基于过失速机动动力学的控制方法  

A control method based on dynamics for post-stall maneuvering

作　　者：张曙光[1] 辛毅[1] 

机构地区：[1]北京航空航天大学509教研室,北京100083

出　　处：《飞行力学》2001年第2期1-4,共4页Flight Dynamics

基　　金：航空基金资助项目 ( 98A51 0 39

摘　　要：为设计过失速大机动飞行控制律 ,按飞行的逆稳态模型考虑非线性因素的影响 ,同时对于陀螺、惯性耦合效应及重力影响进行补偿 ,并直接根据飞行品质要求按隐式模型跟踪法设计反馈控制器。初步设计实例证明 ,这种方法适应于过失速机动动力学特点 ,能够获得发挥飞机操纵潜能、较好地控制飞机实现过失速机动、具有满意飞行品质的控制解 ,并且控制结构易于工程实现。算例还表明 ,即使不加装先进的过失速操纵装置 ,通过对飞行控制律的改进可以进一步发挥飞机本身的气动潜力 。To design the flight control law for post stall and large amplitude maneuvering, nonlinear effects were firstly considered through the inverse steady state model of aircraft, and the gyro and inertial coupling and effects of gravity were compensated according to aircraft dynamics. Based upon all these, the feedback controllers were constructed by the implicit model following technique for satisfactory flying qualities. Preliminary design examples have shown that the design method presented here is suited to post stall maneuvering dynamics and can take full advantage of aircraft control potential. Furthermore, a control solution with satisfactory flying qualities can be conveniently achieved. Examples have also shown that post stall maneuvering ability could be attained to some extent by excellent flight control designs which can employ full aerodynamic potentials, even without advanced post stall control devices.

关 键 词：过失速机动控制 非线性补偿 飞行品质 战斗机 机动动力学 操纵潜能 飞行控制律 气动潜力 过失速迎角 设计 反馈器 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计] V212.12