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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7m/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。
In order to study the suitability of typical fuselage sections and internal facilities, a full-size fuselage section structure with a frame-for-7 frame was designed and built. Typical in-cabin facilities were installed, including 3 rows of aviation seats and 2 sets of luggage The finite element model of the impact of the fuselage section structure and the cabin facilities was established. Through the pre-test and analysis, the vertical impact velocity of the surviving crew was determined to be 7m / s. In the crash test, the material of the impact platform was wood, and 12 load sensors were placed under the impact platform. The crew was simulated by 15 dummies, of which 4 were fitted with sensors and the luggage was replaced with a counterweight. The impact load, structure and dummies’ acceleration response are measured by a dynamic data acquisition device (DAS) and synchronized with the image measurement. The data processing method and the typical structure and dummies response curve are given. By analyzing the energy absorption process and mechanism of fuselage section structure during impact, three design ideas to improve the fitness of fuselage structure are proposed. According to the requirement of airworthiness regulation to the fitness of the structure and the index of human injury, the concept of comprehensive fitness index (ICI) is put forward, which can quantitatively evaluate the fitness of civil aircraft, and according to the evaluation method and test result , The structural fitness of a typical fuselage segment was evaluated. The results of the assessment show that the suitability of the fuselage section structure meets the requirements of the airworthiness regulations for a given crash environment.