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针对高度非线性、强耦合、参数不确定性的高超声速飞行器纵向运动数学模型,设计了一种基于Quasi-continuous高阶滑模理论的控制器,并与传统滑模控制器进行了分析和比较。仿真结果表明,Quasi-continu-ous高阶滑模控制在高度阶跃响应时间上比传统滑模控制减少了30%,速度阶跃响应时间比传统滑模控制减少了约56%。说明所设计的控制器能较好地满足在极端环境中飞行的高超声速飞行器对控制指令响应时间的要求。因此,该项研究对高超声速飞行器控制系统的设计有十分重要的参考价值。
Aiming at the math model of hypersonic vehicle longitudinal motion with highly nonlinear, strong coupling and parameter uncertainty, a controller based on Quasi-continuous high-order sliding mode theory is designed and compared with the traditional sliding mode controller . Simulation results show that Quasi-continuo-ous high-order sliding mode control reduces the step response time by 30% compared with the traditional sliding mode control, and the speed step response time is reduced by 56% compared with the traditional sliding mode control. Which shows that the designed controller can better meet the control command response time requirements of hypersonic vehicles flying in extreme environments. Therefore, this study has very important reference value for the design of hypersonic vehicle control system.