座椅约束下航空假人垂直冲击动态响应特性研究  

RESEARCH ON VERTICAL DYNAMIC CHARACTERISTICS OF AVIATION DUMMY UNDER SEAT CONSTRAINT

作　　者：冯振宇 杨永攀 贺永龙 马士成 解江 王亚锋[3] 杨欢 FENG Zhen-yu;YANG Yong-pan;HE Yong-long;MA Shi-cheng;XIE Jiang;WANG Ya-feng;YANG Huan(Key Laboratory of Civil Aircraft Airworthiness Technology,CAAC,Tianjin 300300,China;School of Airworthiness,Civil Aviation University of China,Tianjin 300300,China;Aviation Key Laboratory of Science and Technology on Structures Impact Dynamics,Aircraft Strength Research Institute of China,Xi'an 710065,China)

机构地区：[1]民航航空器适航审定技术重点实验室,天津300300 [2]中国民航大学适航学院,天津300300 [3]中国飞机强度研究所结构冲击动力学航空科技重点实验室,西安710065

出　　处：《工程力学》2020年第8期246-256,共11页Engineering Mechanics

摘　　要：该文采用试验和仿真相结合的方法,研究垂直冲击下航空假人的动态响应特性。首先开展14 g和19 g滑台冲击试验,对比不同冲击载荷下航空假人的腰椎响应。然后建立航空假人/座椅约束系统分析模型并验证其有效性,研究椅背倾角、座椅俯仰角对乘员腰椎、座椅响应的影响。结果表明:19 g与14 g脉冲下的乘员腰椎峰值压缩载荷、椅盆峰值纵向摩擦力及椅盆峰值压力比值均大于加载脉冲峰值比值,因此腰椎压缩载荷、椅盆纵向摩擦力及椅盆压力对加载脉冲峰值均有放大效应,14 g脉冲持续时间长,腰椎的Y向峰值力矩大于19 g脉冲;乘员腰椎峰值压缩载荷、椅盆峰值压力与椅背倾角均呈2次函数关系,在椅背倾角为110°附近时,乘员的腰椎受伤的风险最大;乘员腰椎峰值压缩载荷、椅盆峰值压力随座椅俯仰角的增大而增大,呈2次函数关系,增长逐渐趋于平缓。The dynamic response of aviation dummy under vertical impact is studied by combing experimental study and numerical simulation.Firstly,14 g and 19 g dynamic impact tests were carried out to compare the lumbar response of aviation dummy under different impact loads.Secondly,the numerical analysis model for aviation dummy/seat restraint system was developed and validated.Then,parametric studies were conducted to investigate the effects of seatback angle and seat pitch angle on occupant injury and seat responses.Results show that the ratios of peak lumbar force,peak longitudinal friction and seat pan pressure are greater than the ratio of peak load pulse under both 14 g and 19 g impacts,so the lumbar force,longitudinal friction force and seat pan pressure all have amplification effect on the peak load pulse.The 14 g pulse has a longer duration,and it causes greater Y-axis peak moment of lumbar and Y-axis peak moment of seat pan than 19 g pulse.The peak compression load of the lumbar and the peak pressure of the seat pan both have a quadratic function relationship with the seat back angle.When the seat back angle is about 110°,the risk of lumbar injury of occupant is the largest.The peak compression load of lumbar and the peak pressure of seat pan increase with the increase of the pitch angle of seat,showing a quadratic function relationship,and the growth gradually becomes gentle.

关 键 词：航空假人 座椅 数值分析 参数化研究 动态响应 

分 类 号：V216.55[航空宇航科学与技术—航空宇航推进理论与工程]