Structure-material Integrated Design for a Spacecraft Rib

Zijie Chen; Ziling Chen; Huang Li; Jie Liu

doi:doi:10.11648/j.ajmme.20200404.11

| Peer-Reviewed

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

Views: Downloads:

Download PDF

Share This Article

Twitter
Linked In
Facebook

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), 2024. Published by Science Publishing Group

Keywords

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

References

[1]	Zhu, J. H., Zhang, W. H., & Xia, L. (2016). Topology optimization in aircraft and aerospace structures design. Archives of Computational Methods in Engineering, 23 (4), 595-622.
[2]	Bendsøe, M. P., & Kikuchi, N. (1988). Generating optimal topologies in structural design using a homogenization method. Computer Methods in Applied Mechanics and Engineering, 71 (2), 197-224.
[3]	Bendsøe, M. P., & Sigmund, O. (1999). Material interpolation schemes in topology optimization. Archive of Applied Mechanics, 69 (9), 635-654.
[4]	Xie, Y. M., & Steven, G. P. (1993). A simple evolutionary procedure for structural optimization. Computers & Structures, 49 (5), 885-896.
[5]	Huang, X., & Xie, Y. M. (2007). Convergent and mesh-independent solutions for the bi-directional evolutionary structural optimization method. Finite Elements in Analysis and Design, 43 (14), 1039-1049.
[6]	Wei, P., Li, Z., Li, X., & Wang, M. Y. (2018). An 88-line MATLAB code for the parameterized level set method based topology optimization using radial basis functions. Structural and Multidisciplinary Optimization, 58 (2), 831-849.
[7]	Cai, S., & Zhang, W. (2020). An adaptive bubble method for structural shape and topology optimization. Computer Methods in Applied Mechanics and Engineering, 360, 112778.
[8]	Guo, X., Zhang, W., & Zhong, W. (2014). Doing topology optimization explicitly and geometrically—a new moving morphable components based framework. Journal of Applied Mechanics, 81 (8).
[9]	https://www.sohu.com/a/359727812_722157.
[10]	Li, H., Luo, Z., Gao, L., & Qin, Q. (2018). Topology optimization for concurrent design of structures with multi-patch microstructures by level sets. Computer Methods in Applied Mechanics and Engineering, 331, 536-561.
[11]	Liu, J., Chen, T., Zhang, Y., Wen, G., Qing, Q., Wang, H.,... & Xie, Y. M. (2019). On sound insulation of pyramidal lattice sandwich structure. Composite Structures, 208, 385-394.
[12]	Teimouri, M., Mahbod, M., & Asgari, M. (2021, February). Topology-optimized hybrid solid-lattice structures for efficient mechanical performance. In Structures (Vol. 29, pp. 549-560). Elsevier.
[13]	Zhang, J., & Yanagimoto, J. (2021). Topology optimization of microlattice dome with enhanced stiffness and energy absorption for additive manufacturing. Composite Structures, 255, 112889.
[14]	Wang, Z. P., Turteltaub, S., & Abdalla, M. (2017). Shape optimization and optimal control for transient heat conduction problems using an isogeometric approach. Computers & Structures, 185, 59-74.
[15]	Wen, G., Ou, H., & Liu, J. (2020). Ultra-wide band gap in a two-dimensional phononic crystal with hexagonal lattices. Materials Today Communications, 24, 100977.
[16]	Yan, X., Huang, X., Zha, Y., & Xie, Y. M. (2014). Concurrent topology optimization of structures and their composite microstructures. Computers & Structures, 133, 103-110.
[17]	Sivapuram, R., Dunning, P. D., & Kim, H. A. (2016). Simultaneous material and structural optimization by multiscale topology optimization. Structural and multidisciplinary optimization, 54 (5), 1267-1281.
[18]	Kazemi, H., Vaziri, A., & Norato, J. A. (2020). Multi-material topology optimization of lattice structures using geometry projection. Computer Methods in Applied Mechanics and Engineering, 363, 112895.
[19]	Wang, Y., Xu, H., & Pasini, D. (2017). Multiscale isogeometric topology optimization for lattice materials. Computer Methods in Applied Mechanics and Engineering, 316, 568-585.
[20]	Remouchamps, A., Bruyneel, M., Fleury, C., & Grihon, S. (2011). Application of a bi-level scheme including topology optimization to the design of an aircraft pylon. Structural and Multidisciplinary Optimization, 44 (6), 739-750.
[21]	Wong, J., Ryan, L., & Kim, I. Y. (2018). Design optimization of aircraft landing gear assembly under dynamic loading. Structural and Multidisciplinary Optimization, 57 (3), 1357-1375.
[22]	Félix, L., Gomes, A. A., & Suleman, A. (2020). Topology optimization of the internal structure of an aircraft wing subjected to self-weight load. Engineering Optimization, 52 (7), 1119-1135.
[23]	Liu, J., Ou, H., He, J., & Wen, G. (2019). Topological design of a lightweight sandwich aircraft spoiler. Materials, 12 (19), 3225.
[24]	Wu, J., Clausen, A., & Sigmund, O. (2017). Minimum compliance topology optimization of shell–infill composites for additive manufacturing. Computer Methods in Applied Mechanics and Engineering, 326, 358-375.
[25]	Yu, H., Huang, J., Zou, B., Shao, W., & Liu, J. (2020). Stress-constrained shell-lattice infill structural optimisation for additive manufacturing. Virtual and Physical Prototyping, 15 (1), 35-48.
[26]	Qiu, W., Jin, P., Jin, S., Wang, C., Xia, L., Zhu, J., & Shi, T. (2020). An evolutionary design approach to shell-infill structures. Additive Manufacturing, 34, 101382.
[27]	Svanberg, K. (1987). The method of moving asymptotes-a new method for structural optimization. International Journal for Numerical Methods in Engineering, 24 (2), 359-373.
[28]	Wang, H., Liu, J., & Wen, G. (2020). An efficient evolutionary structural optimization method for multi-resolution designs. Structural and Multidisciplinary Optimization, 62 (2), 787-803.
[29]	Long, K., Gu, C., Wang, X., Liu, J., Du, Y., Chen, Z., & Saeed, N. (2019). A novel minimum weight formulation of topology optimization implemented with reanalysis approach. International Journal for Numerical Methods in Engineering, 120 (5), 567-579.
[30]	Sigmund, O. (2001). A 99 line topology optimization code written in Matlab. Structural and Multidisciplinary Optimization, 21 (2), 120-127.
[31]	Yi, B., Zhou, Y., Yoon, G. H., & Saitou, K. (2019). Topology optimization of functionally-graded lattice structures with buckling constraints. Computer Methods in Applied Mechanics and Engineering, 354, 593-619.
[32]	Chen, Z., Long, K., Wen, P., & Nouman, S. (2020). Fatigue-resistance topology optimization of continuum structure by penalizing the cumulative fatigue damage. Advances in Engineering Software, 150, 102924.
[33]	Gomes, P., & Palacios, R. (2020). Aerodynamic-driven topology optimization of compliant airfoils. Structural and Multidisciplinary Optimization, 62, 2117-2130.
[34]	Liu, J., Wen, G., & Xie, Y. M. (2016). Layout optimization of continuum structures considering the probabilistic and fuzzy directional uncertainty of applied loads based on the cloud model. Structural and Multidisciplinary Optimization, 53 (1), 81-100.

Cite This Article

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

Copy | Download

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

Copy | Download

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

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

Download PDF

Sections

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

Copy | Download

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

Copy | Download

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