级间气动推冲分离系统动态建模与仿真

Dynamic Modeling and Simulation of Stages Pneumatic Thrust Separation System

针对低成本、清洁、可重复使用及基于高压气动推冲器的的运载火箭级间分离系统,设计合理的分离时序,根据不同分离阶段建立分离体的动力学模型;根据气体动力学原理建立包括气瓶、气缸、管路的动态数学模型;最后在MATLAB/Simulink中搭建仿真模型,得到分离过程中气动系统压力变化和分离体运动参数变化曲线,并通过仿真分析分离气缸缸径、气管管径等参数对分离距离的影响规律,同时考虑残余推力偏心和质心偏差等因素对分离的影响,采用Monte Carlo方法分析了分离过程中分离体的相对运动范围。结果表明:所建立数学模型能够正确反映分离过程中参数的变化,且在偏差干扰条件下,分离体相对运动在安全范围内,进一步验证了该分离系统具有可行性。

In view of a stage separation system based on high-pressure pneumatic thrusters for low-cost,clean and reusable launch rockets,a reasonable separation sequence was designed.A dynamic model of the separating body was established for different separation stages.A dynamic mathematical model,including gas cylinders,cylinders and pipelines,was established based on the principles of gas dynamics.Finally,a simulation model was built in MATLAB/Simulink,yielding curves of pressure changes in the pneumatic system and changes in the motion parameters of the separating body during the separation process.The influence of parameters such as the diameter of the separation cylinder and the diameter of the gas pipelines on the separation distance was analyzed by simulation.The impact of factors such as residual thrust eccentricity and center of mass deviation on separation was also considered.The Monte Carlo method was used to analyze the relative motion range of the separating body during the separation process.The results show that the established mathematical model can correctly reflect the change of parameters in the separation process,and the relative motion of the separator is within the safe range under the bias interference condition,the feasibility of separation system is verified.