摘要
降低直升机的振动水平一直是直升机研制过程中最为关键的技术问题之一。研究直升机结构振动主动控制的频域控制算法和流程,并基于某型直升机空测数据与其控制通道频响函数实测数据,进行从时域到频域再返回时域的振动控制全过程的仿真,探讨与比较在线系统参数识别的两种方法(最小均方法和卡尔曼滤波法)、频域法的时域控制中重要参数的设置等,得出有价值的结论,为真实工程应用中方法的选择提供参考和依据。
Reducing the vibration level of helicopter fuselage is always one of the crucial technical issues,in the development of helicopter. The control algorithms and approaches of active control of structural responses for helicopter in frequency domain were studied. Based on true flight measured data and measured frequency responses of control path for a typical helicopter, the whole processes between frequency and time domains were simulated, in which two online parameter identification methods (Least Mean Square and Kalman Filter), setting of important parameters for control in time domain by using the method in frequency domain were studied and compared. And some valuable conclusions have been drawn as reference and basis for method selection in the future real engineering applications.
出处
《系统仿真学报》
CAS
CSCD
北大核心
2009年第20期6347-6351,共5页
Journal of System Simulation
关键词
直升机结构响应主动控制
最小均方法
卡尔曼滤波
参数识别
active control of structural response for helicopter
least mean square
Kalman filter
parameter identification