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中文摘要：
为了有效地消除被控系统中高度非线性，强耦合及参数不确定性对于控制系统所造成的影响，设计了Terminal滑模变结构动态逆控制方法。该方法通过引入一种增广滑模超平面，给出任意阶系统选择Terminal滑模面的具体数学表达式，并基于李雅普诺夫稳定性理论得出相应控制器，保证了输出跟踪误差能够在有限的时间内达到零，并且误差趋于零的时间可以根据情况任意设置。并以高超声速飞行器为例，设计了基于高超声速飞行器纵向模型的Tenninal滑膜鲁棒控制器，使其能够在高度非线性、多变量和不稳定特性作用下，跟踪高度和速度指令.最后的仿真结果表明，采用Terminal滑模与动态逆相结合的控制方法，有效的弥补了非线性动态逆需要精确模型的缺点，有效地改善了整个控制系统的性能，使系统具有良好的鲁棒性.
英文摘要：
A funetion augmented sliding hyperplane is introduced to guarantee that the output tracking error converges to zero in finite time which can be set arbitrarily. The terminal sliding mode dynamic inversion control method is applied to a generic hypersonic vehicle longitudinal model, which is nonlinear, muhivariable and unstable system with uncertain parameters. The velocity and altitude reference ean be tracked while maintaining physical feasibility of the control input and the state. Simulation results indicate that the proposed methodology may constitute a feasible approach towards the development of robust nonlinear controllers for this type of applications.
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