摘要
对超机动飞机在大迎角机动下的控制律进行设计,并完成相关仿真验证。通过引入推力矢量技术,建立带推力矢量的飞机非线性数学模型;采用奇异摄动理论,将飞机状态划分为快慢变换不同的回路,分别应用动态逆设计飞行控制律;并采用PID控制补偿由于未精确建模带来的系统逆误差;最后对所设计的控制律进行了机动指令飞行仿真。仿真结果表明,设计的控制律能在大迎角机动条件下控制飞机跟踪指令飞行,并保证闭环系统的稳定性。
A technique which used to design the flight control system for a highly maneuverable aircraft was described,and the related simulation was finished.The nonlinear model of a maneuverable aircraft which with thrust vector control（TVC） was established.The singular perturbation theory was used to separate the dynamics into fast and slow sub-systems,the dynamic inversion theory was used to design the control laws of the two sub-systems separately,the PID control theory was used to compensate the system inversion error.To evaluate the control performance,the maneuver generator was designed to simulate the pilot inputs,the simulations results show that the control law can ensure the stability of the closed-loop system,and track the inputs well under the conditions of high angle of attack.
出处
《飞行力学》
CSCD
北大核心
2009年第2期67-71,共5页
Flight Dynamics
关键词
超机动飞行
推力矢量
大迎角
动态逆控制
supermaneuverable flight
thrust vector control（TVC）
high angle of attack
dynamic inversion control
