不依赖剩余飞行时间的数据驱动攻击时间控制导引律  

Data-Driven-Based Impact Time Control Guidance Law Independent of Time-to-Go

作　　者：黄嘉 常思江[1] 陈琦[1] 张海洋 HUANG Jia;CHANG Sijiang;CHEN Qi;ZHANG Haiyang(School of Energy and Power Engineering,Nanjing University of Science and Technology,Nanjing 210094,Jiangsu,China;China Ordnance Industry Navigation and Control Technology Research Institute,Beijing 100089,China)

机构地区：[1]南京理工大学能源与动力工程学院,江苏南京210094 [2]中国兵器工业导航与控制技术研究所,北京100089

出　　处：《兵工学报》2023年第8期2299-2309,共11页Acta Armamentarii

基　　金：江苏省自然科学基金项目(BK20200498)。

摘　　要：针对导弹的攻击时间控制问题,基于比例导引法和数据驱动方法设计出一种不依赖剩余飞行时间信息的两阶段攻击时间控制导引律。第1阶段为攻击时间控制阶段,在比例导引法框架下仿真构建弹道倾角与导弹飞行状态之间的关系数据集,利用神经网络方法离线训练出相应的映射网络模型,根据该映射网络可在导弹飞行过程中实时解算攻击时间对应的理想弹道倾角,导引指令将控制实际弹道倾角收敛至该理想弹道倾角;第2阶段则直接采用比例导引法,最终实现导弹攻击时间控制。不同条件下的仿真结果验证了该导引律的可行性和有效性,与现有同类导引律相比,所设计导引律对攻击时间的控制精度更高、所需控制能量更少。理论分析表明,该导引律可通过更换映射网络推广至攻击角度控制。To solve the problem of missile impact time control,a two-stage impact time control guidance law is designed based on proportional navigation guidance and the data-driven method,which is independent of time-to-go information.The first stage is the impact time control stage.The relationship data set between the flight path angle and the flight state of the missile is constructed by simulation under the framework of proportional navigation guidance method,and then the corresponding mapping network model is trained offline by using the neural network method.According to the mapping network,the ideal flight path angle corresponding to the impact time can be calculated in real time during missile flight,and the guidance command will control the actual flight path angle converging to the ideal one.In the second stage,the proportional navigation guidance law is directly applied,and the missile impact time control is finally realized.The simulation results under different conditions verify the feasibility and effectiveness of the proposed guidance law.Compared with the existing similar guidance laws,the proposed one can control the impact time with higher precision and less control energy.In addition,the theoretical analysis shows that the guidance law can be extended to impact angle control by changing the mapping network.

关 键 词：数据驱动方法 比例导引法 理想弹道倾角 攻击时间控制 攻击角度控制 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]