Volume 37 Issue 5
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LIU Shijie, LIU Dengfeng, MA Xiaoqiu, LIANG Guozhu. Predicting method of safety life of reusable liquid rocket engine turbopump[J]. Journal of Aerospace Power, 2022, 37(5): 1079-1089. doi: 10.13224/j.cnki.jasp.20210420
Citation: LIU Shijie, LIU Dengfeng, MA Xiaoqiu, LIANG Guozhu. Predicting method of safety life of reusable liquid rocket engine turbopump[J]. Journal of Aerospace Power, 2022, 37(5): 1079-1089. doi: 10.13224/j.cnki.jasp.20210420
shu

Predicting method of safety life of reusable liquid rocket engine turbopump

doi: 10.13224/j.cnki.jasp.20210420
  • 1.

    Beijing Aerospace Propulsion Institute，China Aerospace Science and Technology Corporation，Beijing 100076，China

  • 2.

    Laboratory of Science and Technology on Cryogenic Liquid Propulsion，Beijing Aerospace Propulsion Institute，China Aerospace Science and Technology Corporation，Beijing 100076，China

  • 3.

    School of Astronatuics，Beihang University，Beijing 102206，China

  • Received Date: 2021-08-08
  • Publish Date: 2022-05-28
    Abstract
  • Based on the life distribution model of complex system and fault tree analysis （FTA） theory，a safety life prediction method of turbopump was established.As an example，the safety life of the high pressure liquid hydrogen turbopump （HPFTP） of the space shuttle main engine （SSME） was verified to demonstrate this method.The results showed that：（1） The life of complex system roughly followed the exponential distribution when the number of HPFTP critical components was more than 10，and a more reliable result accompanied a larger number.（2） The mean time between failure （MTBF） and mean time to repairment （MTTR）of HPFTP was 76 917 h and 8 879 h，respectively，and the safety life of 0.998 8 reliability was 25 575 s，which can be used 49 times safely；the safety life of 0.999 6 reliability was 8 521 s，which can be used for 16 times；the reliability was 0.999 7 for 11 times safety use.（3） The key components of HPFTP safety life were turbine blade and nozzle，and their corresponding critical importance was 0.217 5 and 0.216 6，respectively，and the critical importance of both liquid collector and the impeller was 0.174 2.This work can provide a reference for the reusability research of complex components such as liquid rocket engine turbopump.

     

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    • References(19)
  • [1]
    CIKANEK H A.Characteristics of space shuttle main engine failures[R].AIAA-87-1939,1987.
    [2]
    ABDUL-AZIZ A,THOMPSON R L.Thermal-structural analysis of space shuttle main engine （SSME） hot section components[R].NASA-22404,1988.
    [3]
    PASTER R D,STOHLER S L.SSME evolution[R].AIAA-1989-2618，1989.
    [4]
    WILLIAMS W C.Report of the SSME assessment team[R].Washington DC：National Aeronautics and Space Administration,N93-21645,1993.
    [5]
    ABDUL-AZIZ A.Structural evaluation of a space shuttle main engine （SSME） high pressure fuel turbopump turbine blade[R].NASA-CR-198428,1996.
    [6]
    BLAIR J C,RYAN R S.Lessons learned in engineering[R].NASA/CR-216468,2011.
    [7]
    刘士杰,梁国柱.航天飞机主发动机高压燃料涡轮泵的故障模式[J].航空动力学报，2015,30（3）:611-626.
    [8]
    DRENICK R F.The failure law of complex equipment[J].Journal of the Society for Industrial and Applied Mathematics，1960,8（4）:680-690.
    [9]
    TANG S D,WANG F Q.Reliability analysis for a repairable parallel system with time-varying failure rates[J].Applied Mathematics:A Journal of Chinese Universities，2005,20（1）:85-90.
    [10]
    COLLINS D H,WARR R L.Failure time distributions for complex equipment[J].Quality and Reliability Engineering International,2018,35（1）:1-9.
    [11]
    刘士杰,梁国柱.FTA方法在SSME高压氢泵可靠性分析中的应用[C]∥2011年中国航天第三专业信息网学术交流会论文集.甘肃 敦煌：中国航天第三专业信息网,2011:790-797.
    [12]
    刘士杰,康红雷,梁国柱,液体火箭发动机重复使用性指标分配方法的初探[C]∥第三届空天推进技术会议论文集.福建 厦门:中国航天科技集团第六研究院有限公司，2021:82-91.
    [13]
    金星,洪延姬,沈怀荣,等.工程系统可靠性数值分析方法[M].北京:国防工业出版社,2002.
    [14]
    FRAGOLA J R,MAGGIO G.Probabilistic risk assessment of the space shuttle.phase 3:a study of the potential of losing the vehicle during nominal operation[R].NASA-CR-197810,1995.
    [15]
    丁定浩,可靠性与维修性工程:系统与电路结构的分析和设计[M].北京:电子工业出版社,1986.
    [16]
    SINGH C.Calculating the time-specific frequency of system failure[J].IEEE Transactions on Reliability，1979,R-28（2）:124-126.
    [17]
    SINGH C,BILINTON R.A new method to determine the failure frequency of a complex system[J].Microelectronics Reliability，1973,12（5）:459-465.
    [18]
    石彬,基于故障树的EPS系统可靠性及失效模式仿真研究[D]:杭州:浙江大学,2007.
    [19]
    刘士杰,梁国柱,重复使用液体火箭发动机可用度的数字仿真[J].北京航空航天大学学报，2015,41（12）:132-140.
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