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首页> 外文期刊>Reliability Engineering & System Safety >Dynamic reliability analysis for the reusable thrust chamber: A multi-failure modes investigation based on coupled thermal-structural analysis
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Dynamic reliability analysis for the reusable thrust chamber: A multi-failure modes investigation based on coupled thermal-structural analysis

机译：可重复使用推力室的动态可靠性分析：一种基于耦合热结构分析的多功能模式研究

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摘要

To evaluate the dynamic reliability of the thrust chamber in the reusable rocket engine (RRE) under mull-failure modes, a reliability analysis based on the coupled thermal-structural finite element model and the multiple response surface (MRS) is proposed. Through the deterministic thermal-structural simulation, two major failure modes, the static strength failure and cyclic cumulative damage, are examined. While the random variables are introduced concerning working loads, geometrical dimensions, and material properties. The reliability of a typical reusable LOX/H2 rocket engine thrust chamber is examined by the proposed method. The feasibility of the proposed method is validated by comparing our results with that from the traditional Monte Carlo simulation and the influences of sampling methods as well as set sizes are investigated. This study provides an efficient and steadfast approach to evaluate the reliability of thrust chambers in the reusable rocket engine and quantifies the importance ranking of working loads, geometrical dimensions, and material properties for the chamber reliability, which provides a valuable insight into the reliability-based design and optimization process for reusable rocket engines
机译：为了评估在Mull破坏模式下可重复使用火箭发动机（RRE）中推力室的动态可靠性，提出了基于耦合的热结构有限元模型和多响应表面（MRS）的可靠性分析。通过确定性的热结构模拟，检查两个主要的故障模式，静态强度失效和循环累积损坏。虽然随机变量涉及工作负载，几何尺寸和材料属性。通过所提出的方法检查典型可重用LOX / H2火箭发动机推力室的可靠性。通过将我们的结果与传统的蒙特卡罗模拟的结果进行比较，验证了所提出的方法的可行性，并研究了采样方法的影响以及设定尺寸。本研究提供了一种有效和坚定的方法来评估可重复使用的火箭发动机中推力室的可靠性，并量化室内可靠性的工作负荷，几何尺寸和材料特性的重要性排名，这提供了对基于可靠性的有价值的洞察力可重复使用火箭发动机的设计与优化过程

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  • 来源
    《Reliability Engineering & System Safety》 |2020年第12期|107080.1-107080.13|共13页
  • 作者

    Qi Yaqun; Jin Ping; Li Ruizhi; Zhang Sheng; Cai Guobiao;

  • 作者单位

    Beihang Univ Sch Astronaut Beijing 102206 Peoples R China|Minist Educ Key Lab Spacecraft Design Optimizat & Dynam Simul Beijing Peoples R China|Beihang Univ Shen Yuan Honors Coll Beijing 100191 Peoples R China;

    Beihang Univ Sch Astronaut Beijing 102206 Peoples R China|Minist Educ Key Lab Spacecraft Design Optimizat & Dynam Simul Beijing Peoples R China|9 South Third St Shahe Higher Educ Pk Beijing 102206 Peoples R China;

    Beihang Univ Sch Astronaut Beijing 102206 Peoples R China|Minist Educ Key Lab Spacecraft Design Optimizat & Dynam Simul Beijing Peoples R China;

    Xian Aerosp Prop Inst Sci & Technol Liquid Rocket Engine Lab Xian 710100 Peoples R China;

    Beihang Univ Sch Astronaut Beijing 102206 Peoples R China|Minist Educ Key Lab Spacecraft Design Optimizat & Dynam Simul Beijing Peoples R China;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Reusable regeneratively cooled thrust chamber; Dynamic reliability analysis; Multi-failure modes; Static strength; Cyclic accumulative damage;

    机译：可重复使用的再生冷却推力室;动态可靠性分析;多功能模式;静态强度;循环累积损坏;

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