RESEARCH OF THE ENGINEERING ESTIMATION METHOD ON LAUNCHING FAILURE OF THE UAV OF HONEYCOMB SANDWICH

Abstract

Abstract: The composite honeycomb sandwich is widely used for the airframe of small UAV, and the design of honeycomb sandwich is needed to meet the requirements of UAV technology evolving. Aiming at the launching test of small UAV, we analyze the modeling and the engineering estimate based on the classical beam bending theory and the basic assumption of thin panel which is based on the shear theory of Reissner, and compare with the results of finite element. The results show that the eviation of the maximum stress on the top panel is 3% and the eviation of the maximum stress on the bottom panel is 10.8%, and the results are consistent with the destruction of launching test. The result shows that the method of engineering estimate has certain guiding significance for the actual design of honeycomb sandwich.

Key words: UAV, launching, honeycomb sandwich, engineering estimate, FEM

CLC Number:

TB332

ZHANG En-yang, LIU Bo, LU Zhen-yu, FENG Kun-cheng. RESEARCH OF THE ENGINEERING ESTIMATION METHOD ON LAUNCHING FAILURE OF THE UAV OF HONEYCOMB SANDWICH[J]. COMPOSITES SCIENCE AND ENGINEERING, 2015, 0(9): 5-10.

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