冲击载荷作用下机身壁板破坏效应及结构优化  

Failure effect and structure optimization of a fuselage panel under impact load

作　　者：李永鹏 徐豫新[1,2,3] 杨祥 李旭东 LI Yongpeng;XU Yuxin;YANG Xiang;LI Xudong(State Key Laboratory of Explosion Science and Technology,Beijing Institute of Technology,Beijing 100081,China;Key Laboratory of High Energy Density Materials of Ministry of Education,Beijing Institute of Technology,Beijing 100081,China;Chongqing Innovation Center,Beijing Institute of Technology,Chongqing 401120,China;Shanghai Aircraft and Research Institute,Shanghai 201210,China;School of Mechatronic Engineering,North University of China,Taiyuan 030051,China)

机构地区：[1]北京理工大学爆炸科学与技术国家重点实验室,北京100081 [2]北京理工大学高能量密度材料教育部重点实验室,北京100081 [3]北京理工大学重庆创新中心,重庆401120 [4]上海飞机设计研究院,上海201210 [5]中北大学机电工程学院,太原030051

出　　处：《振动与冲击》2023年第14期40-47,共8页Journal of Vibration and Shock

基　　金：科技三项(KJKT 19-057)。

摘　　要：研究非包容抗爆结构约束下,冲击波和端头两种冲击载荷对机身壁板的破坏效应。以定向非包容抗爆结构冲击位置处机身壁板为研究对象,通过有限元数值模拟,分析了在非包容抗爆结构约束下冲击波和端头两种载荷作用于不同位置时,机身壁板的破坏模式和程度,并以限制机身壁板破坏范围为目的,对冲击位置处机身壁板进行了结构优化。结果表明:在冲击波作用下机身壁板的主要破坏模式为蒙皮剪切冲塞、沿筋和垂直于筋撕裂以及筋条断裂,在端头作用下则为蒙皮沿筋和垂直于筋撕裂以及筋条断裂;冲击位置对端头载荷作用下机身壁板的破坏程度影响较冲击波明显;端头冲击筋条位置对机身壁板的整体破坏程度较小,为较优的冲击方案;垂直加筋对两种冲击模式下机身壁板的破口扩展均有明显约束效果,但对端头作用下的约束效果更佳,端头冲击筋间或筋条位置时,增加垂直加筋壁板损伤面积分别减小了56%和39%。研究结果可为民机用非包容抗爆容器结构设计及冲击位置处机身壁板结构设计提供指导。Under the constraint of a non-containment explosion-proof structure,the damage effect of shock wave and plug on the fuselage panel was studied.Taking the fuselage panel locating at the impact position of the directional non-containment explosion-proof structure as the research object,through finite element numerical simulation,the failure mode and degree by the shock wave and plug acting on the body panel at different positions under the constraint of the non-containment explosion-proof structure were analyzed.Then,in order to limit the damage range of the fuselage panel,the structure of the fuselage panel at the impact position was optimized.The results show that the main failure modes of the fuselage panel under shock wave impact are skin shear plug,rib tearing along and perpendicular to the tendons,and rib fracture,while under plug impact,the skin is torn along and perpendicular to the tendons and the ribs are broken.The influence of impact position on the damage degree of the fuselage panel under plug impact is more obvious than that of shock wave impact.The position of the plug impact bar has less influence on the damage of the fuselage panel as a whole,so it is a better impact design scheme.Vertical reinforcement has obvious restraint effect on the crack expansion of the fuselage panel under the two impact modes,but the restraint effect is better while under the action of the plug impact bar.When the plug hits at the position between two tendons or at a single rib,the damage area of the vertical reinforcement panel is reduced by 56%and 39%respectively.The research results provide a guidance for the structural design of non-containment explosion-proof vessels for civil aircrafts and the structural design of fuselage panels at the impact position.

关 键 词：最小风险炸弹位置 机身壁板 结构响应 数值仿真 2020-T3铝合金 

分 类 号：V223.2[航空宇航科学与技术—飞行器设计]