飞行器低空大动压整流罩旋抛分离数值模拟  

Numerical Simulation of Rocket Fairing Spin Separation in Low-Altitude High-Dynamic-Pressure Environment

作　　者：李易 欧树彦 梁伟栋 董佳宝 庄至栋 LI Yi;OU Shuyan;LIANG Weidong;DONG Jiabao;ZHUANG Zhidong(Shaanxi Aerospace Flight Vehicle Design Key Laboratory,Northwestern Polytechnical University,Xi'an 710072,Shaanxi,China;Shanghai Electro-Mechanical Engineering Institute,Shanghai 201109,China)

机构地区：[1]西北工业大学陕西省空天飞行器设计重点实验室,陕西西安710072 [2]上海机电工程研究所,上海201109

出　　处：《空天防御》2025年第1期102-108,共7页Air & Space Defense

摘　　要：为研究低空大动压环境下飞行器整流罩旋抛分离的运动特性,本文采用CFD-刚体动力学耦合仿真的方法开展数值模拟。分析了该过程的流场结构以及整流罩的动力学行为;着重研究了来流非对称条件下,两瓣整流罩张开速度不一致情况以及整流罩脱钩角发生变化情况下的张开动力学。研究表明:来流不对称时,其中一瓣整流罩分离受到抑制,不利于安全分离;为此增大脱钩角有助于增加整流罩的迎风面积,加快其远离飞行器的速度。To investigate the motion characteristics of the fairing separation of aircraft in a low-altitude high-dynamic-pressure environment,a numerical simulation was applied using the CFD-rigid body dynamics coupling method.This study has revealed the flow structure and dynamic behavior of the fairing during the process.Specifically,focused on the asymmetric inflow conditions,the disparate opening speeds of the two fairing halves,and the variations in the detachment angle of the fairing.Results show that under asymmetric inflow conditions,the separation of one half of the fairing is suppressed,being detrimental to a safe separation.Increasing the detachment angle is beneficial in terms of enlarging the windward area of the fairing while accelerating its separation from the aircraft.

关 键 词：火箭整流罩 大动压 分离 高超声速 数值模拟 

分 类 号：V411[航空宇航科学与技术—航空宇航推进理论与工程]