Damping of flight control cabin in small unmanned helicopter and flight-test validation

被引：0

作者：

Ma, Xianglin ^{[1
]}

Zhang, Chenglin ^{[1
]}

Han, Jinglong ^{[2
]}

机构：

[1] National Key Laboratory of Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing, 210016, China

[2] Institute of Vibration Engineering Research, Nanjing University of Aeronautics and Astronautics, Nanjing, 210016, China

来源：

Nanjing Hangkong Hangtian Daxue Xuebao/Journal of Nanjing University of Aeronautics and Astronautics | 2010年 / 42卷 / 05期

关键词：

Flight control systems - Modal analysis - Shock absorbers - Helicopters - Finite element method - Unmanned aerial vehicles (UAV) - Aircraft control - Cabins (aircraft);

D O I：

暂无

中图分类号：

学科分类号：

摘要：

The problem on the flight control cabin damping of a small unmanned helicopter with taking off weight 100 kg is studied, and the finite element modeling method for the coupling system of the flight control cabin is presented. To modify the finite element model according to the test data of the simulated tests with many practicalities, to calculate the shaking situation and to analyze the parameter effects of the flight control cabin with the modified model, the shock absorber is obtained for meeting needs of the intensity and the shaking character. Throughout many flight tests, it is verified that the flight control cabin damping system has a good performance. The research resolves the difficult problem of the shaking of the flight control cabin and provides the security guarantees for the unmanned helicopter flight.

引用

页码：543 / 549

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