基于Quasi-continuous高阶滑模理论的高超声速飞行器控制

Quasi-Continuous High-Order Sliding Mode Theory for Hypersonic Flight Vehicle

针对高度非线性、强耦合、参数不确定性的高超声速飞行器数学模型,首先应用精确线性化将其非线性的数学模型转化成符合控制设计要求的等效线性模型,然后引入了Quasi-continuous高阶滑模控制理论,同时采用鲁棒精确微分器来克服测量的困难。模拟结果表明所设计的控制器对参数不确定性具有很好的鲁棒性,而且达到了期望的性能指标。

To deal with highly nonlinear,tightly coupled mathematic model with parametric uncertainty for hypersonic vehicle,firstly,the theory of feedback linearization introduced can convert accurately nonlinear mathematic model into equivalent linear model for controllers design.Then,Quasi-continuous high-order sliding mode control theory is proposed,and at the same time,robust exact differentiator is designed in order to overcome the difficulties in the measure.Simulation results demonstrate that the proposed controllers are robust with respect to parametric uncertainty and meet the performance requirements.