摘要
飞机在大迎角飞行和低空滑行中容易出现轨迹偏离,需要进行飞行轨迹偏离修正控制,提高飞行稳定性.提出一种基于Lyapunove动态逆泛函的飞行轨迹偏离误差反馈控制数学模型.采用纵向模型构建飞机的运动数学模型和弹道方程,采用链式法则进行飞行轨迹的摄动参数线性化处理,在速度坐标系中使用欧拉四元素估计方法计算姿态角,以飞行的航向角、横滚角和俯仰角为约束参量模型构建Lyapunove函数,对Lyapunove函数求导,通过动态逆泛函构建控制律,实现飞行轨迹偏离误差反馈控制.仿真结果表明,采用该模型进行飞行控制的稳定性较好,姿态参量的跟踪精度较高,轨迹偏离误差较小,控制品质较优.
In the high angle of attack and low altitude, it is easy to deviate from the trajectory, so the flight tra}ectory deviation correction control is needed co improve the flight stability. This paper presents a mathematical model of flight trajectory error feedback control based on I.yapunove dynamic inverse function. Mathematical model of motion and trajectory equation is constructed using longitudinal plane model, using the chain rule of the flight trajectory perturbation parameter estimation method using linearized Euler four elements in velocity coordinates calculation of attitude angle, flying at the heading angle, roll angle and pitch angle for constructing I.yapunove function constraint parameter model of Lyapunove through the dynamic inverse function derivation, functional construction control law of flight trajectory deviation error feedback control. The simulation results show that the model has better stability in flight control, higher tracking precision of attitude parameters, less error of trajectory deviation and better control quality.
出处
《微电子学与计算机》
CSCD
北大核心
2017年第6期104-108,共5页
Microelectronics & Computer
关键词
飞行
轨迹偏离
误差
反馈
控制
数学模型
flight
trajectory deviation
error
feedback
control
mathematical model
