摘要
本文采用了可以预先确定飞行品质的控制律设计方法即模型跟踪法,对某战斗机的纵向控制律进行了设计,提出了一种简单且适用的求解控制律增益的迭代方法,同时给出了部分计算结果和结论。
The model following technique is used in the design of longitudinal control law for a fighter in this paper. The technique is a control law design method which can specify the flight qualities prior to the design. A simple and appropriate iterative method to solve the control law gains is presented and some results of calculation and conclusions are given.
出处
《飞行力学》
CSCD
北大核心
1991年第1期35-45,共11页
Flight Dynamics
