高超声速验证飞行器助推分离段流场数值研究

推进技术 ›› 2002, Vol. 23 ›› Issue (3): 219-222.

高超声速验证飞行器助推分离段流场数值研究

郭正,刘君,李晓斌,瞿章华

国防科技大学航天与材料工程学院湖南长沙410073;国防科技大学航天与材料工程学院湖南长沙410073;国防科技大学航天与材料工程学院湖南长沙410073;国防科技大学航天与材料工程学院湖南长沙410073

发布日期:2021-08-15
基金资助:
国防科技预研基金项目 (98J13 4 1 KJ0 131)

Numerical study of flow past hypersonic research vehicle with detaching booster

Inst of Aerospace and Material Engineering, National Univ of Defence Technology, Changsha 410073, China;Inst of Aerospace and Material Engineering, National Univ of Defence Technology, Changsha 410073, China;Inst of Aerospace and Material Engineering, National Univ of Defence Technology, Changsha 410073, China;Inst of Aerospace and Material Engineering, National Univ of Defence Technology, Changsha 410073, China

Published:2021-08-15

摘要/Abstract

摘要： 为了模拟有相对运动的多体非定常绕流 ,发展了基于弹簧近似的非结构动网格方法及耦合动网格的Euler解算器。作为方法验证 ,模拟了俯仰振动的NACA0 0 12翼型绕流 ,计算结果与实验及文献结果非常接近。采用二维近似外形 ,对高超声速验证飞行器助推分离段流场进行了数值研究 ,得到了不同时刻由于多体相对运动形成的干扰流场结构以及分离过程的气动力参数。

关键词: 助推器分离;非定常流;流动分布;数值仿真;欧拉方程

Abstract: Dynamic unstructured grid methodology and ALE Euler solver for complex multi body flows involving moving boundaries were developed Pitching NACA0012 airfoil flow was simulated as a demonstration of the method, results of which compare well with that of experiment and literature The methodology then was applied to simulate the flow past Hyper X research vehicle when separating with its booster Though the simulation performed on 2 D approximate configuration, complex flow structures at different instants were obtained as well as force and moment coefficients during the whole course

Key words: Booster separation;Unsteady flow;Flow distribution;Numerical simulation;Euler equation

郭正,刘君,李晓斌,瞿章华. 高超声速验证飞行器助推分离段流场数值研究[J]. 推进技术, 2002, 23(3): 219-222.