小型空射无人飞行器设计与试验  

Design and experiment of a small air-launched UAV

作　　者：鲁亚飞 陈清阳[1] 王鹏[1] 王波[2] 郭正[1] LU Yafei;CHEN Qingyang;WANG Peng;WANG Bo;GUO Zheng(College of Aerospace Sciences and Engineering,National University of Defense technology,Changsha 410073,China;National Innovation Institute of Defense Technology,Chinese Academy of Military Science,Beijing 100171,China)

机构地区：[1]国防科技大学空天科学学院,长沙410073 [2]军事科学院国防科技创新研究院,北京100171

出　　处：《航空学报》2023年第15期314-324,共11页Acta Aeronautica et Astronautica Sinica

基　　金：国家级项目。

摘　　要：以典型长时区域空中侦察任务为背景,提出一种大展弦比小型空射无人飞行器系统设计方案;以起飞重量4 kg、航时1 h、载荷0.5 kg、收纳尺寸不大于ϕ0.120 m×0.914 m为指标约束,对空射无人飞行器的总体气动布局、折叠展开机构、气动参数仿真估算、关键分系统设计与选型等开展详细论述;采用试制的原理样机,开展空中发射试验,对设计空射无人机空中发射、快速机翼展开、巡航飞行等进行验证。结果表明,设计的空射无人机在发射过程中机翼、尾翼等机构能够迅速展开,巡航速度与设计值符合,滚转角、俯仰角等变化在可控范围内,发射过程中重量变化和扰动对载机的影响可控,有效飞行航时约为65 min,符合设计预期。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 ϕ0.120 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.

关 键 词：空射无人飞行器 系统设计 气动布局 折叠展开机构 验证试验 

分 类 号：V279[航空宇航科学与技术—飞行器设计]