航天推进技术研究院主办
[1]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(06):6-13.
Fang Lei,Liu Wei.Research on heat transf．er characteristic of regeneratiVely cooled attitude control engine thmst chamber[J].Journal of Rocket Propulsion,2008,34(06):6-13.
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Fang Lei,Liu Wei.Research on heat transf．er characteristic of regeneratiVely cooled attitude control engine thmst chamber[J].Journal of Rocket Propulsion,2008,34(06):6-13.
姿控用再生冷却推力室传热特性研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
34
期数:
2008年06期
页码:
6-13
栏目:
研究与设计
出版日期:
2008-12-30
- Title:
- Research on heat transf．er characteristic of regeneratiVely cooled attitude control engine thmst chamber
- Keywords:
- attitude control engine thrust chamber; regeneratiVe c00ling; wall temperature; heat flllx
- 分类号:
- V434
- 文献标志码:
- A
- 摘要:
- 对采用MON一25／MMH推进剂的姿控用再生冷却推力室的传热特性进行了研究。 首先使用二维传热计算程序。对推力室壁及再生冷却剂MMH的传热特性进行了初步评估，然 后运用CFD软件对该问题进行了三维数值模拟．最后将两种方法的计算结果与常温300K和 低温243K入口条件下的MON一25／MMH再生冷却推力室热试车状态进行对比。发现三者基本 一致。
- Abstract:
- Heat transfer characteristics of regeneratively cooled attitude control engine thllJst chamber with MON一25／MMH pmpellant were studied．Firstly，heat transfer characteristics of thrust chamber waJl and regenerative coolant MMH were evaluated by the two dimensional heat transfer calculation code，then the three dimensional model was numerically simulated with the CFD soft— ware．The numerical results are well in agreement with the hot fire tests parameters of regenemtively cooled thlllst chamber with MON一25／MMH propellant at different working temperature of 298K and 243K．The results show that the numerical method can be used to evaluate the wall temperature，the heat nux thmugh the waU，and the temperature increase of coolant．The numerical results are ex． pected to be helpful for the design，especially for the design of regeneratiVely cooled attitude control engine thlllst chamber．
参考文献/References:
[l]Fmehlich A，Immich H，Lebail F'et a1．Three--dimensional
now Analysis in a Rocket Engine c001ant Channel of High
Depth，Widtll Ratio[R]．AIAA 9l一21 83．
[2]Cados H M，Femando L，Antonio F C da Silva'et a1．
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[3]Lai Y G，Przekwas A J，Nguyen H．A Concurrem Muhi—
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[4]Knab 0，Fr0Hehlich A,Wennerberg D'et aL Advanced
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[5]吴峰，曾敏，王秋旺，等．通道深宽比对液体火箭发动机推
力室再生冷却的影响[J]．航空动力学报，2007，22(1)：
114．118．
[6]刘国球．液体火箭发动机原理[M]．北京：中国宇航出版
社．1993．
[7]杨世铭，陶文铨．传热学(第三版)[M]．北京：高等教育出
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[81金属材料手册(下册)[M]．北京：中国运载火箭技术研究
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备注/Memo
收稿日期：2008_08一13；修回日期：2008-09一19。 作者简介：方磊(1981一)，男，硕士，研究领域为轨姿控火箭发动机设计。
更新日期/Last Update:
1900-01-01