摘要
本文应用多输入、多输出跟踪模型法,对CCV型飞机纵向飞行控制系统的解耦控制律问题进行了研究。并以某型飞机为例,说明如何应用该方法确定三种纵向直接力模态的动态解耦控制律。
The multiple-input and multiple-output model following method is applied to the analysis of the longitudinal decoupling control law for a CCV type aircraft. The procedure to determine dynamical decoupling control laws is illustrated throught numerical examples for a CCV-type flighter aircraft while performing three longitudinal direct force control maneuvers.
出处
《飞行力学》
CSCD
北大核心
1992年第3期16-26,共11页
Flight Dynamics
关键词
主动控制技术
解耦控制律
飞机
Active control technique Direct force control Decoupling control law Model following method
