基于滚动时域控制的寻的导弹末制导律研究  

Terminal Guidance Law Based on Receding Horizon Control for Homing Missile

作　　者：罗德林[1] 李玉峰[1] 吴文海[1] 沈春林[1] 

机构地区：[1]南京航空航天大学自动化学院,南京210016

出　　处：《南京航空航天大学学报》2005年第1期52-56,共5页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：针对近距机动目标的拦截 ,设计了基于滚动时域控制的寻的导弹末制导律。本导引律在最优导引律 (OPG)研究成果基础上 ,采用滚动时域控制技术 ,将追踪过程分为若干有限时域的追踪 ,并在每个时域内 ,将追踪过程视为初始条件不断更新的非机动追踪模型 ,进行最优追踪制导 ,反复进行直到截获目标。它无需知道目标的未来运动轨迹 ,能有效追踪拦截机动目标 ,克服了 OPG要求完全知道目标未来运动轨迹的应用条件限制 ,并且简化了计算。仿真研究表明 ,该导引律性能优于 TPN,APN,接近 OPG。该导引律算法简单、有效 ,切合实际 ,可为工程应用提供参考。To the interception of short r ange maneuvering target, a terminal guidance law for the homing missile is prese nted based on receding horizon control(RHC). On the basis of research achievemen t of optimal guidance law (OPG), it employs the RHC technique to divide the whol e pursuit process into some sequential ones with the finite time horizon. In eac h time region, the optimal control solution to the pursuit problem is implemente d and the target is presumed to move in a non-maneuvering way with initial stat e updated. The process is repeated until the target is intercepted. The designed guidance law can effectively guide the missile to intercept the maneuvering tar get without needing to know the future motion of a target. It overcomes the limi tation to apply OPG,which requires a complete knowledge of the target′s motion is available to the missile, and simplifies calculations. Simulation results sho w that the performance of the designed guidance law is superior to that of TPN a nd APN, and close to that of OPG. Due to the algorithm is simple effective and s uitable to realistic scenarios, it can provide a reference for real engineering application.

关 键 词：滚动时域控制 导引律 机动目标追踪/拦截 仿真 

分 类 号：V448[航空宇航科学与技术—飞行器设计]