Thermo-Structural Response Caused by Structure Gap and Gap Design for Solid Rocket Motor Nozzles

被引：10

作者：

Sun, Lin ^{[1
,2
]}

Bao, Futing ^{[1
,2
]}

Zhang, Ning ^{[3
]}

Hui, Weihua ^{[1
,2
]}

Wang, Shaozeng ^{[4
]}

Zhang, Nan ^{[4
]}

Deng, Heng ^{[4
]}

机构：

[1] Northwestern Polytech Univ, Sci & Technol Combust Internal Flow & Thermal Str, Xian 710072, Shaanxi, Peoples R China

[2] Northwestern Polytech Univ, Sch Astronaut, Xian 710072, Shaanxi, Peoples R China

[3] AVIC Qing An Grp Co Ltd, Aviat Equipment Res Inst, Xian 710077, Shaanxi, Peoples R China

[4] Xian Modern Control Technol Res Inst, Xian 710065, Shaanxi, Peoples R China

来源：

ENERGIES | 2016年 / 9卷 / 06期

基金：

中国国家自然科学基金;

关键词：

structure gap; frictional interfaces; thermo-structural; gap design;

D O I：

10.3390/en9060430

中图分类号：

TE [石油、天然气工业]; TK [能源与动力工程];

学科分类号：

0807 ; 0820 ;

摘要：

The thermo-structural response of solid rocket motor nozzles is widely investigated in the design of modern rockets, and many factors related to the material properties have been considered. However, little work has been done to evaluate the effects of structure gaps on the generation of flame leaks. In this paper, a numerical simulation was performed by the finite element method to study the thermo-structural response of a typical nozzle with consideration of the structure gap. Initial boundary conditions for thermo-structural simulation were defined by a quasi-1D model, and then coupled simulations of different gap size matching modes were conducted. It was found that frictional interface treatment could efficiently reduce the stress level. Based on the defined flame leak criteria, gap size optimization was carried out, and the best gap matching mode was determined for designing the nozzle. Testing experiment indicated that the simulation results from the proposed method agreed well with the experimental results. It is believed that the simulation method is effective for investigating thermo-structural responses, as well as designing proper gaps for solid rocket motor nozzles.

引用

页数：21