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Polymers
Special Issues
Advanced Polymer Composites in Aerospace Applications
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Advanced Polymer Composites in Aerospace Applications

A special issue of Polymers (ISSN 2073-4360). This special issue belongs to the section "Polymer Applications".

Deadline for manuscript submissions: closed (25 February 2024) | Viewed by 2313

Special Issue Editors

Dr. Ning An

E-Mail Website
Guest Editor
Associate Professor, School of Aeronautics and Astronautics, Sichuan University, Chengdu 610065, China
Interests: composite structures; thin-walled structures; deployable structures; finite element method; structural mechanics; mechanical metamaterials
Prof. Dr. Xiaofei Ma

E-Mail Website
Guest Editor
Xi'an Institute of Space Radio Technology, Xi'an, China
Interests: space antennas; deployable structures
Prof. Dr. Jinxiong Zhou

E-Mail Website
Guest Editor
State Key Laboratory for Strength and Vibration of Mechanical Structures, School of Aerospace, Xi’an Jiaotong University, Xi’an 710049, China
Interests: solid mechanics; mechanics of composite structures; finite element method; structural optimization; mechanics of fluid–structure interaction

Special Issue Information

Dear Colleagues,

Polymer composites are increasingly used in aerospace applications due to their lightweight and high specific stiffness and strength properties. Many structural components in the aerospace industry are designed as thin-walled laminated structures, which allows them to be elastically folded into a small volume for easy transportation and deployed to construct large-scale structures for potential use. These structures are known as deployable structures, and they may be subjected to a wide range of mechanical loads (e.g., tension, compression, bending and twisting, etc.) under working conditions, including both static and dynamic effects. The anisotropic property of composite laminates makes it more challenging to study the nonlinear deformation behaviour of deployable structures made of polymer composites. Analytical methods, numerical simulation techniques as well as experiments are in urgent need to investigate and optimize the performance of composite deployable structures.

The aim of this Special Issue is to provide an opportunity to discuss recent progress in theoretical, computational, and experimental studies on the design and analysis of composite deployable structures. Both original research papers and review articles are welcome. The scope includes but is not limited to:

  1. Multiscale modelling of polymer composites.
  2. Synthesis and characterization of polymer composites for aerospace applications.
  3. Shape memory polymer composites and applications.
  4. Design and optimization of novel composite deployable structures.
  5. Deployment dynamics of space deployable structures.
  6. Failure and instability of thin-walled composite structures.

Dr. Ning An
Prof. Dr. Xiaofei Ma
Prof. Dr. Jinxiong Zhou
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. Polymers is an international peer-reviewed open access semimonthly 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 2700 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

  • fibrous polymer composites
  • textile composites
  • composite structures
  • thin-walled structures
  • space deployable structures
  • multiscale analysis
  • folding and deployment analysis
  • modeling and characterization
  • simulation and optimization

Published Papers (2 papers)

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Research

14 pages, 5916 KiB  
Article
Configuration Design and Verification of Shear Compliant Border in Space Membrane Structure
by Anbo Cao, Zhiquan Liu, Qiuhong Lin and Hui Qiu
Polymers 2024, 16(7), 951; https://doi.org/10.3390/polym16070951 - 30 Mar 2024
Viewed by 527
Abstract
To solve the non-uniformity of stress in space membrane structure and the lack of shear compliant border configuration design method, shear compliant borders are designed, optimized, and verified in terms of configuration. Firstly, an orthotropic model of the borders is built by combining [...] Read more.
To solve the non-uniformity of stress in space membrane structure and the lack of shear compliant border configuration design method, shear compliant borders are designed, optimized, and verified in terms of configuration. Firstly, an orthotropic model of the borders is built by combining Hill and Christensen-Lo composite material models. Secondly, a finite element form-finding method is put forward by establishing rectangular and cylindrical coordinates in different areas. The configuration of borders is obtained and the influence of the borders on the edge of the membrane is 0.23%, which means that the borders are compatible with the existing tensegrity systems, especially the tensioning components and the cable sleeves. Thirdly, simulation verifies that borders can cut the spread of shear stress and improve the stress uniformity in membrane structure. The maximum stress in the membrane effective area is decreased by 35.6% and the stress uniformity is improved by 30.5%. Finally, a membrane extension experiment is committed to compare the flatness of membrane surface under shear stress with and without shear compliant borders. The borders decrease the increment speed of flatness by 58.1%, which verifies the amelioration of stress uniformity. The shear compliant border configuration design method provides a reference for space membrane structure stress-uniform design. Full article
(This article belongs to the Special Issue Advanced Polymer Composites in Aerospace Applications)
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13 pages, 7578 KiB  
Article
Study on Mechanical Properties of Carbon Nanotube Reinforced Composites
by Zhouyi Li, Haoran Liu and Yuan Li
Polymers 2023, 15(16), 3362; https://doi.org/10.3390/polym15163362 - 10 Aug 2023
Cited by 1 | Viewed by 1246
Abstract
In this study, carbon fiber composite laminates were modified by carbon nanotube films. In-plane and out-of-plane compression tests were carried out in a wide strain rate range (10−3–103/s). Results display that the out-of-plane compressive properties are improved by CNT [...] Read more.
In this study, carbon fiber composite laminates were modified by carbon nanotube films. In-plane and out-of-plane compression tests were carried out in a wide strain rate range (10−3–103/s). Results display that the out-of-plane compressive properties are improved by CNT interlaminar toughening because CNT can hinder the propagation of interlayer cracks; however, the dynamic in-plane compression performance is decreased due to the lack of resin in CNT film that leads to delamination inside of CNT film in advance. To optimize the material preparation process, two methods were used to prepare the mode I fracture test: (a) curing the prepreg by autoclave process; and (b) curing of resin preform by vacuum resin-transmitted molding (VARTM). Results showed that CNT prolonged the crack propagation path and improved the interlaminar fracture properties when the preform was infiltrated with resin and cured by VARTM. In addition, it was found that the interlaminar thickness was almost linear with the number of CNT layers. Full article
(This article belongs to the Special Issue Advanced Polymer Composites in Aerospace Applications)
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