|Table of Contents|

Finite element analysis of grain temperature field for a solid rocket motor(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2019年02期
Page:
32-35
Research Field:
研究与设计
Publishing date:

Info

Title:
Finite element analysis of grain temperature field for a solid rocket motor
Author(s):
LI YuanSUN ZhanpengZHOU YanqingSUN DiHUANG Weiwei
(Xi'an Institute of Aerospace Power Technology, Xi'an 710025, China)
Keywords:
solid rocket motor grain temperature field heat transfer finite element analysis
PACS:
V435.14
DOI:
-
Abstract:
In order to explore a simple and effective technical approach to the temperature field of solid rocket motor grain under variable ambient temperature, the grain temperature field of a solid rocket motor under temperature circulating test was studied by means of finite element heat transfer analysis.Two-dimension and three-dimension heat transfer models were established for different grain structures.By comparing the calculated results with the test results, the two-dimensional heat transfer method can improve the calculation efficiency of the grain temperature field, and the calculation results are in good agreement with the test results, which can meet the test prediction requirements.Therefore, in the engineering analysis, in order to obtain the effective analysis results quickly, the two-dimensional heat transfer model can be used to analyze the grain temperature field of solid rocket motor.The two-dimensional non-fin grain model is suitable for simulating the temperature field of the grain far away from the fin, and the two-dimensional fin-having grain model is suitable for simulating the temperature field near the grain fin.

References:

[1] 李葆萱.固体推进剂性能[M].西安:西北工业大学出版社,1990.
[2] 陈汝训.固体火箭发动机设计与研究(上)[M].北京:宇航出版社,1991.
[3] 王勖成.有限单元法[M].北京:清华大学出版社,2003.
[4] 周红梅,李季颖,袁嵩,等. 固化降温过程中固体火箭发动机药柱温度场应力场分析[J].导弹与航天运载技术,2015(1):104-106.
[5] 赵峰,常新龙.某固体推进剂湿热老化模型[J].火箭推进,2008,34(1):59-62. ZHAO Feng,CHANG Xinlong.Hygrothermal aging life model of a composite solid propellant[J].Journal of Rocket Propulsion,2008,34(1):59-62.
[6] 李高春,董可海,张勇,等.环境温度作用下固体火箭发动机药柱的累积损伤规律[J].火炸药学报,2010,33(4):19-22.
[7] 袁军.交变环境温度下固体发动机药柱温度场分析[J].固体火箭技术,2015,38(6):818-820.
[8] 郑亚,陈军,鞠玉涛,等.固体火箭发动机传热学[M].北京:北京航空航天大学出版社,2006.
[9] 朱智春,蔡峨.固体火箭发动机药柱三维温度场应力场有限元分析[J].推进技术,1997,18(2):21-26.
[10] 张建伟,孙冰.固体火箭发动机药柱三维结构非线性分析[J].宇航学报,2006,27(5):871-875.
[11] 丁永强,兰飞强.温度载荷下材料参数对药柱结构完整性的影响[J].航空兵器,2007(5):49-51.

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Last Update: 2019-04-30