高支柱起落架走步振动与稳定性分析

doi:10.12382/bgxb.2023.0629

摘要/Abstract

摘要：

为改善装备碳陶刹车盘的高支柱起落架走步振动问题,对走步规律进行了深入分析。阐述走步机理,碳陶刹车盘摩擦特性引起的负斜率刹车力矩会向起落架航向系统引入负阻尼,引起走步振动的发散。基于3自由度走步动力学方程,开展了刹车力矩参数、起落架结构参数以及机身初始速度对走步振动的影响研究,定义了走步振动发散的临界状态,并提出刹车压力随刹车动静盘相对转速减小的走步控制策略。仿真结果表明:刹车盘摩擦系数负斜率绝对值的减小,刹车压力的降低,支柱刚度和阻尼的增大都可增加走步系统的稳定性,刹车盘摩擦的最小值提高至0.186可确保飞机以任意速度刹车走步稳定;刹车压力下降的斜率随刹车速度的不同而改变,飞机从144km/h开始刹车,刹车压力降低24.7%可使走步振动收敛,轮轴航向加速度峰值降低77.23%。

关键词: 起落架走步, 刹车振动, 碳陶刹车盘, 负斜率刹车力矩

Abstract:

In order to improve the gear walk instability of high strut landing gear equipped with carbon ceramic brake discs, the rule of gear walk is analyzed thoroughly. The gear walk mechanism is explained. The braking torque with negative slope caused by the friction characteristics of the carbon ceramic brake disc can introduce negative damping to the longitudinal system of the landing gear, which causes the divergence of walking vibration. The effects of the brake torque parameters, the structural parameters of landing gear and the initial velocity of aircraft on gear walk are studied. Finally, a gear walk control strategy for reducing the braking pressure with the relative angular velocity of brake stators and rotors is proposed. The result shows that the decrease in the absolute value of negative slope of brake disc friction coefficient and the braking pressure, as well as the increase in the longitudinal stiffness and damping of strut will all contribute to the stability of gear walk. The stable gear walk can be achieved at any initial velocity of aircraft by increasing the minimum friction coefficient of brake disc to 0.186. The dropping slope of braking pressure is closely related to the initial velocity of aircraft. The simulated results of aircraft braking from 144km/h show that a 24.7% dropping in braking pressure can lead to the convergence of unstable gear walk and a 77.23% reduction in the longitudinal acceleration peak of wheel axle.

Key words: gear walk, brake vibration, carbon ceramic brake disc, braking torque with negative slope

中图分类号:

V214.3⁺3

杜晓琼, 李斌, 罗琳胤, 刘木君, 杨荣. 高支柱起落架走步振动与稳定性分析[J]. 兵工学报, 2024, 45(8): 2793-2805.

DU Xiaoqiong, LI Bin, LUO Linyin, LIU Mujun, YANG Rong. Analysis of Walking Vibration and Stability of High Strut Landing Gear[J]. Acta Armamentarii, 2024, 45(8): 2793-2805.

图/表 21

图1 起落架走步危害

Fig.1 Hazards of gear walk

图2 3自由度走步模型

Fig.2 3-DOF gear walk model

图3 结合系数和滑移率关系

Fig.3 Relationship curve of ground adhesion coefficient and slip rate

表1 高支柱起落架结构及刹车系统参数

Table 1 Structure and brake system parameters of high strut landing gear

参数	数值	参数	数值
m_a/kg	2×10⁴	R_g/m	0.49
m_g/kg	760	F_N/N	2.07×10⁵
m_ω/kg	280	p_bmax/MPa	10
L_g/m	2.7	S_p/m²	0.01
J_g/(kg·m²)	1.86×10³	N_m	8
J_ω/(kg·m²)	33	R/m	0.19
k_g/(N·m·rad^-1)	2.3×10⁷	r/m	0.12
c_g/(N·m·rad^-1)	7×10³

图4 轮轴航向加速度试飞数据

Fig.4 Flight test curve of longitudinal acceleration of wheel axle

图5 碳陶盘刹车力矩台架试验结果

Fig.5 Test curve of braking torque of carbon ceramic brake discs

图6 刹车盘摩擦系数与动静盘相对转速

Fig.6 Change of the friction coefficient of brake disc with the relative angular velocity of brake stators and rotors

图7 起落架走步等效模型

Fig.7 Equivalent model of landing gear walk

图8 刹车压力随时间变化

Fig.8 Braking pressure-time

图9 刹车盘摩擦系数斜率对轮轴航向加速度的影响

Fig.9 The influence of friction coefficient slope on the longitudinal acceleration of wheel axle

图10 刹车压力对轮轴航向加速度的影响

Fig.10 The influence of braking pressure on the longitudinal acceleration of wheel axle

图11 刹车压力上升速率

Fig.11 Loading rate of braking pressure

图12 机身初始速度对轮轴航向加速度的影响

Fig.12The influence of initial aircraft velocity on the longitudinal acceleration of wheel axle

图13 支柱刚度和阻尼系数对轮轴航向加速度的影响

Fig.13 The influence of strut stiffness and damping coefficient on the longitudinal acceleration of wheel axle

图14 临界值与机身初始速度关系

Fig.14 Relationship between the critical value and the initial velocity of aircraft

表2 临界值bminc与机身初始速度

Table 2 Critical value bminc and initial velocity of aircraft

v_a0/(km·h^-1)	36	54	72	90	108	126	144
b_minc	0.186	0.181	0.176	0.174	0.170	0.167	0.164

图15 刚度、阻尼系数增大20%对应的bminc与机身初始速度关系

Fig.15 The curve between bminc and the initial velocity of the fuselage corresponding to a 20% increase in stiffness and damping coefficient

图16 临界刹车力矩与动静盘相对转速

Fig.16 Curves of the critical braking torque and the relative angular velocity of brake stators and rotors

Fig.17 刹车压力控制系统原理

Fig.17 Schematic diagram of braking pressure control system

图18 控制系统变量

Fig.18 The variables of control system

图19 仿真结果

Fig.19 Simulated results

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