Flight Dynamics, Control & Simulation (2nd Edition)

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

Deadline for manuscript submissions: 25 November 2024 | Viewed by 3542

Special Issue Editor


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Guest Editor
Department of Mechanical and Aerospace Engineering, Politecnico di Torino, Corso Castelfidardo, 39, 10129 Torino, TO, Italy
Interests: aircraft design; green aviation; aerodynamics; flight mechanics; innovation; multidisciplinary optimization; flight dynamics; new aircraft concepts; hybrid-electric aircraft
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Special Issue Information

Dear Colleagues,

The research in the field of transport aviation is constantly facing new complex and ambitious challenges. More and more, new aircraft concepts, new types of propulsion, novel techniques for aircraft control, and overall disruptive innovations are being studied, investigated, and developed. The study of flight dynamics has always been of particular relevance when it comes to investigate the behaviour of innovative transport aircraft, to assess their stability and controllability characteristics, and to evaluate their performance. Depending on the level of fidelity used, flight simulation models, methods, and tools make it possible to characterize the aeromechanical behaviour of aircraft at any stage of design process, from the initial conceptual stages to the most advanced detailed analysis. Such models are relevant to the advancements of different fields of transport aeronautics, such as the enhancement of flight safety, the optimization of mission performance, the development of new concepts for aircraft operations (e.g., urban air mobility), and the establishment of virtual certification methods. This Special Issue aims to collect as broadly as possible the most up-to-date contributions regarding the application of flight dynamics models for the characterization of transport aircraft aeromechanic features. In particular, great emphasis is placed on the development and application of simulation models aimed at analysing the performance of aircraft with a high degree of innovation, whether in terms of architecture, systems, or propulsion. In addition, the development and validation of new methodologies for aeromechanical analysis and optimization, advanced simulation, novel flight control techniques, and flight dynamics analysis tools for multidisciplinary design workflows, also represent contributions of great relevance to increase the knowledge in the field.

Dr. Karim Abu Salem
Guest Editor

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Keywords

  • flight dynamics
  • performance analysis
  • flight simulation
  • advanced controls
  • new aircraft concepts
  • innovation
  • multidisciplinary optimization
  • flight mechanics

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Related Special Issue

Published Papers (3 papers)

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Research

27 pages, 5387 KiB  
Article
Control-Oriented System Identification of Turbojet Dynamics
by Francisco Villarreal-Valderrama, Eduardo Liceaga-Castro, Diana Hernandez-Alcantara, Carlos Santana-Delgado, Selcuk Ekici and Luis Amezquita-Brooks
Aerospace 2024, 11(8), 630; https://doi.org/10.3390/aerospace11080630 - 1 Aug 2024
Viewed by 913
Abstract
The autonomous operation of turbojets requires reliable, accurate, and manageable dynamical models for several key processes. This article describes a practical robust method for obtaining turbojet thrust and shaft speed models from experimental data. The proposed methodology combines several data mining tools with [...] Read more.
The autonomous operation of turbojets requires reliable, accurate, and manageable dynamical models for several key processes. This article describes a practical robust method for obtaining turbojet thrust and shaft speed models from experimental data. The proposed methodology combines several data mining tools with the intention of handling typical difficulties present during experimental turbojet modeling, such as high noise levels and uncertainty in the plant dynamics. The resulting shaft speed and thrust models achieved a percentage error of 0.8561% and 3.3081%, respectively, for the whole operating range. The predictive power of the resulting models is also assessed in the frequency domain. The turbojet cut frequencies are experimentally determined and were found to match those predicted by the identified models. Finally, the proposed strategy is systematically tested with respect to popular aeroengine models, outperforming them both in the time and frequency domains. These results allow us to conclude that the proposed modeling method improves current modeling approaches in both manageability and predictive power. Full article
(This article belongs to the Special Issue Flight Dynamics, Control & Simulation (2nd Edition))
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29 pages, 9042 KiB  
Article
Investigation of Fluid Dynamics in Various Aircraft Wing Tank Designs Using 1D and CFD Simulations
by Kerem Karahan and Sertac Cadirci
Aerospace 2024, 11(7), 519; https://doi.org/10.3390/aerospace11070519 - 27 Jun 2024
Viewed by 729
Abstract
Jet fuel in aircraft fuel tanks moves due to acceleration resulting from maneuvers. The movement mentioned here directly impacts the Center of Gravity (CG). The aircraft’s flight mechanics are significantly affected by the deviation of its CG on the aircraft body, and excessive [...] Read more.
Jet fuel in aircraft fuel tanks moves due to acceleration resulting from maneuvers. The movement mentioned here directly impacts the Center of Gravity (CG). The aircraft’s flight mechanics are significantly affected by the deviation of its CG on the aircraft body, and excessive deviation is undesirable. Preventing CG deviation is achieved by designing various baffles within the fuel tank. In this study, design details of the baffles were investigated with the help of an artificial neural network (ANN) model, 1D simulations, and computational fluid dynamics (CFD) calculations. The 1D simulations, which model the fuel movement, were used to understand the general behavior of the fluid in the tank. CFD calculations simulating turbulent fluid flow in three dimensions were used to confirm the results of the 1D simulations and provide more detailed information. A simulation set is created utilizing five parameters: barrier usage, volume fraction, cutout diameter, number of cutouts, and cutout location. Compared to the barrierless design, the barrier usage as a parameter changes either on baffle number 1, 3, and 6, or on baffle number 2, 4, and 7. The fuel volume fraction parameter accounts for 30%, 45%, and 60% of the interior volume. The diameters of the cutout holes vary between 30 mm and 156 mm and are used as categorized among the baffles. Cutout holes are applied on baffles in single, twin, and triplet forms and their locations are subjected to a divergence of either −20 mm or +20 mm from the z-axis. Based on these parameters, the maximum deviation and the retreat time of CG constitute the output parameters. The importance of the input parameters on the outputs was obtained with the help of an ANN algorithm created from the results of all possible combinations of a sufficient number of 1D simulations. To obtain more detailed results and confirm the importance of input parameters on outputs, selected cases were simulated with CFD. As a result of all analyses, it was revealed that barrier usage is the most dominant input parameter on CG deviation followed by volume fraction, cutout hole diameter, cutout divergence, and finally, the number of cutout holes. This study identifies the dominant input parameters to control fuel sloshing, specifically CG deviation and retreat time in the fuel tank, and proposes baffle designs to promote robust flight stability. Full article
(This article belongs to the Special Issue Flight Dynamics, Control & Simulation (2nd Edition))
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24 pages, 2586 KiB  
Article
Robust Approximate Optimal Trajectory Tracking Control for Quadrotors
by Rong Li, Zhengliang Yang, Gaowei Yan, Long Jian, Guoqiang Li and Zhiqiang Li
Aerospace 2024, 11(2), 149; https://doi.org/10.3390/aerospace11020149 - 13 Feb 2024
Cited by 2 | Viewed by 1272
Abstract
This paper uses the adaptive dynamic programming (ADP) method to achieve optimal trajectory tracking control for quadrotors. Relying on an established mathematical model of a quadrotor, the approximate optimal trajectory tracking control, which consists of the steady-state control input and the approximate optimal [...] Read more.
This paper uses the adaptive dynamic programming (ADP) method to achieve optimal trajectory tracking control for quadrotors. Relying on an established mathematical model of a quadrotor, the approximate optimal trajectory tracking control, which consists of the steady-state control input and the approximate optimal feedback control input, is designed for a nominal system. Considering the compound disturbances in position and attitude dynamic models, disturbance observers are introduced. The estimated values are used to design robust compensation inputs to suppress the effect of the compound disturbances for good trajectory tracking performance. Theoretically, the Lyapunov theorem demonstrates the stability of a closed-loop system. The robustness and effectiveness of the proposed controller are confirmed by the simulation results. Full article
(This article belongs to the Special Issue Flight Dynamics, Control & Simulation (2nd Edition))
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