基于涡管模型的倾转四旋翼气动干扰快速分析

doi:10.7527/S1000-6893.2024.30705

Abstract

Abstract:

In order to address the challenge of accurately and rapidly evaluating the aerodynamic interference between rotors in the overall design and flight dynamics modeling of quad-tiltrotor aircraft， a fast analysis method for multirotor aerodynamic interference based on the vortex tube wake model is developed. Based on the classical vortex theory， the wake vortex system of each rotor is abstracted as a semi-infinite vortex tube， and a semi-analytical solution for the induced velocity at any point in space by rotor vortex tubes is derived. This forms an efficient computation method for aerodynamic interference between multirotor. Combined with the dynamic inflow model accounting for rotor self-induced velocity， an accurate and efficient model for calculating the induced velocity in multirotor is established. Based on this， the model is validated using wind tunnel test results of thrust-power performance curves for coaxial and tandem rotors. Finally， the aerodynamic interference characteristics between the four rotors of a scaled model of a quad-tiltrotor aircraft are analyzed during the helicopter mode and tilt transition mode. The results show that the model can capture the influence of vertical and horizontal spacing on aerodynamic interference between rotors relatively and accurately， making it suitable for fast analysis of multirotor aerodynamic interference. The aerodynamic interference characteristics between rotors near the helicopter mode of quad-tiltrotor aircraft vary significantly. A reasonable aerodynamic layout and rotor rotation direction design can effectively improve the induced velocity of the disturbed rotor and the load distribution on the rotor disc.

Key words: quad-tiltrotor, vortex tube wake, aerodynamic interference, induced velocity, flight dynamics

CLC Number:

V212.4

Yeping WANG, Honglei JI, Pan ZHOU, Yi YE. Fast analysis of aerodynamic interference for quad-tiltrotor based on vortex tube model[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(2): 130705.

Figures/Tables 24

Fig.1

Fig.2

Fig.3

Table 1

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Fig.5

Fig.6

Table 2

Main parameters of tandem rotors

参数	数值
旋翼转速/（rad·s^-1）	$40 π$
旋翼半径/m	1.02
旋翼实度	0.037
翼型升力线斜率	5.73
翼型零升力阻力系数	0.008
翼型二次升力阻力系数	0.4
诱导功率修正因子	1.2
风洞试验1纵/垂向间距	1.8R/0.2R
风洞试验2纵/垂向间距	2.05R/0.4R

Table 2

Fig.7

Fig.8

Fig.9

Table 3

Fig.10

Fig.11

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Fig.13

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Fast analysis of aerodynamic interference for quad-tiltrotor based on vortex tube model

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References 38

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参数	数值
旋翼间距/m	0.3
旋翼转速/（rad·s^-1）	81.472 0
旋翼半径/m	2
旋翼实度	0.1
翼型升力线斜率/rad^-1	5.73
翼型零升力阻力系数	0.01
翼型二次升力阻力系数	0.3
诱导功率修正因子	1.05

参数	数值
旋翼转速/（rad·s^-1）	211.90
旋翼半径/m	0.58
旋翼实度	0.093 8
翼型升力线斜率	5.73
翼型零升力阻力系数	0.011 5
翼型二次升力阻力系数	0.4
诱导功率修正因子	1.15
前翼横向间距	3.2R
后翼横向间距	4.2R
前后翼纵向间距	2R
前后翼垂向间距	0.2R