ICS 49.020
CCS V 35
National Standard of the People’s Republic of China
GB 42590-2023
Safety requirements for civil unmanned aircraft system
民用無人駕駛航空器系統(tǒng)安全要求
(English translation)
Issue date: 2023-05-23 Implementation date: 2024-06-01
Issued by the State Administration for Market Regulation
the Standardization Administration of the People's Republic of China
Safety requirements for civil unmanned aircraft system
1 Scope
This document specifies the safety requirements for civil unmanned aircraft system products (hereinafter referred to as "unmanned aircrafts") and describes the corresponding test methods.
This document is applicable to the development, production, delivery and use of micro unmanned aircrafts, light unmanned aircrafts and small unmanned aircrafts other than model aircrafts.
2 Normative references
The following documents contain requirements 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 3222.2-2022 Acoustics - Description, measurement and assessment of environmental noise - Part 2: Determination of sound pressure levels
GB/T 17626.2-2018 Electromagnetic compatibility - Testing and measurement techniques - Electrostatic discharge immunity test
GB/T 20441.4-2006 Measurement microphones - Part 4: Specifications for working standard microphones
GB/T 35018-2018 Classification and grading for civil unmanned aircraft system
GB/T 38152-2019 Terminology for unmanned aircraft system
GB/T 38909-2020 Electromagnetic compatibility requirements and test methods for civil small and light unmanned aircraft system
GB/T 38930-2020 Requirements and test methods of the capability of wind resistance for civil small and light unmanned aircraft system
GB/T 41300-2022 Unique product identification code for civil unmanned aerial vehicle
3 Terms, definitions and abbreviations
3.1 Terms and definitions
For the purposes of this document, the terms and definitions given in GB/T 35018-2018 and GB/T 38152-2019 and the following apply.
3.1.1
unmanned aircraft; UA
aircraft without an onboard pilot and with its own power system
Note: Unmanned aircrafts are classified into micro, light, small, medium and large types.
3.1.2
micro unmanned aircraft
unmanned aircraft with an empty weight of less than 0.25kg, a maximum absolute flight altitude of no more than 50m and a maximum level flat speed of no more than 40km/h, which is equipped with radio transmitting equipment conforming to the technical requirements of having micro-power and limited signal range, and can be manually intervened in the control at any time during the whole flight
3.1.3
light unmanned aircraft
unmanned aircraft with an empty weight of no more than 4kg, a maximum take-off weight of no more than 7kg and a maximum level flat speed of no more than 100km/h, which features the airspace keeping capacity and reliable under-surveillance capacity in line with airspace management requirements, and can be manually intervened in the control at any time during the whole flight
Note: Excluding micro unmanned aircrafts.
3.1.4
small unmanned aircraft
unmanned aircraft with an empty weight of no more than 15kg and a maximum take-off weight of no more than 25kg, which features the airspace keeping capacity and reliable under-surveillance capacity in line with airspace management requirements, and can be manually intervened in the control at any time during the whole flight
Note: Excluding micro and light unmanned aircrafts.
3.1.5
electric fence
function of the unmanned aircraft to notify or warn the unmanned aircraft operator or to automatically execute a flight plan when it detects that it is approaching, entering, or located at the appropriate geographic range based on its position information and geographic range data
3.2 Abbreviations
For the purposes of this document, the following abbreviations apply.
EIRP: Effective Isotropic Radiated Power
ID: Identity
RMS: Root Mean Square
UTC: Coordinated Universal Time
4 Safety requirements
4.1 Electric fence
Light and small unmanned aircrafts shall provide their operators with a notification or warning or automatically execute a flight plan upon detecting a potential or ongoing conflict with a specific geographic range. In this case, one or more flight plans may be chosen, such as preventing takeoff, limiting flying altitude, hovering, landing, and returning.
4.2 Remote identification
Light and small unmanned aircrafts shall actively submit identification information to the integrated supervision service platform through the network while carrying out flight activities. They shall automatically broadcast the identification information via WLAN (Wi-Fi) or Bluetooth during flight. Remote identification performed by unmanned aircrafts shall meet the requirements of Annex A.
4.3 Emergency disposal
Light and small unmanned aircrafts shall have one or more disposal capacities such as hovering/circling around in the air, returning, landing and opening the parachute when encountering unexpected situations such as data link interruption or loss and power/fuel shortage during flight. In case of navigation failure, they shall provide the unmanned aircraft operator with a notification or warning by means of the operating software or other means as described in the product manual.
4.4 Structural strength
The structural strength of unmanned aircrafts shall meet the following requirements:
a) The structure of the unmanned aircraft shall have sufficient strength and stiffness to withstand various specified loads, without undergoing harmful deformation;
b) The main load-bearing structure of the unmanned aircraft shall not be damaged when it bears a load of 1.33 times the maximum take-off weight.
4.5 Airframe structure
4.5.1 Sharp edges
The airframe and component structures of unmanned aircrafts shall be free from any sharp edge that may cause harm to the user in normal use or maintenance.
4.5.2 Blades
For micro and light unmanned aircrafts without blade protectors, the blades shall be such designed to minimize scratches to personnel. Blades shall not be made of metal materials, and they shall meet any of the following requirements:
a) In case of asymmetric blades, the tip leading edge radius (R1) shall be greater than 1mm, as shown in Figure 1a);
b) The radius of circular blade tip (R2) shall be greater than 1mm, as shown in Figure 1b);
c) The square tip chord (A) shall be greater than 2mm or the ratio of tip chord to maximum tip chord (B) shall be greater than 30%, whichever is larger, as shown in Figure 1c);
d) The blades shall be foldable when colliding with each other;
e) For fixed wings, the blades shall be installed at the tail to prevent cuts caused by collision.
4.6 Complete aircraft dropping
For micro and light unmanned aircrafts powered by Li-ion batteries, they shall meet the following requirements in the event of complete aircraft dropping:
a) Adjust the battery pack of the unmanned aircraft to 30%±2% of the full power, and then let the unmanned aircraft fall freely and vertically from a height of 10m (see Figure 2), the unmanned aircraft shall not explode or catch fire;
b) If the unmanned aircraft is equipped with drop protection measures such as parachutes, record the maximum drop speed of the unmanned aircraft when the parachute is open, convert this speed into the free-fall height (known as the equivalent altitude) of the unmanned aircraft without protection measures, and then carry out the drop test according to the equivalent altitude.
Foreword III
1 Scope
2 Normative references
3 Terms, definitions and abbreviations
3.1 Terms and definitions
3.2 Abbreviations
4 Safety requirements
4.1 Electric fence
4.2 Remote identification
4.3 Emergency disposal
4.4 Structural strength
4.5 Airframe structure
4.6 Complete aircraft dropping
4.7 Power source system
4.8 Controllability
4.9 Error-proofing
4.10 Detection and avoidance
4.11 Data link protection
4.12 Electromagnetic compatibility
4.13 Wind resistance
4.14 Noise
4.15 Light
4.16 Identification
4.17 Instruction manual
5 Test methods
5.1 Electric fence
5.2 Remote identification
5.3 Emergency disposal
5.4 Structural strength
5.5 Airframe structure
5.6 Complete aircraft dropping
5.7 Power source system
5.8 Controllability
5.9 Error-proofing safety test
5.10 Detection and avoidance
5.11 Data link protection
5.12 Electromagnetic compatibility
5.13 Wind resistance
5.14 Noise test
5.15 Light
5.16 Identification
5.17 Instruction manual
6 Implementation of this standard
Annex A (Normative) Remote identification
A.1 Requirements for remote identification
A.2 Test methods
