小型空射无人飞行器设计与试验

doi:10.7527/S1000-6893.2023.28642

Abstract

Abstract:

A design scheme for a small-sized air-launched Unmanned Aerial Vehicle （UAV） system with a large aspect ratio is proposed in this paper for a typical long-range aerial reconnaissance mission. Constraints are as follows： 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 effectiveness 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， variations 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 design expectations.

Key words: air-launched UAV, system design, aerodynamic layout, folding and unfolding mechanism, verification test

CLC Number:

V279

Yafei LU, Qingyang CHEN, Peng WANG, Bo WANG, Zheng GUO. Design and experiment of a small air-launched UAV[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(15): 528642-528642.

Figures/Tables 17

Fig.1

Table 1

Fig.2

Table 2

Fig.3

Fig.4

Table 3

Overall aerodynamic performance simulated in different installation angles of wing

迎角/（°）	$C L$	$C D$
-1	0.215	0.020
0	0.330	0.029
1	0.445	0.036
2	0.565	0.040
3	0.683	0.043
4	0.801	0.050
5	1.089	0.058

Table 3

Fig.5

Table 4

Fig.6

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

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指标	数值
起飞重量/kg	4
载荷能力/kg	0.5
航时/h	1
平均续航速度/（m·s^-1）	25
典型工作高度，AGL^*/m	300
收纳尺寸/m	⌀0.12×0.914

指标	数值
机身长度/m	0.914
机翼翼展/m	1.6
机翼弦长/m	0.1
展弦比	16
机翼面积/m²	0.16
上反角/（°）	3
尾翼长度/m	0.28
尾翼弦长/m	0.05
尾翼夹角/（°）	84
尾力臂/m	0.5
平尾容量	0.6
垂尾容量	0.04

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Design and experiment of a small air-launched UAV

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