CAJ | 학술논문

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.基于直升机全局模型的结构响应频域主动控制方法,采用自行研制的数字信号处理(DSP)测控软件进行了多输入多输出的试验研究.在对控制通道频响矩阵的在线识别上分别采用了卡尔曼(Kalman)滤波法和最小均方法(LMS),重点探讨了权矩阵、识别量初始值等对控制效果的影响,并对两种识别方法进行了对比,得出了有价值的结论,为真实工程应用中方法以及对应参数的选择提供参考和依据.
강저직승궤적진동수평일직시직승궤연제과정중최위관건적기술문제지일.기우직승궤전국모형적결구향응빈역주동공제방법,채용자행연제적수자신호처리(DSP)측공연건진행료다수입다수출적시험연구.재대공제통도빈향구진적재선식별상분별채용료잡이만(Kalman)려파법화최소균방법(LMS),중점탐토료권구진、식별량초시치등대공제효과적영향,병대량충식별방법진행료대비,득출료유개치적결론,위진실공정응용중방법이급대응삼수적선택제공삼고화의거.
Reducing the vibration level of helicopter fuselage is always one of the crucial technical issues in the development of helicopter. Based on the control approaches of active control of structural responses in frequency domain and the global model for helicopter, a multi input multi output experimental study is conducted using self developed control software of digital signal processing. Kalman filter and Least Mean Square method are adopted to identify frequency response function matrix of control channel respectively. The effects of weighting matrix and initial values of parameters etc to control performance are emphatically discussed. In addition, comparisons between the mentioned two methods are also performed. All beneficial conclusions from this experiment can provide reference and basis for application of real projects.