基于抗鸟撞性能的尾翼前缘结构设计研究  

Structural design of tail wing leading edge based on bird impact resistance

作　　者：胡海波 HU Haibo(China Aviation General Aircraft Research Institute Co.,Ltd.,Zhuhai 519040,China)

机构地区：[1]中航通飞研究院有限公司,广东珠海519040

出　　处：《应用科技》2022年第3期129-135,共7页Applied Science and Technology

摘　　要：为了验证飞机翼面抗鸟撞结构设计的合理性,本文基于某型飞机尾翼前缘翼型,对前缘抗鸟撞结构理论计算方法进行分析,同时研究了数值仿真方法中壳单元尺寸、光滑粒子流(smoothed particle hydrodynamics,SPH)粒子数目和接触算法选择对仿真精度的影响。结果表明:当选择6 mm壳单元尺寸、SPH粒子质量取0.0503 g时,SPH方法具有较好的仿真精度。并利用光滑粒子数值仿真方法和鸟撞实验对得到的结构进行验证,证明了该优化布置方法的可靠性。In order to verify the rationality of aircraft wing anti-bird impact structure design,based on the wing leading edge of an aircraft,the design principle and theoretical calculation method of leading edge anti-bird impact structure are studied in this paper.The effects of the shell element size,number of smoothed particle hydrodynamics(SPH)particles and selection of the contact algorithm on the simulation accuracy are studied in the numerical simulation method.Results show that when the size of 6mm shell element is selected and the mass of SPH particles is 0.0503g,the SPH method has better simulation accuracy.The obtained structure is verified by the smooth particle numerical simulation method and bird strike test,which proves reliability of the optimal arrangement method.

关 键 词：垂尾前缘 能量法原理 SPH方法 鸟撞 结构优化布局 鸟撞实验 仿真分析 适航条例 

分 类 号：V19[航空宇航科学与技术—人机与环境工程]