Energy-absorbing characteristics of a typical sub-cargo fuselage section of a transport category aircraft

FENG Zhenyu; CHENG Kun; ZHAO Yifan; LI Henghui; XIE Jiang; MOU Haolei; WANG Yafeng; Ge Yujing

doi:10.7527/S1000-6893.2019.22907

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2019 , Vol. 40 >Issue 9: 222907 - 222907

DOI: https://doi.org/10.7527/S1000-6893.2019.22907

Solid Mechanics and Vehicle Conceptual Design

Energy-absorbing characteristics of a typical sub-cargo fuselage section of a transport category aircraft

FENG Zhenyu ,
CHENG Kun ,
ZHAO Yifan ,
LI Henghui ,
XIE Jiang ,
MOU Haolei ,
WANG Yafeng ,
Ge Yujing

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1. Key Laboratory of Civil Aircraft Airworthiness Technology, Civil Aviation Administration of China, Tianjin 300300, China;
2. College of Airworthiness, Civil Aviation University of China, Tianjin 300300, China;
3. Aviation Key Laboratory of Science and Technology on Structures Impact Dynamics, Aircraft Strength Research Institute of China, Xi'an 710065, China

Received date: 2019-01-11

Revised date: 2019-02-15

Online published: 2019-06-24

Supported by

Aeronautical Science Foundation of China (2017ZD67002); Boeing Foundation (20180159214)

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Abstract

To study the crash characteristics of a typical sub-cargo fuselage section under impact load, a crash test is carried out with a three-frame and two-span sub-cargo fuselage section specimen. To study its failure modes and dynamic responses, the test specimen is upside down on a force measuring platform, and the mass of 478.5 kg impacted the test specimen vertically at the speed of 3.95 m/s. Also, a finite element model is established to analyze the correlation between the test and the simulation results and to study the energy absorption characteristics. The results show that the middle stanchions of the three frames are uniformly bent from 32 frame to 34 frame, and the fuselage frames are caused to bend and twist in the same direction, thereby causing the C-channel stanchions to undergo bending deformation in the opposite direction to the middle stanchions and finally forming two plastic hinges at the joint of the fuselage frames with the C-channel stanchions. The failure of the fasteners is mainly caused by the shear failure of 22 flat head rivets at the joint of the stringers and shear webs in the vicinity of the middle stanchions. The peak values of initial acceleration and impact force are 25.1g and 173 kN. The simulation results are well correlated with the test results. The deformation mode of simulation is in good agreement with the experimental results. The maximum compression displacement obtained by simulation is 3.7% different from the test result 24.3 mm, and the peak value of initial acceleration obtained by simulation is 4% different from the test result 25.1g. The simulation analysis finds that the fuselage frames and the middle stanchions are the main energy absorbing components, and the energy absorption contribution accounts for 32.1% and 30.4% of the total energy absorption.

Key words： sub-cargo fuselage section; impact test; analysis; deformation mode; acceleration response; energy-absorbing characteristics

Cite this article

FENG Zhenyu , CHENG Kun , ZHAO Yifan , LI Henghui , XIE Jiang , MOU Haolei , WANG Yafeng , Ge Yujing . Energy-absorbing characteristics of a typical sub-cargo fuselage section of a transport category aircraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019 , 40(9) : 222907 -222907 . DOI: 10.7527/S1000-6893.2019.22907

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