滚转角度对民机机身结构耐撞性能的影响  

EFFECTS OF ROLL ANGLES ON CIVIL AIRCRAFT FUSELAGE CRASHWORTHINESS

作　　者：邹田春[1] 牟浩蕾[1] 任健[1] 冯振宇[1] 

机构地区：[1]中国民航大学民用航空器适航审定技术与管理研究中心,天津300300

出　　处：《机械强度》2014年第1期139-143,共5页Journal of Mechanical Strength

基　　金：中国民航局科技项目(MHRD201010)资助~~

摘　　要：适坠性已经并将继续是飞机安全的一个重要关注点。为了研究不同滚转角度对机身结构动态响应特性的影响,针对典型的运输类飞机机身结构,建立货舱地板下部为波纹板布局形式的机身段有限元模型,分析该机身段在0°、5°、10°和15°的滚转角度下,以6.67 m/s的坠撞速度撞击刚性地面时的坠撞特性,对比分析不同滚转角度下机身段的破坏模式和座椅与地板连接处的加速度—时间历程曲线。结果表明:不同滚转角度会对机身结构的变形以及座椅处加速度响应产生显著影响,采用合适的应急着陆方式可以有效提高飞机的适坠性能。Crashworthiness has been and will continue to be the main concern in aviation safety. The effects of roll angles on fuselage section crashworthiness for civil aircraft were investigated. A fuselage section structure with waved-plate under the cargo floor concerning the typical civil transport category aircraft section is suggested, and the finite element model of fuselage section is developed to simulate the vertical drop test subjected to 6.67 m/s impact velocity under the conditions of 0°, 5°, 10° and 15 ° roll angles respectively. A comparative analysis of acceleration histories and failure modes of fuselage section under every condition are given. The results show that the change of roll angles will significantly affect fuselage deformation and the seat peak overloads, and the crashworthiness capability of aircraft structure can be effectively improved by choosing the appropriate landing way.

关 键 词：机身段 适坠性 滚转角度 破坏模式 加速度 

分 类 号：V223[航空宇航科学与技术—飞行器设计] TP391.9[自动化与计算机技术—计算机应用技术]