基于弹道预测的脉冲修正弹末段控制方法  

Terminal control method for trajectory correction projectile equipped with pulse based on trajectory prediction

作　　者：常思江[1] 曹小兵[1] 刘铁铮[2] 

机构地区：[1]南京理工大学能源与动力工程学院,南京210094 [2]中国兵器科学研究院,北京100089

出　　处：《海军工程大学学报》2012年第6期84-88,共5页Journal of Naval University of Engineering

摘　　要：针对脉冲修正弹箭的控制方法问题,探讨了一种基于快速弹道预测的弹道末段控制方法。在一定假设下,对三自由度质点弹道方程组进行解析求解,得到一组精度较好的弹道诸元解析模型;基于该解析模型,提出一种通过估算剩余飞行时间进行快速弹道预测的方法;在此基础上,提出了适配的脉冲控制参数(脉冲作用方位、脉冲作用个数)的确定方法。以某脉冲修正弹为研究对象,采用Monte Carlo打靶法,在一组相同扰动源条件下分别对无控和有控弹道进行了数值仿真。仿真结果表明:该控制方法可有效提高脉冲修正弹的落点精度,有控落点圆概率误差比无控落点圆概率误差减小80%以上。Aiming at the problem for pulse-control trajectory correction projectiles, a terminal control method based on rapid trajectory prediction was discussed. According to some assumptions, the analytical solution of the 3D point mass trajectory equations results in a set of analytical model with good accuracy. Based on the analytical model, a rapid and accurate method for predicting the impact point through estimating the time-to-go was also proposed. And then the suitable method for determining the pulse-control parameters （i. e. , pulse-control direction and the number of pulses） was established. Considering a type of trajectory correction projectiles with impulse control as example, the numerical simulations of unguided and guided trajectory were both conducted with the same disturbance factors by using Monte Carlo method. The simulation results indicate that this control method is able to improve the accuracy of impact point and that the CEP reduction for guided impact point is more than 80%.

关 键 词：弹道预测 脉冲发动机 弹道修正弹 剩余飞行时间 

分 类 号：TJ765.1[兵器科学与技术—武器系统与运用工程]