Abstract

To more accurately characterize the load characteristics of birds under the impact of aviation structures, this study conducted computed tomography scanning of a 1-kg chicken and proposed a geometric model of the bird, including bones, muscles, viscera, and cavities. The constitutive model of fluid dynamics was used to describe the rheological properties of muscle viscera, and a bilinear follow-up plastic model with failure was proposed to describe the mechanical behavior of bones under high-speed impact, and then the bone and muscle/viscera models were assembled into a refined bird model to establish a finite element model. The model was verified with bird impact testing on a rigid target. By comparing and analyzing the impact pressure with the traditional bird model, it was found that the initial impact pressure and stagnation flow pressure of the CT scan refined bird model were lower than those of the traditional bird model and were close to the experimental values. The reason for this phenomenon is that the CT scan refined bird model to some extent reproduces the response of the real structure inside the bird body during the impact process, the high strength level of the bone part model will reduce the material’s movement speed after the bird body model rheological changes, and it well demonstrates the phenomenon of reduced mixing density after rheological deformation during simulation.

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Data Availability Statement

All data, models, and code generated or used during the study appear in the published article.

Acknowledgments

The work reported in this paper was supported by two National Science and Technology Major Projects (Grant Nos. 2017-IV-0006-0043 and MJ-2020-F-10) and the Fundamental Research Funds for the Central Universities (NC2022001).

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Go to Journal of Aerospace Engineering
Journal of Aerospace Engineering
Volume 37Issue 6November 2024

History

Received: Aug 20, 2023
Accepted: Apr 11, 2024
Published online: Jul 27, 2024
Published in print: Nov 1, 2024
Discussion open until: Dec 27, 2024

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Engineer, State Key Laboratory of Mechanics and Control for Aerospace Structures, Nanjing Univ. of Aeronautics and Astronautics, Nanjing 210016, China. Email: [email protected]
Mingyu Wang [email protected]
State Key Laboratory of Mechanics and Control for Aerospace Structures, Nanjing Univ. of Aeronautics and Astronautics, Nanjing 210016, China. Email: [email protected]
Fengqi Zhang [email protected]
Ph.D. Candidate, Aero-Engine Thermal Environment and Structure Key Laboratory of Ministry of Industry and Information Technology, College of Energy and Power Engineering, Nanjing Univ. of Aeronautics and Astronautics, Nanjing 210016, China. Email: [email protected]
Haiyang Zhang [email protected]
Engineer, Key Laboratory of Impact Dynamics on Aero Engine, Shenyang Engine Research Institute of China Aviation Engine Group Co., Ltd., Liaoning Province 110000, China. Email: [email protected]
Professor, Aero-Engine Thermal Environment and Structure Key Laboratory of Ministry of Industry and Information Technology, College of Energy and Power Engineering, Nanjing Univ. of Aeronautics and Astronautics, Nanjing 210016, China (corresponding author). ORCID: https://orcid.org/0000-0001-5941-7781. Email: [email protected]
Professor, Aero-Engine Thermal Environment and Structure Key Laboratory of Ministry of Industry and Information Technology, College of Energy and Power Engineering, Nanjing Univ. of Aeronautics and Astronautics, Nanjing 210016, China. ORCID: https://orcid.org/0000-0002-4168-036X. Email: [email protected]

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