典型航空器结构抗冰雹、仿真鸟弹冲击特性及其对比研究

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摘要

为研究典型航空水平安定面和机翼前缘结构抗冰雹和仿真鸟弹冲击特性，通过D80空气炮系统开展相关试验，研究弹体速度和结构类型对抗冰雹、仿真鸟弹冲击特性的影响，并基于经验证的有限元模型，开展机翼前缘结构抗等动能冰雹、仿真鸟弹冲击对比研究。结果表明：随着弹动能的增加，撞击凹坑深度及塑性变形区域越大，且远远大于弹的直径；撞击后不同规格机翼前缘结构变形趋势一致，但前缘曲率越大，凹坑深度及塑性变形区域越大；在等动能弹冲击下，仿真鸟弹和冰雹在典型航空器结构上形成的凹坑形式及撞击力-时间曲线趋势是一致的，但仿真鸟弹撞击凹坑尺寸及撞击力载荷峰值更大。因此，同等条件下仿真鸟弹的威胁性更大，结构设计中需作为主要考虑因素。

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	张宇
	王彬文
	白春玉
	刘小川
	郭军

关键词 ：机翼前缘结构, 水平安定面结构, 冰雹冲击, 仿真鸟弹, 冲击特性

Abstract：Here, to study anti-impact characteristics of typical aircraft horizontal stabilizer and wing leading edge structure against hail and simulated bird projectile, relevant tests were conducted with D80 air gun system to study effects of projectile velocity and structure type on anti-impact characteristics of the two structures against hail and simulated bird projectile.Based on the verified finite element model, contrastive study on anti-impact features of wind leading edge structure against hail and simulated bird projectile with equal kinetic energy was performed.The results showed that with increase in kinetic energy of hail and projectile, depth of impact crater and plastic deformation zone become larger, and they are much larger than diameters of hail and projectile;deformation trends of wing leading edge structures with different sizes are the same after impact, but the larger the curvature of leading edge, the larger the crater depth and plastic deformation zone; under impact of hail and projectile with equal kinetic energy, crater shapes and impact force-time curve trends formed due to hail and projectile impacting, respectively are consistent, but crater size and impact force load peak value due to impact of simulated bird projectile are larger; under the same conditions, threat of simulated bird projectile is larger, and it should be the main factor to be considered in structural design.

Key words： wing leading edge structure horizontal stabilizer structure;hail impact simulated bird projectile;impact characteristics

收稿日期: 2020-02-10 出版日期: 2021-09-28

引用本文:

张宇，王彬文，白春玉，刘小川，郭军. 典型航空器结构抗冰雹、仿真鸟弹冲击特性及其对比研究[J]. 振动与冲击, 2021, 40(18): 307-314.
ZHANG Yu, WANG Binwen, BAI Chunyu, LIU Xiaochuan, GUO Jun. Anti-impact characteristics and contrastive study of typical aircraft structures against hail and simulated bird projectile. JOURNAL OF VIBRATION AND SHOCK, 2021, 40(18): 307-314.

链接本文:

http://jvs.sjtu.edu.cn/CN/ 或 http://jvs.sjtu.edu.cn/CN/Y2021/V40/I18/307

［1］ARIAS A,LOPEZ-PUENTE J, LOYA J A,et al.Analysis of high-speed impact problems in the aircraft industry［M］.Vienna:Springer,2014.
［2］WANG F S,YUE Z F,YAN W Z.Factors study influencing on numerical simulation of aircraft windshield against bird strike［J］.Shock and Vibration,2011,8:407-424.
［3］栗牧怀,李海.减少鸟害事件保障民用航空安全［J］.民航经济与技术,2000(5)：35-38.
SU Muhuai,LI Hai.Decreasing the bird strike to guarantee the flight safety［J］.Ciuil Aviation Economics and Technology,2000(5)：35-38.
［4］刘永强,王向盈,唐长红,等.四种飞机蒙皮材料抗鸟撞性能对比研究［J］.航空材料学报,2015,35(5):82-89.
LIU Yongqiang,WANG Xiangying,TANG Changhong,et al.Performance comparison of four anti-bird strike aircraft skin material［J］.Journal of Aeronautical Materials,2015,35(5): 82-89.
［5］谢灿军, 童明波, 刘富, 等.民用飞机平尾前缘鸟撞数值分析及试验验证［J］.振动与冲击, 2015, 34(14):172-178.
XIE Canjun,TONG Mingbo,LI Fu,et al.Numerical analysis and experimental verification of bird impact on civil aircraft’s horizontal tail wing leading edge［J］.Journal of Vibration and Shock,2015,34(14):172-178.
［6］刘军,李玉龙,郭伟国,等.鸟体本构模型参数反演I:鸟撞平板试验研究［J］.航空学报,2011,32(5):802-811.
LIU Jun, LI Yulong, GUO Weiguo, et al.Parameters inversion on bird constitutive model part I: study on experiment of bird striking on plate［J］.Acta Aeronautics et Astronautica Sinica,2011,32(5):802-811.
［7］刘洋,张建军,张积亭,等.典型金属加筋板鸟撞实验研究［J］.机械科学与技术,2015,34(9):1461-1466.
LIU Yang,ZHANG Jianjun,ZHANG Jiting,et al.Experimental investigation of bird strike for stiffened metal plate［J］.Mechanical Science and Technology for Aerospace Engineering,2015,34(9):1461-1466.
［8］王会利.机翼前缘结构鸟撞仿真分析与试验验证［J］.长春理工大学学报(自然科学版),2015,38(3):60-67.
WANG Huili.Bird strike simulation and test validation for wing leading edge［J］.Journal of Changchun University of Science and Technology(Natural Science Edition),2015,38(3):60-67.
［9］李娜,吴志斌,孔令勇,等.某型飞机平尾前缘抗鸟撞优化设计［J］.飞机设计,2014,34(5):15-19.
LI Na,WU Zhibin, KONG Lingyong, et al.Optimal design of the leading edge of a horizontal tail［J］.Aircraft Design,2014,34(5):15-19.
［10］贾建东.飞机典型结构抗鸟撞设计与分析［D］.南京：南京航空航天大学,2010.
［11］张晓晴,丁铁,龙舒畅,等.复合材料加筋壁板的抗冰雹冲击动力响应及损伤预测［J］.华南理工大学学报(自然科学版),2017,45(5):120-128.
ZHANG Xiaoqing, DING Tie, LONG Shuchang,et al.Dynamic response and damage prediction of composite stiffened panel under hail impact［J］.Journal of South China University of Technology (Natural Science Edition),2017,45(5):120-128.
［12］陈星.基于ABAQUS的冰雹撞击有限元分析［D］.呼和浩特：内蒙古工业大学,2013.
［13］黄兴.航空飞行器冰雹冲击研究进展［J］.佳木斯大学学报(自然科学版),2016,34(5):688-691.
HUANG Xing.Research progress of hail impact on aerocraft［J］.Journal of Jiamusi University(Natural Science Edition),2016,34(5):688-691.
［14］刘小川,郭军,孙侠生,等.用于鸟撞试验的仿真鸟弹研究［J］.实验力学,2012,27(5):623-629.
LIU Xiaochuan,GUO Jun,SUN Xiasheng,et al.Investigation on the artificial bird projectile used in bird strike test［J］.Journal of Experimental Mechanics,2012,27(5):623-629.
［15］GORAJ Z J, KUSTRON K.Review of current research trends in bird strike and hail impact simulations on wing leading edge［J］.Aircraft Engineering and Aerospace Technology, 2018,90(4):602-612.
［16］刘军, 李玉龙, 郭伟国,等.鸟体本构模型参数反演I：鸟撞平板试验研究［J］.航空学报, 2011,32(5):802-811.
LIU Jun, LI Yulong, GUO Weiguo, et al.Parameters inversion on bird constitutive model Part I：study on experiment of bird striking on plate［J］.Acta Aeronautica et Astronautica Sinica,2011,32(5):802-811.