超声速滑翔飞行器最优转角控制数学建模仿真  

Mathematical Modeling and Simulation of Optimal Angle Control for Supersonic Glide Vehicle

作　　者：陈婷婷[1] 李凤[1] 

机构地区：[1]南昌大学科学技术学院,江西南昌330029

出　　处：《计算机仿真》2016年第6期23-26,共4页Computer Simulation

摘　　要：对飞行器的转角进行高精度控制可以提高控制精度。由于超声速飞行器的飞行速度过快,控制惯性过大,会造成机身异常振动,当前的角度控制方法无法对异常振动进行很好的抑制,以牺牲控制精度的方法解决,弊端明显。提出改进奇异摄动理论算法的高超声速滑翔飞行器的转角控制建模方法。先对高超声速滑翔飞行器在飞行过程中的动态稳定性进行详细的分析,获取飞行器在飞行过程中的转角控制需求,引入状态相关黎卡提方程设计出高超声速滑翔飞行器转角控制的基本策略,在融合奇异摄动思想理论,计算飞行器各个参数之间的相关性,将设计出的飞行器转角控制基本策略细化为快慢回路两部分,针对快慢回路分别设计了控制器,建立精确的高超声速滑翔飞行器的最优转角控制模型。仿真结果证明,改进方法的最优转角控制建模方法设计精确度高,为飞行器转角优化控制提供了原理依据。A modeling method for angle control of hypersonic glide vehicle based on the improved singular pertur- bation theory algorithm is proposed. Firstly, the dynamic stability of hypersonic glide vehicle in the process of flight is analyzed to obtain the requirement of angle control in the flight process of the aircraft, and the Riccati equation re- lated to the status is introduced to design the basic strategy for the angle control of hypersonic glide vehicle. Then, the singular perturbation theory is fused, and the correlation among the parameters of the aircraft is calculated. The designed basic strategy for angle control of the aircraft is refined as fast loop and slow loop. The controller is designed for the fast and slow loops, respectively, and the accurate and optimal angle control model of hypersonic glide vehicle is established. Simulation results show that the proposed method has high precision for the optimal angle control.

关 键 词：高超声速滑翔飞行器 转角控制 奇异摄动理论 

分 类 号：V44[航空宇航科学与技术—飞行器设计]