摘要
在给定性能指标前提下设计飞行器PID控制器参数一般是依靠经验与试凑方法完成的。但随着飞行速度的不断提高，依靠经验或试凑的盲目性也显得愈发突出。为了避免这种盲目性，本文利用幅值一相角裕度测试因子法对系统在指定指标下PID控制器参数的边界与可行域进行了研究，并应用于飞行器俯仰通道PD控制器的参数可行域的分析之中以据此求取控制器参数。方法具有较高的精确性。
The way to design the PID parameter of aerocraft Controller under the specified application commonly based on experience or try. But with the increase of aeroeraft speed, the blindness of try becomes more serious. To avoid the blindness, the article researches on the boundary and feasible area of PID parameter by the gain - phase margins tester method, and applies the result to the aircraft＇ s pitch plane control loop to get its PID parameter, Which shows high accuracy.
