一种小型无人直升机飞控舱减振及飞行验证

Damping of Flight Control Cabin in Small Unmanned Helicopter and Flight-Test Validation

研究了起飞质量为100 kg的小型无人直升机飞控舱减振问题,通过建立飞控舱耦合系统有限元模型,利用大量实物模态试验得出的试验数据,对所建有限元模型进行修正。利用修正过的模型对飞控舱进行振动计算及参数影响分析,得到了满足强度和振动特性要求的减振器。经过大量飞行试验,验证了飞控舱减振系统具有良好性能,故解决了飞控舱振动过大难题,为无人直升机进行自驾飞行提供了安全保证。

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.