Search for Articles:
Title / Keyword
Author / Affiliation / Email
Journal
Article Type
 
 
Advanced Search
 
Section
Special Issue
Volume
Issue
Number
Page
 
3.4
2.1
Journals
Aerospace
Special Issues
Recent Advances in Computational Mechanics
share announcement

Recent Advances in Computational Mechanics

A special issue of Aerospace (ISSN 2226-4310).

Deadline for manuscript submissions: closed (31 May 2022) | Viewed by 25603

Special Issue Editor

Prof. Dr. Yui-Chuin Shiah

E-Mail Website
Guest Editor
Department of Aeronautics and Astronautics, National Cheng Kung University, Tainan 701, Taiwan
Interests: computational mechanics; boundary element method; fracture mechanics; computer aided design and analysis
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

In aerospace engineering, computational mechanics has been playing a crucial role for the simulation and operation of complex systems. With various disciplines involved, computational mechanics serves to advance the design of applications in aerospace engineering. Despite the already considerable development in computational mechanics, its application to aerospace engineering is still in great demand for providing reliable numerical simulations. Its development is essential to expedite the innovation of aerospace applications. All fields related to the computational issues in applications of aerospace engineering are considered important, for example, fatigue and fracture analysis, multi-phase flow simulation, structural analysis, computational fluid dynamics, dynamic analysis of structures, aeroacoustics, mass transport, heat transfer, etc. Although the fields themselves serve as independent disciplines, they are sometimes cross-related to reveal coupled behaviors, e.g., aeroelasticity, thermoelasticity, and so forth. As a matter of fact, the coupling of related fields is even more challenging in system design, and thus demands exceptional care with in-depth investigation. In aerospace engineering, topics in this regard cover a wide range of fields and cannot be named, one-by-one, completely. 

Although majorly characterized by computer computation, computational mechanics is also correlated to fundamental studies that often serve as a core associated with computational efficiency. In fundamental studies, theoretical development and analytical derivations are also considered bases of exploring novel computational methodologies to either improve the accuracy or increase the efficiency. Other fundamental studies may also target computational aspects, but with focuses on investigating special phenomena worthy of exceptional attentions in practice of applications. Certainly, there is no versatile approach considered absolutely perfect for treating all kinds of problems. Various methodologies, either with domain modeling or boundary modeling, can be applied, while the goal is placed at providing reliable simulations with great efficiency. In all, studies providing dissemination of the computational aspects or principals applied to applications in aerospace engineering are within the scope.

Prof. Dr. Yui-Chuin Shiah
Guest Editor

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

  • computational mechanics
  • computational methodologies
  • computational algorithms
  • coupling of fields
  • aerospace engineering
  • domain or boundary modeling

Benefits of Publishing in a Special Issue

  • Ease of navigation: Grouping papers by topic helps scholars navigate broad scope journals more efficiently.
  • Greater discoverability: Special Issues support the reach and impact of scientific research. Articles in Special Issues are more discoverable and cited more frequently.
  • Expansion of research network: Special Issues facilitate connections among authors, fostering scientific collaborations.
  • External promotion: Articles in Special Issues are often promoted through the journal's social media, increasing their visibility.
  • e-Book format: Special Issues with more than 10 articles can be published as dedicated e-books, ensuring wide and rapid dissemination.

Further information on MDPI's Special Issue polices can be found here.

Published Papers (6 papers)

Download All Papers
Order results
Result details
Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:

Research

16 pages, 6005 KiB  
Article
Predicting the Remaining Useful Life of Landing Gear with Prognostics and Health Management (PHM)
by Tzu-Hsuan Hsu, Yuan-Jen Chang, He-Kai Hsu, Tsung-Ti Chen and Po-Wen Hwang
Aerospace 2022, 9(8), 462; https://doi.org/10.3390/aerospace9080462 - 20 Aug 2022
Cited by 21 | Viewed by 12524
Abstract
Landing gear is an essential part of an aircraft. However, the components of landing gear are susceptible to degradation over the life of their operation, which can result in the shimmy effect occurring during take-off and landing. In order to reduce unplanned flight [...] Read more.
Landing gear is an essential part of an aircraft. However, the components of landing gear are susceptible to degradation over the life of their operation, which can result in the shimmy effect occurring during take-off and landing. In order to reduce unplanned flight disruptions and increase the availability of aircraft, the predictive maintenance (PdM) technique is investigated in this study. This paper presents a case study on the implementation of a health assessment and prediction workflow for remaining useful life (RUL) based on the prognostics and health management (PHM) framework of currently in-service aircraft, which could significantly benefit fleet operators and aircraft maintenance. Machine learning is utilized to develop a health indicator (HI) for landing gear using a data-driven approach, whereas a time-series analysis (TSA) is used to predict its degradation. The degradation models are evaluated using large volumes of real sensor data from in-service aircraft. Finally, the challenges of implementing a built-in PHM system for next-generation aircraft are outlined. Full article
(This article belongs to the Special Issue Recent Advances in Computational Mechanics)
►▼ Show Figures

Figure 1

22 pages, 16552 KiB  
Article
A Strong Form Meshless Method for the Solution of FGM Plates
by Ladislav Sator, Vladimir Sladek and Jan Sladek
Aerospace 2022, 9(8), 425; https://doi.org/10.3390/aerospace9080425 - 4 Aug 2022
Cited by 3 | Viewed by 1642
Abstract
Laminated composite structures suffer from failure because of concentrations of gradient fields on interfaces due to discontinuity of material properties. The rapid development of material science enables designers to replace classical laminated plate elements in aerospace structures with more advanced ones made of [...] Read more.
Laminated composite structures suffer from failure because of concentrations of gradient fields on interfaces due to discontinuity of material properties. The rapid development of material science enables designers to replace classical laminated plate elements in aerospace structures with more advanced ones made of functionally graded materials (FGM), which are microscopic composite materials with continuous variation of material coefficients according to the contents of their micro-constituents. Utilization of FGM eliminates the inconvenience of laminated structures but gives rise to substantial changes in structural design This paper deals with the presentation of a strong formulation meshless method for the solution of FGM composite plates. Recall that the fourth-order derivatives of deflections are involved in the governing equations for plate structures. However, the high-order derivatives of field variables in partial differential equations (PDE) lead to increasing inaccuracy of approximations. For that reason, the decomposition of the high-order governing equations into the second-order PDE is proposed. For the spatial approximation of field variables, the meshless moving least square (MLS) approximation technique is employed. The reliability (numerical stability, convergence, and accuracy) as well as computational efficiency of the developed method is illustrated by several numerical investigations of the response of FGM plates with the transversal gradation of material coefficients under stationary and/or transient mechanical and thermal loadings. Full article
(This article belongs to the Special Issue Recent Advances in Computational Mechanics)
►▼ Show Figures

Figure 1

24 pages, 6897 KiB  
Article
Shape Optimisation of Assembled Plate Structures with the Boundary Element Method
by Llewellyn Morse, Vincenzo Mallardo, Zahra Sharif-Khodaei and Ferri M.H. Aliabadi
Aerospace 2022, 9(7), 381; https://doi.org/10.3390/aerospace9070381 - 15 Jul 2022
Cited by 2 | Viewed by 1912
Abstract
A novel methodology is presented for performing sensitivity analyses of assembled plate structures using the Boundary Element Method (BEM). The main novelty of this work is that the exact implicit derivatives of the BEM formulations for assembled plate structures have been derived for [...] Read more.
A novel methodology is presented for performing sensitivity analyses of assembled plate structures using the Boundary Element Method (BEM). The main novelty of this work is that the exact implicit derivatives of the BEM formulations for assembled plate structures have been derived for the first time and incorporated into a newly developed Implicit Differentiation Method (IDM), enabling sensitivity analyses to be conducted for more complex and realistic structures in a more accurate, robust, and efficient manner than previous approaches. Three numerical examples are investigated to validate the derived exact implicit derivatives and to demonstrate how they could be used for a potential application involving the shape optimisation of a complex X-core structure from the canard of a Eurofighter Typhoon fighter jet. Results show that the newly developed IDM is more accurate, robust, and efficient when compared to alternative methodologies using derivatives obtained from methods such as the Finite Difference Method (FDM) and the Finite Element Method (FEM). Full article
(This article belongs to the Special Issue Recent Advances in Computational Mechanics)
►▼ Show Figures

Figure 1

16 pages, 5358 KiB  
Article
Identification of Time Variations of Moving Loads Applied to Plates Resting on Viscoelastic Foundation Using a Meshfree Method
by Sogol Behradnia, Amir Khosravifard, Mohammad-Rahim Hematiyan and Yui-Chuin Shiah
Aerospace 2022, 9(7), 357; https://doi.org/10.3390/aerospace9070357 - 5 Jul 2022
Cited by 1 | Viewed by 1777
Abstract
Dynamic identification of the intensity of the moving loads applied to structures is an important task in aerospace, marine, and transportation industries. In the present work, a general technique is presented for identification of the time variations in moving loads applied to plate [...] Read more.
Dynamic identification of the intensity of the moving loads applied to structures is an important task in aerospace, marine, and transportation industries. In the present work, a general technique is presented for identification of the time variations in moving loads applied to plate structures resting on viscoelastic foundation. The identification problem is formulated as an inverse problem, which utilizes dynamic responses. The direct analyses required for the identification problem are performed by a meshfree method based on the moving node technique. In this technique, a node, which travels with the applied force, is utilized in the meshfree method. Since there is no connectivity between the nodes of meshfree methods, this technique can be implemented easily, while reducing the computational labor. Another benefit of this technique is that any simple or complicated trajectory of the moving load can be handled without any additional concerns. Two numerical example problems are solved and the effects of several parameters, including the measurement error, and number of sensors on the accuracy of the results are investigated. Through the examples, it is shown that the presented technique can identify the time variations in moving loads efficiently and accurately. Full article
(This article belongs to the Special Issue Recent Advances in Computational Mechanics)
►▼ Show Figures

Figure 1

15 pages, 1768 KiB  
Article
Efficient Modeling of Heat Conduction across Thin Surface Coatings on 3D Anisotropic Substrate
by Yui-Chuin Shiah, Po-Wen Hwang, Mohammad-Rahim Hematiyan and Nguyen Anh Tuan
Aerospace 2022, 9(6), 321; https://doi.org/10.3390/aerospace9060321 - 13 Jun 2022
Cited by 3 | Viewed by 1967
Abstract
In aerospace applications, surface coatings have been widely applied for variouspurposes. One typical example is the use of thermal barrier coating (TBC) applied on anisotropic substrate for enhancing the heat resistance of the substrate under severe operational environments. Numerical modeling of thin coatings [...] Read more.
In aerospace applications, surface coatings have been widely applied for variouspurposes. One typical example is the use of thermal barrier coating (TBC) applied on anisotropic substrate for enhancing the heat resistance of the substrate under severe operational environments. Numerical modeling of thin coatings usually present difficulties for most techniques, due to their dimensional orders being far below that of the substrate. This paper presents a numerical methodology to efficiently model the heat conduction across thin layered coatings on 3D, generally anisotropic, media by the boundary element method (BEM). In the modeling, singularities of the surface-integrals are weakened by using Green’s Second Identity, where a newly introduced function is solved by the finite volume method. Using the proposed approach, the heat conduction problem can be efficiently analyzed, despite the great difference in dimensional orders in comparison with that of the substrate beneath, by simply employing very coarse surface meshes. Such analysis shows great efficiency in calculating the nearly singular boundary integrals for the modeling. Finally, two benchmark examples of thermal barrier coatings are analyzed to illustrate the effectiveness of this approach. Full article
(This article belongs to the Special Issue Recent Advances in Computational Mechanics)
►▼ Show Figures

Figure 1

17 pages, 4205 KiB  
Article
Stress Intensity Factors for a Non-Circular Hole with Inclusion Layer Embedded in a Cracked Matrix
by Chenchun Chiu, Shaochen Tseng, Chingkong Chao and Jheyuan Guo
Aerospace 2022, 9(1), 17; https://doi.org/10.3390/aerospace9010017 - 29 Dec 2021
Cited by 4 | Viewed by 2633
Abstract
The failure analysis of a non-circular hole with an inclusion layer embedded in an infinite cracked matrix under a remote in-plane uniform load is presented. In this study, a series solution of stress functions for both the matrix and inclusion layer is obtained [...] Read more.
The failure analysis of a non-circular hole with an inclusion layer embedded in an infinite cracked matrix under a remote in-plane uniform load is presented. In this study, a series solution of stress functions for both the matrix and inclusion layer is obtained using the complex variable theory in conjunction with the method of conformal mapping. The stress intensity factor (SIF) can then be determined numerically by solving the singular integral equation (SIE) for the interaction among different crack sites, material properties, and geometries of irregular holes with an inclusion layer. In particular, the failure behavior of composite structures associated with an approximately triangular hole and an approximately square hole with inclusion layers, such as those of oxides, nitrides, and sulfides, is examined in detail. The results demonstrate that a softer layer would enhance the SIF and a stiffer layer would restrain the SIF when a crack is near the inclusion layer. It can be concluded that crack propagation would be suppressed by a stiffer layer even when a micro-defect such as a hole resides in the inclusion layer. Full article
(This article belongs to the Special Issue Recent Advances in Computational Mechanics)
►▼ Show Figures

Figure 1

Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:
 
Displaying articles 1-6
Back to TopTop