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Flight test requirements for flight performance of civil large and medium fixed-wing unmanned aircraft
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Basic data
| Standard ID | GB/T 43504-2023 (GB/T43504-2023) |
| Description (Translated English) | Flight test requirements for flight performance of civil large and medium fixed-wing unmanned aircraft |
| Sector / Industry | National Standard (Recommended) |
| Classification of Chinese Standard | V35 |
| Classification of International Standard | 49.020 |
| Word Count Estimation | 18,172 |
| Date of Issue | 2023-12-28 |
| Date of Implementation | 2024-04-01 |
| Issuing agency(ies) | State Administration for Market Regulation, China National Standardization Administration |
Similar standards
GB/T 36258|GB 46860|GB/T 43504-2023: Flight test requirements for flight performance of civil large and medium fixed-wing unmanned aircraft
---This is a DRAFT version for illustration, not a final translation. Full copy of true-PDF in English version (including equations, symbols, images, flow-chart, tables, and figures etc.) will be manually/carefully translated upon your order.
ICS 49:020
CCSV35
National Standards of People's Republic of China
Civil large and medium-sized fixed-wing UAV flight performance flight
Test requirements
fixed-wingunmannedaircraft
2024-04-01 Implementation
State Administration for Market Regulation
Released by the National Standardization Administration Committee
Table of contents
PrefaceⅠ
1 Scope 1
2 Normative references 1
3 Terms and Definitions 1
4 General requirements 1
4:1 Test flight conditions 1
4:2 Test flight object 2
4:3 Documents and information 2
4:4 Personnel requirements 2
4:5 Testing and Modification 2
4:6 Data processing 2
4:7 Result evaluation 3
5 Detailed requirements 3
5:1 Airspeed System Calibration 3
5:2 Takeoff performance 3
5:3 Climb performance 5
5:4 Maximum flight speed 6
5:5 Minimum level flight speed 7
5:6 Ceiling 7
5:7 Battery life performance 8
5:8 Horizontal acceleration and deceleration performance 9
5:9 Hovering performance10
5:10 Decline performance11
5:11 Landing performance12
5:12 Task performance13
6 Test flight report 14
Foreword
This document complies with the provisions of GB/T 1:1-2020 "Standardization Work Guidelines Part 1: Structure and Drafting Rules of Standardization Documents"
Drafting:
Please note that some contents of this document may involve patents, and the issuing organization of this document does not assume the responsibility for identifying patents:
This document is proposed and coordinated by the National Aircraft Standardization Technical Committee (SAC/TC435):
This document was drafted by: China Flight Test Research Institute, China Aviation Comprehensive Technology Research Institute, China Aviation Industry Corporation Shenyang Flying
Aircraft Design Institute, Xi'an Aisun Technology Group Co:, Ltd:, Aison UAV Testing Jingbian Co:, Ltd:, Aviation Industry Corporation of China
Xi'an Aircraft Design Institute:
The main drafters of this document: Zhang Peitian, Yin Wenqiang, Hu Yingdong, Wu Xinlong, Shu Zhenjie, An Ran, Wang Feng, Zhang Zejing, Tang Tang, Yun Zhengping,
Zhong Hai, Pan Jihui, Li Jian, He Zhengyan, Zhu Xiaoping, Shi Guichao, Wang Jiuyuan, Li Lijin, Niu Zhenzhong, Wang Wei:
Civil large and medium-sized fixed-wing UAV flight performance flight
Test requirements
1 Scope
This document specifies the content, purpose, conditions, implementation, data processing and results of civil large and medium-sized fixed-wing UAV flight performance flight tests:
fruit assessment and other requirements:
This document applies to the flight performance of civilian large and medium-sized fixed-wing UAVs (hereinafter referred to as UAVs) with a maximum take-off weight of not less than 150kg:
The performance flight test, the flight performance test of pure electric UAVs and other types of UAVs shall be carried out as a reference:
2 Normative reference documents
The contents of the following documents constitute essential provisions of this document through normative references in the text: Among them, the dated quotations
For undated referenced documents, only the version corresponding to that date applies to this document; for undated referenced documents, the latest version (including all amendments) applies to
this document:
GB/T 38152 Unmanned aircraft system terminology
3 Terms and definitions
The terms and definitions defined in GB/T 38152 and the following apply to this document:
3:1
After the engine is installed, its power is lost compared with the bench power:
Note: The installed power loss varies with the engine power status and the flight status of the drone:
3:2
accelerationmethod
A test flight method to determine the acceleration performance, climb performance, maximum flight speed and other subjects of the UAV using horizontal acceleration:
3:3
take-offweight take-offweight
The amount of fuel required to complete the mission and the total weight of the drone when effectively loaded:
Note: Unless otherwise specified, takeoff weight generally refers to the weight of the drone before the engine is started:
3:4
normal flight weightnormalflightweight
Under specified conditions, the drone carries a flight weight of 50% of the fuel inside the aircraft:
4 General requirements
4:1 Test flight conditions
Test flight site conditions (altitude, runway) and environmental conditions (atmospheric temperature, atmospheric pressure, atmospheric humidity, wind speed, wind direction, visibility
etc:) should comply with the relevant provisions in the technical requirements for unmanned aerial vehicle systems:
...
