集成多旋翼气动干扰的UAM飞行动力学模型

doi:10.7527/S1000-6893.2025.31280

Abstract

Abstract:

To address the challenge of strong aerodynamic interference in multi-rotor electric Vertical Take-Off and Landing （eVTOL） aircraft and the difficulty of quickly and efficiently analyzing its impact on flight performance and flight quality， an Urban Air Mobility （UAM） flight dynamics model integrated with multi-rotor aerodynamic interference is developed. First， by combining classical vortex theory and dynamic inflow model， a dynamic inflow model suitable for flight dynamics analysis of multirotor is established， accounting for the effects of coupling between rotor flapping and rigid-body motion， thus forming a flight dynamics model that incorporates multirotor aerodynamic interference. Then， the accuracy of this model is validated through comparison with data from international literature， and the impact of multirotor aerodynamic interference on the equilibrium characteristics and required power characteristics of the aircraft is analyzed. Finally， a small-disturbance linearized model is used to study the effect of multirotor aerodynamic interference on the stability of the aircraft. The results show that aerodynamic interference between rotors mainly affects the flight performance and handling qualities of the aircraft in low- to medium-speed flight conditions. Aerodynamic interference slightly reduces the required power of the front rotors while significantly increasing that of the rear rotors， substantially altering the aircraft’s longitudinal control characteristics. Multirotor aerodynamic interference significantly enhances the speed and yaw static stability during hover/low-speed flight and improves the lateral static stability in medium-speed flight； however， it causes the angle-of-attack static stability to become unstable， leading to a deterioration in dynamic stability for the heave and spiral modes.

Key words: quadrotor aircraft, aerodynamic interference, flight dynamics, static stability, dynamic stability

CLC Number:

V212.4

Yeping WANG, Honglei JI, Qingyu KANG, Haoxuan DENG, Chang WANG. Integration of multirotor aerodynamic interference in UAM flight dynamics model[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(11): 531280.

Figures/Tables 15

Fig.1

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Fig.4

Table 1

Primary parameters of quadrotor［29］

参数	取值
全机重量/ $k g$	600.924
绕 $x$ 轴转动惯量/（ $k g ⋅ m 2$ ）	1 056.82
绕 $y$ 轴转动惯量/（ $k g ⋅ m 2$ ）	1 153.57
绕 $z$ 轴转动惯量/（ $k g ⋅ m 2$ ）	1 395.83
重心位置/m	（0.120 8， 0， 0.274 3）
旋翼实度	0.065
旋翼半径/m	1.981 2
旋翼转速/（rad·s^-1）	69.230 8
桨叶扭度/（°）	-12
桨叶绕挥舞铰质量静矩	4.860 5
桨叶绕挥舞铰惯性矩	6.321 0
翼型阻力系数	0.01
翼型升力线斜率/rad^-1	5.73
前旋翼横向间距/m	2.7R
后旋翼横向间距/m	2.7R
前、后旋翼纵向间距/m	2.7R
前、后旋翼垂向间距/m	0.35R

Table 1

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Fig.6

Fig.7

Fig.8

Fig.9

Fig.10

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Fig.14

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Integration of multirotor aerodynamic interference in UAM flight dynamics model

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