Journal articles on the topic 'Modelling electric aircraft'
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Booker, Julian, Caius Patel, and Phillip Mellor. "Modelling Green VTOL Concept Designs for Reliability and Efficiency." Designs 5, no. 4 (October 28, 2021): 68. http://dx.doi.org/10.3390/designs5040068.
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All-electric and hybrid-electric aircraft are a future transport goal and a possible ‘green’ solution to increasing climate-related pressures for aviation. Ensuring the safety of passengers is of high importance, informed through appropriate reliability predictions to satisfy emerging flight certification requirements. This paper introduces another important consideration related to redundancy offered by multiplex electric motors, a maturing technology which could help electric aircraft manufacturers meet the high reliability targets being set. A concept design methodology is overviewed involving a symbolic representation of aircraft and block modelling of two important figures of merit, reliability, and efficiency, supported by data. This leads to a comparative study of green aircraft configurations indicating which have the most potential now, and in the future. Two main case studies are then presented: an electric tail rotor retrofitted to an existing turbine powered helicopter (hybrid) and an eVTOL aircraft (all-electric), demonstrating the impact of multiplex level and number of propulsion channels on meeting target reliabilities. The paper closes with a summary of the important contribution to be made by multiplex electric machines, well as the advancements necessary for green VTOL aircraft sub-systems, e.g., power control unit and batteries, to improve reliability predictions and safety further.
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Frosina, Emma, Carmine Caputo, Gianluca Marinaro, Adolfo Senatore, Ciro Pascarella, and Giuseppe Di Lorenzo. "Modelling of a Hybrid-Electric Light Aircraft." Energy Procedia 126 (September 2017): 1155–62. http://dx.doi.org/10.1016/j.egypro.2017.08.315.
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Thirukumaran, Sanmugasundaram, Paul Ratnamahilan Polycarp Hoole, Harikrishnan Ramiah, Jeevan Kanesan, Kandasamy Pirapaharan, and Samuel Ratnajeevan Herbert Hoole. "A new electric dipole model for lightning-aircraft electrodynamics." COMPEL: The International Journal for Computation and Mathematics in Electrical and Electronic Engineering 33, no. 1/2 (December 20, 2013): 540–55. http://dx.doi.org/10.1108/compel-12-2012-0385.
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Purpose – As commercial and military aircraft continue to be subject to direct lightning flashes, there is a great need to characterize correctly the electrical currents and electric potential fluctuations on an aircraft to determine alternative design approaches to minimizing the severity of the lightning-aircraft dynamics. Moreover, with the increased severity of thunderstorms due to global warming, the need arises even more to predict and quantify electrical characteristics of the lightning-aircraft electrodynamics, which is normally not measurable, using a reliable electric model of the aircraft. Such a model is advanced here. The paper aims to discuss these issues. Design/methodology/approach – The case considered in this paper is that of an aircraft directly attached to an earth flash lightning channel. The paper develops a new approach to modelling the aircraft using electric dipoles. The model has the power to represent sharp edges such as wings, tail ends and radome for any aircraft with different dimensions by using a number of different sized dipoles. The distributed transmission line model (TLM) of the lightning return stroke incorporating the distributed aircraft model is used to determine aircraft electrical elements and finally the electric current induced on the aircraft body due to lightning's interaction with the aircraft. The model is validated by the waveform method and experimental results. Findings – The dipole model proposed is a very powerful tool for minute representation of the different shapes of aircraft frame and to determine the best geometrical shape and fuselage material to reduce electric stress. This charge simulation method costs less computer storage and faster computing time. Originality/value – The paper for the first time presents a computer-based simulation tool that allows scientists and engineers to study the dynamics of voltage and current along the aircraft surface when the aircraft is attached to a cloud to ground lightning channel.
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Vankan, Jos, and Wim Lammen. "Parallel hybrid electric propulsion architecture for single aisle aircraft - powertrain investigation." MATEC Web of Conferences 304 (2019): 03008. http://dx.doi.org/10.1051/matecconf/201930403008.
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This paper presents an investigation of the fuel- and energy-saving potential through the introduction of several hybrid electric propulsion (HEP) and more electric aircraft (MEA) systems on single aisle aircraft. More specifically, for an A320NEO the following main electric systems are considered: electric motors, batteries and power electronics for parallel HEP, electric components for replacement of the main pneumatic and hydraulic non-propulsive systems like environmental control system and actuators, and electric power transport and supply. The power sizing of the electric components, as well as their mass effects on overall aircraft mission performance are evaluated by system modelling of the aircraft, turbofan and the considered electric components. It is found for the considered aircraft and missions that the fuel saving potential of parallel HEP systems alone is very limited or absent. Typically the combination of HEP and MEA technologies shows potential for improved energy efficiency due to synergies of the involved systems and their operation.
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Khairuddin, Ismail Mohd, Anwar P. P. A. Majeed, Ann Lim, Jessnor Arif M. Jizat, and Abdul Aziz Jaafar. "Modelling and PID Control of a Quadrotor Aerial Robot." Advanced Materials Research 903 (February 2014): 327–31. http://dx.doi.org/10.4028/www.scientific.net/amr.903.327.
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This paper elucidates the modeling of a + quadrotor configuration aerial vehicle and the design of its attitude and altitude controllers. The aircraft model consists of four fixed pitch angle propeller, each driven by an electric DC motor. The hovering flight of the quadrotor is governed by the Newton-Euler formulation. The attitude and altitude controls of the aircraft were regulated using heuristically tuned (Proportional-Integral-Derivative) PID controller. It was numerically simulated via Simulink that a PID controller was sufficient to bring the aircraft to the required altitude whereas the attitude of the vehicle is adequately controlled by a PD controller.
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Hu, Josin, and Julian Booker. "Preliminary Sizing of Electric-Propulsion Powertrains for Concept Aircraft Designs." Designs 6, no. 5 (October 13, 2022): 94. http://dx.doi.org/10.3390/designs6050094.
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The drive towards a greener and more sustainable future is encouraging the aviation industry to move towards increasing electrification of its fleet. The development of electric propulsion technologies also requires new approaches to assess their viability in novel configurations. A methodology is proposed which consists of four sub-procedures; powertrain modelling, performance analysis, aerodynamic modelling, and sizing. This approach initially considers powertrain modelling using AIAA symbol representations, and a review of the available literature establishes state-of-the-art component values of efficiency, specific power, specific energy, and specific fuel consumption. The sizing procedure includes a mission and aerodynamic analysis to determine the energy and power requirements, and it relies on a mass regression model based on full-electric, hybrid, VTOL and fixed-wing aircraft found in the literature. The methodology has been applied to five case studies which are representative of a wide range of missions and configurations. Their predicted masses from the sizing procedure have been validated against their actual masses. The predicted total mass shows generally good agreement with the actual values, and in addition, accurate values for active mass have been predicted. A sensitivity analysis of the sizing procedure suggests that future work may include a more accurate analysis of aerodynamics and mission if the methodology were to be applied for selecting aircraft concepts.
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Loong, Ling Jin, Chockalingam Aravind Vaithilingam, Gowthamraj Rajendran, and Venkatkumar Muneeswaran. "Modelling and analysis of vienna rectifier for more electric aircraft applications using wide band-gap materials." Journal of Physics: Conference Series 2120, no. 1 (December 1, 2021): 012027. http://dx.doi.org/10.1088/1742-6596/2120/1/012027.
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Abstract This paper presents a comprehensive study on the switching effects of wide bandgap devices and the importance of power electronics in an aircraft application. Silicon (Si), silicon carbide (SiC), and gallium nitride (GaN) are wide bandgap devices that act as a power electronic switch in the AC-DC converter for More Electric Aircraft (MEA) applications. Therefore, it is important to observe their converting efficiency to identify the most suitable wide bandgap device among three devices for AC-DC converters in aircraft applications to provide high efficiency and high-power density. In this study, the characteristics of Si, SIC, and GaN devices are simulated using PSIM software. Also, this paper presents the performance of the Vienna rectifier for aircraft application. The Vienna rectifier using Si, SiC, and GaN devices are simulated using PSIM software for aircraft application. GaN with Vienna rectifier provides better performance than Si and SiC devices for aircraft applications among the three devices. It gives high efficiency, high power density, low input current THD to meet IEEE-519 standard, and high-power factor at mains.
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Doctor, Faiyaz, Thomas Budd, Paul D. Williams, Matt Prescott, and Rahat Iqbal. "Modelling the effect of electric aircraft on airport operations and infrastructure." Technological Forecasting and Social Change 177 (April 2022): 121553. http://dx.doi.org/10.1016/j.techfore.2022.121553.
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Memmolo, V., F. Orefice, F. Nicolosi, and F. Ricci. "Design of near-zero emission aircraft based on refined aerodynamic model and structural analysis." IOP Conference Series: Materials Science and Engineering 1226, no. 1 (February 1, 2022): 012067. http://dx.doi.org/10.1088/1757-899x/1226/1/012067.
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Abstract During recent years, aircraft manufacturers focused their attention on environmentally friendly and aerodynamically efficient aircraft concepts that could allow a radical reduction of emissions. The use of hybrid-electric powertrain is one of the most effective ways to design near-zero emission aircraft. These aircraft are highly performing and sophisticated. Hence, the design process must be extremely accurate and should make use of multidisciplinary design optimization. It is indeed crucial to establish both aerodynamic and structural models to simulate the aircraft performance and design required according to top level aircraft requirements. Despite the largely discussed literature about preliminary design of such an unconventional aircraft, there is still a lack of reliable weight estimation approaches, simulation-based mission analysis and optimization tools. In order to step towards higher technological readiness levels, the purpose of this paper is to describe and apply a design platform for conventional, turboelectric, hybrid-electric and full-electric aircraft, integrating aero-propulsive interactions, accurate power system modelling and medium-fidelity structural weight estimation. In particular, the comprehensive structural analysis of the aircraft wing opportunely designed according to certification specification and equipped with different powertrain architectures shows that it is worth looking into structural dynamics from preliminary design to estimate aircraft weight properly. Meanwhile, the mission analysis reveals performance benefits by implementing distributed engines all over the wingspan.
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Khan, YM, A. Rolando, F. Salucci, CED Riboldi, and L. Trainelli. "Hybrid-electric and hydrogen powertrain modelling for airplane performance analysis and sizing." IOP Conference Series: Materials Science and Engineering 1226, no. 1 (February 1, 2022): 012071. http://dx.doi.org/10.1088/1757-899x/1226/1/012071.
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Abstract This paper describes a framework for parametric modelling of hybrid-electric powertrain components for innovative airplane configurations. These models are used in scalability studies and performance analysis of novel propulsion architecture. The methodology involves culmination of these models in a set of tools specifically developed to study the initial and conceptual sizing of hybrid-electric aircraft. This allows quick parametric evaluation of various configurations based on components at different technology readiness levels, such as batteries and fuel cells. Characteristics and performance of the power-train components are evaluated using computational analysis as well as laboratory tests. This information is used to develop numerical models described in the paper and to validate the sizing of fundamental propulsion components. Applications to two variants of a commuter aircraft are given, one using a serial hybrid-electric architecture based on a thermal engine, and the other using a fuel-cell system fed by a gaseous hydrogen tank.
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Pinheiro Melo, Sofia, Alexander Barke, Felipe Cerdas, Christian Thies, Mark Mennenga, Thomas S. Spengler, and Christoph Herrmann. "Sustainability Assessment and Engineering of Emerging Aircraft Technologies—Challenges, Methods and Tools." Sustainability 12, no. 14 (July 14, 2020): 5663. http://dx.doi.org/10.3390/su12145663.
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Driven by concerns regarding the sustainability of aviation and the continued growth of air traffic, increasing interest is given to emerging aircraft technologies. Although new technologies, such as battery-electric propulsion systems, have the potential to minimise in-flight emissions and noise, environmental burdens are possibly shifted to other stages of the aircraft’s life cycle, and new socio-economic challenges may arise. Therefore, a life-cycle-oriented sustainability assessment is required to identify these hotspots and problem shifts and to derive recommendations for action for aircraft development at an early stage. This paper proposes a framework for the modelling and assessment of future aircraft technologies and provides an overview of the challenges and available methods and tools in this field. A structured search and screening process is used to determine which aspects of the proposed framework are already addressed in the scientific literature and in which areas research is still needed. For this purpose, a total of 66 related articles are identified and systematically analysed. Firstly, an overview of statistics of papers dealing with life-cycle-oriented analysis of conventional and emerging aircraft propulsion systems is given, classifying them according to the technologies considered, the sustainability dimensions and indicators investigated, and the assessment methods applied. Secondly, a detailed analysis of the articles is conducted to derive answers to the defined research questions. It illustrates that the assessment of environmental aspects of alternative fuels is a dominating research theme, while novel approaches that integrate socio-economic aspects and broaden the scope to battery-powered, fuel-cell-based, or hybrid-electric aircraft are emerging. It also provides insights by what extent future aviation technologies can contribute to more sustainable and energy-efficient aviation. The findings underline the need to harmonise existing methods into an integrated modelling and assessment approach that considers the specifics of upcoming technological developments in aviation.
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Koch, Christopher. "Parametric whirl flutter study using different modelling approaches." CEAS Aeronautical Journal 13, no. 1 (October 6, 2021): 57–67. http://dx.doi.org/10.1007/s13272-021-00548-0.
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AbstractThis paper demonstrates the importance of assessing the whirl flutter stability of propeller configurations with a detailed aeroelastic model instead of local pylon models. Especially with the growing use of electric motors for propulsion in air taxis and commuter aircraft whirl flutter becomes an important mode of instability. These configurations often include propeller which are powered by lightweight electric motors and located at remote locations, e.g. the wing tip. This gives rise to an aeroelastic instability called whirl flutter, involving the gyroscopic whirl modes of the engine. The driving parameters for this instability are the dynamics of the mounting structure. Using a generic whirl flutter model of a propeller at the tip of a lifting surface, parameter studies on the flutter stability are carried out. The aeroelastic model consists of a dynamic MSC.Nastran beam model coupled with the unsteady ZAERO ZONA6 aerodynamic model and strip theory for the propeller aerodynamics. The parameter studies focus on the influence of different substructures (ranging from local engine mount stiffness to global aircraft dynamics) on the aeroelastic stability of the propeller. The results show a strong influence of the level of detail of the aeroelastic model on the flutter behaviour. The coupling with the lifting surface is of major importance, as it can stabilise the whirl flutter mode. Including wing unsteady aerodynamics into the analysis can also change the whirl flutter behaviour. This stresses the importance of including whirl flutter in the aeroelastic stability analysis on aircraft level.
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Binz, F., and D. Moormann. "Actuator modelling for attitude control using incremental nonlinear dynamic inversion." International Journal of Micro Air Vehicles 12 (January 2020): 175682932096192. http://dx.doi.org/10.1177/1756829320961925.
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Recently, the concept of incremental nonlinear dynamic inversion has seen an increasing adoption as an attitude control method for a variety of aircraft configurations. The reasons for this are good stability and robustness properties, moderate computation requirements and low requirements on modelling fidelity. While previous work investigated the robust stability properties of incremental nonlinear dynamic inversion, the actual closed-loop performance may degrade severely in the face of model uncertainty. We address this issue by first analysing the effects of modelling errors on the closed-loop performance by observing the movement of the system poles. Based on this, we analyse the neccessary modelling fidelity and propose simple modelling methods for the usual actuators found on small-scale electric aircraft. Finally, we analyse the actuator models using (flight) test data where possible.
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Donateo, Teresa, Ludovico Cucciniello, Luciano Strafella, and Antonio Ficarella. "Control Oriented Modelling of a Turboshaft Engine for Hybrid Electric Urban Air-Mobility." E3S Web of Conferences 197 (2020): 05003. http://dx.doi.org/10.1051/e3sconf/202019705003.
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The electrification of aircraft is a well-established trend in recent years in order to achieve economic and environmental sustainability. In this framework, an application particularly interesting for hybrid electric power system is represented by urban air-mobility. For this application, the authors presented a parallel hybrid electric power system including a turboshaft engine and two electric motors and proposed a quasi-stationary simulation tool. As a further step, this paper deals with the dynamic modelling of the same turboshaft engine within the framework of a hybrid electric system where the pilot command is interpreted as a power request to be satisfied by the engine and the electric machine according to the selected energy management strategy. In this work, the dynamic behaviour of the turboshaft engine is analysed with and without the help of the electric motors to satisfy the power demand.
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Qiao, Guan, Geng Liu, Zhenghong Shi, Yawen Wang, Shangjun Ma, and Teik C. Lim. "A review of electromechanical actuators for More/All Electric aircraft systems." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 232, no. 22 (December 28, 2017): 4128–51. http://dx.doi.org/10.1177/0954406217749869.
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Conventional hydraulic actuators in aircraft systems are high maintenance and more vulnerable to high temperatures and pressures. This usually leads to high operating costs and low efficiency. With the rapid development of More/All Electric technology, power-by-wire actuators are being broadly employed to improve the maintainability, reliability, and manoeuvrability of future aircraft. This paper reviews the published application and development of the airborne linear electromechanical actuator. First, the general configuration, merits, and limitations of the gear-drive electromechanical actuator and the direct-drive electromechanical actuator are analysed. Second, the development state of the electromechanical actuator testing systems is elaborated in three aspects, namely the performance testing based on room temperature, testing in a thermal vacuum environment, and iron bird. Common problems and tendencies of the testing systems are summarized. Key technologies and research challenges are revealed in terms of fault-tolerant motor, high-thrust mechanical transmission, multidisciplinary modelling, thermal management, and thermal analysis. Finally, the trend for future electromechanical actuators in More/All Electric Aircraft applications is summarized, and future research on the airborne linear electromechanical actuators is discussed.
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Yang, Tao, Serhiy Bozhko, and Greg Asher. "Active front‐end rectifier modelling using dynamic phasors for more‐electric aircraft applications." IET Electrical Systems in Transportation 5, no. 2 (June 2015): 77–87. http://dx.doi.org/10.1049/iet-est.2014.0030.
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Cardone, Massimo, Bonaventura Gargiulo, and Enrico Fornaro. "Modelling and Experimental Validation of a Hybrid Electric Propulsion System for Light Aircraft and Unmanned Aerial Vehicles." Energies 14, no. 13 (July 1, 2021): 3969. http://dx.doi.org/10.3390/en14133969.
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This article presents a numerical model of an aeronautical hybrid electric propulsion system (HEPS) based on an energy method. This model is designed for HEPS with a total power of 100 kW in a parallel configuration intended for ultralight aircraft and unmanned aerial vehicles (UAV). The model involves the interaction between the internal combustion engine (ICE), the electric motor (EM), the lithium battery and the aircraft propeller. This paper also describes an experimental setup that can reproduce some flight phases, or entire missions, for the reference aircraft class. The experimental data, obtained by reproducing two different take-offs, were used for model validation. The model can also simulate anomalous operating conditions. Therefore, the tests chosen for the model validation are characterized by the EM flux weakening (“de-fluxing”). This model is particularly suitable for preliminary stages of design when it is necessary to characterize the hybrid system architecture. Moreover, this model helps with the choice of the main components (e.g., ICE, EM, and transmission gear ratio). The results of the investigation conducted for different battery voltages and EM transmission ratios are shown for the same mission. Despite the highly simplified model, the average margin of error between the experimental and simulated results was generally under 5%.
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Garza, Pablo, Suresh Perinpanayagam, Sohaib Aslam, and Andrew Wileman. "Qualitative Validation Approach Using Digital Model for the Health Management of Electromechanical Actuators." Applied Sciences 10, no. 21 (November 4, 2020): 7809. http://dx.doi.org/10.3390/app10217809.
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An efficient and all-inclusive health management encompassing condition-based maintenance (CBM) environment plays a pivotal role in enhancing the useful life of mission-critical systems. Leveraging high fidelity digital modelling and simulation, scalable to digital twin (DT) representation, quadruples their performance prediction and health management regime. The work presented in this paper does exactly the same for an electric braking system (EBS) of a more-electric aircraft (MEA) by developing a highly representative digital model of its electro-mechanical actuator (EMA) and integrating it with the digital model of anti-skid braking system (ABS). We have shown how, when supported with more-realistic simulation and the application of a qualitative validation approach, various fault modes (such as open circuit, circuit intermittence, and jamming) are implemented in an EMA digital model, followed by their impact assessment. Substantial performance degradation of an electric braking system is observed along with associated hazards as different fault mode scenarios are introduced into the model. With the subsequent qualitative validation of an EMA digital model, a complete performance as well as reliability profile of an EMA can be built to enable its wider deployment and safe integration with a larger number of aircraft systems to achieve environmentally friendly objectives of the aircraft industry. Most significantly, the qualitative validation provides an efficient method of identifying various fault modes in an EMA through rapid monitoring of associated sensor signals and their comparative analysis. It is envisaged that when applied as an add-on in digital twin environment, it would help enhance its CBM capability and improve the overall health management regime of electric braking systems in more-electric aircraft.
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Garriga, Ana García, Parithi Govindaraju, Sangeeth Saagar Ponnusamy, Nicola Cimmino, and Laura Mainini. "A modelling framework to support power architecture trade-off studies for More-Electric Aircraft." Transportation Research Procedia 29 (2018): 146–56. http://dx.doi.org/10.1016/j.trpro.2018.02.013.
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Jianzhi, DENG, SONG Wenyan, YANG Guangjun, JIANG Feng, and XIONG Neng. "Aircraft/Engine Integrated Design for an Air-superiority Unmanned Aerial Vehicle." Journal of Physics: Conference Series 2235, no. 1 (May 1, 2022): 012060. http://dx.doi.org/10.1088/1742-6596/2235/1/012060.
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Abstract Aiming at the demand of efficient energy management for wide flight envelope of air-superiority unmanned aerial vehicle (UAV), an conceptual and preliminary design of air-superiority UAV with oil-electric hybrid power was proposed based on the idea of integrated aircraft and engine modelling. The evaluation model of the UAV aerodynamic performance and the thrust requirements of full flight envelope were determined, then the matching configuration of target turbofan engine was proposed. According to general design parameters of UAV, the simulation model and constraint relations for aircraft-engine integration performance calculation were established, parameters were optimized for typical multi-mission conditions, the tactical performance of future advanced air superiority UAV was predicted. The integrated design method of air superiority UAV upon hybrid electric turbofan can also be applied to improve the performance of UAVs in service, which established in this paper has good engineering practical value.
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LP, Ponyaev. "Geometrical Theory of the Periodical Spheroid Transformation in Modelling of the Ecology Hybrid Electric and Modular Aircraft/ Airship and Flight Simulation." Environmental Sciences and Ecology: Current Research (ESECR 3, no. 2 (February 10, 2022): 1–3. http://dx.doi.org/10.54026/esecr/1048.
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This article is devoted to the search for the Geometry Periodic Table Regularities architect structures in the space-group set and 2D/3D integrating variation of the any Geometric Transformations of the polar Spheroid shells models and Adaptive Simulation of the Synthesis of integral-differential layouts of the Aircraft and Airship and their Full Flight or Processing Training Simulations with spherical visual panoramic screen matrix. Using idea as the periodic table of the variety of elements proposed by Mendeleev DI., which allows us to naturally discover new yet unknown elements, it is possible to create a similar geometric table-matrix of element-by-element transformation of the layout forms of the aircraft for the development of a digital computer modeling complex in an Artificial intelligence environment, as a digital double of a qualified human designer. Perhaps the industry of electric vehicles and electric water transport and space projects can follow this path, as it is flexibly and variously
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Yezeguelian, Axel, and Askin T. Isikveren. "Methods to improve UAV performance using hybrid-electric architectures." Aircraft Engineering and Aerospace Technology 92, no. 5 (April 16, 2020): 685–700. http://dx.doi.org/10.1108/aeat-11-2019-0227.
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Purpose When comparing and contrasting different types of fixed-wing military aircraft on the basis of an energetic efficiency figure-of-merit, unmanned aerial vehicles (UAVs) dedicated to tactical medium-altitude long-endurance (MALE) operations appear to have significant potential when hybrid-electric propulsion and power systems (HEPPS) are implemented. Beginning with a baseline Eulair drone, this paper aims to examine the feasibility of retro-fitting with an Autarkic-Parallel-HEPPS architecture to enhance performance of the original single diesel engine. Design/methodology/approach In view of the low gravimetric specific energy performance attributes of batteries in the foreseeable future, the best approach was found to be one in which the Parallel-HEPPS architecture has the thermal engine augmented by an organic rankine cycle (ORC). For this study, with the outer mould lines fixed, the goal was to increase endurance without increasing the Eulair drone maximum take-off weight beyond an upper limit of +10%. The intent was to also retain take-off distance and climb performance or, where possible, improve upon these aspects. Therefore, as the focus of the work was on power scheduling, two primary control variables were identified as degree-of-hybridisation for useful power and cut-off altitude during the en route climb phase. Quasi-static methods were used for technical sub-space modelling, and these modules were linked into a constrained optimisation algorithm. Findings Results showed that an Autarkic-Parallel-HEPPS architecture comprising an ORC thermal energy recovery apparatus and high-end year-2020 battery, the endurance of the considered aircraft could be increased by 11%, i.e. a total of around 28 h, including de-icing system, in-flight recharge and emergency aircraft recovery capabilities. The same aircraft with the de-icing functionality removed resulted in a 20% increase in maximum endurance to 30 h. Practical implications Although the adoption of Series/Parallel-HEPPS only solutions do tend to generate questionable improvements in UAV operational performance, combinations of HEPPS with energy recovery machines that use, for example, an ORC, were found to have merit. Furthermore, such architectural solutions could also offer opportunity to facilitate additional functions like de-icing and emergency aircraft recovery during engine failure, which is either not available for UAVs today or prove to be prohibitive in terms of operational performance attributes when implemented using a conventional PPS approach. Originality/value This technical paper highlights a new degree of freedom in terms of power scheduling during climbing transversal flight operations. A control parameter of cut-off altitude for all types of HEPPS-based aircraft should be introduced into the technical decision-making/optimisation/analysis scheme and is seen to be a fundamental aspect when conducting trade-studies with respect to degree-of-hybridisation for useful power.
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Lowke, J. J. "From Switching Arcs to Ball Lightning to Curing Cancer!" PLASMA PHYSICS AND TECHNOLOGY 6, no. 2 (2019): 194–99. http://dx.doi.org/10.14311/ppt.2019.2.194.
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Previous modelling of switching has been through calculation of reductions in temperature of the arc at "current zero". "Enthalpy density" as a function of temperature is found to be an important property. New calculations now include an account of non-equilibrium electron density as a function of time through current zero and it is found that electron attachment rates, which are very large for SF<sub>6</sub>, could be a dominant property. Modelling discharges is having other successes, for example in explaining "ball lightning" observations inside of houses and aircraft, which suddenly appear, usually at glass windows. Discharge modelling suggests these observations might be explained by the production of "singlet delta" metastable molecules of oxygen in electrical discharges in air. If metastable densities are sufficient, electrons can be produced from the detachment of negative ions to produce radiation and explain ball lightning. An exciting new development is that plasmas from electric corona in air have been found to reduce the size of cancer tumours. These excited oxygen molecules have also been proposed as having a role in this remarkable interchange between classical electrical engineering and medical science.
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YANG, Tao, Serhiy BOZHKO, Patrick WHEELER, Shaoping WANG, and Shuai WU. "Generic functional modelling of multi-pulse auto-transformer rectifier units for more-electric aircraft applications." Chinese Journal of Aeronautics 31, no. 5 (May 2018): 883–91. http://dx.doi.org/10.1016/j.cja.2018.03.010.
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Moreno, R. Felix, JT Economou, D. Bray, and K. Knowles. "Modelling and simulation of a fuel cell powered electric drivetrain for wide body passenger aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 227, no. 4 (February 2013): 608–17. http://dx.doi.org/10.1177/0954410012473389.
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Vouros, Stavros, Mavroudis Kavvalos, Smruti Sahoo, and Konstantinos Kyprianidis. "Enabling the potential of hybrid electric propulsion through lean-burn-combustion turbofans." Journal of the Global Power and Propulsion Society 5 (September 16, 2021): 164–76. http://dx.doi.org/10.33737/jgpps/140592.
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Hybrid-electric propulsion has emerged as a promising technology to mitigate the adverse environmental impact of civil aviation. Boosting conventional gas turbines with electric power improves mission performance and operability. In this work the impact of electrification on pollutant emissions and direct operating cost of geared turbofan configurations is evaluated for an 150-passenger aircraft. A baseline two-and-a-half-shaft geared turbofan, representative of year 2035 entry-into-service technology, is employed. Parallel hybridization is implemented through coupling a battery-powered electric motor to the engine low-speed shaft. A multi-disciplinary design space exploration framework is employed comprising modelling methods for multi-point engine design, aircraft sizing, performance and pollutant emissions, mission and economic analysis. A probabilistic approach is developed considering uncertainties in the evaluation of direct operating cost. Sensitivities to electrical power system technology levels, as well as fuel price and emissions taxation are quantified at different time-frames. The benefits of lean direct injection are explored along short-, medium-, and long-range missions, demonstrating 32% NO<italic><sub>x</sub></italic> savings compared to traditional rich-burn, quick-mix, lean-burn technologies in short-range operations. The impact of electrification on the enhancement of lean direct injection benefits is investigated. For hybrid-electric powerplants, the take-off-to-cruise turbine entry temperature ratio is 2.5% lower than the baseline, extending the corresponding NO<italic><sub>x</sub></italic> reductions to the level of 46% in short-range missions. This work sheds light on the environmental and economic potential and limitations of a hybrid-electric propulsion concept towards a greener and sustainable civil aviation.
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Guglieri, G. "Effect of autopilot modes on flight performances of electric mini-UAVs." Aeronautical Journal 117, no. 1187 (January 2013): 57–69. http://dx.doi.org/10.1017/s0001924000007752.
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Abstract Great attention is focused on the development of both remotely controlled and unmanned flying vehicles. As a matter of fact, the design of such vehicles is a topical direction of development for modern aeronautics. Among such promising flying vehicles, micro- and mini-UAVs play a leading role. The present paper proposes a method to validate the inclusion of the relevant modelling elements in a comprehensive simulation tool reproducing some of the flight phases of a mini-UAV. The energy balance budget and the dynamic response of the aircraft during the automatic flight are investigated, assessing the impact of autopilot configuration, such as altitude-airspeed holding modes and suggesting a setting guideline for flight mode selection compatible with the features of commercial autopilots.
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BEN MOSBAH, Abdallah, Ruxandra Mihaela BOTEZ, Soumaya MEDINI MEDINI, and Thien-My DAO. "Artificial Neural Networks-Extended Great Deluge Model to predict Actuators Displacements for a Morphing Wing Tip System." INCAS BULLETIN 12, no. 4 (December 4, 2020): 13–24. http://dx.doi.org/10.13111/2066-8201.2020.12.4.2.
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Resin-based fiber composite materials have received attention in aerospace composite engineering, particularly in aircraft morphing structures, due to their high mechanical characteristics, such as stiffness, and because of their potential to highly reduce the structural mass of modern aircraft. Aircraft morphing is referred to as the ability of an aircraft’s surface to change its geometry in flight. The modelling of a dynamic morphing wing system is here studied. The morphing wing was controlled using four electric actuators situated inside of the wing model. The main role of these actuators was to modify the wing upper surface shape designed and manufactured with a flexible material, so that the laminar-to-turbulent flow transition point can move closer to the wing trailing edge, thus causing a minimum viscous drag, for various flow conditions. To determine the skin deflections in the four actuators points, both LVDT and dial indicator gages were positioned on the wing. Four Linear Variable Differential Transducers (LVDTs) were used to indicate the positions of the four actuators, and four Dial Indicators gages were positioned on the wing to measure the real deflections of the flexible composite skin in the four actuation points. The relationship between the Dial Indicators’ values and the LVDTs’ values for a same set-point command signal had a nondeterministic and unpredictable behavior (not a linear one). The values of the displacements given by the LVDTs were different than the values given by the Dial Indicators. In this paper, an Artificial Neural Network (ANN) model was investigated created with the aim to predict the displacements of the wing upper surface skin in real time using four actuators. The proposed model was trained using the Extended Great Deluge (EGD) algorithm.
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Mayorga-Macías, Walter A., Luis E. González-Jiménez, Marco A. Meza-Aguilar, and Luis F. Luque-Vega. "Low-Cost Experimental Methodology for the Dynamic Model Approximation of Multirotor Actuators." International Journal of Aerospace Engineering 2020 (July 11, 2020): 1–9. http://dx.doi.org/10.1155/2020/9263961.
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A methodology for the experimental modelling of the electric actuators of a multirotor is presented in this work. These actuators are usually brushless DC motors which are driven by electronic speed controllers in an open loop. The duty cycle of a PWM signal, generated by the electronic control unit, is the input of the electronic controller. However, during the control design procedure for the multirotor, it is important to account with a model of the actuators as its dynamical features define the closed-loop performance of the overall aircraft. Hence, a procedure, based on low-cost electronic components, to obtain approximated transfer functions of the actuators of a multirotor is presented. Moreover, as the proposed signal processing algorithms are simple, the computational capabilities of the required embedded system are also low. Given that different control schemes require different information from the actuator, two models were obtained: a duty cycle vs. angular velocity transfer function and a duty cycle vs. consumed current transfer function. The effectivity of the proposal is validated with experimental results on common electric actuators of a multirotor.
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Liu, Bing, Bowen Xu, Tong He, Wei Yu, and Fanghong Guo. "Hybrid Deep Reinforcement Learning Considering Discrete-Continuous Action Spaces for Real-Time Energy Management in More Electric Aircraft." Energies 15, no. 17 (August 30, 2022): 6323. http://dx.doi.org/10.3390/en15176323.
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The increasing number and functional complexity of power electronics in more electric aircraft (MEA) power systems have led to a high degree of complexity in modelling and computation, making real-time energy management a formidable challenge, and the discrete-continuous action space of the MEA system under consideration also poses a challenge to existing DRL algorithms. Therefore, this paper proposes an optimisation strategy for real-time energy management based on hybrid deep reinforcement learning (HDRL). An energy management model of the MEA power system is constructed for the analysis of generators, buses, loads and energy storage system (ESS) characteristics, and the problem is described as a multi-objective optimisation problem with integer and continuous variables. The problem is solved by combining a duelling double deep Q network (D3QN) algorithm with a deep deterministic policy gradient (DDPG) algorithm, where the D3QN algorithm deals with the discrete action space and the DDPG algorithm with the continuous action space. These two algorithms are alternately trained and interact with each other to maximize the long-term payoff of MEA. Finally, the simulation results show that the effectiveness of the method is verified under different generator operating conditions. For different time lengths T, the method always obtains smaller objective function values compared to previous DRL algorithms, is several orders of magnitude faster than commercial solvers, and is always less than 0.2 s, despite a slight shortfall in solution accuracy. In addition, the method has been validated on a hardware-in-the-loop simulation platform.
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Buticchi, Giampaolo, Levy Ferreira Costa, and Marco Liserre. "Multi-port DC/DC converter for the electrical power distribution system of the more electric aircraft." Mathematics and Computers in Simulation 158 (April 2019): 387–402. http://dx.doi.org/10.1016/j.matcom.2018.09.019.
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Zhang, He, Christophe Saudemont, Benoît Robyns, and Régis Meuret. "Comparison of different DC voltage supervision strategies in a local Power Distribution System of More Electric Aircraft." Mathematics and Computers in Simulation 81, no. 2 (October 2010): 263–76. http://dx.doi.org/10.1016/j.matcom.2010.05.009.
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Zhang, Wensen, Jian Fu, Yongling Fu, Jinlin Zhou, and Xudong Han. "System Performance Analysis for Trimmable Horizontal Stabilizer Actuator Focusing on Nonlinear Effects: Based on Incremental Modelling and Parameter Identification Methodology." Sensors 21, no. 19 (September 28, 2021): 6464. http://dx.doi.org/10.3390/s21196464.
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With the development of more/all electric aircraft, replacement of the traditional hydraulic servo actuator (HSA) with an electromechanical actuator (EMA) is becoming increasingly attractive in the aerospace field. This paper takes an EMA for a trimmable horizontal stabilizer as an example and focuses on how to establish a system model with an appropriate level of complexity to support the model-based system engineering (MBSE) approach. To distinguish the nonlinear effects that dominate the required system performance, an incremental approach is proposed to progressively introduce individual nonlinear effects into models with different complexity levels. Considering the special design and working principle of the mechanical power transmission function for this actuator, the nonlinear dynamics, including friction and backlash from the no-back mechanism, and the nonlinear compliance effect from the mechanical load path are mainly taken into consideration. The modelling principles for each effect are addressed in detail and the parameter identification method is utilized to model these nonlinear effects realistically. Finally, the responses from each model and experimental results are compared to analyze and verify how each individual nonlinearity affects the system’s performance.
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Parmantier, J. P., C. Guiffaut, D. Roissé, C. Girard, F. Terrade, S. Bertuol, I. Junqua, and A. Reinex. "Modelling EM-Coupling on Electrical Cable-Bundles with a Frequency-Domain Field-to-Transmission Line Model Based on Total Electric Fields." Advanced Electromagnetics 9, no. 3 (December 7, 2020): 15–31. http://dx.doi.org/10.7716/aem.v9i3.1531.
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This article deals with modelling of EM-coupling on cable-bundles installed in 3D structures. It introduces a modified-Field-to-Transmission-Line model for which the specificity is to account for the reciprocal interaction between EM-fields and induced currents by considering equivalent total field sources. The first part of the paper is devoted to the derivation of this model starting from Agrawal’s classical Field-to-Transmission-Line applied on a two-wire Transmission-Line and leads to a Transmission-Line model in which the signal-wire is now referenced to a fictitious surrounding cylinder acting as a return conductor. The modified-Field-to-Transmission-Line model is then obtained by modifying this derived-model in such a way that is made compatible with numerical approaches and tools based on Agrawal’s Field-to-Transmission-Line model. This modification involves a kL coefficient equal to the ratio of the two per-unit-length inductances of the classical and derived Field-to-Transmission-Line models. Validations of this modified formulation clearly show the capability of this model to predict precise wire responses including EM-radiation losses. The second part of the paper is devoted to its extension to Multiconductor-Transmission-Line-Networks. The process relies on the capability to define an equivalent wire model of the cable-bundle in order to derive the kL coefficient and to numerically evaluate equivalent total field sources. Validation of this extrapolation is presented on a real aircraft test-case involving realistic cable-bundles in order to assess the potentiality of the method for future problems of industrial complexity.
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Kozlova, Mariia, Timo Nykänen, and Julian Yeomans. "Technical Advances in Aviation Electrification: Enhancing Strategic R&D Investment Analysis through Simulation Decomposition." Sustainability 14, no. 1 (December 31, 2021): 414. http://dx.doi.org/10.3390/su14010414.
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Computational decision-making in “real world” environmental and sustainability contexts frequently requires the need to contrast numerous uncertain factors and difficult-to-capture dimensions. Monte Carlo simulation modelling has frequently been employed to integrate the uncertain inputs and to construct probability distributions of the resulting outputs. Visual analytics and data visualization can be used to support the processing, analyzing, and communicating of the influence of multi-variable uncertainties on the decision-making process. In this paper, the novel Simulation Decomposition (SimDec) analytical technique is used to quantitatively examine carbon emission impacts resulting from a transformation of the aviation industry toward a state of greater airline electrification. SimDec is used to decompose a Monte Carlo model of the flying range of all-electric aircraft based upon improvements to batteries and motor efficiencies. Since SimDec can be run concurrently with any Monte Carlo model with only negligible additional overhead, it can easily be extended into the analysis of any environmental application that employs simulation. This generalizability in conjunction with its straightforward visualizations of complex stochastic uncertainties makes the practical contributions of SimDec very powerful in environmental decision-making.
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Gallagher, M. W., P. J. Connolly, I. Crawford, A. Heymsfield, K. N. Bower, T. W. Choularton, G. Allen, M. J. Flynn, G. Vaughan, and J. Hacker. "Observations and modelling of microphysical variability, aggregation and sedimentation in tropical anvil cirrus outflow regions." Atmospheric Chemistry and Physics 12, no. 14 (July 26, 2012): 6609–28. http://dx.doi.org/10.5194/acp-12-6609-2012.
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Abstract. Aircraft measurements of the microphysics of a tropical convective anvil (at temperatures ~−60 °C) forming above the Hector storm, over the Tiwi Islands, Northern Australia, have been conducted with a view to determining ice crystal aggregation efficiencies from in situ measurements. The observed microphysics have been compared to an explicit bin-microphysical model of the anvil region, which includes crystal growth by vapour diffusion and aggregation and the process of differential sedimentation. It has been found in flights made using straight and level runs perpendicular to the storm that the number of ice crystals initially decreased with distance from the storm as aggregation took place resulting in larger crystals, followed by their loss from the cloud layer due to sedimentation. The net result was that the mass (i.e. Ice Water Content) in the anvil Ci cloud decreased, but also that the average particle size (weighted by number) remained relatively constant along the length of the anvil outflow. Comparisons with the explicit microphysics model showed that the changes in the shapes of the ice crystal spectra as a function of distance from the storm could be explained by the model if the aggregation efficiency was set to values of Eagg~0.5 and higher. This result is supported by recent literature on aggregation efficiencies for complex ice particles and suggests that either the mechanism of particle interlocking is important to the aggregation process, or that other effects are occuring, such as enhancement of ice-aggregation by high electric fields that arise as a consequence of charge separation within the storm. It is noteworthy that this value of the ice crystal aggregation efficiency is much larger than values used in cloud resolving models at these temperatures, which typically use E~0.0016. These results are important to understanding how cold clouds evolve in time and for the treatment of the evolution of tropical Ci in numerical models.
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Lago, F., J. J. Gonzalez, P. Freton, F. Uhlig, N. Lucius, and G. P. Piau. "A numerical modelling of an electric arc and its interaction with the anode: part III. Application to the interaction of a lightning strike and an aircraft in flight." Journal of Physics D: Applied Physics 39, no. 10 (May 5, 2006): 2294–310. http://dx.doi.org/10.1088/0022-3727/39/10/045.
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Toghyani, Somayeh, Florian Baakes, Ningxin Zhang, Helmut Kühnelt, Walter Cistjakov, and Ulrike Krewer. "(Digital Presentation) Model-Assisted Design of Oxide-Based All-Solid-State Li-Batteries with Hybrid Electrolytes for Aviation." ECS Meeting Abstracts MA2022-02, no. 4 (October 9, 2022): 484. http://dx.doi.org/10.1149/ma2022-024484mtgabs.
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There is a growing interest in the sustainability of the aviation industry sector over the past years due to the environmental issues associated with traditional aviation engines. Electric and hybrid aircrafts are considered promising technologies for reducing fuel consumption and enhancing system efficiency [1]. However, electrical energy storage systems require a higher capacity-to-weight ratio than today’s Li-ion batteries to fulfil the high demands in this area. Safety restrictions imposed by liquid electrolytes motivate the development of next-generation chemistries, such as oxide-based all-solid-state batteries (ASSB) for aviation, which have non-flammable electrolytes [2]. This option is investigated in the context of the IMOTHEP European project that aims at identifying promising hybrid aircraft configurations and studying the associated technology. However, the major drawbacks of oxide-based solid electrolytes are weak contact between electrode and electrolyte interface, low mechanical flexibility, and high density, which limit their use for high gravimetric energy density applications. To mitigate the aforementioned concerns, the solid polymer composite electrolytes approach could be applied, where oxides are mixed with polymer electrolytes [3]. Designing an optimum cell without ion transport limitations using experimental investigations is time- as well as resource-intensive due to the large number of iterations in production and evaluation required to achieve a well-performing design. Physics-based modelling is able to create a platform that can directly assess the impact of cell structure on battery performance and provide knowledge concerning limiting processes within the cell. Therefore, we here present the first study that combines a pseudo-two-dimensional model for the model-assisted evaluation of Li-ASSB with various hybrid electrolytes and single-ion conductor electrolytes with an evolutionary algorithm to identify optimum cell designs to reach a higher gravimetric energy density (see Fig. 1-a). To this end, we first compared the performance of several hybrid electrolytes with their experimental properties, to identify which electrolyte performs well with present technology and which has the potential to become an attractive alternative in the future. Our findings reveal that based on available ASSB technology, single ion-conducting electrolytes cannot achieve a higher gravimetric energy density than hybrid electrolytes at low current rates due to their high density, as shown in Fig. 1-b. ASSB based on 12.7 vol% of garnet Li6.4La3Zr1.4Ta0.6O12 (LLZTO) is the best option based on present manufacturing constraints. Furthermore, our study revealed that hybrid electrolytes based on 10 wt% of Li1.3Al0.3Ti1.7(PO4)3 (LATP) could be promising for future aircraft if researchers succeed to decrease its electrolyte thickness and chemical stability in contact with lithium metal anode. Further, sensitivity analyses enabled us to identify that the cathode thickness and volume fraction of cathode materials are critical parameters for the cell design of ASSB. Therefore, we applied a global optimisation to enhance gravimetric energy density by changing these two electrode design parameters. After optimisation, gravimetric and volumetric energy densities of 618 Wh kg-1 and 1251 Wh L-1 for 0.1C discharge are achieved, respectively, indicating that the cell with the optimal electrode design could meet the mission demand in the aviation industry with a gravimetric energy density of 500 Wh kg-1 and volumetric energy density of 1000 Wh L-1. In conclusion, the findings of this study show that our physics-based modelling in conjunction with an optimisation algorithm predicts the optimal composition of ASSB for a given constraint and thus supports the time- and cost-effective development of batteries that fulfil mission requirements, e.g. in the aviation sector. This work is conducted in the frame of the project IMOTHEP (Investigation and Maturation of Technologies for Hybrid Electric Propulsion), which has received funding from the European Union’s Horizon 2020 research and innovation program under grant agreement No 875006 IMOTHEP. References: M. Tariq, A. I. Maswood, C. J. Gajanayake, and A. K. Gupta, IECON Proc. (Industrial Electron. Conf. 4429 (2016). J. Hoelzen, Y. Liu, B. Bensmann, C. Winnefeld, A. Elham, J. Friedrichs, and R. Hanke-Rauschenbach, Energies 11, 1 (2018). G. Piana, F. Bella, F. Geobaldo, G. Meligrana, and C. Gerbaldi, J. Energy Storage 26, 100947 (2019). S.Toghyani, , F. Baakes, N. Zhang, H. Kühnelt, W. Cistjakov, U. Krewer, J. Electrochem. Soc (2022). Figure 1
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Toghyani, Somayeh, Walter Cistjakov, Florian Baakes, and Ulrike Krewer. "(Digital Presentation) Conceptual Design of Oxide-Based Solid-State Li-Battery for Urban Air Mobility." ECS Meeting Abstracts MA2022-02, no. 28 (October 9, 2022): 1068. http://dx.doi.org/10.1149/ma2022-02281068mtgabs.
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In metropolitan areas, traffic congestion and pollution are serious challenges due to the continuous rapid growth in the number of vehicles and population. These concerns have prompted a global trend toward the electrification of transportation powertrains. Electric vertical take-off and landing (eVTOL) aircraft is an efficient and safe alternative mode of transportation with a significant impact on urban mobility, which attracts considerable attention [1]. It could avoid traffic on the ground and allow people to commute between two locations in less time while requiring no additional run-up space. Nevertheless, one of the main challenges with such aircraft is to provide electrical storage systems, such as batteries, which are safe, efficient, reliable, and capable of producing the energy and power demand to meet mission requirements [2]. High flammability and risk of thermal runaway in current Li-ion batteries motivate to develop next-generation chemistries such as all-solid-state batteries (ASSB) as alternative electrical storage systems for eVTOL. However, ASSB currently suffer from low solid electrolyte conductivity, as well as non-utilised active material, and significant reaction overpotentials due to a small effective active area [3]. Electrode composition and structure have a crucial impact on three performance-relevant microstructure parameters, i.e. effective active area, effective ionic conductivity, and effective electronic conductivity. However, considering these restrictions experimentally by producing and evaluating a wide range of design parameters to achieve a well-performing design for ASSB is both time- and resource-intensive. To address these issues, we conduct model-based structure evaluation. Here, we extend the P2D model with a microstructure surrogate model based on Laue's work [4] for Li-ASSB (see Fig. 1-a), because electrode microstructure is important for the effective parameters. Further, this link between the P2D model and microstructure modelling could provide a better understanding of the electrode structure and especially the effects of percolation, which cannot be properly covered by classical Bruggeman approaches. This model is then incorporated into a global optimisation algorithm to determine the optimal design of solid-state cathode with respect to eVTOL power demand. Finally, we compare the performance of the battery at the identified optimal electrode design, electrode reference design, and electrode design with that of the Bruggeman approach. Based on our prior research, we identified that hybrid electrolytes with 12.7 vol% LLZTO had the best performance among other types of hybrid electrolytes at a relatively high C-rate, i.e. 1C. Therefore, we employed this electrolyte for the modelling of Li-ASSB for eVTOL application [5]. Fig. 1-b shows an exemplary result from a simpler model without percolation, i.e. Bruggemann approach, and a microstructure surrogate model. As can be observed, taking into account a more realistic structure in the electrode, the ASSB could only meet 32% of the mission requirements. However, optimisation of solid-state cathode structure significantly increases flight time in comparison to the reference electrode. In summary, we could show that future electrification of transportation powertrains will necessitate optimisation of the solid-state electrode structure and composition in order to meet the high demands for energy and power density. Also, our work highlights the urgent need to consider microstructure physical effects at an early stage of design for a realistic sizing of batteries. References Jain et.al., Proc. 4th Int. Conf. Electron. Commun. Aerosp. Technol. (2020) 1173–1178 Donateo et.al., Aerospace 7, no. 5 (2020): 56 Bielefeld et.al., The Journal of Physical Chemistry C 123, no. 3 (2018): 1626-1634 Laue et.al., Energy Technology, 8(2) (2020): 1801049 Toghyani, et.al., J. Electrochem. Soc (2022). Figure 1
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Akash, Arumugam, Vijayaraj Stephen Joseph Raj, Ramesh Sushmitha, Boga Prateek, Sankarasubramanian Aditya, and Veloorillom Madhavan Sreehari. "Design and Analysis of VTOL Operated Intercity Electrical Vehicle for Urban Air Mobility." Electronics 11, no. 1 (December 22, 2021): 20. http://dx.doi.org/10.3390/electronics11010020.
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This paper discusses the conceptual design of an intercity electrical vertical take-off-and-landing aircraft. A literature survey of existing eVTOL aircrafts, configuration selection, initial sizing, weight estimation, modelling and analysis was conducted. The present intercity eVTOL aircraft has the capability to carry four passengers along with one pilot for a distance of 500 km. Two specific aircraft modes, such as air-taxi and air-cargo mode, are considered in the present design. Market entry is predicted before 2031. Subsequently, innovative technologies are incorporated into the design. The present design features an aerodynamically shaped fuselage, tapered wing and a V-tail design. It can carry a nominal payload of 500 kg to a maximum range of 500 km at a cruise speed of Mach 0.168. The present eVTOL is comprised of a 5 m-long fuselage and an 11 m wingspan. It utilizes six tilt-rotor propeller engines. The maximum take-off weight and empty weight are 1755 kg and 1255 kg, respectively. The unit price is expected to be between USD 14.83 and 17.36 million. This aircraft has an aesthetically pleasing, intelligent and feasible design.
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Desantes, José M., Ricardo Novella, Luis M. García-Cuevas, and Marcos Lopez-Juarez. "Feasibility Study for a Fuel Cell-Powered Unmanned Aerial Vehicle with a 75 Kg Payload." Transactions on Aerospace Research 2022, no. 2 (June 1, 2022): 13–30. http://dx.doi.org/10.2478/tar-2022-0008.
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Abstract Among the possible electric powerplants currently driving low-payload UAVs (up to around 10 kg of payload), batteries offer certain clear benefits, but for medium-payload operation such as aerotaxis and heavy-cargo transportation UAVs, battery capacity requirements restrict their usage due to high weight and volume. In light of this situation, fuel cell (FC) systems (FCS) offer clear benefits over batteries for the medium-payload UAV segment (> 50 kg). Nevertheless, studies regarding the application of FCS powerplants to this UAV segment are limited and the in-flight performance has not been clearly analysed. In order to address this knowledge gap, a feasibility analysis of these particular applications powered by FCS is performed in this study. A validated FC stack model (40 kW of maximum power) was integrated into a balance of plant to conform an FCS. As a novelty, the management of the FCS was optimized to maximize the FCS efficiency at different altitudes up to 12500 ft, so that the operation always implies the lowest H2 consumption regardless of the altitude. In parallel, an UAV numerical model was developed based on the ATLANTE vehicle and characterized by calculating the aerodynamic coefficients through CFD simulations. Then, both models were integrated into a 0D-1D modelling platform together with an energy management strategy optimizer algorithm and a suitable propeller model. With the preliminary results obtained from the FCS and UAV models, it was possible to ascertain the range and endurance of the vehicle. As a result, it was concluded that the combination of both technologies could offer a range over 600 km and an endurance over 5 h. Finally, with the integrated UAV-FCS model, a flight profile describing a medium altitude, medium endurance mission was designed and used to analyse the viability of FC-powered UAV. The results showed how UAVs powered by FCS are viable for the considered aircraft segment, providing competitive values of specific range and endurance.
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Palmer, Joseph, and Essam Shehab. "Modelling of cryogenic cooling system design concepts for superconducting aircraft propulsion." IET Electrical Systems in Transportation 6, no. 3 (September 2016): 170–78. http://dx.doi.org/10.1049/iet-est.2015.0020.
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Alrashed, Mosab, Theoklis Nikolaidis, Pericles Pilidis, and Soheil Jafari. "Turboelectric Uncertainty Quantification and Error Estimation in Numerical Modelling." Applied Sciences 10, no. 5 (March 6, 2020): 1805. http://dx.doi.org/10.3390/app10051805.
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Turboelectric systems can be considered complex systems that may comprise errors and uncertainty. Uncertainty quantification and error estimation processes can, therefore, be useful in achieving accurate system parameters. Uncertainty quantification and error estimation processes, however, entail some stages that provide results that are more positive. Since accurate approximation and power optimisation are crucial processes, it is essential to focus on higher accuracy levels. Integrating computational models with reliable algorithms into the computation processes leads to a higher accuracy level. Some of the current models, like Monte Carlo and Latin hypercube sampling, are reliable. This paper focuses on uncertainty quantification and error estimation processes in turboelectric numerical modelling. The current study integrates the current evidence with scholarly sources to ensure the incorporation of the most reliable evidence into the conclusions. It is evident that studies on the current subject began a long time ago, and there is sufficient scholarly evidence for analysis. The case study used to obtain this evidence is NASA N3-X, with three aircraft conditions: rolling to take off, cruising and taking off. The results show that the electrical elements in turboelectric systems can have decent outcomes in statistical analysis. Moreover, the risk of having overload branches is up to 2% of the total aircraft operation lifecycle, and the enhancement of the turboelectric system through electrical power optimisation management could lead to higher performance.
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Todd, Rebecca, Virgilio Valdivia, Frank J. Bryan, Andrés Barrado, Antonio Lázaro, and Andrew J. Forsyth. "Behavioural modelling of a switched reluctance motor drive for aircraft power systems." IET Electrical Systems in Transportation 4, no. 4 (December 2014): 107–13. http://dx.doi.org/10.1049/iet-est.2014.0007.
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C., Kamali, and Shikha Jain. "Multiplicative Error State Kalman Filter vs Nonlinear Complimentary Filter for a High Performance Aircraft Attitude Estimation." Defence Science Journal 66, no. 6 (October 31, 2016): 630. http://dx.doi.org/10.14429/dsj.66.8838.
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<p>Modern control law designs increasingly use aircraft attitude information to improve aircraft manoeuverability. Attitude information allows for gravity term compensations in the longitudinal as well as lateral directional control laws of a typical fighter aircraft. Methodologies and comparisons of multiplicative error state Kalman filter (MEKF) and nonlinear complimentary filter for estimation of attitudes of a high performance aircraft using its onboard autonomous sensors is presented. Shows a problem in pitch angle estimation beyond ± 80 deg in the MEKF and a solution is proposed for the same for the first time. Also presents novel aiding sensor modelling for the implementation of attitude heading reference system for this class of aircraft for the first time. The filter formulations are evaluated using full range manuoevering real flight test data.</p>
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Tomasz Lusiak, Andrej Novak, Martin Bugaj, and Radovan Madlenak. "Assessment of Impact of Aerodynamic Loads on the Stability and Control of the Gyrocopter Model." Communications - Scientific letters of the University of Zilina 22, no. 4 (October 1, 2020): 63–69. http://dx.doi.org/10.26552/com.c.2020.4.63-69.
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Aerodynamic modelling currently relates to development of mathematical models to describe the aerodynamic forces and moments acting on the aircraft. It is a challenging part of aerodynamics that defines a comprehensive approach to using traditional methods and modern techniques to obtain relevant data. The most complicated task for the aerodynamics and flight dynamics is definition, computation and quantification of the aerodynamic description of an object. This paper presents how to determine the aerodynamic load on a gyrocopter and defines the effect on its stability and control. The first step to solution is to develop simpler approximate aerodynamic model - a model that can be used in analysis of aerodynamic load and can represent the aerodynamic properties of the gyrocopter with an acceptable degree of accuracy. Control and stability are very important parts of aircraft characteristics and therefore those characteristics were analyzed in simulation. Finally, the aerodynamic data outputs are assessed in terms of impact of aerodynamic loads on stability and control of the gyrocopter model.
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Nowakowski, Mirosław. "Measuring and Recording Systems Used in Flight Tests of Aircraft." Solid State Phenomena 180 (November 2011): 222–31. http://dx.doi.org/10.4028/www.scientific.net/ssp.180.222.
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Flight tests and measurements are usually performed for newly built or modernised aircraft utilised by the Polish Armed Forces. In the course of flight tests the airborne equipment is also investigated. The main goal of the performed tests is to verify tactical performance and to identify technical parameters of aircraft and/or equipment under examination. The airborne experimental data is also applied to the aircraft flight dynamics modelling, subsequently used for the design and construction of a flight simulator. The equipment is usually arranged of the following components: ̶ sensors/measuring devices capable of converting physical parameters into optical, mechanical, or electrical signals (indicators, transmitters, sensors, transducers); ̶ conditioning systems - intermediary devices used to amplify and/or adjust any signal gained to some required value or form; ̶ recording and storing devices (data recorders, cameras, etc.); ̶ devices applied to the decoding and processing of the acquired data (decoders, computers). Some selected problems of aircraft flight tests will be discussed in the paper. A brief description of the applied experimental apparatus will be provided first. Next, the attention will be focused on the experimentally gathered data utilised in the identification of aircraft flight dynamics characteristics and on the data applied to the evaluation of selected design parameters.
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Panigrahi, Siddhant, Yenugu Siva Sai Krishna, and Asokan Thondiyath. "Design, Analysis, and Testing of a Hybrid VTOL Tilt-Rotor UAV for Increased Endurance." Sensors 21, no. 18 (September 7, 2021): 5987. http://dx.doi.org/10.3390/s21185987.
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Unmanned Aerial Vehicles (UAVs) have slowly but steadily emerged as a research and commercial hotspot because of their widespread applications. Due to their agility, compact size, and ability to integrate multiple sensors, they are mostly sought for applications that require supplementing human effort in risky and monotonous missions. Despite all of these advantages, rotorcrafts, in general, are limited by their endurance and power-intensive flight requirements, which consequently affect the time of flight and operational range. On the other hand, fixed-wing aircrafts have an extended range, as the entire thrust force is along the direction of motion and are inherently more stable but are limited by their takeoff and landing strip requirements. One of the potential solutions to increase the endurance of VTOL rotorcrafts (Vertical Take-Off and Landing Vehicles) was to exploit the thrust vectoring ability of the individual actuators in multi-rotors, which would enable take-off and hovering as a VTOL vehicle and flight as a fixed-wing aircraft. The primary aim of this paper is to lay out the overall design process of a Hybrid VTOL tilt-rotor UAV from the initial conceptual sketch to the final fabricated prototype. The novelty of the design lies in achieving thrust vectoring capabilities in a fixed-wing platform with minimum actuation and no additional control complexity. This paper presents novel bi-copter that has been designed to perform as a hybrid configuration in both VTOL and fixed wing conditions with minimum actuators in comparison to existing designs. The unified dynamic modelling along with the approximation of multiple aerodynamic coefficients by numerical simulations is also presented. The overall conceptual design, dynamic modeling, computational simulation, and experimental analysis of the novel hybrid fixed-wing bi-copter with thrust vectoring capabilities aiming to substantially increase the flight range and endurance compared to the conventional aircraft rotorcraft configurations are presented.
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Botez, R. M., M. J. Tchatchueng Kammegne, and L. T. Grigorie. "Design, numerical simulation and experimental testing of a controlled electrical actuation system in a real aircraft morphing wing model." Aeronautical Journal 119, no. 1219 (September 2015): 1047–72. http://dx.doi.org/10.1017/s0001924000011131.
Full textAbstract:
AbstractThe paper focuses on the modelling, simulation and control of an electrical miniature actuator integrated in the actuation mechanism of a new morphing wing application. The morphed wing is a portion of an existing regional aircraft wing, its interior consisting of spars, stringers, and ribs, and having a structural rigidity similar to the rigidity of a real aircraft. The upper surface of the wing is a flexible skin, made of composite materials, and optimised in order to fulfill the morphing wing project requirements. In addition, a controllable rigid aileron is attached on the wing. The established architecture of the actuation mechanism uses four similar miniature actuators fixed inside the wing and actuating directly the flexible upper surface of the wing. The actuator was designed in-house, as there is no actuator on the market that could fit directly inside our morphing wing model. It consists of a brushless direct current (BLDC) motor with a gearbox and a screw for pushing and pulling the flexible upper surface of the wing. The electrical motor and the screw are coupled through a gearing system. Before proceeding with the modelling, the actuator is tested experimentally (stand alone configuration) to ensure that the entire range of the requirements (rated or nominal torque, nominal current, nominal speed, static force, size) would be fulfilled. In order to validate the theoretical, simulation and standalone configuration experimental studies, a bench testing and a wind-tunnel testing of four similar actuators integrated on the real morphing wing model are performed.
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Bilal, Ahmad, Syed Muhammad Hamza, Ziauddin Taj, and Shuaib Salamat. "Multi‐frequency analysis of Gaussian process modelling for aperiodic RCS responses of a parameterised aircraft model." IET Radar, Sonar & Navigation 14, no. 7 (July 2020): 1061–67. http://dx.doi.org/10.1049/iet-rsn.2019.0421.
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