CAJ | 학술논문

在设计飞行器最优反馈控制时，针对系统具有控制时滞的特性，采用连续状态变换思想，将具有时滞的控制系统转化为无时滞的控制系统，求使得无时滞控制系统性能指标最小的解，利用这个解去求原系统的状态函数，进而得到时滞反馈控制与状态变换后最优控制之间的关系，求出最优时滞反馈控制的增益。对某型无人直升机实验所得的悬停数据进行仿真验证，仿真结果证明了所提方法的有效性。
재설계비행기최우반궤공제시，침대계통구유공제시체적특성，채용련속상태변환사상，장구유시체적공제계통전화위무시체적공제계통，구사득무시체공제계통성능지표최소적해，이용저개해거구원계통적상태함수，진이득도시체반궤공제여상태변환후최우공제지간적관계，구출최우시체반궤공제적증익。대모형무인직승궤실험소득적현정수거진행방진험증，방진결과증명료소제방법적유효성。
Since a system has a characteristic of control delay during the design of the aircraft optimal feed-back controller,the delay control system is transformed to a non-delay control system by utilizing the continuous states transform method.Then using the solution of the non-delay control system,which makes the performance index smallest,the state function of the original system can be calculated.With the help of relationship between the delay feedback control and the state-transformed optimal control,it can help find the gain of the optimal time-delay feedback control.Simulation is made to verify the hovering data of unmanned helicopter experiments and the results validate the proposed control method.