滑模方法在空空导弹制导律中的应用
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摘要
针对空中机动目标,采用滑模变结构方法设计了一种空空导弹三维制导律。在考虑三维拦截的情况下,建立了导弹与目标之间的空间相对运动方程。基于滑模变结构控制理论,推导得到了俯仰和偏航通道的末制导律。对于滑模制导律固有的抖振问题,用饱和函数sta(s)代替理想滑动模态中的sgn(s)函数来实现准滑动模态控制,即在边界层外采用切换控制,在边界层内采用线性化反馈控制,有效地减小了抖振的发生。数值仿真结果表明,所设计的制导律相对于比例制导律,对机动目标有更好的拦截效果。
A 3-D guidance law for air to air missiles is designed with sliding-mode variable structure.The relative movement equation between missile and target is built with the consideration of 3-D interception condition.Pitching channel and yaw channel guidance law in the terminal phase are derived based on sliding mode control.For the buffet of sliding-mode guidance law,a saturation function sat(s) is used instead of sgn(s) function to realize the quasi-sliding mode control.The buffet is greatly reduced when with the switching control adopted within the boundary layer and linear feedback control adopted out of the boundary layer.The numerical simulation results showed that,compared with proportional guidance law,the sliding mode guidance law has better performance.
A 3-D guidance law for air to air missiles is designed with sliding-mode variable structure.The relative movement equation between missile and target is built with the consideration of 3-D interception condition.Pitching channel and yaw channel guidance law in the terminal phase are derived based on sliding mode control.For the buffet of sliding-mode guidance law,a saturation function sat(s) is used instead of sgn(s) function to realize the quasi-sliding mode control.The buffet is greatly reduced when with the switching control adopted within the boundary layer and linear feedback control adopted out of the boundary layer.The numerical simulation results showed that,compared with proportional guidance law,the sliding mode guidance law has better performance.
引文
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[11]王善敏,姜长生.空空导弹三维智能滑模导引律设计[J].航空兵器,2009,(6):8-12.
[12]刘金锟.滑模变结构控制MATLAB仿真[M].北京:清华大学出版社,2005:44-45.
[2]王刚,刘念涛,刘维龙.空空导弹变结构自适应三维制导律[J].弹箭与制导学报,2008,28(6):11-13.
[3]任义元,袁建平,方群.空空导弹变结构末制导律研究[J].计算机仿真,2009,26(10):25-28.
[4]孙胜,周荻.有限时间收敛变结构导引律[J].宇航学报,2008,29(4):1258-1262.
[5]闫斌斌,黄新文,闫杰.针对目标机动的变结构制导参数设计[J].西北工业大学学报,2009,27(4):499-502.
[6]Brierley S D,Longchamp R.Application of sliding modecontrol to air-air interception problem[J].IEEE Transac-tions on Aerospace and Electronic Systems,1990,26(21):306-325.
[7]Zhou D,Mu Chun-d,Ling Q,et al.Study of optimal slid-ing-mode guidance law[J].Chinese Journal of Aeronau-tics,1999,12(4):236-241.
[8]Shieh C-S.Design of three-dimensional missile guidancelaw via tunable nonlinear H∞control with saturation con-straint[J].IET Control Theory Application(S1751-8644),2007,1(3):757-763.
[9]Yuan Li-ying,Li Shi-yong.Missile guidance law design u-sing nonlinear output regulation and T-S model[C]//In-dustrial Electronics and Applications,ICIEA 2007,2ndIEEE Conference.USA:IEEE,2007:1037-1041.
[10]郑守军,姜长生.空空导弹三维自适应模糊滑模制导律设计[J].电光与控制,2008,15(1):12-16.
[11]王善敏,姜长生.空空导弹三维智能滑模导引律设计[J].航空兵器,2009,(6):8-12.
[12]刘金锟.滑模变结构控制MATLAB仿真[M].北京:清华大学出版社,2005:44-45.