箭载浮空器投放过程热力学与动力学仿真分析

Simulation and Analysis of Thermal and Dynamic Properties of Rocket-Borne Aerostat During Deployment

基于常规浮空器上升过程的模型,建立箭载浮空器系统充气展开过程的热力学与动力学模型,利用Matlab编程的方式对具体算例进行仿真计算,详细分析了高度、压差、气体温度等随时间变化的特性。探究了投放高度、充气开始时刻降速、充气时长等因素对系统运动过程的影响。结果表明,通过合理控制上述三个变量,可以减小系统充气结束时与目标高度的距离,以减少压差和到位时间,实现充气展开过程的优化。理论模型和仿真程序可为箭载浮空器发放参数的选择提供参考。

Based on the model of the aerostat during ascent,the thermal and dynamic models of the inflatable process of the rocket-borne aerostat were established.A specific example was simulated by Matlab programming,and the altitude,pressure difference,and gas temperature were analyzed in detail.Effects of the delivery height,initial ve⁃locity and inflation time during the deployment of the system were explored.The results show that the distance be⁃tween the end of the inflation process and the target height can be reduced by reasonably controlling the above three variables,so as to lower the pressure difference and arrival time,and realize achieving the optimization of the deploy⁃ment process.The theoretical models and simulation program can provide a reference for the selection of launch pa⁃rameters of the rocket-borne aerostat.