ISO 21384-2:2021
Unmanned aircraft systems — Part 2: UAS components
This document specifies requirements for ensuring the quality and safety of the design and manufacture of unmanned aircraft systems (UAS) that include unmanned aircraft (UA), remote pilot stations (RPS), datalinks, payloads, and associated support equipment.
This document includes information regarding the unmanned aircraft, any associated remote pilot station (RPS)(s), the command and control links (C2 Link), any other required data links (e.g. payload, traffic management information, vehicle identification) and any other system elements as can be required. This document does not cover passenger carrying UAS or technical requirements for the design and manufacturing for UAS components.
This document does not include equipment considerations unique to compliance with UA traffic management systems.
The document is applicable to the reasonable expected use of a UAS.
This document is applicable:
a) to UAS designed for use where a State aviation authority has determined a Certificate of Airworthiness (C of A) is not required;
b) where a C of A is required, to complement technical standards published by the aviation authority for the purposes of building the certification basis; or
c) as an alternative means of compliance if acceptable to the aviation authority.
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Foreword
Introduction
1 Scope
2 Normative references
3 Terms and definitions
4 Abbreviated terms
5 General design requirements for UAS
5.1 General
5.2 Function and reliability
5.2.1 Design
5.2.2 Components
5.3 Maintainability and supportability
5.3.1 Design
5.3.2 Documentation
5.3.3 Support
5.4 Fatigue durability
5.5 Aircraft identification features
5.6 Transportation, storage and packaging
6 Aircraft structures
6.1 Overview
6.2 Damage tolerance assessment
6.3 UA construction
6.4 Moving parts
6.5 Attached parts
7 Propulsion
7.1 Propulsion risk management
7.2 Engines and motors
7.2.1 General requirements
7.2.2 Mounting and installation
7.2.3 Combustion engines
7.2.4 Electric motors
7.2.5 Electronic speed controller (ESC) requirements
7.3 Thrust mechanisms
7.3.1 Propellers and rotors
7.3.2 Turbine and fans
8 Electrical systems
8.1 General
8.2 Electrical safety
8.3 Airborne electrical systems
8.4 Ground electrical systems
8.4.1 UAS electrical components on the ground
8.4.2 RPS power system
8.4.3 Labelling
9 Energy sources
9.1 Batteries
9.1.1 General
9.1.2 Protective measures
9.1.3 Precautions
9.2 Combustible fuels
9.3 Fuel cells
9.3.1 General requirements
9.3.2 General safety requirements
9.3.3 Protective measures
10 Equipment
10.1 Avionic equipment (general)
10.2 Flight control system (FCS)
10.2.1 General requirement
10.2.2 Flight control hardware
10.2.3 Flight control software
10.2.4 Course accuracy
10.2.5 Airspeed
10.3 Flight control actuators
10.4 Diagnostics
10.5 Navigation systems
10.5.1 General
10.5.2 Global Navigation Satellite System (GNSS) receiver
10.5.3 Real time kinematic (RTK) augmentation
10.5.4 Inertial measurement unit (IMU)
10.5.5 Magnetic compass
10.6 Attitude sensors
10.6.1 Altimeter
10.6.2 Airspeed sensor
10.6.3 Optical sensor
10.7 Hardware and software redundancy
10.8 Failure modes
11 C2 Link
11.1 Performance and design
11.2 Antenna module design
11.3 Operations
11.4 Monitoring
11.5 Protocol
11.6 Data features
11.6.1 General
11.6.2 UA status data
11.6.3 Delay requirements
11.7 Reliability requirements
11.8 Security requirements
12 Remote pilot station
12.1 General
12.2 Features
12.2.1 General
12.2.2 Data monitoring systems requirements
12.3 Design requirements
12.3.1 System
12.3.2 Structure
12.3.3 Human factors engineering and ergonomics design
12.4 Functional requirements
12.4.1 Mission planning
12.4.2 Data link control
12.4.3 Flight Control Commands
12.5 Displays
12.5.1 Instrumentation
12.5.2 Readability
12.5.3 Accuracy
12.5.4 Warnings, cautions, and advisories
12.5.5 Display/interface failures
12.5.6 Track and parameter display
12.5.7 C2 Link status display
12.5.8 Telemetry parameter record
12.6 Performance requirements
12.6.1 Environmental adaptability
12.6.2 Reliability
12.7 Safety
12.8 Collision avoidance (CA) systems
13 Payload
13.1 General requirements
13.2 Safety marking
13.3 Wiring design
13.4 Payload power supply
13.5 Storage requirement
14 Airworthiness
14.1 Documentation
14.1.1 Instructions
14.1.2 Manuals and handbooks
14.1.3 Procedural changes
14.2 Composition of an operator’s manual
14.2.1 Technical specifications
14.2.2 Flight performance
14.2.3 Aircraft weights
14.2.4 Flight control accuracy
14.2.5 Dimensions
14.2.6 Atmospheric and other environments adaptability
14.3 Electromagnetic compatibility considerations
14.4 Noise
14.5 Built-in test and monitoring
14.6 System safety program
14.6.1 Selection of design materials
14.6.2 Properties and processes
14.6.3 Mass properties
14.6.4 Corrosion
14.6.5 Material limitations
14.6.6 Fire hazards
14.6.7 Equipment separation
15 UAS software
15.1 Software architecture and design
15.2 Safety
15.3 Security
15.4 Software compliance
15.5 Software development life cycle
16 Other considerations
16.1 Ground equipment
16.2 Multi vehicle control
16.3 Jamming and spoofing
17 Automation
17.1 General
17.2 Software development lifecycle
17.3 Remote pilot intervention
17.4 System data collection
17.5 Automation risk assessment
17.6 Automation system architecture
Annex A (informative) Software risk management
Annex B (informative) Electromagnetic environmental effects (E3)
Bibliography
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Foreword
Introduction
1 Scope
2 Normative references
3 Terms and definitions
4 Abbreviated terms
5 General design requirements for UAS
5.1 General
5.2 Function and reliability
5.2.1 Design
5.2.2 Components
5.3 Maintainability and supportability
5.3.1 Design
5.3.2 Documentation
5.3.3 Support
5.4 Fatigue durability
5.5 Aircraft identification features
5.6 Transportation, storage and packaging
6 Aircraft structures
6.1 Overview
6.2 Damage tolerance assessment
6.3 UA construction
6.4 Moving parts
6.5 Attached parts
7 Propulsion
7.1 Propulsion risk management
7.2 Engines and motors
7.2.1 General requirements
7.2.2 Mounting and installation
7.2.3 Combustion engines
7.2.4 Electric motors
7.2.5 Electronic speed controller (ESC) requirements
7.3 Thrust mechanisms
7.3.1 Propellers and rotors
7.3.2 Turbine and fans
8 Electrical systems
8.1 General
8.2 Electrical safety
8.3 Airborne electrical systems
8.4 Ground electrical systems
8.4.1 UAS electrical components on the ground
8.4.2 RPS power system
8.4.3 Labelling
9 Energy sources
9.1 Batteries
9.1.1 General
9.1.2 Protective measures
9.1.3 Precautions
9.2 Combustible fuels
9.3 Fuel cells
9.3.1 General requirements
9.3.2 General safety requirements
9.3.3 Protective measures
10 Equipment
10.1 Avionic equipment (general)
10.2 Flight control system (FCS)
10.2.1 General requirement
10.2.2 Flight control hardware
10.2.3 Flight control software
10.2.4 Course accuracy
10.2.5 Airspeed
10.3 Flight control actuators
10.4 Diagnostics
10.5 Navigation systems
10.5.1 General
10.5.2 Global Navigation Satellite System (GNSS) receiver
10.5.3 Real time kinematic (RTK) augmentation
10.5.4 Inertial measurement unit (IMU)
10.5.5 Magnetic compass
10.6 Attitude sensors
10.6.1 Altimeter
10.6.2 Airspeed sensor
10.6.3 Optical sensor
10.7 Hardware and software redundancy
10.8 Failure modes
11 C2 Link
11.1 Performance and design
11.2 Antenna module design
11.3 Operations
11.4 Monitoring
11.5 Protocol
11.6 Data features
11.6.1 General
11.6.2 UA status data
11.6.3 Delay requirements
11.7 Reliability requirements
11.8 Security requirements
12 Remote pilot station
12.1 General
12.2 Features
12.2.1 General
12.2.2 Data monitoring systems requirements
12.3 Design requirements
12.3.1 System
12.3.2 Structure
12.3.3 Human factors engineering and ergonomics design
12.4 Functional requirements
12.4.1 Mission planning
12.4.2 Data link control
12.4.3 Flight Control Commands
12.5 Displays
12.5.1 Instrumentation
12.5.2 Readability
12.5.3 Accuracy
12.5.4 Warnings, cautions, and advisories
12.5.5 Display/interface failures
12.5.6 Track and parameter display
12.5.7 C2 Link status display
12.5.8 Telemetry parameter record
12.6 Performance requirements
12.6.1 Environmental adaptability
12.6.2 Reliability
12.7 Safety
12.8 Collision avoidance (CA) systems
13 Payload
13.1 General requirements
13.2 Safety marking
13.3 Wiring design
13.4 Payload power supply
13.5 Storage requirement
14 Airworthiness
14.1 Documentation
14.1.1 Instructions
14.1.2 Manuals and handbooks
14.1.3 Procedural changes
14.2 Composition of an operator’s manual
14.2.1 Technical specifications
14.2.2 Flight performance
14.2.3 Aircraft weights
14.2.4 Flight control accuracy
14.2.5 Dimensions
14.2.6 Atmospheric and other environments adaptability
14.3 Electromagnetic compatibility considerations
14.4 Noise
14.5 Built-in test and monitoring
14.6 System safety program
14.6.1 Selection of design materials
14.6.2 Properties and processes
14.6.3 Mass properties
14.6.4 Corrosion
14.6.5 Material limitations
14.6.6 Fire hazards
14.6.7 Equipment separation
15 UAS software
15.1 Software architecture and design
15.2 Safety
15.3 Security
15.4 Software compliance
15.5 Software development life cycle
16 Other considerations
16.1 Ground equipment
16.2 Multi vehicle control
16.3 Jamming and spoofing
17 Automation
17.1 General
17.2 Software development lifecycle
17.3 Remote pilot intervention
17.4 System data collection
17.5 Automation risk assessment
17.6 Automation system architecture
Annex A (informative) Software risk management
Annex B (informative) Electromagnetic environmental effects (E3)
Bibliography