火箭侧喷流与栅格舵联合控制弹道仿真

Simulation of the Trajectory of Launch Vehicle Based on Lateral Jet and Grid Fin Combined Control

针对某固体运载器第一级侧向喷流发动机与栅格舵联合控制问题,建立了有控弹道模型。分别分析了侧向喷流发动机与栅格舵的控制能力,通过仿真计算的方法得到了联合控制下飞行弹道的特性,并计算了侧喷流发动机液体推进剂的消耗情况。结果表明采用侧喷流与栅格舵联合控制能够满足运载器弹道设计的要求。

Certain solid launch vehicle was controlled by lateral jet and grid fin. The performance of the fist stage of the flight trajectory was simulated and modeled. The control capability of the lateral＇jet and the grid fin was analyzed and the liquid fuel consumption of the lateral jet engine was calculated. The numeric result of the first stage was presented. The simulation indicates that the trajectory under the control of lateral jet and the grid fin can meet the requirement of launch vehicle system design.