空天防御2025，Vol.8Issue(1)：102-108,7.
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
李易 1欧树彦 1梁伟栋 2董佳宝 2庄至栋2
作者信息
- 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
- 折叠
摘要
Abstract
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Key words
rocket fairing/high dynamic pressure/separation/hypersonic/numerical simulation分类
航空航天引用本文复制引用
李易,欧树彦,梁伟栋,董佳宝,庄至栋..飞行器低空大动压整流罩旋抛分离数值模拟[J].空天防御,2025,8(1):102-108,7.
