直升机操纵杆振动特性测量与分析

Measurement and analysis of helicopter control stick vibration characteristics

基于直升机铰链力矩的研究成果,建立了倾斜器操纵杆载荷的计算模型.在参考常规飞机测试元件的基础上,研制了具有足够强度和灵敏度的测力元件,通过地面试验解决了测量精度与飞行安全之间的矛盾,成功地进行了飞行试验,并获得操纵杆载荷这一重要参数.本文计算结果与试验数据基本一致,激振力的频率与主旋翼的1倍和2倍频率接近.可以满足工程计算要求,为直升机操纵系统的设计和检验提供依据.

A calculation model of the control stick vibration characteristics was set up. Based on the research of helicopter hinge moment, a calculation model of the swashplate con trol stick load was established. With reference to conventional airplane measurement cells, the measurement cell with enough strength and sensitivity was developed, solving the con tradiction between measurement accuracy and flight safety by ground tests. The flight test was successfully conducted, and the important parameter of swashplate control stick load was obtained. The calculation results are basically consistent with experimental data, and the excitation force frequency is close to 1 and 2 times of the main rotor speed. Engineering computation requirement can be achieved, providing a reference for the design and test of helicopter control system.