基于有限元的制导火箭弹空气舵裂纹成因分析  

Analysis on Air Rudder Crack Cause of Guided Rocket Based on Finite Element Method

作　　者：李雅楠 薄大伟 魏福华 Li Ya’nan;Bo Dawei;Wei Fuhua(No.1 Military Representative Office,Military Representative Bureau in Beijing District,Army Equipment Department,Beijing 100071,China)

机构地区：[1]陆军装备部驻北京地区军事代表局驻北京地区第一军事代表室,北京100071

出　　处：《兵工自动化》2024年第4期68-71,90,共5页Ordnance Industry Automation

摘　　要：针对制导火箭弹中空气舵表面出现裂纹的问题,进行有限元仿真分析。通过模拟固化过程的边界约束及固化压力载荷,得出的剪切应力较大位置与实际出现裂纹位置一致;复合材料成型过程中外部施加压力过大会导致空气舵金属芯网格位置与复合材料产生剪切压溃效应,增加结构残余应力,特别是舵芯根部等较薄的复合材料区域出现较大的剪切力时会导致在相应位置的舵面处出现穿透性裂纹;通过优化控制工艺参数能有效改进施压过大以及降温速率过快的情况进而预防表面裂纹的产生。结果表明,该分析为后续空气舵结构设计以及生产制造提供了指导参考。Aiming at the problem of cracks on the surface of the air rudder in the guided rocket,the finite element simulation analysis is carried out.By simulating the boundary constraint and curing pressure load during the curing process,the location of the larger shear stress is consistent with the location of the actual crack;In the process of composite molding,excessive external pressure will lead to shear crushing effect between the metal core grid position of the air rudder and the composite material,which will increase the residual stress of the structure,especially when the thinner composite material area such as the root of the rudder core has a large shear force,which will lead to penetrating cracks at the corresponding position of the rudder surface;By optimizing and controlling the process parameters,it can effectively improve the situation of too much pressure and too fast cooling rate,and then prevent the occurrence of surface cracks.The results show that the analysis provides a reference for the subsequent structural design and manufacturing of the air rudder.

关 键 词：仿真 裂纹 空气舵 制导火箭弹 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程] TJ393