液体姿控火箭发动机地面试验热结构分析

胡海峰; 鲍福廷; 蔡强; 刘旸

液体姿控火箭发动机地面试验热结构分析

西北工业大学航天学院,西安 710072

计量
- 文章访问数: 1651
- HTML浏览量: 7
- PDF量: 9
- 被引次数: 0
出版历程
- 收稿日期: 2010-07-04
- 修回日期: 2010-10-27
- 刊出日期: 2011-02-28

Analysis of thermo-structure for attitude liquid rocket engine in ground test

School of Astronautics, Northwestern Polytechnical University,Xian 710072,China

摘要

摘要: 以液膜冷却结合辐射冷却的液体姿控火箭发动机为研究对象.采用一体化计算模型分析传热,同时应用有限元方法对给定温度条件的热结构进行了耦合分析,最后讨论了推力室在外压作用及温度载荷条件下结构的屈曲稳定性.计算结果与参考的试验结果接近,最高温度误差为3.67%,说明该一体化计算传热模型的有效性.考虑热载荷作用得到的屈曲载荷值较不考虑热载荷作用提高了大约5.7933%.该结果为工程设计提供了有益的参考.
- 液体姿控火箭发动机 /
- 推力室 /
- 液膜冷却 /
- 热结构分析 /
- 屈曲分析
Abstract: A research on the attitude liquid rocket engine using the film cooling and radiation cooling methods was performed.A model based on film cooling heat transfer,which employs an integrated analysis method,was presented by this paper.The finite element method (FEM) was used for coupling analysis of the thermal and structure of thruster chamber under the condition of calculated wall temperature and pressure distributions.At last,with use of the FEM,the thruster chamber buckling was discussed under the condition of the given temperature,pressure and the load of external pressure.The result was close to the referenced experiment result,with the greatest temperature error of 3.67%.The result indicates that the integrated analysis method for the simulation of heat transfer is efficient;taking into account of the thermal load,the buckling load is increased about 5.7933% than that without thermal load.The results provide some theory support for engineering applications.
- attitude liquid rocket engine /
- thruster chamber /
- film cooling /

HTML

参考文献(13)

[1]	肖泽娟,程惠尔,李鹏.姿控发动机真空深冷环境中传热研究[J].热科学与技术,2005,4(2):101-105. XIAO Zejuan,CHENG Huier,LI Peng.Heat transfer research on gesture control engine in vacuum cryogenic environment [J].Journal of Thermal Science and Technology,2005,4(2):101-105.(in Chinese)
[2]	张忠利.姿控发动机热防护研究[J].火箭推进,2008,34(3):18-22. ZHANG Zhongli.Investigation on thermal protection for attitude correction liquid rocket engine[J].Journal of Rocket Propulsion,2008,34(3):18-22.(in Chinese)
[3]	方磊,刘伟.姿控用再生冷却推力室传热特性研究[J].火箭推进,2008,34(6):6-13. FANG Lei,LIU Wei.Research on heat transfer characteristic of regeneratively cooled attitude control engine thrust chamber [J].Journal of Rocket Propulsion,2008,34(3):18-22.(in Chinese)
[4]	董飞,何国强.铣槽结构液体火箭发动机推力室壳体热应力分析[J].火箭推进,2007,33(3):43-46. DONG Fei,HE Guoqiang.Thermal stress analyses of liquid propellant thruster chamber wall with milled slots[J].Journal of Rocket Propulsion,2007,33(3):43-46.(in Chinese)
[5]	孙威,方杰,郑力铭,等.N₂O微推力器性能及喷管热结构分析[J].火箭推进,2008,34(5):5-9. SUN Wei,FANG Jie,ZHENG Liming,et al.N₂O micro-thruster performance and the nozzle thermo-structure analysis[J].Journal of Rocket Propulsion,2008,34(5):5-9.(in Chinese)
[6]	魏鑫,孙冰,郑力铭,等.超燃冲压发动机进气道表面热结构设计与分析[J].航空动力学报,2008,23(11):1961-1965. WEI Xin,SUN Bing,ZHENG Liming,et al.Design and analysis of thermal structure of inlet of scramjet [J].Journal of Aerospace Power,2008,23(11):1961-1965.(in Chinese)
[7]	张贵田.高压补燃液氧煤油发动机[M].北京:国防工业出版社,2005.
[8]	Stechman R C,Oberstone J,Howell J C.Film cooling design criteria for small rocket engines .AIAA-1968-617,1968.
[9]	张锋,仲伟聪.膜冷却推力室传热计算研究[J].火箭推进,2009,35(4):34-37,48. ZHANG Feng,ZHONG Weicong.Computational investigation of heat transfer for film cooling thrust chamber[J].Journal of Rocket Propulsion,2009,35(4):34-37,48.(in Chinese)
[10]	ANSYS Inc.Release 11.0 documentation for ANSYS[M]. Canonsburg:ANSYS Inc.,2007.
[11]	TAN Dongyao.Torsional buckling analysis of thin and thick shells of revolution[J].International Journal of Solids and Structures,2000,37(22):3035-3078.
[12]	王新敏.ANSYS工程结构数值分析[M].北京:人民交通出版社,2007.
[13]	尤军锋,陈汝训.固体火箭发动机壳体后封头屈曲分析[J].固体火箭技术,2008,31(2):173-178. YOU Junfeng,CHEN Ruxun.Buckling analysis on rear dome of solid rocket motor case[J].Journal of Solid Rocket Technology,2008,31(2):173-178.(in English)