任意时间收敛碰撞角约束制导律设计  

Design of Impact Angle Control Guidance Law with Arbitrary Time Convergence

作　　者：刘远贺 谢年好 欧阳海 黎克波[1,2] Liu Yuanhe;Xie Nianhao;Ouyang Hai;Li Kebo(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410072,China;Hunan Key Laboratory of Intelligent Planning and Simulation for Aerospace Missions,Changsha 410072,China)

机构地区：[1]国防科技大学空天科学学院,长沙410072 [2]空天任务智能规划与仿真湖南省重点实验室,长沙410072

出　　处：《航空兵器》2022年第6期34-39,共6页Aero Weaponry

基　　金：国家自然科学基金项目(61690213,12002370);湖南省自然科学基金项目(2019JJ50736)。

摘　　要：针对碰撞角约束制导问题,基于纯比例导引律和任意时间收敛控制方法,设计了任意时间收敛碰撞角约束制导律。首先,推导了基于纯比例导引律的碰撞角误差动力学方程。然后,引入任意时间收敛控制方法,设计了可使碰撞角误差在任意设定的时间段内收敛的碰撞角约束制导律。最后,通过数值仿真算例,对任意时间收敛碰撞角约束制导律的制导性能进行了仿真验证,并与基于最优误差动力学的碰撞角约束制导律进行了对比分析,结果表明,期望碰撞角越大,导弹制导加速度变化越平缓,导弹能量消耗越少,并在该制导律的导引下,导弹能实现以期望收敛时间和终端碰撞角约束的攻击任务。Aiming at the problem of impact angle constrained guidance,an arbitrary time convergent impact angle constrained guidance(ATC-IACG)law against the stationary target is designed based on the pure proportion navigation(PPN)guidance law and the arbitrary time convergence control method.Firstly,the dynamic equation of impact angle error based on the PPN guidance law is derived.Then,the arbitrary time convergence control method is employed,and the ATC-IACG is designed,which could make the impact angle error converge to zero in a predefined convergent time.Finally,the guidance performance of the ATC-IACG law is demonstrated through numerical simulation results,and compared with that of the impact angle control guidance law based on optimal error dynamics.The simulation results show that the larger the expected impact angle,the smoother the change of the missile's guidance acceleration,also the less the missile's energy consumption.Under the guidance law,the missile can achieve the attack mission constrained by the expected convergence time and the terminal impact angle.

关 键 词：制导律 纯比例导引 任意时间收敛 碰撞角约束 固定目标 导弹 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程] V448.2[航空宇航科学与技术—飞行器设计]