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Aerospace
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Design and Analysis of Advanced Composites and Structures in Aerospace
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Design and Analysis of Advanced Composites and Structures in Aerospace

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: closed (31 January 2024) | Viewed by 7782

Special Issue Editors

Prof. Dr. Hongyong Jiang

E-Mail Website
Guest Editor
School of Mechanical Engineering and Electronic Information, China University of Geosciences, Lumo Road, Guanshan Street, Hongshan District, Wuhan 430074, China
Interests: composite design and mechanics; additive manufacturing (continuous fiber 3D printing); durability design; crashworthiness; topological optimization
Dr. Guohua Zhu

E-Mail Website
Co-Guest Editor
School of Automobile, Chang'an University, Middle Section of Nan Erhuan Road, Xi'an City 710064, China
Interests: composite structures; mechanics of lattice materials; multi-scale modeling; crashworthiness; lightweight design
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

The design of advanced composites and structures are very crucial for the rapid development of aerospace. They can provide superior mechanical properties with limited mass, contributing to aircraft safety, controllability, fuel saving, etc. With the development of manufacturing technology (such as 3D printing), more complicated and lightweight composites and structures can be manufactured efficiently to satisfy higher requirements of aerospace. This also stimulates the innovative design of composites and structures. However, the complex and not well-understood mechanical mechanisms of the designed composites and structures limit their extensive applications.

This special issue aims to provide a platform for researchers to share their latest progress in the design and analysis of advanced composites and structures applied in aerospace. A special emphasis is on design principles, analysis methods and complex mechanical mechanisms to guide the design.

Prof. Dr. Hongyong Jiang
Dr. Guohua Zhu
Guest Editors

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Aerospace is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • structural composites
  • hybrid composites
  • 3D printing
  • mechanical behaviors
  • design method

Published Papers (6 papers)

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Research

19 pages, 22448 KiB  
Article
Design and Mechanical Properties of Maximum Bulk Modulus Microstructures Based on a Smooth Topology with Grid Point Density
by Xin Zhou, Chenglin Tao, Xi Liang, Zeliang Liu and Huijian Li
Aerospace 2024, 11(2), 145; https://doi.org/10.3390/aerospace11020145 - 9 Feb 2024
Viewed by 1464
Abstract
The aim of topology optimisation is to determine the optimal distribution of material phases within the periodic cells of a microstructure. In this paper, the density of grid points under element volume fraction is constructed to replace the finite elements in the traditional [...] Read more.
The aim of topology optimisation is to determine the optimal distribution of material phases within the periodic cells of a microstructure. In this paper, the density of grid points under element volume fraction is constructed to replace the finite elements in the traditional SIMP framework, avoiding jagged and blurry boundaries in the computational process due to grid dependence. This is then combined with homogenisation theory, a microstructure topology optimisation algorithm with maximum bulk modulus under prescribed volume constraints is proposed, which can obtain 2D and 3D topologies with smooth boundaries. In addition, a closed form expression for the two-dimensional topological concave edge structure (taking the most typical topology as an example) was derived, and a compression experiment was conducted on the topological microstructure based on 3D metal printing technology. Scanning electron microscopy showed that the powder bonded on the surface of the printed structure was not completely melted and the step effect caused the finite element analysis results to be higher than the experimental results. Overall, the finite element simulation and experimental results of the concave surface structure have good consistency, with high strength and energy absorption effects. Topologies based on grid point density obtain microstructures with smooth boundaries, and the introduction of the Heaviside smoothing function and multiple filtering steps within this algorithm leads to more robust optimisation, facilitating 3D or 4D printing of microstructures that meet specific design requirements and confirming the feasibility of the proposed topology for lightweighting studies. Full article
(This article belongs to the Special Issue Design and Analysis of Advanced Composites and Structures in Aerospace)
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28 pages, 80578 KiB  
Article
Free Vibrations of a New Three-Phase Composite Cylindrical Shell
by Tao Liu, Jinqiu Duan, Yan Zheng and Yingjing Qian
Aerospace 2023, 10(12), 1007; https://doi.org/10.3390/aerospace10121007 - 29 Nov 2023
Cited by 3 | Viewed by 1081
Abstract
The novel concept of a functionally graded three-phase composite structure is derived from the urgent need to improve the mechanical properties of traditional two-phase composite structures in aviation. In this paper, we study the free vibrations of a new functionally graded three-phase composite [...] Read more.
The novel concept of a functionally graded three-phase composite structure is derived from the urgent need to improve the mechanical properties of traditional two-phase composite structures in aviation. In this paper, we study the free vibrations of a new functionally graded three-phase composite cylindrical shell reinforced synergistically with graphene platelets and carbon fibers. We calculate the equivalent elastic properties of the new three-phase composite cylindrical shell using the Halpin-Tsai and Mori-Tanaka models. The governing equations of this three-phase composite cylindrical shell are derived by using first-order shear deformation theory and Hamilton’s principle. We obtain the natural frequencies and mode shapes of the new functionally graded three-phase composite cylindrical shell under artificial boundary conditions. By comparing the results of this paper with the numerical results of finite element software, the calculation method is verified. The effects of the boundary spring stiffness, GPL mass fraction, GPL functionally graded distributions, carbon fiber content, and the carbon fiber layup angle on the free vibrations of the functionally graded three-phase composite cylindrical shell are analyzed in depth. The conclusions provide a certain guiding significance for the future application of this new three-phase composite structure in the aerospace and engineering fields. Full article
(This article belongs to the Special Issue Design and Analysis of Advanced Composites and Structures in Aerospace)
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19 pages, 7697 KiB  
Article
Microstructure Image-Based Finite Element Methodology to Design Abradable Coatings for Aero Engines
by Anitha Kumari Azmeera, Prakash Jadhav and Chhaya Lande
Aerospace 2023, 10(10), 873; https://doi.org/10.3390/aerospace10100873 - 8 Oct 2023
Cited by 1 | Viewed by 1285
Abstract
Upgrading abradable or wearable coatings in the high-temperature zone of aero engines is advised to increase the efficiency and high-density power in gas turbine engines for military or commercial fixed-wing and rotary-wing aircraft. The development of these coated materials is also motivated by [...] Read more.
Upgrading abradable or wearable coatings in the high-temperature zone of aero engines is advised to increase the efficiency and high-density power in gas turbine engines for military or commercial fixed-wing and rotary-wing aircraft. The development of these coated materials is also motivated by minimization of the number of failures in the blade, as well as increasing their resistance to wear and erosion. It is suggested that abradable coatings or seals be used to accomplish this goal. The space between the rotor and the shroud is minimized thanks to an abradable seal at the blade’s tip. Coatings that can withstand abrasion are often multiphase materials sprayed through thermal spray methods, and which consist of a metal matAzmeerix, oxide particles, and void space. The maintenance of an ideal blend of qualities, such as erosion resistance and hardness, during production determines a seal’s effectiveness. The objective of this research is to develop microstructure-based modelling methodology which will mimic the coating wear process and subsequently help in designing the abradable coating composition. Microstructure modelling, meshing, and wear analysis using many tools such as Fusion360, Hyper Mesh, and LS-Dyna, have been employed to develop an abradable coating model and perform wear analysis using a simulated rub rig test. The relation between percentage composition and morphology variations of metal, oxide, and voids to the output parameters such as hardness, abradability, and other mechanical properties is explored using simulated finite analysis models of real micrographic images of abradable coatings. Full article
(This article belongs to the Special Issue Design and Analysis of Advanced Composites and Structures in Aerospace)
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18 pages, 2087 KiB  
Article
A Unified Numerical Approach to the Dynamics of Beams with Longitudinally Varying Cross-Sections, Materials, Foundations, and Loads Using Chebyshev Spectral Approximation
by Haizhou Liu, Yixin Huang and Yang Zhao
Aerospace 2023, 10(10), 842; https://doi.org/10.3390/aerospace10100842 - 27 Sep 2023
Viewed by 686
Abstract
Structures with inhomogeneous materials, non-uniform cross-sections, non-uniform supports, and subject to non-uniform loads are increasingly common in aerospace applications. This paper presents a simple and unified numerical dynamics model for all beams with arbitrarily axially varying cross-sections, materials, foundations, loads, and general boundary [...] Read more.
Structures with inhomogeneous materials, non-uniform cross-sections, non-uniform supports, and subject to non-uniform loads are increasingly common in aerospace applications. This paper presents a simple and unified numerical dynamics model for all beams with arbitrarily axially varying cross-sections, materials, foundations, loads, and general boundary conditions. These spatially varying properties are all approximated by high-order Chebyshev expansions, and discretized by Gauss–Lobatto sampling. The discrete governing equation of non-uniform axially functionally graded beams resting on variable Winkler–Pasternak foundations subjected to non-uniformly distributed loads is derived based on the Euler–Bernoulli beam theory. A projection matrix method is employed to simultaneously assemble spectral elements and impose general boundary conditions. Numerical experiments are performed to validate the proposed method, considering different inhomogeneous materials, boundary conditions, foundations, cross-sections, and loads. The results are compared with those reported in the literature and obtained by the finite element method, and excellent agreement is observed. The convergence, accuracy, and efficiency of the proposed method are demonstrated. Full article
(This article belongs to the Special Issue Design and Analysis of Advanced Composites and Structures in Aerospace)
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19 pages, 8705 KiB  
Article
Dynamic Analysis of a Large Deployable Space Truss Structure Considering Semi-Rigid Joints
by Huaibo Yao, Yixin Huang, Wenlai Ma, Lei Liang and Yang Zhao
Aerospace 2023, 10(9), 821; https://doi.org/10.3390/aerospace10090821 - 21 Sep 2023
Cited by 4 | Viewed by 1266
Abstract
Joints are widely used in large deployable structures but show semi-rigidity due to performance degradation and some nonlinear factors affecting the structure’s dynamic characteristics. This paper investigates the influence of semi-rigid joints on the characteristics of deployable structures in orbit. A virtual connection [...] Read more.
Joints are widely used in large deployable structures but show semi-rigidity due to performance degradation and some nonlinear factors affecting the structure’s dynamic characteristics. This paper investigates the influence of semi-rigid joints on the characteristics of deployable structures in orbit. A virtual connection element of three DOFs is proposed to model the semi-rigid joints. The governing equations of semi-rigid joints are established and integrated into the dynamic equation of the structures. A series of numerical experiments are carried out to validate the proposed model’s accuracy and efficiency, and the deployable truss structures’ static and dynamic responses are analyzed. The results show that semi-rigid joints exacerbate the effects of an in-orbit microvibration on the stability of deployable truss structures. Semi-rigid joints lower the dominant frequencies of structures, leading to a ‘closely-spaced-frequencies’ phenomenon and altering the dynamic responses significantly. The effects of semi-rigid joints on deployable truss structures are long-term and can be used to establish a relationship model between structural performance and service life. Nonlinear effects vary with the external load and depend on the structures’ instantaneous status. These results indicate that semi-rigid joints significantly influence the characteristics of deployable structures, which must be considered in the design and analysis of high-precision in-orbit deployable structures. Full article
(This article belongs to the Special Issue Design and Analysis of Advanced Composites and Structures in Aerospace)
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18 pages, 5967 KiB  
Article
Stress Characteristics and Structural Optimization of Spacecraft Multilayer Insulation Components
by Weiwei Sun, Yue Liu, Qi An, Shouqing Huang and Fangyong Li
Aerospace 2023, 10(7), 577; https://doi.org/10.3390/aerospace10070577 - 21 Jun 2023
Cited by 1 | Viewed by 1096
Abstract
Multilayer insulation (MLI) components are important parts of spacecraft, in which thin films are the core elements. The film thicknesses are generally small, between 10 and 30 μm, to reduce the weight of the spacecraft. During the launch of a spacecraft, there is [...] Read more.
Multilayer insulation (MLI) components are important parts of spacecraft, in which thin films are the core elements. The film thicknesses are generally small, between 10 and 30 μm, to reduce the weight of the spacecraft. During the launch of a spacecraft, there is a rapid drop in the internal pressure, which causes the internal gas to flow out rapidly through the component. The resulting fluid force may cause film damage and failure, thereby directly affecting the normal operation of the spacecraft. Therefore, the mechanical characteristics of the thin films under rapid decompression conditions were investigated during this study. Considering the effects of the flow field stress distributions on the films during the rapid decompression, a fluid–structure interaction (FSI) model for a component was first constructed. The results show that the stress is largest in the outlet film, which is the part of the overall structure most vulnerable to failure. Furthermore, the effects of the structural parameters of the component on the stresses in the different film layers were analyzed using the orthogonal experimental method. The results show that the film thickness had the largest influence, followed by the film hole diameter, the number of component layers, and finally the staggered hole distance. Finally, a structurally optimized design scheme for the component is proposed based on a parameter range analysis with respect to the maximum film stress. After optimization, the maximum stress of the thin film decreased by 97.6%. This research has practical engineering value for the structural design and optimization of MLI components. Full article
(This article belongs to the Special Issue Design and Analysis of Advanced Composites and Structures in Aerospace)
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