS OF WHICH
CP 401 • Ch. de Blandonnet 8
THEY ARE AWARE AND TO PROVIDE SUPPOR TING
CH-1214 Vernier, Geneva
DOCUMENTATION.
Phone: [phone]
IN ADDITION TO THEIR EVALUATION AS
Reference number
Email: [e-mail]
BEING ACCEPTABLE FOR INDUSTRIAL, TECHNO­
ISO/FDIS 4358:2023(E)
Website: www.iso.org
LOGICAL, COMMERCIAL AND USER PURPOSES,
DRAFT INTERNATIONAL STANDARDS MAY ON
Published in Switzerland
OCCASION HAVE TO BE CONSIDERED IN THE
LIGHT OF THEIR POTENTIAL TO BECOME STAN­
DARDS TO WHICH REFERENCE MAY BE MADE IN
ii
  © ISO 2023 – All rights reserved
NATIONAL REGULATIONS. © ISO 2023

---------------------- Page: 2 ----------------------
ISO/FDIS 4358:2023(E)
Contents Page
Foreword .v
Introduction . vi
1 Scope . 1
2 Normative references . 1
3 Terms and definitions . 1
4 General principles . 1
4.1 Test purpose . 1
4.2 Test conditions and requirements . 2
4.2.1 Technical document . 2
4.2.2 Test article . . 2
4.2.3 Equipment and instruments . 2
4.2.4 Personnel requirements . 2
4.3 Test environmental requirements . 2
4.4 Test interruption and recovery. 2
4.5 Test outline . 3
4.6 Test report . 3
5 Test methods . 3
5.1 Test item . 3
5.2 Basic inspection . 5
5.2.1 Completeness . 5
5.2.2 Appearance . 5
5.2.3 Size . 5
5.2.4 Weight and centre of gravity . 5
5.2.5 Moving and rotating parts check . 5
5.2.6 Connectors . 6
5.3 Functional inspection and testing . 6
5.3.1 Identification . 6
5.3.2 Route loading . 6
5.3.3 Self­test . 6
5.3.4 Information display . 6
5.3.5 Data record . 6
5.3.6 Return to home . 6
5.3.7 Automatic obstacle avoidance . 7
5.3.8 Typical failure protection . 7
5.3.9 Take-off/launch and landing/recovery . 7
5.3.10 Warning . 7
5.3.11 Locking and starting of the motor . 7
5.3.12 Control mode switching . 7
5.4 Flight performance test . 8
5.4.1 Maximum take-off weight . 8
5.4.2 Maximum flight range . 8
5.4.3 Maximum flight altitude . 8
5.4.4 Maximum horizontal flight speed. 9
5.4.5 Maximum steady climb rate . 9
5.4.6 Altitude hold performance . 9
5.4.7 Speed hold performance . 10
5.4.8 Flight endurance . 10
5.4.9 Fixed-point hovering . .12
5.4.10 Positioning navigation .12
5.4.11 Trajectory tracking accuracy .12
5.4.12 Capability of wind resistance . 13
5.5 Navigation system test . 13
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ISO/FDIS 4358:2023(E)
5.5.1 Static attitude accuracy.13
5.5.2 Static positioning accuracy . 13
5.6 Data link system test .13
5.6.1 Remote control distance and telemetry distance .13
5.6.2 Information transmission distance . 14
5.7 Environmental test . 14
5.7.1 High temperature . 14
5.7.2 Low temperature .15
5.7.3 Rainfall . 16
5.7.4 Humidity and heat. 16
5.7.5 Vibration . 16
5.7.6 Shock . 16
5.8 Electromagnetic compatibility. 16
5.8.1 General principles . 16
5.8.2 Emission test . 17
5.8.3 Immunity . 18
Annex A (informative) Test procedure of remote control and telemetry distance .24
Bibliography .26
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ISO/FDIS 4358:2023(E)
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 non­governmental, 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.
The procedures used to develop this document and those intended for its further maintenance are
described in the ISO/IEC Directives, Part 1. In particular, the different approval criteria needed for the
different types of ISO documents should be noted. This document was drafted in accordance with the
editorial rules of the ISO/IEC Directives, Part 2 (see www.iso.org/directives).
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. Details of
any patent rights identified during the development of the document will be in the Introduction and/or
on the ISO list of patent declarations received (see www.iso.org/patents).
Any trade name used in this document is information given for the convenience of users and does not
constitute an endorsement.
For an explanation of the voluntary nature of standards, the meaning of ISO specific terms and
expressions related to conformity assessment, as well as information about ISO's adherence to
the World Trade Organization (WTO) principles in the Technical Barriers to Trade (TBT), see
www.iso.org/iso/foreword.html.
This document was prepared by Technical ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 16,
Unmanned aircraft systems.
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.
v
© ISO 2023 – All rights reserved

---------------------- Page: 5 ----------------------
ISO/FDIS 4358:2023(E)
Introduction
Multi-copter unmanned aircraft system (UAS) is the most popular UAS in the market at the time of
publication of this document, but the quality of products can vary significantly. However, it is difficult
to evaluate the function and performance of these products as there is no unified standard test method
and means to evaluate and test the multi­copter UAS. Therefore, the development of test method
standards for civil multi­copter UAS is intended to provide a basis for product testing, in order to
improve the product quality of the multi-copter UAS as a whole.
vi
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---------------------- Page: 6 ----------------------
FINAL DRAFT INTERNATIONAL STANDARD ISO/FDIS 4358:2023(E)
Test methods for civil multi-copter unmanned aircraft
system
1 Scope
This document specifies test methods for civil electric multi-copter unmanned aircraft systems (UAS).
This document is intended to be a general standard for testing the overall UAS functionality with the
support of subsystems.
It is applicable to the category of civil electric multi-copter UAS with maximum take-off mass (MTOM)
level I to level V according to ISO 21895. The configuration control and subsystem (e.g. energy system
and flight control system tests) test methods are out of the scope of this document. In addition, test
methods for operations in snow and icing conditions are not included either, manufacturers have
procedures identified to cope with flight in those conditions.
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 21384­4, Unmanned aircraft systems — Part 4: Vocabulary
ISO 21895, Categorization and classification of civil unmanned aircraft systems
3 Terms and definitions
For the purposes of this document, the terms and definitions given in ISO 21384-4, ISO 21895 and the
following 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
mission profile
specified mission to be performed, including the event and the environment sequence that the test
article experiences
3.2
multi-copter UAS
rotorcraft lifted by two or more power-driven rotors on a substantially vertical axis, capable of
hovering, taking off and landing vertically
4 General principles
4.1 Test purpose
The purpose of the test is to:
a) check whether the functionality, performance of the UAS meets the design requirements;
1
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ISO/FDIS 4358:2023(E)
b) make recommendations on design modifications and whether to conduct supplementary tests.
4.2 Test conditions and requirements
4.2.1 Technical document
The following documents should be prepared before the test:
a) the design documents, figures and interface file which are relevant to the test;
b) operator’s manual;
c) test plan
4.2.2 Test article
The test article shall fulfil the following requirements.
a) The test article shall conform to the product manuals.
b) The number of test article shall meet the test requirements.
c) The test article shall have quality inspection certificates such as the enterprise qualification
certificate.
4.2.3 Equipment and instruments
Test instruments and equipment (including special equipment and auxiliary equipment) shall be
verified and calibrated, and shall be qualified within the flight test limitations and within the validity
period. All the test instruments used should meet the expected use requirements; and its measurement
uncertainty or maximum allowable error should be less than the agreed allowable error range of the
measured parameter. For test process management, refer to ISO/IEC 17025.
4.2.4 Personnel requirements
Testers shall be able to operate the test article and the test equipment proficiently. Testers shall have
the corresponding competence and qualification, if required.
4.3 Test environmental requirements
Unless otherwise specified, all tests shall be performed by measuring and recording test conditions,
including temperature, relative humidity, atmosphere pressure and wind speed.
4.4 Test interruption and recovery
Test interruption and recovery methods are specified as follows.
a) The test is terminated on one of the following conditions.
1) Key indicator(s) of the test article is (are) unqualified.
2) The test article cannot work normally due to a malfunction and cannot be repaired.
b) When the following situations occur during the test, supplementary tests should be carried out as
appropriate.
1) Individual test article failed, the cause has been identified and corrected.
2) The original design or test article configuration was changed.
2
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ISO/FDIS 4358:2023(E)
3) The test article is replaced with the components or devices that affect the technical
performance.
4.5 Test outline
The test plan shall include but not limited to the following:
a) mission profile description;
b) test purpose;
c) test time and location;
d) the number and technical status of the test article and test auxiliary;
e) test article, test classification methods;
f) test requirements;
g) test interruption and recovery;
h) acceptance criteria;
i) test organization;
j) test support;
k) test safety;
m) appendix (e.g. template of data record, collection of formulae).
4.6 Test report
The test report shall include but not limited to the following:
a) serial ID of the test article and pictures of the test article overview and the key components;
b) test general introduction;
c) test item, and necessary specification;
d) test acceptance criteria;
e) test safety (procedures and limitation, etc.);
f) test results;
g) main problems that have occurred in the test and the corresponding treatments;
h) conclusion;
i) issues and suggestions;
i) appendix (e.g. test data histories).
5 Test methods
5.1 Test item
UAS test items are shown in Table 1.
3
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ISO/FDIS 4358:2023(E)
Table 1 — Test item information table
No. Test items Subclause number
1 Completeness 5.2.1
2 Appearance 5.2.2
3 Size 5.2.3
Basic
inspection
4 Weight and centre of gravity 5.2.4
5 Moving and rotating parts check 5.2.5
6 Connectors 5.2.6
7 Identification 5.3.1
8 Route loading 5.3.2
8 Self­test 5.3.3
10 Information display 5.3.4
11 Data record 5.3.5
Functional
12 Return to home 5.3.6
inspection and
13 Automatic obstacle avoidance 5.3.7
testing
14 Typical failure protection 5.3.8
15 Take-off/launch and landing/recovery 5.3.9
16 Warning 5.3.10
17 Locking and starting of motor 5.3.11
18 Control mode switching 5.3.12
19 Maximum take-off mass 5.4.1
20 Maximum flight range 5.4.2
21 Maximum flight altitude 5.4.3
22 Maximum horizontal flight speed 5.4.4
23 Maximum steady climb rate 5.4.5
24 Altitude hold performance 5.4.6
Flight performance
test
25 Speed hold performance 5.4.7
26 Flight endurance 5.4.8
27 Fixed-point hovering 5.4.9
28 Positioning navigation 5.4.10
29 Trajectory tracking accuracy 5.4.11
30 Capability of wind resistance 5.4.12
31 Static attitude accuracy 5.5.1
Navigation system
test
32 Static positioning accuracy 5.5.2
33 Remote control distance and telemetry distance 5.6.1
Data link system
test
34 Information transmission distance 5.6.2
35 High temperature 5.7.1
36 Low temperature 5.7.2
37 Rainfall 5.7.3
Environmental
test
38 Humidity and heat 5.7.4
39 Vibration 5.7.5
40 Shock 5.7.6
4
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ISO/FDIS 4358:2023(E)
TTabablele 1 1 ((ccoonnttiinnueuedd))
No. Test items Subclause number
41 Conductive emission 5.8.2.1
42 Radiation emission 5.8.2.2
Radiated, radio-frequency, electromagnetic field
43 5.8.3.1
immunity
44 Power frequency magnetic field immunity 5.8.3.2
Electromagnetic
45 compatibility Electrostatic discharge immunity 5.8.3.3
test
46 Electrical fast transient/burst immunity 5.8.3.4
47 Surge immunity 5.8.3.5
Immunity to conducted disturbances, induced by
48 5.8.3.6
radio-frequency fields
49 Voltage sag and short supply Interruption 5.8.3.7
5.2 Basic inspection
5.2.1 Completeness
Visual inspection should be adopted for completeness checking. The test article shall be inspected and
recorded item by item by following product lists.
5.2.2 Appearance
Visual inspection shall be applied for appearance checking. The inspected items generally include:
a) the uniformity of equipment coating, the correctness and clarity of product identities (brand, size,
type, model, weight, etc.), and the robustness of stickers (no curl or erase);
b) the completeness of label or mark for connectors, switches, control sticks;
c) damages such as cracks, scratches, corrosions.
5.2.3 Size
The characteristic size of UA and its components (e.g. length, width, height, wheelbase, propeller/rotor
radius) shall be measured and recorded referring to product specifications with size error range.
5.2.4 Weight and centre of gravity
The weight of the UA and its components shall be measured. The centre of gravity shall be within the
allowable range specified by the manufacturer. Measurement methods generally include the following.
a) Mass measurement tools shall be employed for measuring the weight of the UA and its components
(unit: gram). The measurement should include conditions in which the UA is equipped with different
mission loads.
b) The position of centre of gravity is estimated; and it shall be checked with the designed position.
c) Tests shall be performed with the most critical centre of gravity.
5.2.5 Moving and rotating parts check
Visual inspection shall be employed for checking moving parts such as switches, buttons, foldable arms
and control surfaces; and for rotating parts of the vertical lifting elements (hub, blades, blade dumpers,
pitch control mechanism, and all other parts that rotate with the assembly). Mechanical movement
5
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ISO/FDIS 4358:2023(E)
is supposed to be smooth and reliable, without the occurrence of looseness, stagnation, shortage,
deformation, etc.
5.2.6 Connectors
Connectors of the UAS shall be inspected according to indicators; results shall be recorded accordingly.
Inspected items are specified by the manufacturer and may generally include:
a) fool-proofing and locking design, in-place indication;
b) operating friendliness, firm installation and connection robustness;
c) protective design for exposed connecters;
d) skewed, retracted and damaged pins;
e) non­sparking design of power connectors.
5.3 Functional inspection and testing
5.3.1 Identification
While in flight, the identification function of UAS shall be inspected through UAS surveillance system
or a simulated surveillance system. The checked items include:
a) the accuracy of current flight data;
b) whether the identification of UAS and operator meet the requirements of the authority;
c) whether the reporting frequency meets the requirement of the authority.
5.3.2 Route loading
A route of typical flight mission shall be loaded to the UA prior to flight. In this loading process, the
status report shall be examined. Then, how the UA follows the route shall be investigated.
5.3.3 Self-test
Once the power of UAS is engaged, visual inspection shall be used to check the voice or light indications
of self­test results.
5.3.4 Information display
When UAS is powered on at the ground, the display of remote pilot station shall be examined through
visual inspection. Inspected contents should be checked according to the manufa
...

© ISO 2022 – All rights reserved
ISO/DIS FDIS 4358:2022(E)
2022-04-04
ISO/TC 20/SC 16/WG 5
Secretariat: ANSI
Date: 2023-01-16
Test methods for civil multi-copter unmanned aircraft system
FDIS stage
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ISO/DISFDIS 4358:20222023(E)
© ISO 20222023
All rights reserved. Unless otherwise specified, or required in the context of its implementation, no part of this
publication may be reproduced or utilized otherwise in any form or by any means, electronic or mechanical,
including photocopying, or posting on the internet or an intranet, without prior written permission. Permission can
be requested from either ISO at the address below or ISO’s member body in the country of the requester.
ISO copyright office
CP 401 • Ch. de Blandonnet 8
CH-1214 Vernier, Geneva
Phone: + 41 22 749 01 11
Fax: [phone]
EmailE-mail: [e-mail]
Website: www.iso.org
Published in Switzerland
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ISO/DISFDIS 4358:20222023(E)
Contents
Foreword . v
Introduction . vi
1 Scope . 1
2 Normative references . 1
3 Terms and definitions . 1
4 General principles . 1
4.1 Test purpose . 1
4.2 Test conditions and requirements . 2
4.2.1 Technical document . 2
4.2.2 Test article . 2
4.2.3 Equipment and instruments . 2
4.2.4 Personnel requirements . 2
4.3 Test environmental requirements . 2
4.4 Test interruption and recovery . 2
4.5 Test outline . 2
4.6 Test report . 3
5 Test methods . 3
5.1 Test item . 3
5.2 Basic inspection . 5
5.2.1 Completeness . 5
5.2.2 Appearance . 5
5.2.3 Size . 5
5.2.4 Weight and centre of gravity . 5
5.2.5 Moving and rotating parts check . 5
5.2.6 Connectors . 6

5.3 Functional inspection and testing . 6
5.3.1 Identification . 6
5.3.2 Route loading . 6
5.3.3 Self-test . 6
5.3.4 Information display . 6
5.3.5 Data record . 6
5.3.6 Return to home . 6
5.3.7 Automatic obstacle avoidance . 6
5.3.8 Typical failure protection . 7
5.3.9 Take-off/launch and landing/recovery . 7
5.3.10 Warning . 7
5.3.11 Locking and starting of the motor . 7
5.3.12 Control mode switching . 7
5.4 Flight performance test . 7
5.4.1 Maximum take-off weight . 7
5.4.2 Maximum flight range . 7
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ISO/DISFDIS 4358:20222023(E)
5.4.3 Maximum flight altitude . 8
5.4.4 Maximum horizontal flight speed . 8
5.4.5 Maximum steady climb rate . 9
5.4.6 Altitude hold performance . 9
5.4.7 Speed hold performance . 9
5.4.8 Flight endurance . 10
5.4.9 Fixed-point hovering . 11
5.4.10 Positioning navigation . 12
5.4.11 Trajectory tracking accuracy . 12
5.4.12 Capability of wind resistance . 12
5.5 Navigation system test . 12
5.5.1 Static attitude accuracy. 12
5.5.2 Static positioning accuracy. 12
5.6 Data link system test . 13
5.6.1 Remote control distance and telemetry distance . 13
5.6.2 Information transmission distance. 13
5.7 Environmental test . 14
5.7.1 High temperature . 14
5.7.2 Low temperature . 14
5.7.3 Rainfall . 15
5.7.4 Humidity and heat . 15
5.7.5 Vibration . 15
5.7.6 Shock . 15
5.8 Electromagnetic compatibility . 16
5.8.1 General principles . 16
5.8.2 Emission test . 16
5.8.3 Immunity . 18
Annex A (informative) Test procedure of remote control and telemetry distance . 23
Bibliography . 25

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ISO/DISFDIS 4358:20222023(E)
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.
The procedures used to develop this document and those intended for its further maintenance are
described in the ISO/IEC Directives, Part 1. In particular, the different approval criteria needed for the
different types of ISO documents should be noted. This document was drafted in accordance with the
editorial rules of the ISO/IEC Directives, Part 2 (see www.iso.org/directives).
Field Code Changed
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. Details of any
patent rights identified during the development of the document will be in the Introduction and/or on
the ISO list of patent declarations received (see www.iso.org/patents).
Any trade name used in this document is information given for the convenience of users and does not
constitute an endorsement.
For an explanation of the voluntary nature of standards, the meaning of ISO specific terms and
expressions related to conformity assessment, as well as information about ISO's adherence to the World
Trade Organization (WTO) principles in the Technical Barriers to Trade (TBT), see
www.iso.org/iso/foreword.html.
This document was prepared by Technical ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 16,
Unmanned aircraft systems.
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.
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ISO/DISFDIS 4358:20222023(E)
Introduction
Multi-copter unmanned aircraft system (UAS) is the most popular UAS in the market at the time of
publication of this document, but the quality of products can vary significantly. However, it is difficult to
evaluate the function and performance of these products as there is no unified standard test method and
means to evaluate and test the multi-copter UAS. Therefore, the development of test method standards
for civil multi-copter UAS is intended to provide a basis for product testing, in order to improve the
product quality of the multi-copter UAS as a whole.
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ISO/FDIS 4358:2023(E)
Test methods for civil multi-copter unmanned aircraft system
1 Scope
This document specifies test methods for civil electric multi-copter unmanned aircraft systems (UAS).
This document is intended to be a general standard for testing the overall UAS functionality with the
support of subsystems.
It is applicable to the category of civil electric multi-copter UAS with maximum take-off mass (MTOM)
level I to level V according to ISO 21895. The configuration control and subsystem (e.g. energy system
and flight control system tests) test methods are out of the scope of this document. In addition, test
methods for operations in snow and icing conditions are not included either, manufacturers should have
procedures identified to cope/mitigate with flight in those conditions.
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 21384-4, Unmanned aircraft systems — Part 4: Vocabulary
ISO 21895-,, Categorization and classification of civil unmanned aircraft systems
IEC 60068-2-30, Environmental testing - Part 2-30: Tests - Test Db: Damp heat, cyclic (12 h + 12 h cycle)
IEC 60068-2-78:2012, Environmental testing - Part 2-78: Tests - Test Cab: Damp heat, steady state
IEC 60529, Degrees of protection provided by enclosures (IP Code)
3 Terms and definitions
For the purposes of this document, the terms and definitions given in ISO 21384-4, ISO 21895and21895
and the following 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
mission profile
specified mission to be performed, including the event and the environment sequence that the test article
experiences
3.2
multi-copter UAS
Rotorcraftrotorcraft lifted by two or more power-driven rotors on a substantially vertical axis, capable of
hovering, taking off and landing vertically
4 General principles
4.1 Test purpose
The purpose of the test is to:
a) a) Checkcheck whether the functionality, performance of the UAS meets the design requirements;
b) b) Makemake recommendations on design modifications and whether to conduct supplementary
tests.
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ISO/FDIS 4358:2023(E)
4.2 Test conditions and requirements
4.2.1 Technical document
The following documents should be prepared before the test:
a) a) Thethe design documents, figures and interface file which are relevant to the test;
b) b) Operator’soperator’s manual;
c) c) Testtest plan
4.2.2 Test article
The test article shall fulfil the following requirements:.
a) a) The test article shall conform to the product manuals;.
b) b) The number of test article shall meet the test requirements;.
c) c) The test article shall have quality inspection certificates such as the enterprise qualification
certificate.
4.2.3 Equipment and instruments
Test instruments and equipment (including special equipment and auxiliary equipment) shall be verified
and calibrated, and shall be qualified within the flight test limitations and within the validity period. All
the test instruments used should meet the expected use requirements,; and its measurement uncertainty
or maximum allowable error should be less than the agreed allowable error range of the measured
parameter. For test process management, refer to ISO/IEC 17025.
4.2.4 Personnel requirements
Testers shall be able to operate the test article and the test equipment proficiently. Testers shall have the
corresponding competence and qualification, if required.
4.3 Test environmental requirements
Unless otherwise specified, all tests shall be performed by measuring and recording test conditions,
including temperature, relative humidity, atmosphere pressure, and wind speed.
4.4 Test interruption and recovery
Test interruption and recovery methods are specified as follows:.
a) a) The test is terminated on one of the following conditions:.
1) 1) Key indicator(s) of the test article is (are) unqualified;.
2) 2) The test article cannot work normally due to a malfunction and cannot be repaired.
b) b) When the following situations occur during the test, supplementary tests should be carried out
as appropriate:.
1) 1) Individual test article failed, the cause has been identified and corrected;.
2) 2) The original design or test article configuration was changed;.
3) 3) The test article is replaced with the components or devices that affect the technical
performance.
4.5 Test outline
The Testtest plan shall include but not limited to the following:
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ISO/FDIS 4358:2023(E)
a) a) Missionmission profile description;
b) b) Testtest purpose;
c) c) Testtest time and location;
d) d) Thethe number and technical status of the test article and test auxiliary;
e) e) Testtest article, test classification methods;
f) f) Testtest requirements;
g) g) Testtest interruption and recovery;
h) h) Acceptanceacceptance criteria;
i) i) Testtest organization;
j) j) Testtest support;
k) k) Testtest safety;
l) m) Appendixappendix (e.g. template of data record, collection of formulasformulae).
4.6 Test report
TestThe test report shall include but not limited to the following:
a) a) Serialserial ID of the test article and pictures of the test article overview and the key components;
b) b) Testtest general introduction;
c) c) Testtest item, and necessary specification;
d) d) Testtest acceptance criteria;
e) e) Testtest safety (procedures and limitation, etc.).);
f) f) Testtest results;
g) g) Mainmain problems that have occurred in the test and the corresponding treatments;
h) Conclusion;
h) i) Issuesconclusion;
i) issues and suggestions;
j) i) Appendixappendix (e.g. test data histories, ).
5 Test methods
5.1 Test item
UAS test items are shown in Table 1Table 1.
Table 1 — Test item information table
No. Test items Subclause number
1 Completeness 5.2.15.2.1
Basic
inspection
2 Appearance 5.2.25.2.2
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ISO/FDIS 4358:2023(E)
No. Test items Subclause number
3 Size 5.2.35.2.3
4 Weight and centercentre of gravity 5.2.45.2.4
5 Moving and rotating parts check 5.2.55.2.5
6 Connectors 5.2.65.2.6
7 Identification 5.3.15.3.1
8 Route loading 5.3.25.3.2
8 Self-test 5.3.35.3.3
10 Information display 5.3.45.3.4
11 Data record 5.3.55.3.5
Functional
12 Return to home 5.3.65.3.6
inspection and
13 Automatic obstacle avoidance 5.3.75.3.7
testing
14 Typical failure protection 5.3.85.3.8
15 Take-off/launch and landing/recovery 5.3.95.3.9
16 Warning 5.3.105.3.10
17 Locking and starting of motor 5.3.115.3.11
18 Control mode switching 5.3.125.3.12
19 Maximum take-off mass 5.4.15.4.1
20 Maximum flight range 5.4.25.4.2
21 Maximum flight altitude 5.4.35.4.3
22 Maximum horizontal flight speed 5.4.45.4.4
23 Maximum steady climb rate 5.4.55.4.5
24 Altitude hold performance 5.4.65.4.6
Flight
performance test
25 Speed hold performance 5.4.75.4.7
26 Flight endurance 5.4.85.4.8
27 Fixed-point hovering 5.4.95.4.9
28 Positioning navigation 5.4.105.4.10
29 Trajectory tracking accuracy 5.4.115.4.11
30 Capability of wind resistance 5.4.125.4.12
31 Static attitude accuracy 5.5.15.5.1
Navigation system
test
32 Static positioning accuracy 5.5.25.5.2
33 Remote control distance and telemetry distance 5.6.15.6.1
Data link system
test
34 Information transmission distance 5.6.25.6.2
35 High temperature 5.7.15.7.1
36 Low temperature 5.7.25.7.2
37 Rainfall 5.7.35.7.3
Environmental
test
38 Humidity and heat 5.7.45.7.4
39 Vibration 5.7.55.7.5
40 Shock 5.7.65.7.6
41 Conductive emission 5.8.2.15.8.2.1
42 Radiation emission 5.8.2.25.8.2.2
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ISO/FDIS 4358:2023(E)
No. Test items Subclause number
Radiated, radio-frequency, electromagnetic field
43 5.8.3.15.8.3.1
immunity
44 Power frequency magnetic field immunity 5.8.3.25.8.3.2
45 Electrostatic discharge immunity 5.8.3.35.8.3.3
Electromagnetic
46 compatibility Electrical fast transient/burst immunity 5.8.3.45.8.3.4
test
47 Surge immunity 5.8.3.55.8.3.5
Immunity to conducted disturbances, induced by
48 5.8.3.65.8.3.6
radio-frequency fields
49 Voltage sag and short supply Interruption 5.8.3.75.8.3.7
5.2 Basic inspection
5.2.1 Completeness
Visual inspection should be adopted for completeness checking. TestThe test article shall be inspected
and recorded item by item by following product lists.
5.2.2 Appearance
Visual inspection shall be applied for appearance checking. The inspected items generally include:
a) a) Thethe uniformity of equipment coating, the correctness and clarity of product identities (brand,
size, type, model, weight, etc.), and the robustness of stickers (no curl or erase).);
b) b) Thethe completeness of label or mark for connectors, switches, control sticks.;
c) c) Damagesdamages such as cracks, scratches, corrosions.
5.2.3 Size
The characteristic size of UA and its components (e.g. length, width, height, wheelbase, propeller/rotor
radius, etc.)) shall be measured and recorded referring to product specifications with size error range.
5.2.4 Weight and centercentre of gravity
The weight of the UA and its components shall be measured. The centercentre of gravity shall be within
the allowable range specified by the manufacturemanufacturer. Measurement methods generally
include: the following.
a) a) Mass measurement tools shall be employed for measuring the weight of the UA and its
components (unit: gram). The measurement should include conditions in which the UA is equipped
with different mission loadloads.
b) b) The position of centercentre of gravity is estimated,; and it shall be checked with the designed
position.
c) c) Tests shall be performed with the most critical centercentre of gravity.
5.2.5 Moving and rotating parts check
Visual inspection shall be employed for checking moving parts such as switches, buttons, foldable arms
and control surfaces; and for rotating parts of the vertical lifting elements (hub, blades, blade dumpers,
pitch control mechanism, and all other parts that rotate with the assembly). Mechanical movement is
supposed to be smooth and reliable, without the occurrence of looseness, stagnation, shortage,
deformation, etc.
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ISO/FDIS 4358:2023(E)
5.2.6 Connectors
Connectors of the UAS shall be inspected according to indicators,; results shall be recorded accordingly.
Inspected items are specified by the manufacturer, these and may generally include:
a) a) Foolfool-proofing and locking design, in-place indication;
b) b) Operatingoperating friendliness, firm installation and connection robustness;
c) c) Protectiveprotective design for exposed connecters;
d) d) Skewedskewed, retracted and damaged pins;
e) e) Nonnon-sparking design of power connectors.
5.3 Functional inspection and testing
5.3.1 Identification
While in flight, the identification function of UAS shall be inspected through UAS surveillance system or
a simulated surveillance system. The checked items include:
a) a) Thethe accuracy of current flight data;
b) b) Whetherwhether the identification of UAS and operator meet the requirements of the authority;
c) c) Whetherwhether the reporting frequency meets the requirement. of the authority.
5.3.2 Route loading
A route of typical flight mission shall be loaded to the UA prior to flight. In this loading process, the status
report shall be examined. Then, how the UA follows the route shall be investigated.
5.3.3 Self-test
Once the power of UAS is engaged, visual inspection shall be used to check the voice or light indications
of self-test results.
5.3.4 Information display
When UAS is powered on at the ground, the display of remote pilot station shall be examined through
visual inspection. Inspected contents should be checked as the manufacture statesaccording to the
manufacturer's specification.
5.3.5 Data record
The UAS shall be flown in a typical flight mission. After the flight, the recorded data should be read and
inspected. The check items include the integrity of recorded data, the correctness of flight data and
mission data. Both onboard and remote pilot station data record shall be tested.
5.3.6 Return to home
The activation and the manual intervention for abandoning mission shall be checked to confirm
...