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米字型刻痕不锈钢膜片剩余厚度对破裂压力的影响研究 被引量:1

Study on the Influence of Residual Thickness of Stainless Steel Diaphragm with‘UK-flag Shape’Notched on Rupture Pressure
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摘要 膜片破裂压力是冲压发动机点火器的关键性能参数之一,破裂压力的可靠性直接影响发动机点火的成败,其主要影响因素为膜片材料、结构及刻痕剩余厚度。为了确定不锈钢材料米字形刻痕膜片在额定破裂压力范围内膜片的刻痕剩余厚度,通过理论分析、仿真计算和膜片爆破试验,研究了膜片破裂压力与刻痕剩余厚度关系,获得了该类型膜片在要求破裂压力为3.0~5.0MPa时剩余厚度参考值为0.050~0.067mm。而实际生产中由于膜片刻痕厚度不能保证完全均匀,为保证膜片破裂压力稳定可靠,进一步确定了刻痕剩余厚度范围为0.055~0.063mm,散差不大于4μm。 Diaphragm rupture pressure is one of the key performance parameters of ramjet igniter.The reliability of rupture pressure directly affects the success of engine ignition,and its main influencing factors are material,structure and residual thickness of notch.In order to determine the residual thickness of stainless steel‘UK-flag shape’notched diaphragm in the range of rated rupture pressure,theoretical calculation,simulation analysis,and diaphragm burst test to study the relationship between diaphragm rupture pressure and residual thickness.The reference residual thickness are used(0.050~0.067mm)of the diaphragm in the required rupture pressure range(3.0~5.0MPa)is obtained.However,in the actual production,the residual thickness of the diaphragm notch cannot be completely uniform.In order to ensure the stability and reliability of the diaphragm rupture pressure,the residual thickness range of the notch is finally determined as 0.055~0.063mm,and the dispersion is less than 4μm.
作者 郑成斌 马瑞利 许璠 Zheng Chengbin;Ma Ruili;Xu Fan(Xi’an Aerospace Engine Company Limited,Xi’an 710100)
出处 《航天制造技术》 2021年第5期57-61,共5页 Aerospace Manufacturing Technology
关键词 米字型刻痕膜片 剩余厚度 破裂压力 ‘UK-flag Shape’notched diaphragm residual thickness rupture pressure
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  • 1梁辉,孙雨果.推进剂贮箱结构变厚度优化[J].宇航学报,2007,28(5):1349-1352. 被引量:6
  • 2何成旦,李鹤岐,李春旭,应磊,罗岩.隔膜贮箱电子束焊接技术研究[J].真空与低温,2004,10(3):168-171. 被引量:4
  • 3韩世纬,钟景福.多脉冲固体火箭发动机[J].上海航天,1994,11(2):39-43. 被引量:10
  • 4宁建华.光刻膜片在膜片阀中的应用[J].火箭推进,2005,31(1):33-34. 被引量:5
  • 5周仕明,袁杰红.金属膜片贮箱膜片变形的数值模拟与失效分析[J].上海航天,2005,22(6):13-16. 被引量:26
  • 6Kammerer H G,Hughes J,Gribben E.Analytical and material advances in contoured metal diaphragms for positive expulsion tanks[R].Niagara Falls,NY:Atlantic Research Corporation/Liquid Propulsion,1995.
  • 7Ballinger I A,Lay W D,Tam W H.Review and history of PSI elastemeric diaphragm tanks[R].31th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit,1995.
  • 8Benton Joe.Design modification of a diaphragm propellant tank for a pressurant tank application[R].40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit,2004.
  • 9Gorland Sol.Development of a hemispherical metal diaphragm for single cycle liquid-metal positive expulsion systems[R].Cleveland,Ohio:Lewis Research Center,2001.
  • 10Windisch M,Beck R.Numerical simulation and optimization of a hemispherical metallic membrane designed for positive expulsion of a propellant tank[R].Proceedings European Conference on Spacecraft Structures,Materials and Mechanical Testing.Branunschweig Germany,1999.

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