飞机无杆牵引车系统振动特性仿真分析及优化

针对无杆牵引车在推拖飞机过程中造成的飞机起落架振动问题,在Adams环境下建立飞机-无杆牵引车系统动力学模型,在道面的激励下仿真得到起落架支柱处的时域响应和频域响应,分析飞机无杆牵引车抱轮机构距车辆重心位置和牵引速度对飞机前起落架振动的影响。仿真结果表明,抱轮机构位置和速度对起落架垂向振动影响较大,抱轮机构距牵引车重心位置越远,起落架支柱处的加速度均方根值越小,加速度变化较为平缓,且牵引速度在中速5-10km/h时,可有效降低起落架支柱处的振动。建立全参数二次回归方程,选取合适的抱轮机构位置及牵引速度,可使起落架支柱垂向振动加速度均方根值降低56%,降低了起落架振动对飞机安全及结构稳定性的影响,提高飞机的牵引滑行性能。

Simulation Analysis and Optimization of Vibration Characteristics of Aircraft Rodless Tractor System

Aiming at the problem of aircraft landing gear’s vibration caused by the rodless tractor in the process of pushing the towed aircraft,a dynamic model of the aircraft-rodless tractor system was established.Under the excitation of the pavement,time domain response and frequency domain response of the landing gear strut were simulated.The position of the center of the vehicle and the traction speed of the aircraft’s rodless tractor were analyzed.The influence of the distance between rodless tractor’s gravity and clamping mechanism position and the traction speed of the aircraft’s rodless tractor on the vibration of the aircraft landing gear was analyzed.The simulation results show that the position and speed of the clamping mechanism have a great influence on the vertical vibration of the landing gear.The farther the distance between the clamping mechanism position and the gravity of the tractor,the smaller the root mean square value of the acceleration at the landing gear strut,and the acceleration change is gentle.When the traction speed is 5-10 km/h,the vibration at the landing gear strut can be effectively reduced.Establishing a full-parameter quadratic regression equation and selecting the appropriate position and traction speed of the clamping mechanism can reduce the root mean square value of the vertical vibration acceleration of the landing gear strut by 56%,the impact of landing gear vibration on aircraft safety and structural stability is reduced,and the traction performance of the aircraft is improved.