滑翔导弹轨迹跟踪与能量管理模型设计与仿真

Modeling and Simulation of Glide Missile Trajectory Tracking and Energy Management

针对实际弹道在气动、推力偏差和大风干扰下会偏离规划好的标称弹道,进而造成较大的位置、速度散布并产生额外的控制负担的问题,本文开展滑翔导弹轨迹跟踪与能量管理算法模型研究。首先基于任务预划分手段并结合拉偏情况下的计算结果,将弹道预先划分为跟踪段与控速段。在此基础上,跟踪段与控速段各自建立轨迹跟踪模型和空气刹车+倾侧角反转逻辑模型,实现分段减小末端速度、位置散布的目的。最后分别开展对比仿真和蒙特卡洛打靶,仿真结果表明,本文所提出的模型控制误差小于允许范围内且制导精度优于传统跟踪方案,从而为滑翔导弹轨迹跟踪方案提供潜在的技术途径。

In order to solve the problem that the actual trajectory will deviate from the planned nominal one under aerodynamic deviation,thrust deviation and wind interference,which will cause large position and velocity dispersion and extra control burden,the trajectory tracking and energy management model of glide missile is studied in this paper. Firstly,the ballistic trajectory is pre-divided into the tracking section and the speed control section based on the task pre-division method and the simulation results.On this basis,the trajectory tracking model or the air brake + heeling angle reversal model are established respectively in the speed control segment and the tracking segment to achieve the purpose of reducing the terminal velocity and position dispersion. Finally,comparative simulation and Monte Carlo shooting are carried out.The simulation results show that the control error of the model in this paper is less than the allowable range and the guidance accuracy is better than the traditional guidance scheme,which provides a potential technical approach for glide missile trajectory tracking scheme.