Analysis of Reliability Evaluation Method of Reusable Liquid Rocket Engine

GA Yongjing, LI Wenzhao, SONG Qianqiang, CHU Liang, MA Yitong, XIE Shuang, SHEN Bo

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Journal of Deep Space Exploration ›› 2022, Vol. 9 ›› Issue (5) : 498-505. DOI: 10.15982/j.issn.2096-9287.2022.20220035

Analysis of Reliability Evaluation Method of Reusable Liquid Rocket Engine

  • GA Yongjing, LI Wenzhao, SONG Qianqiang, CHU Liang, MA Yitong, XIE Shuang, SHEN Bo
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Abstract

Traditional reliability evaluation of liquid rocket engines requires a large number of verification samples. So the reliability evaluation method of reusable liquid rocket engine was studied. By analyzing the characteristics and failure modes of the instantaneous process of ignition for reusable rocket engines, and taking the instantaneous process of ignition as two independent processes (ignition process and transient development process), and the maximum entropy method and normal allowable limit method were evaluated individually. Meanwhile, the influence of reliability requirements and life shape parameters to total time of hot-fire tests, as well as the change of reliability with the number of tasks performed, were analyzed using the reliability evaluation method under study. It is shown that the proposed evaluation method can obtain higher reliability evaluation results with less test times. With the higher reliability requirements, the total time of hot-fire tests increases greatly; increasing the life shape parameters can greatly reduce the total time of hot-fire tests with the same reliability requirements; and the engine reliability decreases gradually with the increase of the number of tasks performed.

Keywords

reusable liquid rocket engine / reliability evaluation / test plan

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GA Yongjing, LI Wenzhao, SONG Qianqiang, CHU Liang, MA Yitong, XIE Shuang, SHEN Bo. Analysis of Reliability Evaluation Method of Reusable Liquid Rocket Engine. Journal of Deep Space Exploration, 2022, 9(5): 498‒505 https://doi.org/10.15982/j.issn.2096-9287.2022.20220035

References

[1] 龙乐豪,王国庆,吴宝胜,等. 我国重复使用航天运输系统发展现状及展望[J]. 国际太空,2019(9):4-10
[2] 杨勇,王小军,唐一华,等. 重复使用运载器发展趋势及特点[J]. 导弹与航天运载技术,2002(5):15-19
YANG Y,WANG X J,TANG Y H,et al. Development trends and characteristics of reusable launch vehicles[J]. Missiles and Space Vehicles,2002(5):15-19
[3] 郑孟伟,岳文龙,孙纪国,等. 我国大推力氢氧发动机发展思考[J]. 宇航总体技术,2019,3(2):12-17
ZHENG M W,YUE W L,SUN J G,et al. Discussion on Chinese large-thrust hydrogen-oxygen rocket engine development[J]. Astronautical System Engineering Technology,2019,3(2):12-17
[4] 汪钺. 航天飞机主发动机的可靠性是怎样获得的[J]. 国外导弹与宇航,1982(1):37-40
[5] 潘勇,黄进永,胡宁 . 可靠性概论[M]. 北京:电子工业出版社出版,2015.
[6] 宋征宇,方志耕,赫武乐,等. 基于贝叶斯理论的小子样运载火箭可靠性评估技术[J]. 深空探测学报(中英文),2021,8(1):62-69
SONG Z Y,FANG ZH G,HE W L,et al. Research on launch vehicle reliability assesement of small sample based on Bayes theory[J]. Journal of Deep Space Exploration,2021,8(1):62-69
[7] 闻悦,马婷婷,郑平军,等. 重复使用航天运输系统设计与评估[J]. 科学通报,2020,65(9):764-770
YUE W,MA T T,ZHEN P J,et al. Design and assessment of reusable space transportation system[J]. Chinese Science Bulletin,2020,65(9):764-770
[8] 孙国庆. 航天飞机主发动机试验[J]. 国外导弹技术,1980(7):20-27
[9] JOHNSON J R,COLBO H I. Space shuttle main engine progress through the first flight[C]//The 17th AIAA Joint Propulsion Conference. Colorado:Springs,1981.
[10] 谭松林,李宝盛. 液体火箭发动机可靠性[M]. 北京:中国宇航出版社,2014.
[11] 刘洪坤,王维彬. 发动机启动燃气反腔仿真与影响分析[J]. 火箭推进,2011,37(2):30-37
LIU H K,WANG W B. Backflow simulation and its influence analysis for gas generator of LRE[J]. Journal of Rocket Propulsion,2011,37(2):30-37
[12] 张楠,孙慧娟. 低温液体火箭发动机重复使用技术分析[J]. 火箭推进,2020,46(6):1-10
ZHANG N,SUN H J. Analysis on the reusable cryogenic liquid rocket engine technology[J]. Journal of Rocket Propulsion,2020,46(6):1-10
[13] BORIS I K,VLADIMIR K C,FELIX J C. Oxidizer-rich staged combustion rocket engines use and development in Russia[C]//AIAA Space Programs and Technologies Conference. Huntsville,AL:AIAA,1995.
[14] LACEFIELD T C,SPROW W J. High performance Russian NK-33 LOX/Kerosene liquid rocket engine[C]//The 30th AIAA Joint Propulsion Conference. Indianapolis,IN:AIAA,1994.
[15] 徐浩海,刘站国. 补燃循环发动机启动过程涡轮功率控制[J]. 火箭推进,2006,32(4):10-14
XU H H,LIU Z G. Turbine power control of staged combustion cycle engine during start-up[J]. Journal of Rocket Propulsion,2006,32(4):10-14
[16] 王珏,孙慧娟,刘恒,等. 膨胀循环发动机低温启动特性研究[J]. 导弹与航天运载技术,2021(6):7-11
WANG J,SUN H J,LIU H,et al. Research on the start-up characteristics of expander cycle engine with a colder thrust chamber[J]. Missiles and Space Vehicles,2021(6):7-11
[17] BINDER M P. A transient model of the RL10A-3-3A rocket engine[C]//The 31st AIAA Joint Propulsion Conference and Exhibit. San Diego,CA:AIAA,1995.
[18] BINDER M P. RL10A-3-3A rocket engine modeling project:NASA-TM-107318[R]. Washington DC:NASA,1997.
[19] 袁洁,潘亮. 基于发动机试车时序的某钝感点火器燃烧时间可靠性评估[J]. 火箭推进,2015,41(3):87-97
YUAN J,PAN L. Reliability assessment of a certain insensitive igniter based on start-up time-sequence of rocket engine[J]. Journal of Rocket Propulsion,2015,41(3):87-97
[20] 刘杰,王普,刘炳章. 最大熵试验法及其应用[J]. 自动化学报,2007,33(11):1226-1228
LIU J,WANG P,LIU B Z. Test method with the maximum entropy and its application[J]. Acta Automatica Sinical,2007,33(11):1226-1228
[21] 刘炳章,丁同才. 小子样验证高可靠性的可靠性评估方法及其应用[J]. 质量与可靠性,2004(1):19-22
[22] 董海平,柳洋,袁世越. 基于正态容许限法的点火器可靠性评估[J]. 科技创新导报,2021(4):5-9.
DONG H P,LIU Y,YUAN S Y. Reliability evaluation of igniter based on normal allowable limit method[J]. Science and Technology Innovation Herald,2021(4):5-9.
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