A study of incomplete similar models for tyre fragment impact on fuselage structures

KANG Huang; WANG Shu; YAN Wenmin; CUI Hailin; GUO Xianghua; ZHANG Qingming

doi:10.11883/bzycj-2021-0359

Volume 42 Issue 7

Jul. 2022

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KANG Huang, WANG Shu, YAN Wenmin, CUI Hailin, GUO Xianghua, ZHANG Qingming. A study of incomplete similar models for tyre fragment impact on fuselage structures[J]. Explosion And Shock Waves, 2022, 42(7): 073201. doi: 10.11883/bzycj-2021-0359

Citation:

KANG Huang, WANG Shu, YAN Wenmin, CUI Hailin, GUO Xianghua, ZHANG Qingming. A study of incomplete similar models for tyre fragment impact on fuselage structures[J]. Explosion And Shock Waves, 2022, 42(7): 073201. doi: 10.11883/bzycj-2021-0359

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A study of incomplete similar models for tyre fragment impact on fuselage structures

doi: 10.11883/bzycj-2021-0359

1.
Science and Technology on Transient Impact Laboratory, No. 208 Research Institute of China Ordnance Industries, Beijing 102202, China
2.
State Key Laboratory of Explosion Science and Technology, Beijing Institute of Technology, Beijing 100081, China

Received Date: 2021-11-03
Rev Recd Date: 2021-11-30

Available Online: 2022-06-06

Publish Date: 2022-07-25

Abstract

Abstract

In order to reduce the cost for the impact test of the full-size airframe structures, an incomplete similar model was established by the similarity theory. Based on dimensional analysis, the correction relation for the Johnson-Cook linear strain-rate function was formulated. Due to the limitation of manufacturing technology, the effect of the incomplete similar model with distorted thickness on similarity behaviors should be taken into account, so an exponential function was adopted to establish the correction formula for the distorted thickness model. The validity of the simulation model was then verified by comparisons relevant to the deformation on the fuselage, the strain-time curves of target plates and the final deformation profile. In addition, the influences of fragment angle, material property, distortion thickness and light weight on the deformation behavior of the fuselage structure were analyzed. The following main results were obtained. (1) Under the impact velocity of 150 m/s, the most severe impact conditions appear at the impact angle of 90° and the fragment attitude of 180º; by considering various factors, the 3.5-mm-thickness titanium alloy plate is regarded as the best choice for fuselage structures, and it is used as a full-size prototype to verify the similar method. Besides, it’s worth noting that an unconventional phenomenon takes place at the impact angle of 30º, while a reasonable explanation is given. (2) The effect of strain rate on the impact of tire fragments on the fuselage structure is not notable, so the incomplete similar model is in good agreement with the prototype results. (3) The incomplete scaled-down model corrected by this method can effectively predict the deformation behavior of prototype fuselage subjected to the impact of tyre fragments. Although there is a certain deviation between the model and the prototype on the time scale, on the spatial dimensions, the incomplete scaled-down model can effectively correct the prediction error for the maximum center deformation caused by the distortion thickness, and the corrected maximum error is less than 5.1%, indicating that the method can effectively guide the design for airframe structures.
- fuselage structure,
- similarity methods,
- incomplete similar model,
- structure impact

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References(19)

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