Dynamic response of a sandwich panel cored by butterfly-shaped honeycombs with negative Poisson’s ratio to low-velocity impact

YU Yang; FU Tao

doi:10.11883/bzycj-2023-0019

Volume 43 Issue 7

Jul. 2023

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YU Yang, FU Tao. Dynamic response of a sandwich panel cored by butterfly-shaped honeycombs with negative Poisson’s ratio to low-velocity impact[J]. Explosion And Shock Waves, 2023, 43(7): 073103. doi: 10.11883/bzycj-2023-0019

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YU Yang, FU Tao. Dynamic response of a sandwich panel cored by butterfly-shaped honeycombs with negative Poisson’s ratio to low-velocity impact[J]. Explosion And Shock Waves, 2023, 43(7): 073103. doi: 10.11883/bzycj-2023-0019

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Dynamic response of a sandwich panel cored by butterfly-shaped honeycombs with negative Poisson’s ratio to low-velocity impact

doi: 10.11883/bzycj-2023-0019

YU Yang,
FU Tao^,

Department of Mechanical and Electrical Engineering, Kunming University of Science and Technology, Kunming 650500, Yunnan, China

Received Date: 2023-01-17
Rev Recd Date: 2023-05-30

Available Online: 2023-05-30

Publish Date: 2023-07-05

Abstract

Abstract

In order to study the dynamic response of a sandwich panel cored by butterfly-shaped honeycomb with negative Poisson’s ratio to low-velocity impact, a mass-spring (MS) model is applied to obtain the contact force between the spherical impactor and the honeycomb sandwich panel. Meanwhile, based on the Hamilton’s principle and the first-order shear deformation theory, the equation of motion for the butterfly-shaped honeycomb sandwich panel with negative Poisson’s ratio is derived. Besides, the Navier method and Duhamel’s integral are used to solve the vibration displacement of the honeycomb sandwich panel. To validate the theoretical model, the results are compared with the results of ABAQUS’ numerical simulation or published literature. It is shown that the maximum relative error between the numerical modeling results of the first five order natural frequencies and the results of theoretical model calculated in this paper is 6.52%, the maximum relative error between the numerical modeling results of the honeycomb sandwich panel under low-velocity impact and the calculated results of the theoretical model in this paper is 6.84%, and the maximum relative error of the contact force between the theoretical model in this paper and the published studies is 8%, thus verifying the validity of the theoretical model. The results show that the maximum lateral displacement of the honeycomb sandwich panel increases with the increasing velocity of the spherical impactor. Under the same impact load, the impact resistance of the honeycomb sandwich panel increases with the increase of the wall thickness of the unit cell, and decreases with the increase of the unit cell angle. The impact resistance of the honeycomb sandwich panel increases by 3.7% when the thickness of the unit cell wall changes from 1 mm to 3 mm. The lateral displacement of the butterfly-shaped honeycomb sandwich panel decreases while the contact force between the impactor and the honeycomb sandwich panel increases with the increase of the length-width ratio and the height ratio. When the width-length ratio of the honeycomb sandwich panel changes from 1∶1 to 1∶2, the maximum lateral displacement of the honeycomb sandwich panel decreases by 6.1%, and when the height ratio of the top skin layer to the honeycomb core layer changes from 1∶6 to 1∶14, the maximum lateral displacement of the honeycomb sandwich panel decreases by 5.4%, which indicates that the impact resistance of the honeycomb sandwich panel is enhanced and the energy absorption effect is obvious.
- honeycomb sandwich panel,
- low-velocity impact,
- dynamic response,
- first-order shear deformation theory,
- mass-spring model

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References(27)

References

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