共轴双旋翼/尾推桨/传动耦合系统动力学建模与固有特性分析

doi:10.7527/S1000-6893.2023.28945

Abstract

Abstract:

High-speed helicopters use technologies such as advancing blade， reduced rotor rotation speed， and auxiliary propeller to achieve high-speed flight. The coupled system formed by coaxial rigid dual-rotor， variable speed drive train system， and high-power output tail propeller brings new challenges to traditional helicopter torsional vibration analysis. Firstly， a new modeling strategy based on the transfer matrix method is innovatively proposed to address the problem of complex multi-mode coupling torsional vibration system of high-speed helicopters. Compared to the modeling strategy of conventional finite element method， the present method does not require the equivalent processing of the drive train system， nor does it require the derivation of the overall governing equations based on Hamilton’s principle. System governing equations can be directly obtained according to the topology structure of the system. In addition， a virtual geared branch element is innovatively introduced to decouple the topology of the drive train system into multiple independent chain systems， further significantly reducing the difficulty of modeling. Finally， the coupled torsional vibration dynamics of high-speed helicopters under different working conditions is studied based on the proposed method.

Key words: high-speed helicopter, torsional vibration, transfer matrix method, drive train system, dynamic models

CLC Number:

V241

Bo LI, Xiao WANG. Dynamic modeling and modal analysis of coaxial rotors/auxiliary propeller/drive train coupled system[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(9): 528945-528945.

Figures/Tables 23

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Fig.2

Fig.3

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Fig.5

Fig.6

Fig.7

Fig.8

Table 1

Fig.9

Fig.10

Table 2

Table 3

Fig.11

Fig.12

Table 4

Table 5

Torsional stiffness of shaft

序号	（2），（5），（8）	（11）	（14）
$K I l$ /（10⁶N·m·rad^-1）	0.15	2	6

Table 5

Table 6

Table 7

Fig.13

Fig.14

Fig.15

Table 8

References 23

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单元编号	含义	单元类型
1	发动机	刚性圆盘
2、4、6、8、10	传动轴	无质量轴
3	发动机减速器	齿轮单元
5	主减速器	齿轮单元
7	尾桨	刚性圆盘
9、11	桨毂	刚性圆盘
12~15、16~19	旋翼桨叶	梁单元

梁单元编号	展向位置/m	线密度/ （kg·m^-1）	桨叶摆振刚度/ （10⁶ N·m²）
1	~0.3	55	8.0
2	~0.5	40	10.0
3	~0.7	20	4.0
4	~1.2	15	1.5
5	~4.5	10	1.0
6	~4.8	6	0.6
7	~5.0	5	0.5

转速/ （r·min^-1）	方法	1阶	2阶	3阶	4阶
210	本文方法	10.924 4	61.883 4	159.557 3	289.764 1
210	FEM	10.924 4	61.841 4	159.520 9	289.732 2
350	本文方法	11.491 2	63.108 5	160.813 6	291.072 3
350	FEM	11.488 8	63.015 6	160.758 9	291.005 8

飞行状态	计算方法	ω₁/Hz	ω₂/Hz	ω₃/Hz	ω₄/Hz	ω₅/Hz	ω₆/Hz
悬停	本文方法	5.356	11.491	13.705	30.693	34.316	63.109
悬停	FEM	5.325	11.285	13.418	30.669	33.630	64.409
低速飞行	本文方法	5.323	11.491	11.766	22.682	30.701	34.338
低速飞行	FEM	5.388	11.594	12.096	22.619	30.958	33.843
高速飞行	本文方法	5.121	8.929	10.924	22.310	29.511	33.189
高速飞行	FEM	5.053	8.761	11.083	21.927	29.509	33.635

飞行状态	部件	1阶	2阶	3阶	4阶	5阶	6阶
悬停	发动机	-0.449 7	-1.000 0	-1.000 0	-0.066 9	-0.182 4	-0.876 9
	尾桨	0.000 0	0.000 0	0.000 0	0.000 0	0.000 0	0.000 0
	上旋翼	1.442 7	0.876 9	0.838 6	1.032 6	0.095 5	1.000 0
	下旋翼	-0.410 1	0.876 9	0.741 6	-0.017 1	1.065 6	1.000 0
低速飞行	发动机	-0.427 1	-0.711 7	-0.687 8	-0.492 3	-0.076 3	-0.195 9
	尾桨	-0.033 9	-0.347 1	-0.364 4	1.354 0	0.062 2	0.103 7
	上旋翼	1.420 5	0.652 9	0.629 1	0.264 5	1.037 1	0.102 1
	下旋翼	-0.378 1	0.652 9	0.616 4	0.175 7	-0.019 6	1.070 3
高速飞行	发动机	-0.326 7	-0.826 2	-0.687 5	-0.425 7	-0.031 1	-0.072 3
	尾桨	-0.023 9	-0.209 8	-0.314 1	1.310 0	0.029 0	0.044 2
	上旋翼	1.322 0	0.891 1	0.685 9	0.217 6	1.016 4	0.042 8
	下旋翼	-0.253 7	1.196 8	0.685 9	0.136 4	-0.008 4	1.029 0

Dynamic modeling and modal analysis of coaxial rotors/auxiliary propeller/drive train coupled system

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