直升机操纵杆振动特性测量与分析

王放; 陈铭; 徐冠峰

直升机操纵杆振动特性测量与分析

1.
北京航空航天大学航空科学与工程学院, 北京 100191
2.
中国人民解放军总参谋部陆航研究所, 北京 101121

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出版历程
- 收稿日期: 2012-10-16
- 刊出日期: 2013-10-28

Measurement and analysis of helicopter control stick vibration characteristics

1.
School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
2.
Army Aviation Institute, Headquarters of the General Staff, Chinese People's Liberation Army, Beijing 101123, China

摘要

摘要: 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.
- 操纵系统 /
- 振动分析 /
- 载荷测量 /
- 飞行试验 /
- 铰链力矩
Abstract: 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 control stick load was established. With reference to conventional airplane measurement cells, the measurement cell with enough strength and sensitivity was developed, solving the contradiction 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.
- control system /
- vibration analysis /
- load measurement /
- flight test /
- hinge moment

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参考文献(15)

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