一种自适应滑模临近空间飞行器跟踪制导方法
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摘要
普通的基于状态方程线性化的跟踪制导方法用于大扰动临近空间将造成较大的制导方法误差。文中设计了一种具有积分型切换函数的自适应滑模制导方法,该方法基于线性二次型调节器设计反馈增益,并在跟踪制导律中增加了自适应项,修正线性化跟踪制导的方法误差。在文中仿真条件下,文中方法落点偏差约为线性二次型跟踪制导的1/12,在大扰动情况下制导精度提高明显。
Common guidance method by status equation linearization will cause large guidance method error for near space vehicle. In this paper, an adaptive sliding mode guidance law with integral switch function(ISFASMG) was designed to track near space trajectory. ISFASMG designed the feedback gain by linear quadratic regulator(LQR) and corrected linearization error of status function and uncertain disturbances by adding an adaptive term. Under the simulation condition in this paper, the terminal error of ISFASMG is 1/12 of LQR tracking guidance, and the guidance precision is improved significantly in large disturbance environment.
Common guidance method by status equation linearization will cause large guidance method error for near space vehicle. In this paper, an adaptive sliding mode guidance law with integral switch function(ISFASMG) was designed to track near space trajectory. ISFASMG designed the feedback gain by linear quadratic regulator(LQR) and corrected linearization error of status function and uncertain disturbances by adding an adaptive term. Under the simulation condition in this paper, the terminal error of ISFASMG is 1/12 of LQR tracking guidance, and the guidance precision is improved significantly in large disturbance environment.
引文
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[10]李瑜.助推-滑翔导弹弹道优化与制导方法研究[D].哈尔滨:哈尔滨工业大学,2009:141-142.
[2]ZARCHAN Paul.Tactical and Strategic Missile Guidance[M].6th ed.Reston:AIAA,2012:24-28.
[3]刘金琨,孙富春.滑模变结构控制理论及其算法研究与进展[J].控制理论与应用,2007,24(3):407-418.
[4]王青,陈宇,张颖昕,等.最优控制-理论,方法与应用[M].北京:高等教育出版社,2011:168-177.
[5]周荻.寻的导弹新型导引规律[M].北京:国防工业出版社,2002:5-8.
[6]孙胜,张华明,周荻.考虑自动驾驶仪动特性的终端角度约束滑模导引律[J].宇航学报,2013,34(1):69-78.
[7]DUKEMAN G A.Profile-following entry guidance using linear quadratic regulator theory:AIAA 2002-4457[R].[S.l.:s.n.],2002:1-10.
[8]LI Kebo,CHEN Lei,TANG Guojin.Improved differential geometric guidance commands for endoatmospheric interception of high-speed targets[J].Science China:Technological Sciences,2013,56(2):518-528.
[9]雍恩米.高超声速滑翔式再入飞行器轨迹优化与制导方法研究[D].长沙:国防科技大学,2008:97-98.
[10]李瑜.助推-滑翔导弹弹道优化与制导方法研究[D].哈尔滨:哈尔滨工业大学,2009:141-142.