摘要
针对高超声速飞行器存在模型参数不确定和外部干扰的特点,提出了一种自适应滑模变结构控制律设计方法。首先,结合高超声速飞行器数学模型,在引入参考模型的基础上,建立了跟踪误差模型;然后,基于该控制模型设计自适应滑模变结构控制律;最后,对该控制算法的有效性进行了仿真验证。仿真结果表明,所设计的滑模变结构控制系统对高超声速飞行器具有良好的控制效果,可以满足速度和高度精确跟踪控制的要求,并具有较强的鲁棒性。
An adaptive sliding mode control（ SMC） law design method is proposed for hypersonic vehicle with uncertain model parameters and external disturbances. Firstly,a tracking error model is established by combining the dynamic model of hypersonic vehicle and introducing expected reference model. Then,an adaptive sliding mode variable structure control law is designed based on the control model. Finally,the validity of the control algorithm is simulated and the results show that the proposed control scheme can meet the requirements for accurate speed and altitude tracking control and is of strong robustness.
出处
《飞行力学》
CSCD
北大核心
2014年第4期325-328,共4页
Flight Dynamics
基金
国家自然科学基金资助(61104195)
关键词
高超声速飞行器
自适应滑模控制
变结构控制
鲁棒性
hypersonic vehicle
adaptive sliding mode control
variable structure control
robustness
