Command filtered back-stepping control of a flexible air-breathing hypersonic flight vehicle
Command filtered back-stepping control of a flexible air-breathing hypersonic flight vehicle
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DOI：
10.1177/0954410013498578
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发表时间：
2014-07-01
影响因子：
1.1
通讯作者：
Zhou, Hailiang
中科院分区：
文献类型：
--
作者：
Ji, Yuehui;Zong, Qun;Zhou, Hailiang
非线性飞行控制的理论框架被开发并应用于通用吸气式高超声速飞行器的非线性纵向动力学。采用新颖的命令过滤反步技术和动态反演方法相结合来设计动态状态反馈控制器，该控制器提供对高度和速度参考命令的稳定跟踪。新颖的命令过滤反步高度控制消除了传统反步设计中计算解析导数的需要，为控制非线性高超声速飞行器提供了一种简单有效的方法。通过将命令滤波反步方法与基于滑模的积分滤波器、输入状态稳定性分析和小增益定理相结合，提出了一种输入状态稳定性模块化方法。导出了闭环系统的稳定性分析，包括柔性动态和系统输出的收敛性。所提出的控制方案在单独速度和高度参考命令的爬升机动情况下的模拟中得到验证。
A theoretical framework of nonlinear flight control is exploited and applied to nonlinear longitudinal dynamics of a generic air-breathing hypersonic flight vehicle. A combination of novelty command filtered back-stepping technology and dynamic inversion methodology is adopted for designing a dynamic state-feedback controller that provides stable tracking of the altitude and velocity reference commands. The novel command filtered back-stepping altitude control obviates the need to compute analytic derivatives in the traditional back-stepping design, providing a simple and effective way for controlling non-linear hypersonic flight vehicle. An input-to-state stability-modular approach is presented by combining command filtered back-stepping method with sliding-mode-based integral filters, input-to-state stability analysis, and small-gain theorem. The stability analysis of the closed-loop system including the flexible dynamic, and the convergence of the system outputs are derived. The proposed control scheme is verified in simulations in a climbing maneuver case of separate velocity and altitude reference commands.