结构变形对高超声速可变形减速器的动态稳定性影响分析  

The Effect of Structural Deformation on the Dynamic Stability of a Hypersonic Inflatable Aerodynamic Decelerator

作　　者：时晓天[1] 张桂茹[1] 吕蒙 赵渊 高军[1] SHI Xiaotian;ZHANG Guiru;LYU Meng;ZHAO Yuan;GAO Jun(China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《航天返回与遥感》2025年第1期11-20,共10页Spacecraft Recovery & Remote Sensing

基　　金：国家自然科学基金项目(11872348,11802297)。

摘　　要：文章针对高超声速可变形减速器的飞行稳定性预测及回收着陆需求,研究表面结构变形对减速器气动特性的影响效应,重点分析了高度10~50 km、Ma=0.15~4.6关键速域内的静、动态气动特性变化。文章采用求解雷诺平均Navier-Stokes方程(Reynolds average Navier-Stokes,RANS)的数值模拟方法,获得了有无表面结构变形减速器的流场和气动参数。定常计算结果表明:变形效应导致飞行器迎风面存在局部的小尺度流动分离,变形后外形的气动阻力增加。结合刚性动网格技术的俯仰强迫振动,计算结果表明:减速器的动态稳定性受到迎风面高压及背风面分离涡结构的共同作用,迎风面的高气动压力载荷占主导作用,使得减速器的动态稳定性增强;背风面的涡结构导致动态稳定性减弱;轴对称分布的表面结构变形整体上增强了减速器的动态稳定性。According to the requirement of prediction of dynamic stability and recovery and landing of hypersonic inflatable aerodynamic decelerator,this paper presents a detailed analysis of structural deformation effect on the dynamic stability for the decelerator in the most sensitive velocity range of Ma=0.15 to 4.6.The flow field and aerodynamic coefficients of the aircraft with and without structural deformation are obtained with a Reynolds average Navier-Stokes equation solver.Steady simulation results shows that the static structural deformation results in local flow separation on the winward surface of the aircraft and increases the axial aerodynamic coefficient.Unsteady simulation results of forcing pitching oscillation and rigid moving mesh technique show that the high pressure on winward surface stablizes the aircraft dynamic stability while the vortex in the wake flow weakens the vehicle dynamic stability,the axial symmetric structural deformation enhances the decelerator dynamic stability in total.

关 键 词：回收着陆 高超声速可变形减速器 结构变形 动态稳定性 强迫振动 动导数 

分 类 号：V475.9[航空宇航科学与技术—飞行器设计]