Optimal Design of Aircraft

A special issue of Machines (ISSN 2075-1702). This special issue belongs to the section "Machine Design and Theory".

Deadline for manuscript submissions: closed (15 January 2024) | Viewed by 2817

Special Issue Editor


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Guest Editor
School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, China
Interests: aircraft design; aircraft control; intelligent UAV technology; airworthiness technology and management; aerospace safety engineering

Special Issue Information

Dear Colleagues,

Faced with increasingly severe climate and environmental requirements and carbon emission pressure, the concept and pursuit of green aviation has increasingly become the focus of aircraft designers, manufacturers and operators. Aircraft design is an optimization process. How to find a breakthrough in traditional disciplines such as aircraft overall design, aerodynamic design, structural design, flight control design, electronic and electrical system design, and how to achieve high efficiency, energy conservation, environmental protection and other requirements for optimization and tradeoffs has become increasingly urgent. Furthermore, unmanned and intelligent, as well as electric and hydrogen energy, provide valuable solutions for the commercialization of green aviation.

Prof. Dr. Yongjie Zhang
Guest Editor

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Keywords

  • aircraft overall optimization design
  • aerodynamic optimization design of aircraft
  • aircraft structure optimization design
  • optimal design of flight control system
  • aircraft noise suppression and optimization design
  • optimization design of aircraft electronic system
  • optimization design of aircraft electrical system
  • optimization design of aircraft power system
  • UAV optimization design
  • optimization design of electric aircraft
  • optimal design of hydrogen-powered aircraft
  • optimal design of sustainable aviation fuel aircraft

Published Papers (2 papers)

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Research

25 pages, 5365 KiB  
Article
A Three-State Space Modeling Method for Aircraft System Reliability Design
by Yao Wang, Fengtao Wang, Yue Feng and Shancheng Cao
Machines 2024, 12(1), 13; https://doi.org/10.3390/machines12010013 - 25 Dec 2023
Viewed by 928
Abstract
Reliability is an inherent attribute of a system through optimal system design. However, during the aircraft system development process, the reliability evaluation and system function design efforts are often disconnected, leading to a divide between reliability experts and system designers in their work [...] Read more.
Reliability is an inherent attribute of a system through optimal system design. However, during the aircraft system development process, the reliability evaluation and system function design efforts are often disconnected, leading to a divide between reliability experts and system designers in their work schedule. This disconnect results in an inefficient aircraft system reliability optimization process, known as the “two-skin” phenomenon. To address this issue, a three-state space model is proposed. Firstly, an analysis was conducted on the relationship between the system function architecture developed by the system designers and the reliability evaluation performed by the reliability experts. Secondly, based on the principle of function flow, the state of failure was categorized into “physical failure” and “non-physical failure”. Additionally, a new state of “function loss” was introduced as the third state for the system, in addition to the traditional states of “normal” and “faulty”. Thirdly, through the state of “Function loss”, an effective integration of system fault modes and function modes was achieved, leading to an optimized system reliability model. A three-state space modeling method was then developed by transforming the system function architecture into a system reliability model. Finally, this new model was applied to an aircraft’s rudder and fly-by-wire control system. The results demonstrate that the function architecture at the design stage of the system can be accurately transformed into the new three-state space model. The structure aligns closely with the function architecture and can be effectively utilized in quantitative system reliability calculations. In this way, the process of ensuring system reliability can be seamlessly integrated into the system optimization design process. This integration alleviates the issue of disjointed work between reliability experts and system designers, leading to a more streamlined and efficient aircraft system optimization process. Full article
(This article belongs to the Special Issue Optimal Design of Aircraft)
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14 pages, 4983 KiB  
Article
Aerodynamic Performance of V8 Octorotor MAV with Different Rotor Configurations in Hover
by Yao Lei, Zhicheng Feng and Chensong Ma
Machines 2023, 11(4), 429; https://doi.org/10.3390/machines11040429 - 27 Mar 2023
Viewed by 1119
Abstract
A new multirotor aerial vehicle with two rotor arms formed in a V-shape configuration is introduced in this paper. To figure out the aerodynamic interference effects between rotors as an implication of the control method, this paper discusses the aerodynamic performance of the [...] Read more.
A new multirotor aerial vehicle with two rotor arms formed in a V-shape configuration is introduced in this paper. To figure out the aerodynamic interference effects between rotors as an implication of the control method, this paper discusses the aerodynamic performance of the V8 Octorotor MAV with different rotor spacing using both experiments and simulations. A hovering experiment platform is applied to obtain the thrust, power consumption and rotational speed. PL (power loading) is promoted to characterize the aerodynamic performance of the V8 Octorotor MAV. The velocity vector, streamline and turbulent vortices’ distribution of the V8 Octorotor MAV are presented as the simulation results, which indicates that turbulence intensity generated by the MAV dissipates faster in a large rotor spacing. Therefore, rotor vibration is reduced with an increased hovering stability, and the power loading is much improved at G3 (1.2D–1.4D–1.6D–1.8D) with a better aerodynamic performance both with a thrust increment and power decrement. Full article
(This article belongs to the Special Issue Optimal Design of Aircraft)
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