【摘要】 本文讨论了线性系统解耦理论用于实现直接升力控制三种基本模式的飞机解耦控制问题，并以装有直接升力操纵面的小型飞机为例，用通用线性系统解耦控制律计算软件设计了直接升力控制律．计算结果表明，用该理论所设计出的飞机直接升力控制系统可严格地实现直接升力控制的三种基本模式，同时闭环解耦系统是稳定的，且具有良好的动态响应更多还原

【Abstract】 Much research has been done on aircraft direct force control, but no paper in the open literature has presented a satisfactory theoretical method for achieving such control thoroughly. This is due to the fact that relevant published paperes have not used decoupling control theory. The author in this paper attempts to present a theoretical method that can achieve aircraft direct force control thoroughly. Starting from existing linear decoupling control theory, the author studies the problem of dynamic pre-compensation theory and points out that controllable output is the necessary but not sufficient condition for decoupling. Then the author obtains two types of dccoupling modes: (γ,0)-(δe, δf)and (α,0)-(δe, δf ). Eq. (6) in the full paper is the control law corresponding to the two types of decoupling modes just mentioned.As an example, the author takes the direct lift control surface of aircraft and makes use of the author’s own software to obtain the control laws for all three basic modes of direct lift control, using Eq. (6). Computation results indicate that the decoupled systems arc stable and that dynamic responses arc satisfactory.更多还原