运载火箭并联级间分离动力学仿真与分析

Parallel Stage Separation Dynamics Simulations and Analysis on Launch Vehicle

基于间接预测法对并联两级运载火箭的级间分离过程进行了动力学仿真,获得了并联两体分离特性和规律。结果表明,气动力将有利于提高两级间的相对速度和距离,气动力矩对一级的姿态影响小,但会使二级产生较大的俯仰角与攻角。为了改善二级的姿态,基于分离的特性规律提出了分离优化措施,仿真结果表明优化后二级的姿态更加稳定、优化措施有效。最后分析了单一偏差因素、多偏差因素组合对分离运动的影响规律,并通过蒙特卡洛仿真得到了并联级间分离轨迹和姿态的包络范围,以此来评估分离的安全性。

Based on indirect prediction method,the simulation of stage separation process of parallel-two-stage launch vehicles is carried out.The separation characteristics of parallel-two-body are obtained.The results show that aerodynamic forces can help to increase relative velocity and distance between the two stages.Aerodynamic moments have little effect on the attitude of the first stage,but will cause a larger pitch angle and attack angle on the second stage.To improve the attitude of the second stage,a separation optimization measure is proposed based on the separation characteristics.The simulation results show that the attitude of the second stage is more stable after optimization,which means the optimization measure is effective.Finally,both the influence of a single deviation factor and combinations of multiple deviation factors on the separation are analyzed.The range of the separation trajectory and attitude between the parallel stages are obtained through Monte Carlo method.The research can evaluate the safety of separation.