HB 8736-2023 General requirements for civil vertical take-off and landing fixed-wing unmanned aircraft system
1 Scope
This document specifies construction, classification, functions, performance and test for verification requirements for civil vertical take-off and landing (VTOL) fixed-wing unmanned aircraft systems (UAS).
This document applies to civil vertical take-off and landing fixed-wing unmanned aircraft systems (hereinafter referred to as “VTOL UASs”) with a maximum take-off weight not greater than 150kg, and may apply to other types of UASs as a reference.
2 Normative references
The following normative documents contain provisions which, through reference in this text, constitute provisions 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.
GB/T 38152 Terminology for unmanned aircraft system
GB/T 38909 Electromagnetic compatibility requirements and test methods for civil small and light unmanned aircraft system
GB/T 38924
(all parts) Environmental test methods for civil small and light unmanned aircraft system
GB/T 38930 Requirements and test methods of the capability of wind resistance for civil small and light unmanned aircraft system
HB 7809 General technical requirements of propeller for aircraft
HB 8566 General requirements for multi-rotor of unmanned aircraft system
HB 8591 General requirements for light and small fix-wing unmanned aircraft system
3 Terms and definitions
For the purposes of this standard, the terms and definitions given in GB/T 38152 and the following apply.
3.1
vertical take-off and landing (VTOL) fixed-wing unmanned aircraft
fixed-wing unmanned aircraft that relies on its own power plant to take off and land vertically
3.2
mission payload weight
sum of the weight of the airborne equipment required to accomplish a specific mission, and the weight of the energy sources, auxiliary devices, additional mounted structures, etc., required for its proper functioning
3.3
power source weight
weight of the fuel or power cell required for power output
3.4
mission take-off weight
sum of the weight of the empty aircraft, the mission payload weight and the power source weight
Note: It is classified into the maximum take-off weight and normal take-off weight by load.
3.5
fixed-wing mode
process of controlling the attitude, speed and position of a VTOL UAS which is fulfilled mainly relying on the flight control surfaces and horizontal flight propulsion of the unmanned aircraft
3.6
transition mode
process of switching between the VTOL mode and the fixed-wing mode
3.7
vertical take-off and landing (VTOL) mode
process of controlling the attitude, horizontal position and altitude of a VTOL UAS which is fulfilled mainly relying on the forces and moments generated by the VTOL propulsion
4 General requirements
4.1 Construction
The VTOL UAS mainly consists of the following components:
Foreword i
1 Scope
2 Normative references
3 Terms and definitions
4 General requirements
4.1 Construction
4.2 Classification
4.3 Functions
4.4 Dimensions
4.5 Weights
4.6 Flight performance
4.7 Reliability
4.8 Maintainability
4.9 Testability
4.10 Safety
4.11 Guards
4.12 Environmental adaptability
4.13 Electromagnetic compatibility
5 Detailed requirements
5.1 Unmanned aircraft platform
5.2 Data link
5.3 Mission payload
5.4 Ground C2
5.5 Guards
6 Test for verification
6.1 Purpose
6.2 Test classification
6.3 Test items
6.4 Acceptance criteria
