基于侧喷流控制的运载器弹道建模与仿真

Modeling&Simulation Analysis of Launch Vehicle Trajectory Based on Direct Lateral Force Control

直接侧向力技术已在大气层外动能拦截器和大气层内防空导弹中得到成功应用。运载火箭的飞行弹道跨越大气层,可以尝试采用直接侧向力对其进行控制。在介绍直接侧向力控制技术原理的基础上,建立了采用直接侧向力进行姿态控制的运载火箭弹道的简化模型(不考虑风干扰和弹体滚转),运用Matlab/Simulink软件进行了计算机数字仿真,并与传统的摆动喷管控制方式进行了对比,给出了第一级弹道的仿真结果。得出了直接侧向力控制作用下的弹道能够满足运载器总体设计要求的结论。

The direct lateral force technology has been used in ex-atmosphere kinetic-kill vehicle and in the in-ner-atmosphere airdefense missile successfully. It is possible to control the launch vehicle with direct lateral force since the trajectory steps above the atmosphere. With the introduction of the principle of direct lateral force control technology, a simplified trajectory model, in non-wind, non-rolling condition, of the launch vehicle is presented. Digit-simulation is made in Matlab/Simulink software and results are compared with that of traditional control system using deflecting nozzles. The numeric result of the first stage is presented. The simulation indicates that the trajectory under the control of direct lateral force can satisfy the requirement of launch vehicle system design.