Adaptive sliding mode control design for a hypersonic flight vehicle
Adaptive sliding mode control design for a hypersonic flight vehicle
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DOI：
10.2514/1.12596
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发表时间：
2004-09-01
影响因子：
2.6
通讯作者：
Ioannou, PA
中科院分区：
文献类型：
--
作者：
Xu, HJ;Mirmirani, MD;Ioannou, PA
针对一般高超声速飞行器的纵向动力学问题，设计并分析了一种多输入多输出自适应滑模控制器。该车辆模型是非线性的，多变量的，不稳定的，包括不确定的参数。对110，000 It和15马赫的配平巡航条件进行了模拟研究，评估了飞行器对高度和空速阶跃变化的响应。指令为100英尺/秒步进速度和2000英尺步进高度。控制器的鲁棒性进行评估，相对于参数的不确定性，使用仿真。仿真研究表明，所提出的控制器是鲁棒的参数不确定性，并满足性能要求，相对较低的幅度控制输入。
A multi-input/multi-output adaptive sliding controller is designed and analyzed for the longitudinal dynamics of a generic hypersonic air vehicle. This vehicle model is nonlinear, multivariable, and unstable and includes uncertain parameters. Simulation studies are conducted for trimmed cruise conditions of 110,000 It and Mach 15 where the responses of the vehicle to a step change in altitude and airspeed are evaluated. The commands are 100-ft/s step velocity and 2000-ft step altitude. The controller is evaluated for robustness with respect to parameter uncertainties using simulations. Simulation studies demonstrate that the proposed controller is robust with respect to parametric uncertainty and meets the performance requirements with relatively low-amplitude control inputs.