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.
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王放,陈铭,徐冠峰.直升机操纵杆振动特性测量与分析[J].航空动力学报,2013,28(10):2209~2215. WANG Fang, CHEN Ming, XU Guan-feng. Measurement and analysis of helicopter control stick vibration characteristics[J]. Journal Of Aerospace Power,2013,28(10):2209-2215.