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Aerospace
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Advanced Technology for Flying Vehicles
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Advanced Technology for Flying Vehicles

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

Deadline for manuscript submissions: closed (31 August 2023) | Viewed by 1910

Special Issue Editors

Dr. Danilo Ciliberti

E-Mail Website
Guest Editor
Department of Industrial Engineering, University of Naples Federico II, Via Claudio, 21, 80125 Naples, Italy
Interests: aircraft design; flight mechanics; aircraft performance, stability, and control; CFD for applied aerodynamics; wind tunnel testing
Dr. Wenya Zhou

E-Mail Website
Guest Editor
Liaoning Provincial Key Laboratory of Aerospace Advanced Technology, School of Aeronautics and Astronautics, Dalian University of Technology, Dalian 116024, China
Interests: aircraft navigation, guidance and control; dynamics and control of space flexible robots; deformation and vibration control of flexible structure

Special Issue Information

Dear Colleagues,

The development of intelligent materials/structures, sensor networks, control algorithms, and artificial intelligence technology makes it possible for future flying vehicles to be more efficient, adaptable, and intelligent, includingmorphing aircraft. These advanced technologies bring new concepts and also more challenges to the design and control of flying vehicles. The interactions between flight dynamics, aerodynamics, structures, and control must be considered from a systematic perspective to enhance stability and control efficiency. Intelligent sensing and decision-making based on artificial intelligence can improve the all-around flight performance, and can also help us to deal with the challenges in design and control. This Special Issue will focus on, but will not be limited to, intelligent materials and structures, sensing technology, morphing wings, flight control, artificial intelligence, etc.

Dr. Danilo Ciliberti
Dr. Wenya 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. 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

  • intelligent materials and structures
  • sensors
  • morphing aircraft
  • artificial intelligence
  • flight control

Published Papers (2 papers)

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Research

21 pages, 4828 KiB  
Article
Real-Time Performance Optimization for a Camber Morphing Wing Based on Domain Incremental Model under Concept Drifting
by Sijia Jia, Zhenkai Zhang, Qi Dang, Chen Song and Chao Yang
Aerospace 2023, 10(10), 853; https://doi.org/10.3390/aerospace10100853 - 29 Sep 2023
Viewed by 874
Abstract
Compared with traditional wings equipped with conventional control surfaces, variable-camber morphing wings have become a hot research topic in the field of aviation due to their ability to maintain a smooth and continuous overall shape while ensuring excellent aerodynamic performance. This study focuses [...] Read more.
Compared with traditional wings equipped with conventional control surfaces, variable-camber morphing wings have become a hot research topic in the field of aviation due to their ability to maintain a smooth and continuous overall shape while ensuring excellent aerodynamic performance. This study focuses on a high aspect ratio wing with a continuous variable-camber trailing edge. Two precision models were constructed: an aerodynamic model and an aeroelastic model. Based on simulation data obtained from these models, we developed and updated a surrogate model for the wing, with particular emphasis on an incremental modeling approach that takes concept drift into account. Subsequently, using the aforementioned models, we conducted real-time optimization with feedback considerations to reduce drag, lower stress on the main beam, and minimize actuator energy under either steady or slowly varying target lift conditions. Notably, the optimization process resulted in a 4% reduction in drag or a significant decrease of 18.3% in maximum stress. Through computational comparisons, the accuracy of the proposed surrogate model and incremental learning method is demonstrated, along with their efficiency in the context of optimization problems. Full article
(This article belongs to the Special Issue Advanced Technology for Flying Vehicles)
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13 pages, 12285 KiB  
Article
Research on the Performance of Slender Aircraft with Flare-Stabilized-Skirt
by Xueting Pan, Honghao Yue, Shufeng Liu, Fei Yang, Yifan Lu and Gang Chen
Aerospace 2023, 10(10), 844; https://doi.org/10.3390/aerospace10100844 - 28 Sep 2023
Viewed by 723
Abstract
In this paper, a morphing aircraft with a deployable flared skirt is proposed, and the influence of the flare skirt on the static stability of hypersonic aircraft is studied. The theoretical model of static stability of slender aircraft is established, and the position [...] Read more.
In this paper, a morphing aircraft with a deployable flared skirt is proposed, and the influence of the flare skirt on the static stability of hypersonic aircraft is studied. The theoretical model of static stability of slender aircraft is established, and the position of the center of pressure can be used as a theoretical basis to measure static stability. Three-dimensional compressible Reynolds-averaged Navier–Stokes (RANS) solver and an SST k-ω turbulence model are used to analyze the aerodynamic characteristics of the aircraft and the influence effect of the flared skirt on the pressure distribution of the body, and the influence trend on the position of the pressure center is verified. At the same time, the reliability of the code and grid is verified by a classic example, and the results are in good agreement with the experimental data in the current literature. Finally, the static stability of an aircraft with flared skirts with different deployment angles is quantitatively measured by defining the stability derivative at the common point. The results show that the static stability of the aircraft with the same forebody is improved by more than 100% under different flight Mach numbers when the flared skirt deployment angle is 30° compared to 0°. Full article
(This article belongs to the Special Issue Advanced Technology for Flying Vehicles)
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