串列翼货运无人机大攻角气动与操稳特性

doi:10.7527/S1000-6893.2024.31056

Abstract

Abstract:

To achieve accurate cargo airdrop and low-speed undamaged landing in limited area， the high angle of attack aerodynamic and operational characteristics of tandem wing cargo UAV are researched. Considering the aerodynamic nonlinearity at high angle of attack and the strong coupling of front and rear wings of tandem wing UAV， the Detached Eddy Simulation （DES） method is used to analyze the nonlinear aerodynamic characteristics at high angle of attack. The lift coefficient， drag coefficient and pitch moment of each component and aerodynamic center are calculated with the variation of the angle of attack. The influence of different fuselage cross sections on the longitudinal stability of the UAV is further studied. The coupling mechanism of tandem wing is analyzed according to the distribution characteristics of wing surface pressure and the structure of surrounding flow field. A manipulation scheme for the full-motion rear wing at high angle of attack in the tandem wing UAV is proposed. The results show that the static stability of the square fuselage cross section is more stable than the round cross section at high attack angle. In the wide range of attack angle from 0° to 50°， there is aerodynamic coupling between the front and rear wings. The pressure distribution of the rear wing is affected by the aerodynamic coupling between the front and rear wings， and the lift loss of the rear wing is up to 32%. The full-motion rear wing increases the controllable angle of attack to 50°， which can provide sufficient control torque for deep stall landing at high angle of attack.

Key words: tandem wing layout, high angle of attack, aerodynamics, quasi-balanced glide, full-motion rear wing, UAV

CLC Number:

V212.11

Pengqian YANG, Yutong CHEN, Junhui LIU, Jiehao YANG, Jiayuan SHAN, Shijun SUN. Aerodynamic and operational characteristics analysis for tandem wing cargo UAV at high angle of attack[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(9): 131056.

Figures/Tables 29

Table 1

Fig.1

Fig.2

Fig.3

Table 2

Fig.4

Table 3

Grid independence verification

网格数/10⁴	$C L$	$C D$	$η L / %$	$η D / %$
1 000	1.258	0.958	3.3	3.8
1 500	1.301	0.923
2 000	1.303	0.928	0.2	0.5

Table 3

Table 4

Time step independence verification

时间步长/s	$C L$	$C D$	$η L / %$	$η D / %$
$1 × 10 - 2$	1.301	0.923
$5 × 10 - 3$	1.311	0.930	0.7	0.8

Table 4

Fig.5

Fig.6

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

Table 5

Fig.14

Fig.15

Fig.16

Fig.17

Table 6

Static contours of different chord sections of two models

x/C	0.2	0.5	0.8
$α = 0 °$ （SH模型）
$α = 0 °$ （NM模型）
$α = 10 °$ （NM模型）
$α = 50 °$ （NM模型）

Table 6

Fig.18

Fig.19

Fig.20

Fig.21

Fig.22

Fig.23

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几何及气动参数	数值
机身长度/mm	4 837
前后翼高度差/mm	200
前后翼间距/mm	1 975
前/后翼安装角/（°）	0
机身宽度/mm	600
机身高度/mm	600
来流马赫数Ma	0.1

模型名称	示意图
NM模型
CM模型
SQ模型
SH模型

攻角/（°）	NM模型	CM模型
10
40

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Aerodynamic and operational characteristics analysis for tandem wing cargo UAV at high angle of attack

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