小型固体运载器一、二级分离动力学与仿真研究

Axial Stage Separation with Close-loop Attitude Control of a Small Solid Launcher

某低成本小型固体运载器采用侧喷流和栅格舵联合进行姿态控制。针对该布局,设计引入闭环姿态控制的一、二级级间冷分离方案。在描述级间分离过程的基础上,建立了分离运动学与动力学模型,解锁与分离冲量装置模型,气动力模型以及分离姿态控制律模型,讨论了碰撞判断条件,通过Monte Carlo仿真验证了参数不确定条件下分离姿态控制律设计对于避免碰撞和减小上面级初始姿态偏差的有效性。结果表明所设计的分离方案在充分发挥冷分离优势的同时能够弥补由冷分离时间长引起的上面级初始姿态偏差,能够有效避免级间碰撞。为该运载器的级间分离方案提供了一种可能的选择。

A low-cost small solid launcher using both lateral jets and gird fins for its attitude control purpose was designed. According to the layout of the vehicle, this paper designed a cold separation scenario to which a close-loop attitude control scheme is introduced. Based on the description of the separation process, dynamic and kinematic equations were built. Meanwhile the ejector piston model, retro-rocket model, aerodynamic model and attitude control model were also established. The collision detection method was discussed and Monte Carlo simulation was introduced to deal with the uncertainties. Simulation results show that the proposed project can not only reduce the attitude deflection of the vehicle but also avoid interstage collision, so it provides a possible choice for the stage separation of this type of vehicles.