新气动布局飞机的过失速控制律设计  

Post-Stall Maneuver Control Law for Aircrafts with New Control Configuration

作　　者：张平[1] 王东[1] 陈宗基[1] 

机构地区：[1]北京航空航天大学自动化科学与电气工程学院

出　　处：《北京航空航天大学学报》2003年第1期23-26,共4页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：提出了一种多操纵面新气动布局飞机的过失速控制律设计方法 .利用最小二乘拟合方法处理离散气动数据 ,得到连续六自由度非线性飞机方程 ;使用扩展线性化方法将飞机方程简化为工作点族上具有时变特征的线性系统形式 ;使用符号运算方法设计了系统闭环控制律和大攻角下的过失速控制律 .仿真实验表明 ,这种控制律用于现代飞机的过失速机动是有效的 .A post-stall maneuver control law for aircraft with new control surfaces and thrust vector control is proposed. The air dynamic data table is operated by minimal mean-square value of the error between the air data and the combined continued functions. The 6 freedom nonlinear dynamic equations of the aircraft are predigested at static operating points by extended linearization which still possess nonlinear characters. The control laws of the inner closed-loop system and post-stall maneuver are obtained through using symbol operations design. Simulation result shows that the control law is effective for the post-stall maneuver design of modern aircrafts.

关 键 词：非线性控制系统 飞行控制系统 推力矢量控制 扩展线性化 过失速机动控制 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]