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Applied Sciences
Special Issues
Future Aircraft Concepts and Aircraft Design Approaches
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Future Aircraft Concepts and Aircraft Design Approaches

A special issue of Applied Sciences (ISSN 2076-3417). This special issue belongs to the section "Aerospace Science and Engineering".

Deadline for manuscript submissions: closed (30 April 2024) | Viewed by 3199

Special Issue Editors

Dr. Hong Shi

E-Mail Website
Guest Editor
College of Energy & Power Engineering, Jiangsu University of Science and Technology, 2 Mengxi, Jingkou, Zhenjiang 212003, China
Interests: thermal stress compensation for air ducts of aircraft; infrared stealth design of ships; thermal comfort in confined spaces; aerosol transmission risk evaluation; battery thermal performance and life prediction
Dr. Yujie Guo

E-Mail Website
Guest Editor
Aircraft Design Department, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Interests: aircraft design; computational mechanics; composite material structure design; CAD/CAE integration; aircraft digital twin
Dr. Zhaolin Chen

E-Mail Website
Guest Editor
Aircraft Design Department, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Interests: mars helicopter design; low reynolds umber aerodynamics; shock wave-boundary layer interaction
Prof. Dr. Yan Wang

E-Mail Website
Guest Editor
Department of Aerospace Engineering, College of Aerodynamics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Interests: computational fluid dynamics methods and applications; drag reduction and optimal design of flight vehicles; numerical simulation of multi-phase flow; fluid–structure interaction; artificial intelligence and flow control
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

According to data from the Air Transport Action Group, out of the 43 billion tons of CO2 produced by humans in 2019, the aviation industry was responsible for 915 million tons. Evolutionary technology will continue to be developed, bringing with it around a 20% improvement in fuel efficiency to each generation of aircraft. By 2050, it is expected that electric-, hybrid- and hydrogen-powered propulsion will have the potential to serve regional, short-haul and perhaps some medium-haul markets. Companies, such as Airbus, Boeing, Rolls-Royce, General Electric et al., have focused on electric planes, including accelerating research into radical airframe designs, electric and hydrogen propulsion; forming partnerships with non-aviation technology providers; and providing incubator opportunities for new green technology start-ups.

Future aircraft concepts or enhanced designs could make a significant impact on reducing aviation emissions, increasing aircraft life cycles and ensuring safety, which is also a constant challenge in aerospace science and engineering.

This Special Issue “Future Aircraft Concepts and Aircraft Design Approaches” aims to discuss the application of aircraft design techniques and future aircraft concepts. Aircraft design synthesis covers all types of aircraft including civil and military aircraft, from conceptual to detailed design. The topics include aerodynamic analysis, smart structure development, performance optimization and stability design, or discuss the technologies such as zero-emission aircraft, electric and hybrid flight, advanced manufacturing, etc.

Dr. Hong Shi
Dr. Yujie Guo
Dr. Zhaolin Chen
Prof. Dr. Yan Wang
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. Applied Sciences 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 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 (3 papers)

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Research

25 pages, 21920 KiB  
Article
Longitudinal Wind Tunnel Tests of the PROSIB 19-Pax Airplane
by Danilo Ciliberti, Giuseppe Buonagura and Fabrizio Nicolosi
Appl. Sci. 2023, 13(21), 11928; https://doi.org/10.3390/app132111928 - 31 Oct 2023
Viewed by 628
Abstract
This research paper delves into the longitudinal wind tunnel tests conducted on the 19-passengers aircraft model of the Italian PROSIB project. The concept is an innovative small air transport airplane with distributed propellers and hybrid-electric powerplant. The primary objective was to assess its [...] Read more.
This research paper delves into the longitudinal wind tunnel tests conducted on the 19-passengers aircraft model of the Italian PROSIB project. The concept is an innovative small air transport airplane with distributed propellers and hybrid-electric powerplant. The primary objective was to assess its stability and control characteristics in power-off conditions. In addition to the usual investigation of the aircraft components, the study introduced a belly-mounted pod, which served as a battery storage unit, and explored two distinct tail configurations: a body-mounted (low) tail and a T-tail (high). The results obtained from these tests generally confirmed the anticipated characteristics of the aircraft design. The experiments provided data on aerodynamic forces and moments, giving useful indications on the effects of a belly-mounted battery storage unit and tail layout on the aircraft stability and control characteristics. This information could be used by aircraft designers to size an airplane of the same class. Full article
(This article belongs to the Special Issue Future Aircraft Concepts and Aircraft Design Approaches)
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22 pages, 9308 KiB  
Article
Introducing the Box-Wing Airframe for Hybrid-Electric Regional Aircraft: A Preliminary Impact Assessment
by Karim Abu Salem, Giuseppe Palaia and Alessandro Antonio Quarta
Appl. Sci. 2023, 13(18), 10506; https://doi.org/10.3390/app131810506 - 20 Sep 2023
Cited by 1 | Viewed by 934
Abstract
The combination of new airframes with electric and hybrid-electric propulsion is a potential solution to decarbonize aviation. In this context, recent studies have proven that the box-wing airframe, if integrated on a hybrid-electric aircraft belonging to the regional category, can provide significant reductions [...] Read more.
The combination of new airframes with electric and hybrid-electric propulsion is a potential solution to decarbonize aviation. In this context, recent studies have proven that the box-wing airframe, if integrated on a hybrid-electric aircraft belonging to the regional category, can provide significant reductions in fuel consumption. In light of these promising results, this paper aims to present a broader comparison between the box-wing aircraft and the conventional tube-and-wing aircraft, in the context of regional hybrid-electric air transport. An economic analysis is assessed, and the effects deriving from the box-wing introduction, in terms of direct operating costs, are quantitatively evaluated by applying cost models that consider the integration of hybrid-electric propulsion. In parallel, a comparative analysis of greenhouse emissions is proposed, considering both flight- and production-related emissions. The environmental, economic, and operating improvements that the introduction of the box-wing configuration may provide in the context of future regional hybrid-electric aviation are critically detailed. In this regard, the proposed results show that a box-wing hybrid-electric aircraft can reduce cost and emission without affecting compliance with current airport aprons. Finally, a general summary is presented, providing a solution that represents a practical, incremental, and technological step in the path of commercial aviation decarbonization. Full article
(This article belongs to the Special Issue Future Aircraft Concepts and Aircraft Design Approaches)
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15 pages, 9739 KiB  
Article
Thermal Stress Compensation for an Aircraft Engine Duct System Based on a Structural Redesign of Tie Rods
by Xinghai Li, Kai Feng, Jie Yuan, Rui Wang, Kaijie Yang, Rentong Zheng and Yansong Wang
Appl. Sci. 2023, 13(17), 9519; https://doi.org/10.3390/app13179519 - 22 Aug 2023
Viewed by 1091
Abstract
The reliability of the aircraft engine duct system is of paramount importance as it directly affects the safety of the aircraft, particularly under high-temperature and high-pressure cycles. In this study, ANSYS Workbench was used for finite element analysis, and a sleeve-type tie rod [...] Read more.
The reliability of the aircraft engine duct system is of paramount importance as it directly affects the safety of the aircraft, particularly under high-temperature and high-pressure cycles. In this study, ANSYS Workbench was used for finite element analysis, and a sleeve-type tie rod structure was proposed to address the critical problem of tie rod tearing during the operation of the duct system, thereby optimizing thermal stress compensation for the duct system. The research results show the following: (1) The anchor of the traditional tie rod imposes displacement constraints on the thermal deformation of the duct system, leading to stress concentration and even structural failure in the connection area between a duct and a tie rod. (2) The improved sleeve-type tie rod provides greater axial displacement freedom for the duct, effectively mitigating stress concentration phenomena. (3) Taking a worst-case scenario of 537.78 °C and 2 MPa as an example, the sleeve-type tie rod proposed in this paper can reduce the stress at the tie rod connection from 757.61 MPa to less than 25 MPa, a reduction of more than 96%. The original tie rod tearing problem is solved, and the maximum stress of the whole duct system is reduced to 459.25 MPa, which is below the yield strength. Full article
(This article belongs to the Special Issue Future Aircraft Concepts and Aircraft Design Approaches)
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