温度冲击试验对固体发动机喷管堵盖结构影响的仿真分析
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1.航天化学动力技术重点实验室,襄阳 441003;2.湖北航天化学技术研究所,襄阳 441003

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TM3

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Simulation on the Effect of Thermal Shock Experiment on the Structure of Nozzle Closure in Solid Rocket Motor(SRM)
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1.Key Laboratory of Aerospace Chemical Power Technology,Xiangyang 441003;2.Hubei Institute of Aerospace Chemistry Technology,Xiangyang 441003

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    摘要:

    温度冲击试验可模拟极端温度环境对固体发动机结构的影响。本文利用三维有限元方法,通过热-机耦合,分析了一种固体发动机喷管堵盖在温度冲击中的温度、应力和应变的变化情况。结果表明:温度冲击中,喷管堵盖内存在温差,最大可达46 ℃;存在内应力,在铝合金支撑件/EP密封件环形界面处最大,低温-50 ℃时达18.1 MPa,是堵盖最先破坏的位置;EP密封件是堵盖的最薄弱环节,粘接结构最大内应力11.6 MPa,分离结构9.1 MPa;得出了温度冲击下,影响喷管堵盖结构完整性的因素,表明选用低模量和合适线胀系数的密封材料,采用常温成型方法,脱开密封件/支撑件间环形交界面,可有效降低密封件/支撑件的内应力;含GFM/EP/铝合金喷管的真实发动机温度冲击试验结果与预估结果吻合。

    Abstract:

    Thermal shock experiment could test the effect of extreme temperature environment on the structure of SRM.By using thermal-structure interaction method of three-dimension finite element software, change of temperature, stress and strain of a nozzle closure of SRM subjected to thermal shock experiment was obtained. The results show that there exists temperature difference up to 46 ℃ during the temperature shock experiment; there exists differential temperature stress, too; and the stress reaches the largest of 18.13 MPa at the interface of Al alloy support element/EP sealing element at low temperature of -50 ℃, where is the site the nozzle closure breaks first. EP sealing element is the weakest part, and the internal stress in EP with adhesion structure of nozzle closure is 11.6 MPa, while that with separation structure of nozzle closure is 9.1 MPa. The influence factors of the structural integrity of the nozzle closure subjected to temperature load are obtained, which show that the selection of sealing material with low modulus and moderate coefficient of linear expansion, the choice of molding technology at room-temperature, and the separation of the interface of support element/sealing element reduces the internal stress at the interface of support element/sealing element effectively cause by thermal shock experiment. The results from thermal shock experiment for SRM with GFM/EP/Al alloy nozzle meet that of predicted.

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邓康清,李颖,向进,余小波,朱雯娟.温度冲击试验对固体发动机喷管堵盖结构影响的仿真分析[J].宇航材料工艺,2021,51(5):63-71.

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  • 收稿日期:2020-10-19
  • 最后修改日期:2021-09-25
  • 录用日期:2021-01-04
  • 在线发布日期: 2021-10-26
  • 出版日期: