基于复合材料铺层方式差异的导弹发射筒 结构损伤失效数值仿真
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作者单位:

1.湖南航天有限责任公司飞行器技术分公司;2.南京航空航天大学机电学院

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中图分类号:

TJ768.2;TP391.9

基金项目:

航空发动机及燃气轮机基础科学中心重点项目(P2022-AB-IV-002-001)


Numerical simulation on damage and failure of missile launcher structure base on difference of composite material layering mode
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Affiliation:

1.Aircraft Technology Branch of Hunan Aerospace Limited Liability Company;2.College of Mechanical Electrical Engineering,Nanjing University of Aeronautics and Astronautics

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    摘要:

    为探究碳纤维复合材料在便携式武器中的应用,开展了发射筒结构性能与复合材料铺层方法的技术研究。本文通过试验获取某型发射筒的工作压力,并应用有限元数值仿真方法建立不同的碳纤维复合材料铺层模型,进而对发射筒在工作载荷下的力学性能进行研究。研究结果表明,碳纤维铺层方式对发射筒的刚度及损伤失效有较大影响。发射筒在相同工作压力,相同铺层层数和总厚度的条件下,文中铺层方式Ⅰ的发射筒结构最大变形2.41mm,方式Ⅱ最大变形7.66mm,后者是前者的3倍多。根据Hashin失效准则,方式Ⅰ的碳纤维筒体未出现损伤,方式Ⅱ的筒体除中间第6至12层纤维层未出现损伤外,其余各层均萌生了较大范围的起始损伤点。研究结果可为发射筒的结构设计和碳纤维复合材料铺层方案提供参考。

    Abstract:

    In order to explore the application of carbon fiber composite in portable weapons, the technical research on the structural properties of the launcher and the method of composite laminating was carried out. In this paper, the working pressure of a certain type of launcher is obtained through experiments, and different carbon fiber composite layering models are established by using finite element numerical simulation method, Then the mechanical properties of the launcher under working load are studied. The results show that the layering method of carbon fiber has a great influence on the stiffness and damage failure of the launcher. Under the condition of the same working pressure, the same number of layers and the total thickness, In this paper, the maximum deformation of the launcher structure is 2.41mm in the layering mode Ⅰ. The maximun deformation of mode Ⅱ is 7.66mm, and the latter is more than 3 times of the former. According to the Hashin failure criterion, there is no damage in the carbon fiber cylinder of the mode Ⅰ, except for the 6th to 12th fiber layers in the middle of the cylinder according to the mode Ⅱ, a large range of initial damage points were found in other layers. The research results can provide reference for the stucture design of the launcher and the carbon fiber composite layering scheme.

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杨志维,张焯轩,王小春,等. 基于复合材料铺层方式差异的导弹发射筒 结构损伤失效数值仿真[J]. 科学技术与工程, , ():

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  • 收稿日期:2024-03-04
  • 最后修改日期:2024-05-13
  • 录用日期:2024-05-21
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