红外旋转导弹自适应变结构制导律研究
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摘要
针对红外旋转弹制导时间短、精度要求高和高频正弦控制的特点,设计了一种基于红外体制旋转导弹的自适应变结构制导律。建立了导弹与目标的相对运动模型,给出了变结构制导律,并加入变结构项以保证系统对干扰的鲁棒性。为保证制导精度,采用幂次趋近律,通过设置合理的趋近参数保证视线角速度在弹目遭遇前的有限时间内收敛至零。为减小变结构控制产生的高频抖振,设计了一种自适应变增益变结构制导律,根据视线角速度信息对变结构项的增益进行自适应调整,以有效削弱变结构控制中的抖振。基于红外旋转导弹的目标信息获取能力,对变结构制导律的工程实现进行了讨论。以某红外旋转导弹为背景,仿真比较了比例导引律与变结构导引律,结果发现:变结构制导律的所需平均过载、弹道平滑程度、视线角速度和命中精度等明显优于传统比例导引律;对机动和非机动目标,设计的增益自适应变结构制导律均既能保证制导精度,又可避免变结构项引起的抖振。
According to the characteristics of infrared rolling airframe missile such as short guidance time,high precision requirement and high frequency sine control,the design of self-adaption variable structure guidance(VSG)was studied in this paper.The relative motion model of missile and target was established and the variable control guidance law was given.The variable was added to ensure the system robustness to the disturbance.To guarantee the guidance precision,the exponent law was used.The line of sight was converged to zero in the finite time before the missile and target encountered by setting proper asymptotic parameter.To reduce the high frequency chattering caused by variable control,a self-adaption variable structure guidance law was designed,which could adjust the gain of variable item adaptively to decrease the chattering in VSG.The implementation of VSG in engineering was discussed according to the ability of target information acquisition of infrared rotating missile.The simulation of PN and VSG was carried out based on the background of a type of infrared rolling airframe missile.The results showed that the average maneuvering,trajectory smoothness,line of sight rate and missing distance of VSG were better than PN law.The self-adaption variable structure guidance law proposed could ensure the guidance precision and avoid the chattering for both maneuvering target and non-maneuvering target.
According to the characteristics of infrared rolling airframe missile such as short guidance time,high precision requirement and high frequency sine control,the design of self-adaption variable structure guidance(VSG)was studied in this paper.The relative motion model of missile and target was established and the variable control guidance law was given.The variable was added to ensure the system robustness to the disturbance.To guarantee the guidance precision,the exponent law was used.The line of sight was converged to zero in the finite time before the missile and target encountered by setting proper asymptotic parameter.To reduce the high frequency chattering caused by variable control,a self-adaption variable structure guidance law was designed,which could adjust the gain of variable item adaptively to decrease the chattering in VSG.The implementation of VSG in engineering was discussed according to the ability of target information acquisition of infrared rotating missile.The simulation of PN and VSG was carried out based on the background of a type of infrared rolling airframe missile.The results showed that the average maneuvering,trajectory smoothness,line of sight rate and missing distance of VSG were better than PN law.The self-adaption variable structure guidance law proposed could ensure the guidance precision and avoid the chattering for both maneuvering target and non-maneuvering target.
引文
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[2]KUMAR S R,RAO S,GHOSE D.Sliding-mode guidance and control for all-aspect interceptors with terminal angle constraints[J].Journal of Guidance,Control,and Dynamics.2012,35(4):1230-1246.
[3]钱杏芳,林瑞雄,赵亚南.导弹飞行力学[M].北京:北京理工大学出版社,2006.
[4]ZHOU D,MU C D,XU W L.Adaptive sliding-mode guidance of a homing missile[J].Journal of Guidance,Control and Dynamics,1999,22(4):589-594.
[5]周荻.寻的导弹新型导引规律[M].北京:国防工业出版社,2002.
[6]高为炳.变结构控制理论基础[M].北京:中国科学技术出版社,1990.
[7]李士勇,章钱.变结构控制在导弹制导中的应用研究[J].飞航导弹,2009(7):47-51.
[8]李庆波.智能制导律的设计及其仿真研究[D].哈尔滨:哈尔滨工业大学,2013.
[9]宋愿赟,陈万春.高精度快速趋近滑模变结构末端导引方法[J].北京航空航天大学学报,2012,38(3):319-323.
[10]KIM T H,LEE C H,TAHK M J.Time-to-go polynomial guidance with trajectory modulation for observability enhancement[J].IEEE Transactions on Aerospace and Electric System,2013,49(1):55-73.
[11]宋建梅,张天桥带末端落角约束的变结构导引律[J].弹道学报,2001,13(1):16-21.
[12]宋晗,王淼.单通道旋转导弹运动学建模方法研究[J].科技信息,2010(19):27-29.
[13]易彦,周凤岐,周军.旋转导弹的控制信号分析[J].弹箭与制导学报,2000,20(2):48-53.
[14]邹汝平,张延风.旋转导弹自旋频率设计[J].兵工学报,2007,28(2):220-222.
[15]叶尧卿.便携式红外寻的防空导弹设计[M].北京:宇航出版社,1996.