固体火箭发动机结构破坏分析
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摘要
针对固体火箭发动机结构破坏的问题,基于发动机组成结构以及工作原理,采用故障分析方法对造成结构破坏的影响因素进行了分析,通过数值计算及装药受力情况的有限元分析计算进行了机理分析,确认影响原因为火箭发动机设计缺陷导致发动机工作中装药碎裂,燃烧室内部压强急剧升高所致。根据发动机结构破坏机理分析,提出了相应的改进措施,进行了相关验证试验,进一步验证了机理分析的正确性以及改进措施的有效性,为火箭发动机设计提供了参考。
Aimed at the problem of structural damage of solid rocket motor,the failure analysis method is used to analyze the influencing factors of structural damage based on the engine structure and working principle. The mechanism analysis is carried out by numerical calculation and finite element analysis of charge loading. It is confirmed that the rocket engine design defect causes the charge in the engine to be broken,and the internal pressure of the combustion chamber rises sharply. According to the analysis of engine structure failure mechanism,the corresponding improvement measures are proposed,and the relevant verification tests are carried out. The correctness of the mechanism analysis and the effectiveness of the improvement measures are further verified,which provides a reference for rocket engine design.
Aimed at the problem of structural damage of solid rocket motor,the failure analysis method is used to analyze the influencing factors of structural damage based on the engine structure and working principle. The mechanism analysis is carried out by numerical calculation and finite element analysis of charge loading. It is confirmed that the rocket engine design defect causes the charge in the engine to be broken,and the internal pressure of the combustion chamber rises sharply. According to the analysis of engine structure failure mechanism,the corresponding improvement measures are proposed,and the relevant verification tests are carried out. The correctness of the mechanism analysis and the effectiveness of the improvement measures are further verified,which provides a reference for rocket engine design.
引文
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[2]Shiang-woei Chyuan.Nonlinear thermoviscoela stic analysis of solid propellant grains subjected to temperature loading[J].Finite Elements in Analysis and Design,2002,38:613-630.
[3]Shiang-woei Chyuan.Dynamic analysis of solid propellant grains subjected to ignition pressurization loading[J].Journal of Sound and Vibration,2003,268(3):465-483.
[4]Shiang-woei Chyuan.Studies of poisson’s ratio variation for solid propellant grains under ignition pressure loading[J].Pressure vessels and piping,2003,80:871-877.
[5]刘中兵,利凤祥.高过载条件下固体推进剂药柱结构完整性分析计算[J].固体火箭技术,2003,26(2):12-16.
[6]刘中兵,利凤祥.轴向过载下固体推进剂药柱变形研究[J].推进技术,2004,25(2):162-164.
[7]利凤祥,刘中兵.药柱结构对其抗轴向过载能力的影响[J].推进技术,2004,25(2):165-169.
[8]王铮.药柱结构完整性的可靠性分析[J].固体火箭技术,2001,24(1):16-18,38.
[9]王君祺,职世君,张建伟.非均布瞬态内压作用下固体推进剂药柱泊松比随机结构分析[J].固体火箭技术,2012,35(6):747-755.
[10]孟红磊,周长省,鞠玉涛,等.非均布瞬态内压作用下星孔药柱应力分析[J].固体火箭技术,2010,33(3):289-293.
[11]鲍福廷,侯晓.固体火箭发动机设计[M].北京:宇航出版社,2016.
[12]唐金兰,刘佩进.固体火箭发动机原理[M].北京:国防工业出版社,2013.
[13]闵斌.防空导弹固体火箭发动机设计[M].北京:宇航出版社.1993.
[14]叶万举.固体火箭发动机工作过程理论基础[M].长沙:国防科技大学出版社,1985.
[15]潘祖仁.高分子化学[M].北京:化学工业出版社.1986.
[16]张炜,周星,鲍桐.固体推进剂分析测试原理及典型案例[M].北京:国防工业出版社,2016.
[17]费阳.含裂纹固体火箭发动机性能分析[D].长沙:国防科学技术大学,2010.
[18]彭培根,刘培谅.固体推进剂性能及原理[M].长沙:中国人民解放军国防科技大学出版社,1986.