高超声速飞行器自适应反步控制器设计
收稿日期: 2014-03-25
修回日期: 2014-09-15
网络出版日期: 2015-03-31
基金资助
国家自然科学基金 (61374012, 61273083)
Adaptive backstepping controller design for hypersonic vehicle
Received date: 2014-03-25
Revised date: 2014-09-15
Online published: 2015-03-31
Supported by
National Natural Science Foundation of China (61374012, 61273083)
针对含有不确定干扰项的吸气式高超声速飞行器模型,分别设计了基于反馈线性化的速度控制器和基于反步法的航迹控制器,以实现对速度和航迹角参考信号的稳定跟踪。通过指令滤波器得到俯仰角的实际跟踪指令及其一阶、二阶微分信号,可直接设计升降舵控制指令,在解决了虚拟控制量求导"复杂性爆炸"问题的同时,减少了反推计算步数,从而达到提高系统动态性能和优化控制器结构的目的。基于LaSalle不变集原理和Lyapunov理论设计的自适应更新律保证了系统的稳定性。仿真结果表明,所设计的控制器在飞行器存在不确定干扰的情况下仍能满足对参考信号跟踪性能的要求。
路遥 , 董朝阳 , 王青 . 高超声速飞行器自适应反步控制器设计[J]. 航空学报, 2015 , 36(3) : 970 -978 . DOI: 10.7527/S1000-6893.2014.0255
Considering an air-breathing hypersonic vehicle model including uncertain interferences, a feedback linearization velocity controller and an adaptive backstepping flight path controller are proposed respectively to achieve the stable tracking of velocity and flight path angle reference signals. A command filter is employed to obtain the actual tracking commands of pitch angle and their first and second derivative signals, then the control law of elevator can be designed directly, which avoids the "explosion of complexity" of virtual control command derivatives and reduces the steps of inference calculation simultaneously. This method improves the dynamic performance of the control system and optimizes the structure of the controller. The system stability is guaranteed by the adaptive control laws designed using LaSalle's invariant principle as well as Lyapunov theory. Simulation results show that the reference signals' tracking performance can be achieved in the presence of uncertain interferences.
Key words： hypersonic vehicle; backstepping; flight control; uncertainty; command filter
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