航天推进技术研究院主办
[1]王 珺,胡 鹏,颜 勇.液体火箭发动机泵的POGO气蚀动特性试验研究[J].火箭推进,2012,38(04):26-31.
WANG Jun,HU Peng,YAN Yong.Experimental investigation of POGO cavitation dynamic characteristic for liquid rocket engine pump[J].Journal of Rocket Propulsion,2012,38(04):26-31.
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WANG Jun,HU Peng,YAN Yong.Experimental investigation of POGO cavitation dynamic characteristic for liquid rocket engine pump[J].Journal of Rocket Propulsion,2012,38(04):26-31.
液体火箭发动机泵的POGO气蚀动特性试验研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
38
期数:
2012年04期
页码:
26-31
栏目:
研究与设计
出版日期:
2012-08-15
- Title:
- Experimental investigation of POGO cavitation dynamic characteristic for liquid rocket engine pump
- 文章编号:
- 1672-9374(2012)04-0026-06
- Keywords:
- pump cavitation dynamic parameter; POGO; experimental system; cavitation compliance; dynamic gain
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 为获取液体火箭发动机泵的POGO动特性参数，围绕泵的气蚀动特性开展了一系列试验研究。首先描述了试验系统，阐述了试验原理；其次，以泵入口0.5 MPa工况为例，介绍了试验数据的分析过程；最后，结合试验数据给出了气蚀柔度、动态增益等动特性参数的试验结果。结果表明，在泵入口压力0.25~0.86 MPa范围内，无量纲气蚀柔度约为0.6~2，动态增益主要集中在2~5，最高达到13。
- Abstract:
- A series of experimental investigations were performed in order to obtain the POGO dynamic parameters of liquid rocket engine pump. The experimental system is described and the main test principle is expounded. The analysis progress of test data at pump inlet pressure of 0.5 MPa is introduced. Based on test results, the POGO dynamic characteristic parameters, such as cavitation compliance and pump dynamic gain, are given. The investigation shows that, under the condition of pump inlet pressure of 0.25~0.86 MPa, the non-dimensional cavitation compliance is 0.6~2, the pump dynamic gain is 2~5 and the maximum observation value is up to 13.
参考文献/References:
[1]COPPOLINO R F, LOCK M H, RUBIN S. Space shuttle POGO studies, ATR-78(7474)-1[R]. USA: The Aerospace Corporation, 1977.
[2]SHIMURA Takashi. The effects of geometry in the dynamic response of the cavitating LE-7 OX pump[C]//29th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhi- bit. Monterey, CA: AIAA, 1993: 121-131.
[3]PILIPENKO V V. Providing the LPRE-rocket structure dynamic compatibility[C]//29th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Monterey, CA: AIAA, 1993: 202-212.
[4]DOTSON K W, RUBIN S, SAKA B H. Effects of unsteady pump cavitation on propulsion-structure interaction in liquid rockets[C]//45th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics & Materials Conference. Palm Springs, California: AIAA, 2004: 10-20.
[5]IACOPOZZI M, LIGNAROLO V, PREVEL D. POGO characterization of Ariane V turbopump LOX pump with hot water[C]//29th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Monterey, CA: AIAA, 1993: 1-9.
[6]RUBIN Sheldon. An interpretation of transfer function data for a cavitating pump[C]// 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Fort Lauderdale, Florida: AIAA, 2004: 111-121.
[7]RAPPOSELLI Emilio, CERVONE Angelo, TESTA Renzo, et al. Thermal effects on cavitation instabilities in helical inducers[C]//40th AIAA/ASME/SAE/ASEE Joint Propul- sion Conference and Exhibit. Fort Lauderdale, Florida: AIAA, 2004: 151-158.
[8]SHIMAGAKI Mitsuru, WATANABE Mitsuo, HASHIMOTO Tomoyuki, et al. Effect of the casing configurations on the internal flow in rocket pump inducer[C]//42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Sacramento, California: AIAA, 2006: 51-58.
[9]OPPENHEIM B W, RUBIN Sheldon. Advanced POGO stability analysis for liquid rockets, AIAA-92-2454-CP [R]. USA: AIAA, 1992.
[10]张涛, 唐虎, 周江平. 可贮存推进剂泵压式液体火箭发动机多次起动系统研究[J]. 火箭推进, 2010 (3): 19-22.
[11]曹泰岳. 火箭发动机动力学[M]. 长沙: 国防科技大学出版社, 2004
相似文献/References:
[1]邢理想,杜大华,李斌.液氧／煤油补燃火箭发动机氧路低频动特性分析[J].火箭推进,2009,35(05):24.
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备注/Memo
收稿日期：2012-01-15；修回日期：2012-03-06
基金项目：国家“863”项目（2007AA705302)
作者简介：王珺（1984—），男，硕士，工程师，研究领域为液体火箭发动机系统设计
更新日期/Last Update:
1900-01-01