翼尖铰接组合式无人机气动建模方法及布局参数影响

doi:10.7527/S1000-6893.2023.29587

Abstract

Abstract:

The wingtip-hinged multi-body combined Unmanned Aerial Vehicle （UAV） represents a novel conceptual aircraft， comprising multiple individual unmanned aircraft interconnected through wingtip hinges and allowing for relative roll motion. It exhibits significant distinctions in layout parameters and flight dynamics characteristics compared to conventional aircraft， with the presence of aerodynamic coupling between individual unmanned aircraft. First， the state-space vortex lattice method is employed to derive the aerodynamic derivatives specific to this aircraft type. Then， utilizing the Newton-Euler equations， a flight dynamics model is established for trim calculation and stability analysis， elucidating its unstable compound motion flight modes dominated by relative roll motion. Lastly， an investigation is conducted on the influence of layout parameters on flight dynamics stability. The analysis shows that reducing the trim roll angle of individual unmanned aircraft and increasing the sweep angle can enhance flight stability， while an optimal distance between the wing and tail is found to improve flight stability. The research findings can provide guidance and reference for the design of wingtip-hinged multi-body combined UAVs.

Key words: flight dynamics, multi-body combined unmanned aerial vehicle, new concept aircraft, vortex lattice method, aerodynamics layout

CLC Number:

V221

Chao AN, Guixi HUO, Yang MENG, Changchuan XIE, Chao YANG. Aerodynamic modeling methods and influence of layout parameters for wingtip⁃hinged multi⁃body combined UAV[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(6): 629587.

Figures/Tables 32

Fig.1

Fig.2

Fig.3

Table 1

Fig.4

Fig.5

Fig.6

Fig.7

Table 2

Results of aerodynamic derivatives

气动导数	本文方法计算结果	ZONAIR计算结果
$C L α$	4.88	4.89
$C M y α$	-1.92	-1.86
$C Y β$	0.288	0.291
$C M x β$	-0.007 5	-0.007 2
$C M z β$	0.092	0.094
$C Y p$	0.02	0.02
$C M x p$	-0.536	-0.542
$C L q$	9.526	9.619
$C M y q$	-20.25	-20.21
$C Y r$	-0.199	-0.191
$C M z r$	-0.063	-0.065

Table 2

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Table 3

Table 4

Angular components in flight dynamics modes

模态

Δ ϕ 1

Δ ϕ 2

Δ θ 1

Δ θ 2

Δ ψ 1

Δ ψ 2

复合运动

模态1

-1

0.02

9×10^-4

复合运动

模态2

-1

0.015

8×10^-5

Table 4

Fig.13

Table 5

Angular velocity components in flight dynamics modes

模态	$Δ p 1$	$Δ p 2$	$Δ q 1$	$Δ q 2$	$Δ r 1$	$Δ r 2$
复合运动模态1	1.67	-1.67	-0.04	-0.04	-2×10^-3	-2×10^-3
复合运动模态2	-1.49	1.49	0.032	0.032	4×10^-4	4×10^-4

Table 5

Fig.14

Fig.15

Fig.16

Fig.17

Fig.18

Fig.19

Fig.20

Fig.21

Fig.22

Fig.23

Fig.24

Fig.25

Fig.26

Fig.27

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设计参数	数值	设计参数	数值
机翼展长/m	3.0	机翼弦长/m	0.27
副翼展长/m	1.0	副翼弦长/m	0.09
垂尾展长/m	0.24	垂尾弦长/m	0.12
平尾展长/m	0.96	平尾弦长/m	0.12
机翼翼型	NACA0012	平尾、垂尾翼型	NACA0012

阶数	模态	特征根	特征时间/s	模态特征
1~2	短周期模态	-3.791 5±1.593i	3.94	收敛
3	滚转模态	-1.673 4	0.41	收敛
4~5	荷兰滚模态	-0.297 0±0.726i	8.65	收敛
6	复合运动模态1	1.65	0.42	发散
7	复合运动模态2	-0.332 5	2.10	收敛
8~9	长周期模态	-0.000 1±0.011i	570.9	收敛

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Aerodynamic modeling methods and influence of layout parameters for wingtip⁃hinged multi⁃body combined UAV

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