摘要
对某型固体火箭尾舱热环境进行了研究,发现尾舱热环境存在明显的天地差异,通过数值仿真结果分析了对流热环境产生的机理.在真实飞行环境下,火箭尾舱外部绕流产生的激波和发动机喷流激波之间存在剪切层,剪切层与尾舱连通,在激波与剪切层的相互作用下形成非定常漩涡结构,是尾舱内对流加热的来源.剪切层的强弱与对流热流的大小密切相关,根据对流热流产生机理,对一种减小对流热流的结构形式进行了研究,通过减弱火箭尾部的剪切层,大幅减小了对流热流,固体火箭尾舱热环境得到明显改善.
The thermal environment of a solid rocket tail cabin was studied. There is obvious difference between the conditions in the sky and on the ground. The mechanism of convection thermal environment was analyzed by numerical simulation. In the real launch , there is a shear layer between the shock waves from the outflow of rocket tail cabin and fram the engine jet. The shear layer is connected with the tail cabin. An unsteady vortex structure is formed by the shock wave and shear layer , which is the source of convection heat flux in the tail cabin. The strength of shear layer is related to the convection heat flux. According to the mechanism of convection heat flux , a structural form of reducing convection heat flux was calculated. By weakening the shear layer at the rocket tail , the convection heat flux is greatly reduced. The thermal environment of solid rocket tail cabin is obviously ameliorated.
作者
杨学军
沈清
姚瑶
任一鹏
朱莉
YANG Xue-jun;SHEN Qing;YAO Yao;REN Yi-peng;ZHU Li(Ｂｅｉｊｉｎｇ Ｉｎｓｔｉｔｕｔｅ ｏｆ Ａｓｔｒｏｎａｕｔｉｃａｌ Ｓｙｓｔｅｍｓ Ｅｎｇｉｎｅｅｒｉｎｇ Ｂｅｉｊｉｎｇ １０００７６ Ｃｈｉｎａ;
Ｃｈｉｎａ Ａｃａｄｅｍｙ ｏｆ Ａｅｒｏｓｐａｃｅ Ａｅｒｏｄｙｎａｍｉｃｓ Ｂｅｉｊｉｎｇ １０００７４ Ｃｈｉｎａ)
出处
《气体物理》
2019年第1期8-15,共8页
Physics of Gases
关键词
热环境
固体火箭
对流加热
尾舱
剪切层
thermal environment
solid rocket
convection heat flux
tail cabin
shear layer
