机翼前缘结构抗鸟撞试验与仿真分析  

Experimental and Simulation Analysis of Bird Impact Resistance of Wing Leading Edge Structure

作　　者：李旭阳 王计真 郭军[1] 赵子豪 Li Xuyang;Wang Jizhen;Guo Jun;Zhao Zihao(National Key Laboratory of Strength and Structural Integrity,Aircraft Strength Research Institute of China,Xi'an,Shaanxi,710065,China)

机构地区：[1]中国飞机强度研究所强度与结构完整性全国重点实验室,陕西西安710065

出　　处：《飞行器强度研究》2024年第3期60-66,共7页Aircraft Strength Research

摘　　要：本文通过试验与仿真相结合的方法,以某型飞机机翼前缘为研究对象,开展了机翼前缘抗鸟撞性能研究。首先通过有限元数值仿真,得到了机翼前缘结构在鸟弹质量为1.8kg,冲击速度为126m/s和在鸟弹质量为0.9kg,冲击速度为215m/s的工况下的变形失效模式。基于此,对机翼前缘进行了鸟撞试验,验证了仿真分析的正确性与机翼前缘结构的抗鸟撞性能。结果表明,仿真分析与试验结果一致性良好,在低速冲击下,蒙皮和加强肋为主要承载吸能结构,高速冲击下,蒙皮贯穿,机翼腹板成为主要承载吸能结构。This article combines experimental and simulation methods to study the bird impact resistance performance of the leading edge of a certain aircraft wing.Firstly,through finite element numerical simulation,the deformation and failure modes of the wing leading edge structure were obtained under the conditions of a bird projectile mass of 1.8kg and an impact veloci-ty of 126m/s,as well as a bird projectile mass of 0.9kg and an impact velocity of 215m/s.Based on this,bird impact ex-periments were conducted on the leading edge of the wing to verify the correctness of the simulation analysis and the bird im-pact resistance performance of the wing leading edge structure.The results indicate that under low-speed impact,the skin and strengthening ribs are the main load-bearing and energy absorbing structures,while under high-speed impact,the skin penetrates and the wing web becomes the main load-bearing and energy absorbing structure.

关 键 词：机翼前缘 鸟撞 仿真分析 实验验证 

分 类 号：V21[航空宇航科学与技术—航空宇航推进理论与工程]