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Aerospace
Special Issues
Multidisciplinary Multiobjective Design Optimization
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Multidisciplinary Multiobjective Design Optimization

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

Deadline for manuscript submissions: closed (28 February 2022) | Viewed by 27573

Special Issue Editor

Prof. Dr. Sangho Kim

E-Mail Website
Guest Editor
Department of Aerospace Information Engineering, Konkuk University, Seoul 143-701, Korea
Interests: design optimization; aerodynamics; multidisciplinary design optimization

Special Issue Information

Dear Colleagues,

Multidisciplinary design optimization (MD) is a methodology used in the design of complex engineering systems where there the interaction of many different disciplines is present. A multiobjective optimization problem is a mathematical optimization problem that involves multiple objective functions to be optimized simultaneously. The design of an aerospace system is fundamentally a multidisciplinary and multiobjective process. A large number of applications have been in the field of aerospace engineering, such as aircraft and spacecraft design. The goal of this Special Issue is to bring together the state-of-the-art in multidisciplinary multiobjective design optimization technologies in aerospace engineering.

Authors are encouraged to submit a paper to this Special Issue on topics including but not limited to the following:

  • Multidisciplinary design optimization
  • Multi-point optimization
  • Multi-level optimization
  • Multi-fidelity optimization
  • Multi-physics design optimization
  • Decomposition methods
  • Surrogate modeling
    • approximation methods
    • design of experiments for MDO
  • Design under uncertainty
    • Probabilistic/Non-probabilistic approach
    • Robust design
  • Artificial intelligence
    • AI applications for MDO
    • Machine learning

Prof. Dr. Sangho Kim
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.

Published Papers (4 papers)

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Research

17 pages, 5648 KiB  
Article
Systematic Reliability-Based Multidisciplinary Optimization by Parallel Adaptive Importance Candidate Region
by Mengchuang Zhang, Shasha Xia, Xiaochuan Li, Qin Yao, Yang Xu and Zhiping Yin
Aerospace 2022, 9(5), 240; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace9050240 - 26 Apr 2022
Cited by 4 | Viewed by 1768
Abstract
Reliability-based design optimization (RBDO) has become a prevalent design for aeronautical and aerospace engineering. The main problem is that it is impractical in complex cases with multi-failure regions, especially in multi-objective optimization. The active learning method can obtain an adaptive size of samples [...] Read more.
Reliability-based design optimization (RBDO) has become a prevalent design for aeronautical and aerospace engineering. The main problem is that it is impractical in complex cases with multi-failure regions, especially in multi-objective optimization. The active learning method can obtain an adaptive size of samples to get a relatively acceptable accuracy. The problem of RBDO using the traditional active learning Kriging (ALK) method is that the design space is generally still and only one training point is selected, which is not reasonable based on the concept of importance sampling and parallel calculation. As a consequence, the accuracy improvement is limited. In this paper, we investigate the method of obtaining an optimal size of design and reliability to assess space in parallel, simultaneously. A strategy of parallel adaptive candidate (PAIC) region with ALK is proposed and a sequential optimization and reliability assessment (SORA) method is modified to efficiently improve the accuracy. Importance sampling is used as a demonstration for the modified SORA with more accuracy. The method is then verified using mathematical cases and a scooping system of an amphibious aircraft. Full article
(This article belongs to the Special Issue Multidisciplinary Multiobjective Design Optimization)
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26 pages, 30352 KiB  
Article
Advanced Sizing Methodology for a Multi-Mode eVTOL UAV Powered by a Hydrogen Fuel Cell and Battery
by Jae-Hyun An, Do-Youn Kwon, Kwon-Su Jeon, Maxim Tyan and Jae-Woo Lee
Aerospace 2022, 9(2), 71; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace9020071 - 27 Jan 2022
Cited by 22 | Viewed by 10403
Abstract
A critical drawback of battery-powered eVTOL UAVs is their limited range and endurance, and this drawback could be solved by using a combination of hydrogen fuel cells and batteries. The objective of this paper is to develop a sizing methodology for the lift+cruise-type [...] Read more.
A critical drawback of battery-powered eVTOL UAVs is their limited range and endurance, and this drawback could be solved by using a combination of hydrogen fuel cells and batteries. The objective of this paper is to develop a sizing methodology for the lift+cruise-type eVTOL UAV powered by a hydrogen fuel cell and battery. This paper presents the constraints analysis method for forward flight/VTOL multi-mode UAV, the regression model for electric propulsion system sizing, a sizing method for an electric propulsion system and hydrogen fuel cell system, and a transition analysis method. The total mass of the UAV is iteratively calculated until convergence, and the optimization method is used to ensure that the sizing results satisfy the design requirements. The sizing results are the UAV’s geometry, mass, and power data. To verify the accuracy of the proposed sizing methodology, the sizing and the conceptual design phase results of a 25 kg hydrogen fuel-cell-powered UAV are compared. All parameters had an error within 10% and satisfied the design requirements. Full article
(This article belongs to the Special Issue Multidisciplinary Multiobjective Design Optimization)
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20 pages, 6257 KiB  
Article
Aerodynamic Design and Strength Analysis of the Wing for the Purpose of Assessing the Influence of the Bell-Shaped Lift Distribution
by Pavel Hospodář, Armand Drábek and Aleš Prachař
Aerospace 2022, 9(1), 13; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace9010013 - 28 Dec 2021
Cited by 3 | Viewed by 10516
Abstract
This article deals with aerodynamic and structural calculations of several wing designs to compare the influence of the shape on the lift distribution. Various shapes of wings for the required lift and bending moment were optimized to minimize drag and thereby reduce fuel [...] Read more.
This article deals with aerodynamic and structural calculations of several wing designs to compare the influence of the shape on the lift distribution. Various shapes of wings for the required lift and bending moment were optimized to minimize drag and thereby reduce fuel consumption. One example was a wing with a bell-shaped lift distribution, which was proposed by Ludwig Prandtl and has been forgotten over the years. The first part of the paper focuses on minimization of the wing drag coefficient by a low fidelity method and the results are compared with the CFD calculation with good agreement. In the structural part of the analysis, the inner layout of the studied wings was designed. The structural design, containing elementary wing components and optimization loop, was carried out to minimize weight with respect to panel buckling. From these calculations the weights of wings were obtained and compared. In the last part of this study, an analysis of flight performance of an airplane with presented wings was performed for a selected flight mission. Results indicated that, for the free optimized wing, the fuel saving was about six percent. Full article
(This article belongs to the Special Issue Multidisciplinary Multiobjective Design Optimization)
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16 pages, 4738 KiB  
Article
Energy Absorption Characteristics of a CFRP-Al Hybrid Thin-Walled Circular Tube under Axial Crushing
by Rongchao Jiang, Zongyang Gu, Tao Zhang, Dawei Liu, Haixia Sun, Zhenkuan Pan and Dengzhi Peng
Aerospace 2021, 8(10), 279; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace8100279 - 26 Sep 2021
Cited by 14 | Viewed by 2382
Abstract
Thin-walled tubes have gained wide applications in aerospace, automobile and other engineering fields due to their excellent energy absorption and lightweight properties. In this study, a novel method of entropy-weighted TOPSIS was adopted to study the energy absorption characteristics of a thin-walled circular [...] Read more.
Thin-walled tubes have gained wide applications in aerospace, automobile and other engineering fields due to their excellent energy absorption and lightweight properties. In this study, a novel method of entropy-weighted TOPSIS was adopted to study the energy absorption characteristics of a thin-walled circular tube under axial crushing. Three types of thin-walled circular tubes, namely, aluminum (Al) tubes, carbon-fiber-reinforced plastics (CFRP) tubes and CFRP-Al hybrid thin-walled tubes, were fabricated. Quasi-static axial crushing tests were then carried out for these specimens, and their failure modes and energy absorption performance were analyzed. The CFRP material parameters were obtained through tensile, compression and in-plane shear tests of CFRP laminates. The finite element models for the quasi-static axial crushing of these three types of circular tubes were established. The accuracy of the finite element models was verified by comparing the simulation results with the test results. On this basis, the effects of the geometric dimension and ply parameters of a CFRP-Al hybrid thin-walled circular tube on the axial crushing energy absorption characteristics were studied based on an orthogonal design and entropy-weighted TOPSIS method. The results showed that Al tube thickness, CFRP ply thickness and orientation have great effect on the energy absorption performance of a CFRP-Al hybrid thin-walled circular tube, whereas the tube diameter and length have little effect. The energy absorption capability of a CFRP-Al hybrid tube can be improved by increasing the thickness of the Al tube and the CFRP tube as well as the number of ±45° plies. Full article
(This article belongs to the Special Issue Multidisciplinary Multiobjective Design Optimization)
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