Structure-material Integrated Design for a Spacecraft Rib

Zijie Chen; Ziling Chen; Huang Li; Jie Liu

doi:doi:10.11648/j.ajmme.20200404.11

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Structure-material Integrated Design for a Spacecraft Rib

Zijie Chen, Ziling Chen, Huang Li, Jie Liu

Published in American Journal of Mechanical and Materials Engineering (Volume 4, Issue 4)

Received: 20 February 2021 Accepted: 26 February 2021 Published: 4 March 2021

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Abstract

It is the goal that the aerospace industry has been continuously pursuing to meet the lightweight design with excellent mechanical properties. A structure-material integrated design framework is proposed to enhance the load-bearing rate of a spacecraft rib significantly, based on the optimization design theory. The structure-material integrated design framework is realized in two steps by commercial software Altair Solidthinking Inspire. The first step is that topology optimization is performed to a spacecraft rib at the macroscopic scale, with the minimum mass and the constraints of the additive manufacturing process and stress; while the second step is to optimally infill the lattice structure at the microscopic scale by minimizing the mass and constraining the additive manufacturing process and stress. Representative samples for the optimal rib structure are then fabricated by the additive manufacturing technique, and the tensile test is finally carried out to obtained the load-bearing rate for the different samples. The results show that the spacecraft rib's load-bearing rate is increased by 122.73% by the proposed structure-material integrated design framework compared to the traditional one; moreover, it is significantly more efficient than the direct topology optimization and lattice optimization design. The structure-material integrated design framework shown in this study can provide an efficient way to aerospace structures with lightweight and superior mechanical properties.

Published in	American Journal of Mechanical and Materials Engineering (Volume 4, Issue 4)
DOI	10.11648/j.ajmme.20200404.11
Page(s)	81-88
Creative Commons	This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited.
Copyright	Copyright © The Author(s), 2021. Published by Science Publishing Group

Keywords

Spacecraft Rib, Structure-Material Integrated Design Framework, Load-Bearing Rate, Topology Optimization, Lattice Optimization Design

References

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APA Style

Zijie Chen, Ziling Chen, Huang Li, Jie Liu. (2021). Structure-material Integrated Design for a Spacecraft Rib. American Journal of Mechanical and Materials Engineering, 4(4), 81-88. https://doi.org/10.11648/j.ajmme.20200404.11

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ACS Style

Zijie Chen; Ziling Chen; Huang Li; Jie Liu. Structure-material Integrated Design for a Spacecraft Rib. Am. J. Mech. Mater. Eng. 2021, 4(4), 81-88. doi: 10.11648/j.ajmme.20200404.11

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AMA Style

Zijie Chen, Ziling Chen, Huang Li, Jie Liu. Structure-material Integrated Design for a Spacecraft Rib. Am J Mech Mater Eng. 2021;4(4):81-88. doi: 10.11648/j.ajmme.20200404.11

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@article{10.11648/j.ajmme.20200404.11,
  author = {Zijie Chen and Ziling Chen and Huang Li and Jie Liu},
  title = {Structure-material Integrated Design for a Spacecraft Rib},
  journal = {American Journal of Mechanical and Materials Engineering},
  volume = {4},
  number = {4},
  pages = {81-88},
  doi = {10.11648/j.ajmme.20200404.11},
  url = {https://doi.org/10.11648/j.ajmme.20200404.11},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajmme.20200404.11},
  abstract = {It is the goal that the aerospace industry has been continuously pursuing to meet the lightweight design with excellent mechanical properties. A structure-material integrated design framework is proposed to enhance the load-bearing rate of a spacecraft rib significantly, based on the optimization design theory. The structure-material integrated design framework is realized in two steps by commercial software Altair Solidthinking Inspire. The first step is that topology optimization is performed to a spacecraft rib at the macroscopic scale, with the minimum mass and the constraints of the additive manufacturing process and stress; while the second step is to optimally infill the lattice structure at the microscopic scale by minimizing the mass and constraining the additive manufacturing process and stress. Representative samples for the optimal rib structure are then fabricated by the additive manufacturing technique, and the tensile test is finally carried out to obtained the load-bearing rate for the different samples. The results show that the spacecraft rib's load-bearing rate is increased by 122.73% by the proposed structure-material integrated design framework compared to the traditional one; moreover, it is significantly more efficient than the direct topology optimization and lattice optimization design. The structure-material integrated design framework shown in this study can provide an efficient way to aerospace structures with lightweight and superior mechanical properties.},
 year = {2021}
}

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TY  - JOUR
T1  - Structure-material Integrated Design for a Spacecraft Rib
AU  - Zijie Chen
AU  - Ziling Chen
AU  - Huang Li
AU  - Jie Liu
Y1  - 2021/03/04
PY  - 2021
N1  - https://doi.org/10.11648/j.ajmme.20200404.11
DO  - 10.11648/j.ajmme.20200404.11
T2  - American Journal of Mechanical and Materials Engineering
JF  - American Journal of Mechanical and Materials Engineering
JO  - American Journal of Mechanical and Materials Engineering
SP  - 81
EP  - 88
PB  - Science Publishing Group
SN  - 2639-9652
UR  - https://doi.org/10.11648/j.ajmme.20200404.11
AB  - It is the goal that the aerospace industry has been continuously pursuing to meet the lightweight design with excellent mechanical properties. A structure-material integrated design framework is proposed to enhance the load-bearing rate of a spacecraft rib significantly, based on the optimization design theory. The structure-material integrated design framework is realized in two steps by commercial software Altair Solidthinking Inspire. The first step is that topology optimization is performed to a spacecraft rib at the macroscopic scale, with the minimum mass and the constraints of the additive manufacturing process and stress; while the second step is to optimally infill the lattice structure at the microscopic scale by minimizing the mass and constraining the additive manufacturing process and stress. Representative samples for the optimal rib structure are then fabricated by the additive manufacturing technique, and the tensile test is finally carried out to obtained the load-bearing rate for the different samples. The results show that the spacecraft rib's load-bearing rate is increased by 122.73% by the proposed structure-material integrated design framework compared to the traditional one; moreover, it is significantly more efficient than the direct topology optimization and lattice optimization design. The structure-material integrated design framework shown in this study can provide an efficient way to aerospace structures with lightweight and superior mechanical properties.
VL  - 4
IS  - 4
ER  -

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Author Information

Zijie Chen

School of Mechanical and Electric Engineering, Guangzhou University, Guangzhou, P. R. China
Ziling Chen

School of Mechanical and Electric Engineering, Guangzhou University, Guangzhou, P. R. China
Huang Li

School of Mechanical and Electric Engineering, Guangzhou University, Guangzhou, P. R. China
Jie Liu

School of Mechanical and Electric Engineering, Guangzhou University, Guangzhou, P. R. China

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Plain Text BibTeX RIS

APA Style

Zijie Chen, Ziling Chen, Huang Li, Jie Liu. (2021). Structure-material Integrated Design for a Spacecraft Rib. American Journal of Mechanical and Materials Engineering, 4(4), 81-88. https://doi.org/10.11648/j.ajmme.20200404.11

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ACS Style

Zijie Chen; Ziling Chen; Huang Li; Jie Liu. Structure-material Integrated Design for a Spacecraft Rib. Am. J. Mech. Mater. Eng. 2021, 4(4), 81-88. doi: 10.11648/j.ajmme.20200404.11

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AMA Style

Zijie Chen, Ziling Chen, Huang Li, Jie Liu. Structure-material Integrated Design for a Spacecraft Rib. Am J Mech Mater Eng. 2021;4(4):81-88. doi: 10.11648/j.ajmme.20200404.11

Copy | Download

@article{10.11648/j.ajmme.20200404.11,
  author = {Zijie Chen and Ziling Chen and Huang Li and Jie Liu},
  title = {Structure-material Integrated Design for a Spacecraft Rib},
  journal = {American Journal of Mechanical and Materials Engineering},
  volume = {4},
  number = {4},
  pages = {81-88},
  doi = {10.11648/j.ajmme.20200404.11},
  url = {https://doi.org/10.11648/j.ajmme.20200404.11},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajmme.20200404.11},
  abstract = {It is the goal that the aerospace industry has been continuously pursuing to meet the lightweight design with excellent mechanical properties. A structure-material integrated design framework is proposed to enhance the load-bearing rate of a spacecraft rib significantly, based on the optimization design theory. The structure-material integrated design framework is realized in two steps by commercial software Altair Solidthinking Inspire. The first step is that topology optimization is performed to a spacecraft rib at the macroscopic scale, with the minimum mass and the constraints of the additive manufacturing process and stress; while the second step is to optimally infill the lattice structure at the microscopic scale by minimizing the mass and constraining the additive manufacturing process and stress. Representative samples for the optimal rib structure are then fabricated by the additive manufacturing technique, and the tensile test is finally carried out to obtained the load-bearing rate for the different samples. The results show that the spacecraft rib's load-bearing rate is increased by 122.73% by the proposed structure-material integrated design framework compared to the traditional one; moreover, it is significantly more efficient than the direct topology optimization and lattice optimization design. The structure-material integrated design framework shown in this study can provide an efficient way to aerospace structures with lightweight and superior mechanical properties.},
 year = {2021}
}

Copy | Download

TY  - JOUR
T1  - Structure-material Integrated Design for a Spacecraft Rib
AU  - Zijie Chen
AU  - Ziling Chen
AU  - Huang Li
AU  - Jie Liu
Y1  - 2021/03/04
PY  - 2021
N1  - https://doi.org/10.11648/j.ajmme.20200404.11
DO  - 10.11648/j.ajmme.20200404.11
T2  - American Journal of Mechanical and Materials Engineering
JF  - American Journal of Mechanical and Materials Engineering
JO  - American Journal of Mechanical and Materials Engineering
SP  - 81
EP  - 88
PB  - Science Publishing Group
SN  - 2639-9652
UR  - https://doi.org/10.11648/j.ajmme.20200404.11
AB  - It is the goal that the aerospace industry has been continuously pursuing to meet the lightweight design with excellent mechanical properties. A structure-material integrated design framework is proposed to enhance the load-bearing rate of a spacecraft rib significantly, based on the optimization design theory. The structure-material integrated design framework is realized in two steps by commercial software Altair Solidthinking Inspire. The first step is that topology optimization is performed to a spacecraft rib at the macroscopic scale, with the minimum mass and the constraints of the additive manufacturing process and stress; while the second step is to optimally infill the lattice structure at the microscopic scale by minimizing the mass and constraining the additive manufacturing process and stress. Representative samples for the optimal rib structure are then fabricated by the additive manufacturing technique, and the tensile test is finally carried out to obtained the load-bearing rate for the different samples. The results show that the spacecraft rib's load-bearing rate is increased by 122.73% by the proposed structure-material integrated design framework compared to the traditional one; moreover, it is significantly more efficient than the direct topology optimization and lattice optimization design. The structure-material integrated design framework shown in this study can provide an efficient way to aerospace structures with lightweight and superior mechanical properties.
VL  - 4
IS  - 4
ER  -

Copy | Download