摘要
主动控制是直升机旋翼振动控制技术未来发展的主要方向之一。文章针对国内外常用的桨叶后缘襟翼主动控制技术CTHHC和H_(∞)两种控制算法,对比验证各自的优缺点;以旋翼系统的幅频响应特性数据为基础,识别出旋翼系统的参数化模型,并确定针对该控制对象模型的两种不同算法的适合的控制参数。对模型计算得到的桨毂载荷数据进行仿真验证,通过对比分析论证了各算法的优点和缺点。最后结合仿真验证的结果为未来旋翼动力学主动控制试验算法的选择与控制参数调整提供支撑。
The active control of helicopter rotor vibration is one of the main development directions in the future.Based on the active control technology of trailing edge flap,CTHHC and H_(∞)two control algorithms were compared and verified in this paper.The parametric model of rotor system was identified based on the amplitude-frequency response data of rotor system,and the appropriate control parameters of two different algorithms for the control object model were determined.Based on the data of the hub load calculated by the model,the advantages and disadvantages of different algorithms were demonstrated through comparative analysis.Finally,the results of simulation verification provided support for the control algorithm selection and control parameter adjustment of the active control test algorithm for the future rotor dynamics.
作者
朱棣文
胡和平
张仕明
ZHU Diwen;HU Heping;ZHANG Shiming(National Key Laboratory of Helicopter Aeromechanics,China Helicopter Research and Development Institute,Jingdezhen 333001,China)
出处
《直升机技术》
2023年第2期5-10,共6页
Helicopter Technique
关键词
主动控制
控制算法
减振
旋翼动力学
active vibration control
control algorithm
vibration reduction
rotorcraft aeromechanics
