航空学报 > 2013, Vol. 34 Issue (9): 2130-2140   doi: 10.7527/S1000-6893.2013.0182

民机机身段和舱内设施坠撞试验及结构适坠性评估

刘小川1, 郭军2, 孙侠生1,2, 牟让科2   

  1. 1. 西北工业大学 航空学院, 陕西 西安 710072;
    2. 中国飞机强度研究所, 陕西 西安 710065
  • 收稿日期:2012-11-25 修回日期:2013-03-21 出版日期:2013-09-25 发布日期:2013-04-23
  • 通讯作者: 孙侠生,Tel.:029-88268868 E-mail:sunxs623@avic.com.cn E-mail:sunxs623@avic.com.cn
  • 作者简介:刘小川 男, 工程师, 博士研究生。主要研究方向: 飞机结构动力学。Tel: 029-88268229 E-mail: dd1882@hotmail.com;孙侠生 男, 博士, 研究员, 博士生导师。主要研究方向: 飞行器结构设计。Tel: 029-88268868 E-mail: sunxs623@avic.com.cn
  • 基金资助:

    工信部民机科研项目

Drop Test and Structure Crashworthiness Evaluation of Civil Airplane Fuselage Section with Cabin Interiors

LIU Xiaochuan1, GUO Jun2, SUN Xiasheng1,2, MU Rangke2   

  1. 1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
    2. China Aircraft Strength Research Institute, Xi'an 710065, China
  • Received:2012-11-25 Revised:2013-03-21 Online:2013-09-25 Published:2013-04-23
  • Supported by:

    CCTIME Civil Aircraft Research Project

摘要:

为研究典型民机机身段和内部设施的适坠性,设计并制造了7个框距的全尺寸机身段结构,安装了典型的舱内设施,包括3排航空座椅和2套行李架,建立了机身段结构和舱内设施的撞击有限元模型,通过预试验分析,确定乘员可生存的垂直坠撞速度为7 m/s。坠撞试验中,撞击平台材料为木质,撞击平台下方放置了12个载荷传感器,乘员由15个假人模拟,其中4个假人安装了传感器,行李用配重替代。撞击载荷、结构和假人的加速响应由动态数据采集设备(DAS)测量,并与图像测量同步,给出了数据处理方法和典型的结构、假人响应曲线。通过对撞击过程中机身段结构的能量吸收过程和机理进行分析,提出了3条提高机身结构适坠性的设计思路。根据适航条例对结构适坠性的要求和人体伤害指标,提出了综合适坠性评估指数(ICI)的概念,可对民机结构适坠性进行量化评估,并根据该评估方法和试验结果,对典型机身段的结构适坠性进行了评估。评估结果表明,在给定的坠撞环境下,机身段结构的适坠性满足适航规章的要求。

关键词: 民机, 机身段, 适坠性, 坠撞试验, 适坠性评估

Abstract:

A full-scale civil airplane fuselage section with 7 frames is designed and manufactured whose cabin section is configured with three rows of seats and two overhead bins. A finite element model of the fuselage section and cabin Interiors is developed, and a 7 m/s vertical impact condition is confirmed by two pretest analyses. The impact surface is a wooden platform instrumented with 12 load cells. The passengers are simulated by 15 dummies, of whom four are instrumented, and the passenger baggage is simulated by concentrated weights. The impact loads and acceleration responses of the structure and dummies are collected by a data acquisition systems (DAS) which is synchronized to high speed cameras. Experimental data processing methods are introduced and typical experimental curves are presented. The energy absorption process and mechanisms of the fuselage section during the impact are estimated, and three general methods of improving the fuselage structural crashworthiness are proposed. Based on the structural requirements and human injury criteria of the transport airplane airworthiness regulation, a crashworthiness evaluation method called the integrated crashworthiness index (ICI) is introduced, which can score the crashworthiness with a standard formula. The crashworthiness of the fuselage section structure is evaluated with ICI. The evaluation result show that the fuselage section structure meet the crashworthiness requirements well under the given impact environment.

Key words: civil airplane, fuselage section, crashworthiness, drop test, crashworthiness evaluation

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