基于栅格舵的火箭芯一级残骸落点控制问题研究

Research on impact point control of the grid rudder based rocket core first stage

运载火箭芯一级在分离后运动失稳,变为不可控飞行器,在坠落地面时有可能会带来安全问题。为解决该问题,提出一种加装栅格舵实现芯一级落点精确控制的方案。首先给出加装栅格舵以后的芯一级布局形式,通过数值模拟的手段分析其气动特性。然后,给出了再入过程的制导控制方案,设计了控制律、制导律参数。最后,进行了额定弹道仿真和蒙特卡洛拉偏仿真。结果表明,加装栅格舵后,芯一级能够实现姿态的迅速稳定,按照制导要求沿标准弹道飞行,拉偏后落点散布范围小于100 m×100 m,整个方案合理可行。

The carrier rocket core first stage loses its stability after separation and becomes an uncontrollable flying vehicle,which may cause safety problems when it hits the ground.In order to solve this problem,the paper proposes a scheme to install grid rudder to achieve precise control of core first stage landing point.Firstly,the first stage layout of the core after the installation of the grid rudder is given,of which the aerodynamic characteristics are analyzed by numerical simulation.Then,the guidance control scheme of the reentry process is given,and the control law and guidance law parameters are designed.Finally,the rated ballistic simulation and Monte-Carlo pull off simulation were performed.The simulation results show that after the grid rudder is installed,the core can achieve rapid and stable attitude.According to the guidance requirements,it can fly along the standard ballistics.After the deflection,the scattering range is less than 100 m×100 m.The whole scheme is reasonable and feasible.