Design and experiment of a small air-launched UAV

被引：0
|
作者：
Lu Y. [1 ]
Chen Q. [1 ]
Wang P. [1 ]
Wang B. [2 ]
Guo Z. [1 ]
机构：
[1] College of Aerospace Sciences and Engineering, National University of Defense technology, Changsha
[2] National Innovation Institute of Defense Technology, Chinese Academy of Military Science, Beijing
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2023年 / 44卷 / 15期
关键词：
aerodynamic layout; air-launched UAV; folding and unfolding mechanism; system design; verification test;
D O I：
10.7527/S1000-6893.2023.28642
中图分类号：
学科分类号：
摘要：
A design scheme for a small-sized air-launched Unmanned Aerial Vehicle（UAV）system with a large as⁃ pect ratio is proposed in this paper for a typical long-range aerial reconnaissance mission. Constraints are as fol⁃ lows：takeoff weight of 4 kg，endurance time of one hour，payload of 0. 5 kg，and folded dimension not more than ∅ 0. 120 m×0. 914 m. The following details are discussed：the overall aerodynamic layout of the air-launched UAV，folding and unfolding mechanism，the simulation estimation of aerodynamic parameters，the design and selection of key subsystems，etc. A principle prototype is produced，and air launch flight test is carried out to verify the effective⁃ ness of the UAV’s air launch，rapid wing deployment，and cruise flight. Test result shows that the folded wing and tail wing can be unfolded rapidly during the launch process，the cruising speed is conformed to the design value，varia⁃ tions in roll angle and pitch angle are within controllable ranges，the effect of weight changes and airflow disturbance on carriers during launching is controllable，and the effective flight duration is approximately 65 min，which meets de⁃ sign expectations. © 2023 AAAS Press of Chinese Society of Aeronautics and Astronautics. All rights reserved.
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