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Modelling of Aerospace Vehicle Dynamics
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Modelling of Aerospace Vehicle Dynamics

A special issue of Energies (ISSN 1996-1073). This special issue belongs to the section "E: Electric Vehicles".

Deadline for manuscript submissions: closed (31 December 2021) | Viewed by 63631

Special Issue Editors

Dr. Florian Ion Tiberiu Petrescu

E-Mail Website
Guest Editor
Department of Mechanisms and Robots Theory, National University of Science and Technology Polytechnic Bucharest, 060042 Bucharest, Romania
Interests: 3D printing
Special Issues, Collections and Topics in MDPI journals
Dr. Shuhui Li

E-Mail Website
Guest Editor
Department of Center for Advanced Vehicle Technologies, College of Electrical and Computer Engineering, University of Alabama, Tuscaloosa, AL 35487, USA
Interests: smart grid and smart microgrid; renewable energy; systems power; electronics; electric machines and drives; power systems; artificial intelligence and neural networks modeling; analysis and simulation of dynamic systems; massively parallel processing applications software; engineering measurements and instrumentations
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Lorenzo Fedele

E-Mail Website
Guest Editor
Department of Mechanical and Aerospace Engineering, Sapienza University of Rome, Piazzale Aldo Moro, 5, 00185 Roma RM, Italy
Interests: safety; maintenance; management; artificial intelligence; innovative technologies; industrial systems; infrastructures; aerospace vehicle dynamics
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

The Guest Editors are inviting submissions for a Special Issue of Energies on the subject area of "Modelling of Aerospace Vehicle Dynamics". This Special Issue aims to contribute to the study of propulsion systems for modern aerospace vehicles with the obvious aim of improving them, endowing them with the ability to move much faster and more easily in any direction, for a very long time, covering huge distances without the need of refueling as is the case for conventional, chemical propulsion. The rapid deployment of modern aerospace propulsion solutions is based on high-power lasers, especially, lasers that have an extremely high frequency. The propulsion laser has the great advantage of operating at many pulses per second (high frequency indeed). Even if future propellers in aerospace will be electric motors, other modern propulsion systems, such as those with ionic engines, laser propulsion, etc. can be discussed in this Special Issue. “Modelling of Aerospace Vehicle Dynamics” unifies all aspects of flight dynamics for the efficient development of aerospace vehicle simulations. A proof-of-concept simulation has demonstrated improvement in vortex estimation when combining data from the aircraft's moment and the fuel flow sensors. A complete set of tools to build, program, and execute the simulations is necessary. Increasing efficiency in aerospace systems is a key goal across the spectrum of all flying operations. Researchers are constantly striving to present efficient solutions for all phases of flight projects, from development, to fabrication and operation processes. From a new wing design that could exponentially increase total aircraft efficiency to a novel test stand for single-engine electric aircraft, researchers are finding unique solutions that increase efficiency.

This Special Issue will focus on emerging power electronic topologies and applications for power systems and motor drives for aerospace vehicles. Topics of interest for publication include, but are not limited to:

  • Increasing efficiency in aerospace systems;
  • Novel solutions into all phases of flight projects;
  • Recent traction systems for aerospace vehicles;
  • Novel test stand for single-engine electric aircraft;
  • Turbo-electric distributed propulsion;
  • New wing design that could exponentially increase aircraft efficiency;
  • Electromagnetic flow control to enable natural laminar flow wings;
  • Improved accuracy for greater drag reduction and fuel;
  • Jet propulsion;
  • Hall effect thrusters;
  • Gridded electrostatic ion engine;
  • High-energy synchrotron;
  • Linear Van de Graaff accelerator;
  • Large Hadron Collider (LHC) at CERN;
  • Novel renewable energy converter and inverter systems;
  • Virtual synchronous generators;
  • Particle accelerators;
  • Synchrotron radiation;
  • Synchrotron light;
  • High-voltage DC transmission systems;
  • Electrical machines, drives, systems, and applications;
  • New topologies for high voltage inverters and converters;
  • Power electronics in smart grid;
  • AC/DC converters and inverters;
  • Control and optimization of power electronic circuit;

Prof. Dr. Florian Ion Tiberiu Petrescu
Prof. Dr. Shuhui Li
Prof. Dr. Lorenzo Fedele
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. Energies 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 2600 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

  • power electronics
  • novel solutions of flight projects
  • turbo-electric distributed propulsion
  • power systems
  • motor drives
  • new topologies for convertersand inverters
  • high-power applications
  • jet propulsion
  • hall effect thrusters
  • particle accelerators
  • ion thruster
  • MPD thruster
  • VASIMR magnetic field
  • high-energy synchrotron
  • gridded electrostatic ion engine
  • large hadron collider (LHC) at CERN
  • synchrotron radiation
  • synchrotron light
  • LASER
  • synchronous generators
  • vehicle dynamics
  • new wing design
  • natural laminar flow wings

Published Papers (17 papers)

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Research

27 pages, 11784 KiB  
Article
Effects of an Unsteady Morphing Wing with Seamless Side-Edge Transition on Aerodynamic Performance
by Chawki Abdessemed, Abdessalem Bouferrouk and Yufeng Yao
Energies 2022, 15(3), 1093; https://doi.org/10.3390/en15031093 - 01 Feb 2022
Cited by 13 | Viewed by 3135
Abstract
This paper presents an unsteady flow analysis of a 3D wing with a morphing trailing edge flap (TEF) and a seamless side-edge transition between the morphed and static parts of a wing by introducing an unsteady parametrization method. First, a 3D steady Reynolds-averaged [...] Read more.
This paper presents an unsteady flow analysis of a 3D wing with a morphing trailing edge flap (TEF) and a seamless side-edge transition between the morphed and static parts of a wing by introducing an unsteady parametrization method. First, a 3D steady Reynolds-averaged Navier–Stokes (RANS) analysis of a statically morphed TEF with seamless transition is performed and the results are compared with both a baseline clean wing and a wing with a traditional hinged flap configuration at a Reynolds number of 0.7 × 106 for a range of angles of attack (AoA), from 4° to 15°. This study extends some previous published work by examining the inherent unsteady 3D effects due to the presence of the seamless transition. It is found that in the pre-stall regime, the statically morphed wing produces a maximum of a 22% higher lift and a near constant drag reduction of 25% compared with the hinged flap wing, resulting in up to 40% enhancement in the aerodynamic efficiency (i.e., lift/drag ratio). Second, unsteady flow analysis of the dynamically morphing TEF with seamless flap side-edge transition is performed to provide further insights into the dynamic lift and drag forces during the flap motions at three pre-defined morphing frequencies of 4 Hz, 6 Hz, and 8 Hz, respectively. Results have shown that an initially large overshoot in the drag coefficient is observed due to unsteady flow effects induced by the dynamically morphing wing; the overshoot is proportional to the morphing frequency which indicates the need to account for dynamic morphing effects in the design phase of a morphing wing. Full article
(This article belongs to the Special Issue Modelling of Aerospace Vehicle Dynamics)
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22 pages, 7688 KiB  
Article
Aerodynamic Characteristics of Shark Scale-Based Vortex Generators upon Symmetrical Airfoil
by S. Arunvinthan, V.S. Raatan, S. Nadaraja Pillai, Amjad A. Pasha, M. M. Rahman and Khalid A. Juhany
Energies 2021, 14(7), 1808; https://doi.org/10.3390/en14071808 - 24 Mar 2021
Cited by 14 | Viewed by 5853
Abstract
A series of wind tunnel tests were carried out to determine the effect of shark scale-based vortex generators (SSVG) on a NACA 0015 symmetrical airfoil’s aerodynamic characteristics. Three different sets of SSVG with varying geometrical parameters, such as chord length, amplitude, and wavelength, [...] Read more.
A series of wind tunnel tests were carried out to determine the effect of shark scale-based vortex generators (SSVG) on a NACA 0015 symmetrical airfoil’s aerodynamic characteristics. Three different sets of SSVG with varying geometrical parameters, such as chord length, amplitude, and wavelength, were designed and fabricated using 3D printing. The SSVG models were blended to the baseline NACA 0015 symmetrical airfoil. The wind tunnel experiments were performed over the test airfoil mounted with different sets of SSVG at various angles of attack, ranging from 0° to 24° in increments of 3°, and operating in the range of Re = 2 × 105. The results revealed that the SSVG blended test airfoil reduced the drag and increased the maximum coefficient of lift (CLmax), thereby enhancing the overall aerodynamic performance. The SSVG offered noteworthy aerodynamic benefits by effectively altering the flow and causing significant spanwise variation in the flow properties. Additionally, attempts were made to identify the optimum chordwise location to blend the SSVG for effective use. Full article
(This article belongs to the Special Issue Modelling of Aerospace Vehicle Dynamics)
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20 pages, 2293 KiB  
Article
Mathematical Modeling of the Coaxial Quadrotor Dynamics for Its Attitude and Altitude Control
by Wojciech Giernacki, Jarosław Gośliński, Jagoda Goślińska, Tadeo Espinoza-Fraire and Jinjun Rao
Energies 2021, 14(5), 1232; https://doi.org/10.3390/en14051232 - 24 Feb 2021
Cited by 15 | Viewed by 2919
Abstract
In this paper, an easily implementable coaxial quadrotor model and its validation on data from a real unmanned aerial vehicle (UAV), are presented. The proposed mathematical model consists of two parts: description of orientation and position of the UAV in the three-dimensional space. [...] Read more.
In this paper, an easily implementable coaxial quadrotor model and its validation on data from a real unmanned aerial vehicle (UAV), are presented. The proposed mathematical model consists of two parts: description of orientation and position of the UAV in the three-dimensional space. It takes into consideration the gyroscopic effect, influence of the Coriolis force, viscous friction and a several drag-like effects (blade flapping, rotor drag, translational drag and profile drag). In contrast to multirotor models available in the literature, this one is characterized by complementarity in relation to the available control techniques. Depending on selection of these techniques, the model can be narrowed (simplified) to meet the needs without the loss of behaviour adequacy to a real UAV. Full article
(This article belongs to the Special Issue Modelling of Aerospace Vehicle Dynamics)
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22 pages, 1016 KiB  
Article
Longitudinal Actuated Abdomen Control for Energy Efficient Flight of Insects
by Titilayo Ogunwa, Blake McIvor, Nurkhairunisa Awang Jumat, Ermira Abdullah and Javaan Chahl
Energies 2020, 13(20), 5480; https://doi.org/10.3390/en13205480 - 20 Oct 2020
Cited by 4 | Viewed by 2142
Abstract
The actuated abdomens of insects such as dragonflies have long been suggested to play a role in optimisation and control of flight. We have examined the effect of this type of actuation in the simplified case of a small fixed wing aircraft to [...] Read more.
The actuated abdomens of insects such as dragonflies have long been suggested to play a role in optimisation and control of flight. We have examined the effect of this type of actuation in the simplified case of a small fixed wing aircraft to determine whether energetic advantages exist in normal flight when compared to the cost of actuation using aerodynamic control surfaces. We explore the benefits the abdomen/tail might provide to balance level flight against trim changes. We also consider the transient advantage of using alternative longitudinal control effectors in a pull up flight maneuver. Results show that the articulated abdomen significantly reduces energy consumption and increase performance in isolated manoeuvres. The results also indicate a design feature that could be incorporated into small unmanned aircraft under particular circumstances. We aim to highlight behaviours that would increase flight efficiency to inform designers of micro aerial vehicles and to aid the analysis of insect flight behaviour and energetics. Full article
(This article belongs to the Special Issue Modelling of Aerospace Vehicle Dynamics)
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17 pages, 5415 KiB  
Article
Increasing Efficiency in an Aeronautical Engine through Maintenance Evaluation and Upgrades: Analysis of the Reliability and Performance Improvements under Financial Issues
by Lorenzo Fedele, Luca Di Vito and Fulvio Enzo Ramundo
Energies 2020, 13(12), 3059; https://doi.org/10.3390/en13123059 - 12 Jun 2020
Cited by 3 | Viewed by 4217
Abstract
This paper defines a methodology for the evaluation of the technical and economic performance of aeronautical engines through the upgrades introduced during its life. The CFM56 is a high-bypass turbofan engine. The variants share a common design, but the details are different. The [...] Read more.
This paper defines a methodology for the evaluation of the technical and economic performance of aeronautical engines through the upgrades introduced during its life. The CFM56 is a high-bypass turbofan engine. The variants share a common design, but the details are different. The fan and booster evolved over the different iterations of the engine, as did the compressor, combustor, and turbine sections. Maintenance consists of the activities carried out during the life cycle of an engine to ensure safe, reliable, and economic operation. Maintenance costs represent 20–25% of an airline’s operating costs, of which 35–40% refer to the engine. The changes in the performance parameters indicate the state of the engine in the medium to long term: for example, it is possible to detect blade fouling or data on vibrations, and highlight changes in the characteristic behavior of an engine. This work investigates the behavior of the performance parameters in the period prior to an engine development event: a comparison is made with the monitoring of engine vibrations. In the conclusions, a final expressive graph makes us aware of the significant progress, over the years, achieved with the methodology here presented. Full article
(This article belongs to the Special Issue Modelling of Aerospace Vehicle Dynamics)
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20 pages, 6195 KiB  
Article
Automated Design Optimization of a Mono Tiltrotor in Hovering and Cruising States
by Lifang Zeng, Jianxin Hu, Dingyi Pan and Xueming Shao
Energies 2020, 13(5), 1155; https://doi.org/10.3390/en13051155 - 04 Mar 2020
Cited by 2 | Viewed by 2645
Abstract
A mono tiltrotor (MTR) design which combines concepts of a tiltrotor and coaxial rotor is presented. The aerodynamic modeling of the MTR based on blade element momentum theory (BEMT) is conducted, and the method is fully validated with previous experimental data. An automated [...] Read more.
A mono tiltrotor (MTR) design which combines concepts of a tiltrotor and coaxial rotor is presented. The aerodynamic modeling of the MTR based on blade element momentum theory (BEMT) is conducted, and the method is fully validated with previous experimental data. An automated optimization approach integrating BEMT modeling and optimization algorithms is developed. Parameters such as inter-rotor spacing, blade twist, taper ratio and aspect ratio are chosen as design variables. Single-objective (in hovering or in cruising state) optimizations and multi-objective (both in hovering and cruising states) optimizations are studied at preset design points; i.e., hovering trim and cruising trim. Two single-objective optimizations result in different sets of parameter selections according to the different design objectives. The multi-objective optimization is applied to obtain an identical and compromised selection of design parameters. An optimal point is chosen from the Pareto front of the multi-objective optimization. The optimized design has a better performance in terms of the figure of merit (FM) and propulsive efficiency, which are improved by 7.3% for FM and 13.4% for propulsive efficiency from the prototype, respectively. Further aerodynamic analysis confirmed that the optimized rotor has a much more uniform load distribution along the blade span, and therefore a better aerodynamic performance in both hovering and cruising states is achieved. Full article
(This article belongs to the Special Issue Modelling of Aerospace Vehicle Dynamics)
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Graphical abstract

12 pages, 379 KiB  
Article
Energy Efficiency of Linear Electromagnetic Actuators for Flapping Wing Micro Aerial Vehicles
by Blake McIvor and Javaan Chahl
Energies 2020, 13(5), 1075; https://doi.org/10.3390/en13051075 - 01 Mar 2020
Cited by 8 | Viewed by 2418
Abstract
The development of flapping wing systems has been restricted by high power density requirements, comparatively large forces and the requirement for light weight. The use of linear electromagnetic actuators has had a small presence in the flapping wing literature when compared to other [...] Read more.
The development of flapping wing systems has been restricted by high power density requirements, comparatively large forces and the requirement for light weight. The use of linear electromagnetic actuators has had a small presence in the flapping wing literature when compared to other actuator types. This has been due to the high power consumption and low power output of this system when compared to resonant systems. This work assesses linear electromagnetic actuators presented in the literature and demonstrates the performance improvements achieved when the mechanism natural frequency is appropriately tuned. This process shows a reduction of input power consumption to 13% of the original power consumption. This improvement, combined with appropriate power electronic design, can reduce the perceived gap between linear electromagnetic actuators and solid-state actuators. Full article
(This article belongs to the Special Issue Modelling of Aerospace Vehicle Dynamics)
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17 pages, 3241 KiB  
Article
Identification, Categorisation and Gaps of Safety Indicators for U-Space
by Javier Alberto Pérez-Castán, Fernando Gómez Comendador, Ana Belén Cardenas-Soria, Dominik Janisch and Rosa M. Arnaldo Valdés
Energies 2020, 13(3), 608; https://doi.org/10.3390/en13030608 - 31 Jan 2020
Cited by 11 | Viewed by 2940
Abstract
Many civilian applications of commercial unmanned aircraft are being planned to operate in the years ahead. Several countries have developed their own framework to design the operation of unmanned aircraft and the different services that demand safe operation. This paper focuses on the [...] Read more.
Many civilian applications of commercial unmanned aircraft are being planned to operate in the years ahead. Several countries have developed their own framework to design the operation of unmanned aircraft and the different services that demand safe operation. This paper focuses on the European framework denoted as U-space which concludes with the joint integration of manned and unmanned aircraft in the airspace. U-space is a set of novel services and specific procedures designed to provide safe and efficient access into the airspace to the airspace users. U-space constitutes a management system to organise unmanned operations and provides relevant information to drone operators as well as manned aircraft, air navigation service providers and authorities. The understanding of associated hazards and risks to unmanned aircraft is a critical issue for their operation in complex and non-segregated airspaces. The safety assessment developed herein is crucial to identify safety indicators for U-space. In addition, the identification of safety indicators was used to identify gaps in U-spaces services that are not correctly covered by the U-space framework. Particularly, several safety indicators are identified that currently U-space services do not consider and can imply an increase in the operational risk of unmanned operations. Full article
(This article belongs to the Special Issue Modelling of Aerospace Vehicle Dynamics)
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27 pages, 9918 KiB  
Article
Aerodynamic Shape Optimization of a Wavy Airfoil for Ultra-Low Reynolds Number Regime in Gliding Flight
by Hui Tang, Yulong Lei, Xingzhong Li, Ke Gao and Yanli Li
Energies 2020, 13(2), 467; https://doi.org/10.3390/en13020467 - 17 Jan 2020
Cited by 4 | Viewed by 3414
Abstract
The effect of the number of waves and the width of the ridge and valley in chord direction for a wavy airfoil was investigated at the angle of attack of 0 ∘ and Reynolds number of 10 3 through using the two-dimensional direct [...] Read more.
The effect of the number of waves and the width of the ridge and valley in chord direction for a wavy airfoil was investigated at the angle of attack of 0 ∘ and Reynolds number of 10 3 through using the two-dimensional direct numerical simulation for four kinds of wavy airfoil shapes. A new method for parameterizing a wavy airfoil was proposed. In comparison with the original corrugated airfoil profile, the wavy airfoils that have more distinct waves show a lower aerodynamic efficiency and the wavy airfoils that have less distinct waves show higher aerodynamic performance. For the breakdown of the lift and drag concerning the pressure stress and friction stress contributions, the pressure stress component is significantly dominant for all wavy airfoil shapes concerning the lift. Concerning the drag, the pressure stress component is about 75 % for the wavy airfoils that have more distinct waves, while the frictional stress component is about 70 % for the wavy airfoils that have less distinct waves. From the distribution of pressure isoline and streamlines around wavy airfoils, it is confirmed that the pressure contributions of the drag are dominant due to high pressure on the upstream side and low pressure on the downside; the frictional contribution of the drag is dominant due to large surface areas of the airfoil facing the external flow. The effect of the angle of attack on the aerodynamic efficiency for various wavy airfoil geometries was studied as well. Aerodynamic shape optimization based on the continuous adjoint approach was applied to obtain as much as possible the highest global aerodynamic efficiency wavy airfoil shape. The optimal airfoil shape corresponds to an increase of 60 % and 62 % over the aerodynamic efficiency and the lift from the initial geometry, respectively, when optimal airfoil has an approximate drag coefficient compared to the initial geometry. Concerning an fixed angle of attack, the optimal airfoil is statically unstable in the range of the angle of attack from − 1 ∘ to 6 ∘ , statically quasi-stable from − 6 ∘ to − 2 ∘ , where the vortex is shedding at the optimal airfoil leading edge. Concerning an angle of attack passively varied due to the fluid force, the optimal airfoil keeps the initial angle of attack value with an initial disturbance, then quickly increases the angle of attack and diverges in the positive direction. Full article
(This article belongs to the Special Issue Modelling of Aerospace Vehicle Dynamics)
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25 pages, 5614 KiB  
Article
Numerical Investigation of the Aerodynamic Characteristics and Attitude Stability of a Bio-Inspired Corrugated Airfoil for MAV or UAV Applications
by Hui Tang, Yulong Lei, Xingzhong Li and Yao Fu
Energies 2019, 12(20), 4021; https://doi.org/10.3390/en12204021 - 22 Oct 2019
Cited by 11 | Viewed by 4291
Abstract
In this study, two-dimensional (2D) and three-dimensional (3D) numerical calculations were conducted to investigate the aerodynamic characteristics, especially the unsteady aerodynamic characteristics and attitude stability of a bio-inspired corrugated airfoil compared with a smooth-surfaced airfoil (NACA2408 airfoil) at the chord Reynolds number of [...] Read more.
In this study, two-dimensional (2D) and three-dimensional (3D) numerical calculations were conducted to investigate the aerodynamic characteristics, especially the unsteady aerodynamic characteristics and attitude stability of a bio-inspired corrugated airfoil compared with a smooth-surfaced airfoil (NACA2408 airfoil) at the chord Reynolds number of 4000 to explore the potential applications of non-traditional, corrugated dragonfly airfoils for micro air vehicles (MAVs) or micro-sized unmanned aerial vehicles (UAVs) designs. Two problem settings were applied to our numerical calculations. First, the airfoil was fixed at a constant angle of attack to analyze the aerodynamic characteristics and the hydrodynamic moment. Second, the angle of attack of airfoils was passively changed by the fluid force to analyze the attitude stability. The current numerical solver for the flow field around an unsteady rotating airfoil was validated against the published numerical data. It was confirmed that the corrugated airfoil performs (in terms of the lift-to-drag ratio) much better than the profiled NACA2408 airfoil at low Reynolds number R e = 4000 in low angle of attack range of 0 ∘ – 6 ∘ , and performs as well at the angle of attack of 6 ∘ or more. At these low angles of attack, the corrugated airfoil experiences an increase in the pressure drag and decrease in shear drag due to recirculation zones inside the cavities formed by the pleats. Furthermore, the increase in the lift for the corrugated airfoil is due to the negative pressure produced at the valleys. It was found that the lift and drag in the 2D numerical calculation are strong fluctuating at a high angle of attacks. However, in 3D simulation, especially for a 3D corrugated airfoil with unevenness in the spanwise direction, smaller fluctuations and the smaller average value in the lift and drag were obtained than the results in 2D calculations. It was found that a 3D wing with irregularities in the spanwise direction could promote three-dimensional flow and can suppress lift fluctuations even at high angles of attack. For the attitude stability, the corrugated airfoil is statically more unstable near the angle of attack of 0 ∘ , has a narrower static stable range of the angle of attack, and has a larger amplitude of fluctuations of the angle of attack compared with the profiled NACA2408 airfoil. Based on the Routh–Hurwitz stability criterion, it was confirmed that the control systems of the angle of attack passively changed by the fluid force for both two airfoils are unstable systems. Full article
(This article belongs to the Special Issue Modelling of Aerospace Vehicle Dynamics)
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15 pages, 3884 KiB  
Article
T–S Fuzzy Modeling for Aircraft Engines: The Clustering and Identification Approach
by Muxuan Pan, Hao Wang and Jinquan Huang
Energies 2019, 12(17), 3284; https://doi.org/10.3390/en12173284 - 26 Aug 2019
Cited by 8 | Viewed by 2514
Abstract
This paper presents a data-based Takagi-Sugeno (T–S) fuzzy modeling approach for aircraft engines in the flight envelope. We propose a series of T–S fuzzy models for engines with flight conditions as premises and engine linear dynamic models as consequences. By engine dynamic clustering, [...] Read more.
This paper presents a data-based Takagi-Sugeno (T–S) fuzzy modeling approach for aircraft engines in the flight envelope. We propose a series of T–S fuzzy models for engines with flight conditions as premises and engine linear dynamic models as consequences. By engine dynamic clustering, we determine rough T–S fuzzy models to approximate the nonlinear dynamics of engines in the flight envelope. After that, the maximum–minimum distance-based fuzzy c-means (MMD-FCM) algorithm comes to refine the fuzzy rules and the least square method (LSM) comes to identify premise parameters for each single rough model. The proposed MMD-FCM algorithm guarantees the refined results are stable and reasonable, and the identification improves the accuracy of the steady and transient phases. The model verification showed that the T–S fuzzy models for engines had a high accuracy with a steady error less than 5%, and that the root mean squared error (RMSE) of transient errors was less than 8 × 10−4 with good generalization ability in the flight envelope. Full article
(This article belongs to the Special Issue Modelling of Aerospace Vehicle Dynamics)
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22 pages, 16153 KiB  
Article
Numerical Study of Variable Camber Continuous Trailing Edge Flap at Off-Design Conditions
by Mohammed Abdul Raheem, Prasetyo Edi, Amjad A. Pasha, Mustafa M. Rahman and Khalid A. Juhany
Energies 2019, 12(16), 3185; https://doi.org/10.3390/en12163185 - 20 Aug 2019
Cited by 7 | Viewed by 3687
Abstract
Numerical simulations are performed to study the outboard airfoil of advanced technology regional aircraft (ATRA) wings with five different variable camber continuous trailing edge flap (VCCTEF) configurations. The computational study aims to improve the aerodynamic efficiency of the airfoil under cruise conditions. The [...] Read more.
Numerical simulations are performed to study the outboard airfoil of advanced technology regional aircraft (ATRA) wings with five different variable camber continuous trailing edge flap (VCCTEF) configurations. The computational study aims to improve the aerodynamic efficiency of the airfoil under cruise conditions. The design of outboard airfoil complies with the hybrid laminar flow control design criteria. This work is unique in terms of analysis of the effects of VCCTEF on the ATRA wing’s outboard airfoil during the off-design condition. The Reynolds–Averaged Navier–Stokes equations coupled with the Spalart-Allmaras turbulence model are employed to perform the simulations for the baseline case and VCCTEF configurations. The current computational study is performed at an altitude of 10 km with a cruise Mach number of 0.77 and a Reynolds number of 2.16 × 107. Amongst all five configurations of VCCTEF airfoils studied, a flap having a parabolic profile (VCCTEF 123) configuration shows the maximum airfoil efficiency and resulted in an increase of 6.3% as compared to the baseline airfoil. Full article
(This article belongs to the Special Issue Modelling of Aerospace Vehicle Dynamics)
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25 pages, 3045 KiB  
Article
UAV Payload Transportation via RTDP Based Optimized Velocity Profiles
by Abdullah Mohiuddin, Tarek Taha, Yahya Zweiri and Dongming Gan
Energies 2019, 12(16), 3049; https://doi.org/10.3390/en12163049 - 08 Aug 2019
Cited by 23 | Viewed by 4457
Abstract
This paper explores the application of a real-time dynamic programming (RTDP) algorithm to transport a payload using a multi-rotor unmanned aerial vehicle (UAV) in order to optimize journey time and energy consumption. The RTDP algorithm is developed by discretizing the journey into distance [...] Read more.
This paper explores the application of a real-time dynamic programming (RTDP) algorithm to transport a payload using a multi-rotor unmanned aerial vehicle (UAV) in order to optimize journey time and energy consumption. The RTDP algorithm is developed by discretizing the journey into distance interval horizons and applying the RTDP sweep to the current horizon to get the optimal velocity decision. RTDP sweep requires the current state of the UAV to generate the next best velocity decision. To the best of the authors knowledge, this is the first time that such real-time optimization algorithm is applied to multi-rotor based transportation. The algorithm was first tested in simulations and then experiments were performed. The results show the effectiveness and applicability of the proposed algorithm. Full article
(This article belongs to the Special Issue Modelling of Aerospace Vehicle Dynamics)
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17 pages, 3701 KiB  
Article
DSP Implementation of a Neural Network Vector Controller for IPM Motor Drives
by Yang Sun, Shuhui Li, Malek Ramezani, Bharat Balasubramanian, Bian Jin and Yixiang Gao
Energies 2019, 12(13), 2558; https://doi.org/10.3390/en12132558 - 03 Jul 2019
Cited by 4 | Viewed by 4651
Abstract
This paper develops a neural network (NN) vector controller for an interior mounted permanent magnet (IPM) motor by using a Texas Instrument TMS320F28335 digital signal processor (DSP). The NN controller is developed based on the complete state-space equation of an IPM motor and [...] Read more.
This paper develops a neural network (NN) vector controller for an interior mounted permanent magnet (IPM) motor by using a Texas Instrument TMS320F28335 digital signal processor (DSP). The NN controller is developed based on the complete state-space equation of an IPM motor and it is trained to achieve optimal control according to approximate dynamic programming (ADP). A DSP-based NN control system is built for an IPM motor drives system, and a high efficient DSP program is developed to implement the NN control algorithm while considering the limited memory and computing capability of the TMS320F28335 DSP. The DSP-based NN controller is able to manage IPM motor control in linear, over, and six-step modulation regions to improve the efficiency of IPM drives and to allow for the full utilization of DC bus voltage with space-vector pulse-width modulation (SVPWM). The experiment results show that the proposed NN controller is able to operate with a sampling period of 0.1ms, even with limited DSP resources of up to 150 MHz cycle time, which is applicable in practical motor industrial implementations. The NN controller has demonstrated a better current and speed tracking performance than the conventional standard vector controller for IPM operation in both the linear and over-modulation regions. Full article
(This article belongs to the Special Issue Modelling of Aerospace Vehicle Dynamics)
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12 pages, 2664 KiB  
Article
On the Use of Infrared Thermography and Acousto—Ultrasonics NDT Techniques for Ceramic-Coated Sandwich Structures
by Yuxia Duan, Hai Zhang, Stefano Sfarra, Nicolas P. Avdelidis, Theodoros H. Loutas, George Sotiriadis, Vassilis Kostopoulos, Henrique Fernandes, Florian Ion Petrescu, Clemente Ibarra-Castanedo and Xavier P.V. Maldague
Energies 2019, 12(13), 2537; https://doi.org/10.3390/en12132537 - 01 Jul 2019
Cited by 9 | Viewed by 3667
Abstract
Ceramic-coated materials used in different engineering sectors are the focus of world-wide interest and have generated a need for inspection techniques that detect very small structural anomalies. Non-destructive testing is increasingly being used to evaluate coating thickness and to test for coating flaws. [...] Read more.
Ceramic-coated materials used in different engineering sectors are the focus of world-wide interest and have generated a need for inspection techniques that detect very small structural anomalies. Non-destructive testing is increasingly being used to evaluate coating thickness and to test for coating flaws. The main pros of non-destructive testing is that the tested object remains intact and available for continued use afterward. This paper reports on an integrated, non-destructive testing approach that combines infrared thermography and acousto-ultrasonics to evaluate advanced aerospace sandwich structure materials with the aim of exploring any potential for detecting defects of more than one type. Combined, these two techniques successfully detected fabrication defects, including inclusions and material loss. Full article
(This article belongs to the Special Issue Modelling of Aerospace Vehicle Dynamics)
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25 pages, 3470 KiB  
Article
Impact of Trajectories’ Uncertainty in Existing ATC Complexity Methodologies and Metrics for DAC and FCA SESAR Concepts
by Victor Fernando Gomez Comendador, Rosa María Arnaldo Valdés, Andrija Vidosavljevic, Marta Sanchez Cidoncha and Shutao Zheng
Energies 2019, 12(8), 1559; https://doi.org/10.3390/en12081559 - 24 Apr 2019
Cited by 6 | Viewed by 3546
Abstract
The most relevant SESAR 2020 solutions dealing with future Capacity Management processes are Dynamic Airspace Configuration (DAC) and Flight Centric ATC (FCA). Both concepts, DAC and FCA, rely on traffic flow complexity assessment. For this reason, complexity assessments processes, methods and metrics, become [...] Read more.
The most relevant SESAR 2020 solutions dealing with future Capacity Management processes are Dynamic Airspace Configuration (DAC) and Flight Centric ATC (FCA). Both concepts, DAC and FCA, rely on traffic flow complexity assessment. For this reason, complexity assessments processes, methods and metrics, become one of the main constraints to deal with the growing demand and increasing airspace capacity. The aim of this work is to identify the influence of trajectories’ uncertainty in the quality of the predictions of complexity of traffic demand and the effectiveness of Demand Capacity Balance (DCB) airspace management processes, in order to overcome the limitations of existing complexity assessment approaches to support Capacity Management processes in a Trajectory-Based Operations (TBO) environment. This paper presents research conducted within COTTON project, sponsored by the SESAR Joint Undertaking and EU’s Horizon 2020 research and innovation program. The main objective is to deliver innovative solutions to maximize the performance of the Capacity Management procedures based on information in a TBO environment. Full article
(This article belongs to the Special Issue Modelling of Aerospace Vehicle Dynamics)
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22 pages, 4430 KiB  
Article
Fault Diagnosis and Fault-Tolerant Control Scheme for Quadcopter UAVs with a Total Loss of Actuator
by Ngoc Phi Nguyen and Sung Kyung Hong
Energies 2019, 12(6), 1139; https://doi.org/10.3390/en12061139 - 23 Mar 2019
Cited by 37 | Viewed by 4896
Abstract
Fault-tolerant control has drawn attention in recent years owning to its reliability and safe flight during missions. In this article, an active fault-tolerant control method is proposed to control a quadcopter in the presence of actuator faults and disturbances. Firstly, the dynamics of [...] Read more.
Fault-tolerant control has drawn attention in recent years owning to its reliability and safe flight during missions. In this article, an active fault-tolerant control method is proposed to control a quadcopter in the presence of actuator faults and disturbances. Firstly, the dynamics of the quadcopter are presented. Secondly, a robust adaptive sliding mode Thau observer is presented to estimate the time-varying magnitudes of actuator faults. Thirdly, a fault-tolerant control scheme based on sliding mode control and reconfiguration technique is designed to maintain the quadcopter at the desired position despite the presence of faults. Unlike previous studies, the proposed method aims to integrate the fault diagnosis and a fault-tolerant control scheme into a single unit with total loss of actuator. Simulation results illustrate the efficiency of the suggested algorithm. Full article
(This article belongs to the Special Issue Modelling of Aerospace Vehicle Dynamics)
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