Relevant bibliographies by topics / Modelling electric aircraft

Academic literature on the topic 'Modelling electric aircraft'

Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 2023

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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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Dissertations / Theses on the topic "Modelling electric aircraft"

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Groch, Matthew. "HV Transmission line and tower inspection safe-fly zone modelling and metrology." Thesis, Stellenbosch : Stellenbosch University, 2013. http://hdl.handle.net/10019.1/85795.

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Thesis (MEng)-- Stellenbosch University, 2013.
ENGLISH ABSTRACT: The deployment of Unmanned Aerial Vehicles (UAV) for power line inspection requires the definition of safe-fly zones. Transient Over-Voltages (TOVs) on the Overhead Transmission Lines (OHTLs) put the UAV at risk if it encroaches on these zones. In order to determine the safe-fly zones of a UAV in the vicinity of OHTLs, realistic full-scale experimental tests are done. Non-linearity in breakdown effects renders small-scale testing and computational work inaccurate. Experimental work is used to describe the close-up approach distances for worst-case scenarios. Testing cannot provide a full solution due to the limitation of the equipment available. Further tests must therefore be done at a specialised facility. Experiments are run in two phases, namely non-linear and linear tests in the High Voltage (HV) laboratory. The non-linear tests are done to derive Minimum Approach Distances (MAD). The linear experiments are used to calibrate FEKO, the simulation tool, to the measurement environment. Once correlation between the linear test data and the simulated data is found, confidence is derived in both the simulation model and the test setup. The simulations can then be used to determine a geometric factor as an input into F. Rizk’s prediction equations. The Rizk equations are used to describe the safe-fly zones alongside OHTLs as an addition to the non-linear experimental work. Along with the standard’s suggestions, the Rizk predictions are formulated in such a way that line-specific solutions can be determined. The suggested clearance values are provided in terms of per unit values, which can be selected in accordance with historical line data. Power line sparking is investigated to better understand the line radiation phenomenon. This understanding could assist in the line inspection process, as well as in the layout of power lines near radio quiet areas. Knowledge of OHTL radiation patterns can aid in the location of corona and sparking sources in the inspection process. Aerial sparking measurements are taken using a UAV carrying a spectrum analyser. Measured sparking levels are used to verify a Computational Electromagnetic (CEM) model. The CEM model can then be used to further investigate OHTL radiation characteristics.
AFRIKAANSE OPSOMMING: Die aanwending van Onbemande Vliegtuie (UAVs) vir kraglyn inspeksies, vereis die definiëring van veilige vlieg sones. Oorspannings (TOVs) op oorhoofse kraglyne (OHTLs) kan hierdie vliegtuie in gevaar stel as hulle die grense van hierdie sones oorskry. Om die veilige vlieg sones van 'n UAV in die omgewing van OHTLs te bepaal, is realistiese volskaalse toetse gedoen. Die nie-lineariteit in afbreek effekte lewer onakkurate kleinskaal toetse en rekenaar werk. Eksperimentele werk word gebruik om die benaderde afstande vir die ergste geval te beskryf. Hierdie werk kan nie 'n volledige oplossing gee nie as gevolg van ‘n beperking op huidige toerusting. Dit beteken dat verdere toetse, by ‘n meer gespesialiseerde fasiliteit, gedoen moet word. Eksperimente is uitgevoer in twee fases: nie-lineêre en lineêre toetse in die Hoogspannings (HV) laboratorium. Die nie-lineêre toetse word gedoen om die kleinste-benaderde-afstand (MAD) af te lei en die lineêre eksperimente word gebruik om FEKO (‘n numeriese elektromagnetika simulasie program) met die metings omgewing te kalibreer. Sodra daar ‘n korrelasie tussen die lineêre data en die gesimuleerde data is, kan daar aangeneem word dat die simulasie model en die toets-opstelling betroubaar is. Die simulasies kan dan gebruik word om 'n meetkundige faktor te bepaal as 'n bydrae tot F. Rizk se voorspellings vergelykings. Die Rizk vergelykings word gebruik om die veilige vlieg sones langs die OHTLs te beskryf. Dit kan dus gebruik word as ‘n toevoeging tot die nie-lineêre eksperimentele werk. Saam met die normale meet standaard voorstellings, is die Rizk voorspellings geformuleer sodat dit die lyn spesifieke oplossings kan bepaal. Die voorgestelde verklarings waardes word in per eenheid waardes beskryf, wat dan gekies kan word met ooreenstemmende historiese lyn data. Kraglyn-vonke word ondersoek om die lyn-bestraling verskynsel beter te verstaan. Hierdie begrip kan in die lyn inspeksie proses en in die uitleg van kraglyne naby radiostilte-areas help. Kennis van OHTL bestralings patrone kan help met die identifisering van corona en vonk-bronne tydens die inspeksie proses. 'n UAV met 'n aangehegte spektrum analiseerder is gebruik om die lug-vonkende metings te neem. Vonk vlakke wat gemeet is word dan gebruik om 'n Numeriese Elektromagnetiese (CEM) model te bevestig. Die CEM model kan dan gebruik word om OHTL bestralings eienskappe verder te ondersoek.
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Khanna, Yash. "Conceptual design and development of thermal management system for hybrid electric aircraft engine. : A study to develop a physical model and investigate the use of Mobil Jet Oil II as coolant for aircraft electrical propulsion under different scenarios and time horizons." Thesis, Mälardalens högskola, Framtidens energi, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:mdh:diva-46612.

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The ever-increasing levels of greenhouse gas emissions has led to the scientific community starting to explore the viability of electrical aircraft system, with the most prominent research and product development for hybrid electric system, which forms the transition phase from combustion to fully electric aircrafts. The primary objective of this thesis is to find solutions towards thermal management of the electrical components of a hybrid electric aircraft propulsion system, which generate a significant amount of heat while operating at heavy load conditions required to propel an aircraft. In view of these objectives a micro channel cold plate liquid cooling system, has been dynamically modelled using a combination of lumped parameter and thermal resistance methods of heat transfer analysis. The study investigates the prospects of using Mobil Jet Oil II, typically used as an aircraft lubricant as a coolant for the thermal management system. The primary components of this model are lithium ion battery, DC-AC inverter, permanent magnet motor, cross flow finned micro channel heat exchanger, centrifugal pump and ducts. The electrical components have been dimensioned according to energy storage and load requirements considering their efficiencies and gravimetric power/energy. The system has been simulated and analyzed under different scenarios considering the coolant inlet temperature, air temperature across the heat exchanger and on two-time horizons. Analysis has been done to study the dynamic trends of the component temperature and the coolant at different stages of the system. The scope of the study includes an evaluation of the added weight of the thermal management system under different time horizons and their comparison with results from a reference study. From the simulation results it can be concluded that Mobil Jet Oil II is a promising option as a coolant and therefore its use as a common fluid for gas turbine lubrication and as coolant, will benefit the aircraft as now no extra coolant reservoir is required, allowing reduction in weight carried by the aircraft.
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Glassock, Richard R. "Design, modelling and measurement of hybrid powerplant for unmanned aerial vehicles (UAVs)." Thesis, Queensland University of Technology, 2012. https://eprints.qut.edu.au/61052/1/Richard_Glassock_Thesis.pdf.

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The success or effectiveness for any aircraft design is a function of many trade-offs. Over the last 100 years of aircraft design these trade-offs have been optimized and dominant aircraft design philosophies have emerged. Pilotless aircraft (or uninhabited airborne systems, UAS) present new challenges in the optimization of their configuration. Recent developments in battery and motor technology have seen an upsurge in the utility and performance of electric powered aircraft. Thus, the opportunity to explore hybrid-electric aircraft powerplant configurations is compelling. This thesis considers the design of such a configuration from an overall propulsive, and energy efficiency perspective. A prototype system was constructed using a representative small UAS internal combustion engine (10cc methanol two-stroke) and a 600W brushless Direct current (BLDC) motor. These components were chosen to be representative of those that would be found on typical small UAS. The system was tested on a dynamometer in a wind-tunnel and the results show an improvement in overall propulsive efficiency of 17% when compared to a non-hybrid powerplant. In this case, the improvement results from the utilization of a larger propeller that the hybrid solution allows, which shows that general efficiency improvements are possible using hybrid configurations for aircraft propulsion. Additionally this approach provides new improvements in operational and mission flexibility (such as the provision of self-starting) which are outlined in the thesis. Specifically, the opportunity to use the windmilling propeller for energy regeneration was explored. It was found (in the prototype configuration) that significant power (60W) is recoverable in a steep dive, and although the efficiency of regeneration is low, the capability can allow several options for improved mission viability. The thesis concludes with the general statement that a hybrid powerplant improves the overall mission effectiveness and propulsive efficiency of small UAS.
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Wu, Tao. "Integrative system modelling of aircraft electrical power systems." Thesis, University of Nottingham, 2010. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.537690.

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Zoccatelli, Michele, and Edoardo Nascimbeni. "Transformation of the Aviation industry : Exploring alternative renewal fuel pathways." Thesis, KTH, Skolan för industriell teknik och management (ITM), 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-301640.

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This master thesis will be part of a larger project called Sustainable Energy Transition in Aviation (SETA), which will be done in collaboration with the Division of Sustainability, Industrial Dynamics and Entrepreneurship (SIDE) at INDEK. The overall thesis aims to contribute to accelerate the energy transition within the aviation sector, with a focus on three technologies: bio-based jet fuels, hydrogen fuels and electrical aircraft. Moving on, this research project is being pursued because aviation is one of the most important CO2 emitters in Sweden. Indeed it accounts for 5% of total Swedish emissions (Klimatpolitiska Rådet, 2020). Due to its complexity as a socio technical system and its tight interrelations between its components, aviation is struggling to change. Therefore, a transformative pressure is raising in order to meet 2030 and 2045 targets. The aim of the research is to highlight how the introduction of alternative fuels and technologies might help aviation to reach carbon neutrality. Moreover, the aviation industry could be classified as a socio-technical system, thereby a conceptual framework was used to better analyze its transition. The Multi-Level Perspective framework (MLP) was thus applied with the intent of describing how the sustainable energy transformation will happen at the different levels. Through interviews it was possible to underline the different challenges within the aviation system, while also highlighting future scenarios of the air transport sector. Furthermore, by developing a modelling analysis through the LEAP software, it was possible to hypothesized several scenarios where biofuels, hydrogen and electric airplanes growth varies under specific assumptions. Finally, the analysis highlighted that the introduction of these alternative technologies will be crucial to support aviation in its green transformation. Indeed, between year 2015 and 2045, the total emissions from the analyzed transport sector were reduced by 90%. Therefore, aviation will essentially need these new technologies in order to transform and become greener.
Detta examensarbete kommer att ingå i ett större projekt som heter Sustainable Energy Transition in Aviation (SETA), vilket kommer att göras i samarbete med avdelningen för hållbarhet, industriell dynamik och entreprenörskap (SIDE) vid INDEK. Den övergripande avhandlingen syftar till att bidra till att påskynda energiövergången inom flygsektorn, med fokus på tre tekniker: biobaserade jetbränslen, vätgasbränslen och elektriska flygplan. Detta forskningsprojekt pågår eftersom luftfarten skapar stora mängder koldioxidutsläpp i Sverige. Det står för 5% av de totala svenska utsläppen (Klimatpolitiska Rådet, 2020). På grund av dess komplexitet som ett sociotekniskt system och dess snäva samband mellan komponenter, kämpar luftfarten för att förändras. Därför ökar ett transformerande tryck för att nå 2030 och 2045 mål. Syftet med forskningen är att belysa hur införandet av alternativa bränslen och tekniker kan hjälpa luftfarten att nå koldioxidneutralitet. Dessutom kan flygindustrin klassificeras som ett socio-tekniskt system, varigenom en konceptuell ram användes för att bättre analysera dess övergång. Multi-Level Perspective Framework (MLP) tillämpades således med avsikten att beskriva hur den hållbara energiomvandlingen kommer att ske på de olika nivåerna. Genom intervjuer var det möjligt att ta fram de olika utmaningarna inom flygsystemet, samtidigt som man framhävde framtida scenarier inom lufttransportsektorn. Genom att utveckla en modelleringsanalys genom LEAPprogramvaran var det dessutom möjligt att hypotisera flera scenarier där biodrivmedel, väte och elektriska flygplanstillväxt varierar under specifika antaganden. Slutligen visade analysen att införandet av dessa alternativa tekniker kommer att vara avgörande för att stödja luftfarten i dess gröna omvandling. Mellan 2015 och 2045 minskade de totala utsläppen från den analyserade transportsektorn med 90%. Därför kommer luftfarten i huvudsak att behöva dessa nya tekniker för att förändras och bli grönare.
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Yang, Tao. "Development of dynamic phasors for the modelling of aircraft electrical power systems." Thesis, University of Nottingham, 2013. http://eprints.nottingham.ac.uk/13548/.

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As the More-Electric Aircraft (MEA) has been identified as a major trend of future aircraft, the on-board Electrical Power System (EPS) will see significant increased numbers of Power Electronic Converters (PECs) and motor drive systems. In order to study the behaviour and performance of the EPS in MEA, extensive simulation studies need to be done during the system design process. This in return, gives the need to have computationally efficient and accurate models to reduce the design period. In this thesis, the Dynamic Phasor (DP) is used for modelling EPS in the MEA. The DP technique is a general averaging method and naturally a frequency-domain analysis tool. Compared with other averaging models, which is only efficient under balanced conditions, the DP model maintains efficiency under both balanced and unbalanced conditions. The DP technique has been widely used in modelling the constant, single frequency EPS. In this thesis, the DP technique is extended to modelling time-varying frequency EPS. The application of DP in modelling a multi-generator, multi-frequency system is for the first time, developed in this thesis. The developed theory allows a wider application of the DPs. The developed DP model covers key elements in MEA electrical power systems, including the synchronous generator, control, transmission lines, uncontrolled rectifiers, PWM converters and 18-pulse autotransformer rectifier units. The DP model library developed based on this thesis allows the flexibility to study various EPS’s by integrating elements from the library. A twin-generator aircraft EPS, which is based on the More Open Electrical Technology (MOET) large aircraft EPS architecture, is used to demonstrate the application of DP models. Comparing the DP model with the ABC model (models in three-phase coordinates) and the DQ0 model (models in a synchronous dq frame), the efficiency and the accuracy of the DP model are demonstrated under both balanced and unbalanced conditions.
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Handy, Peter James. "The characterisation, modelling and detection of series arc faults in aircraft electrical power distribution systems featuring solid state power controllers (SSPCs)." Thesis, University of Warwick, 2016. http://wrap.warwick.ac.uk/80134/.

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Electrical power demand in aircraft has grown significantly over the last century, and this trend continues with the More Electric Aircraft (MEA) and All Electric Aircraft (AEA) concepts. Higher voltages such as 270VDC are required to deliver additional power to loads and to optimise aircraft mass. Increased voltages inflict more stress on the Electrical Wiring Interconnect System (EWIS) and increase the impact of series arc faults caused by wiring defects. Solid State Power Controllers (SSPCs) are used to provide fast protection in high voltage distribution systems. The aim of this work is the characterisation, modelling, simulation and detection of series arc faults in 28VDC and 270VDC electrical power distribution systems featuring SSPCs. The majority of passive detection schemes in the literature were designed based on empirical data rather than well characterised electric arc parameters, and thus nuisance trips are unavoidable. To address this series arc faults in 28VDC and 270VDC solid state power distribution systems were characterised using the SAE5692 "Loose terminal" method [8], and it was found that 270VDC arc faults cause a minimal ~5.6% reduction in loop current and load voltage compared with ~54% in 28VDC systems. SSPC output voltage transients caused by series arcs were found to be limited by the presence of SSPC snubbers. Increasing the system loop inductance was found to improve series arc stability resulting in fewer arc quench events. Increasing the capacitive load reduces arc stability and causes arcs to quench more readily thus simplifying detection. These results were later used to experimentally validate a novel series arc fault SPICE model based on the static Nottingham V-I model [9] and wider solid state electrical system model. The arc current and SSPC output voltage results were also used to create a prototype passive series arc fault detection system, which has been demonstrated to SAE5692 under laboratory conditions [8]. A novel multilayer PCB current sensor was developed and experimentally validated for this prototype. To further reduce nuisance trips an innovative active arc fault perturbation scheme was simulated and experimentally demonstrated using SSPC modulation to stimulate and detect arc quench. Another novel complementary series arc fault prevention / confirmation scheme was simulated and experimentally validated using SSPC leakage currents. To minimise nuisance trips due to manufacturing and installation errors a unique Built-In Test (BIT) scheme was also developed and experimentally validated using the SSPC to create artificial current and voltage stimuli.
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Giraud, Xavier. "Méthodes et outils pour la conception optimale des réseaux de distribution d'électricité dans les aéronefs." Phd thesis, Institut National Polytechnique de Toulouse - INPT, 2014. http://tel.archives-ouvertes.fr/tel-00955887.

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Dans le domaine aéronautique, la dernière décennie a été marquée par une augmentation constante et progressive du taux d'électrification des systèmes embarqués. L'avion plus électrique est aujourd'hui vu comme un axe d'amélioration majeure pour l'industrie aéronautique permettant d'atteindre des objectifs toujours plus ambitieux : réduction de l'impact environnemental, rationalisation des coûts de maintenance... Dans ce contexte, le réseau de distribution électrique joue un rôle majeur. Les architectes doivent imaginer de nouveaux concepts architecturaux afin d'assurer le " service " de fourniture d'électricité tout en minimisant la masse et le coût. Ainsi les travaux de cette thèse proposent des méthodes d'aide à la conception pour les architectes de réseau. Le manuscrit se divise en 2 parties pouvant être vues comme 2 études distinctes et qui sont introduites dans le chapitre 1. La 1ère partie, traitée dans les chapitres 2 et 3, développe des méthodes et outils afin de résoudre de manière automatique et optimale 2 tâches de l'architecte : la définition des reconfigurations du réseau et l'identification de l'allocation des charges. La formalisation de ces 2 problématiques met en lumière une caractéristique commune : l'explosion combinatoire. Ainsi les résolutions sont réalisées à l'aide de méthodes issues de la recherche opérationnelle. Un processus général est défini afin de traiter les 2 tâches de manière consistante. Les aspects liés à la reconfiguration sont traités à l'aide de : la théorie des graphes pour modéliser la connectivité du réseau, un système expert capturant les règles métiers et la programmation linéaire sélectionnant les reconfigurations les plus performantes. La méthode a été appliquée avec succès sur des réseaux avions existants (A400M et A350) ainsi que sur des réseaux plus électriques prospectifs. La deuxième tâche consistant en l'allocation des charges a été résolue à l'aide de méthodes stochastiques. L'algorithme génétique utilisant une méthode de nichage se révèle être le plus performant en proposant à l'architecte réseau des solutions performantes et variées. La 2ème partie, traitée dans le chapitre 4, s'intéresse à un nouveau concept le " cœur électronique modulaire et mutualisé ". Cet organe de distribution, étroitement lié à l'avion plus électrique, se caractérise par la mutualisation de " m " modules électronique de puissance pour " c " charges électriques. Les méthodes développées dans le chapitre 4 vise à concevoir de manière optimale ce nouveau cœur en ayant 2 degrés de liberté : le nombre " m " de modules et les reconfigurations entre les " m " modules et les " c " charges. De nouveau, la formalisation du problème met en évidence l'explosion combinatoire à laquelle est confronté le concepteur. Le principal objectif de cette étude est de proposer un cadre méthodologique pour la résolution de ce problème de conception. Ainsi une heuristique a été développée pour résoudre ce problème combinatoire. Une attention particulière a été portée pour développer des modèles de composants simples et génériques dans une procédure générale organisée. Enfin une cartographie a été réalisée afin de dégager d'une part les formes de solutions les plus performantes et d'identifier les éléments ayant les impacts les plus significatifs sur la masse du système complet.
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Book chapters on the topic "Modelling electric aircraft"

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Yazar, Isil, Ranjan Vepa, and Fikret Caliskan. "Current State of the Art of Modelling and Simulation of Propulsion Systems for Hybrid-Electric Aircraft." In Progress in Sustainable Aviation, 37–64. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-031-12296-5_3.

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Conference papers on the topic "Modelling electric aircraft"

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Kascak, Peter, Timothy Dever, and Ralph Jansen. "Electric Aircraft Propulsion Power System Impedance Modelling Methodology." In AIAA Propulsion and Energy 2021 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-3307.

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Dever, Timothy P., Peter E. Kascak, and Ralph H. Jansen. "Megawatt Electric Aircraft Propulsion Power System Impedance Modelling." In 2022 IEEE/AIAA Transportation Electrification Conference and Electric Aircraft Technologies Symposium (ITEC+EATS). IEEE, 2022. http://dx.doi.org/10.1109/itec53557.2022.9814046.

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Marshall, J. "Reliability enhancement methodology and modelling for electronic equipment - the REMM project." In IEE Colloquium. Electrical Machines and Systems for the More Electric Aircraft. IEE, 1999. http://dx.doi.org/10.1049/ic:19990841.

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Lukic, Milos, Paolo Giangrande, Christian Klumpner, and Michael Galea. "Modelling and Analysis of an Aircraft On-board Electric Taxiing System." In 2019 22nd International Conference on Electrical Machines and Systems (ICEMS). IEEE, 2019. http://dx.doi.org/10.1109/icems.2019.8921709.

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Cross, A. M., A. J. Forsyth, and G. Mason. "Modelling and Simulation Strategies for the Electric Systems of Large Passenger Aircraft." In Power Systems Conference. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2002. http://dx.doi.org/10.4271/2002-01-3255.

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Porru, Mario, Alessandro Serpi, Andrea Floris, and Alfonso Damiano. "Modelling and real-time simulations of electric propulsion systems." In 2016 International Conference on Electrical Systems for Aircraft, Railway, Ship Propulsion and Road Vehicles & International Transportation Electrification Conference (ESARS-ITEC). IEEE, 2016. http://dx.doi.org/10.1109/esars-itec.2016.7841438.

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Hammadi, Moncef, Jean-Yves Choley, Olivia Penas, and Alain Riviere. "Multidisciplinary approach for modelling and optimization of Road Electric Vehicles in conceptual design level." In 2012 Electrical Systems for Aircraft, Railway and Ship Propulsion (ESARS). IEEE, 2012. http://dx.doi.org/10.1109/esars.2012.6387488.

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Gomez, Pere Izquierdo, Alberto Barragan Moreno, Jun Lin, and Tomislav Dragicevic. "Data-Driven Thermal Modelling for Anomaly Detection in Electric Vehicle Charging Stations." In 2022 IEEE/AIAA Transportation Electrification Conference and Electric Aircraft Technologies Symposium (ITEC+EATS). IEEE, 2022. http://dx.doi.org/10.1109/itec53557.2022.9813767.

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Yang, T., S. V. Bozhko, and G. M. Asher. "Fast functional modelling for 18-pulse autotransformer rectifier units in more- electric aircraft." In 6th IET International Conference on Power Electronics, Machines and Drives (PEMD 2012). IET, 2012. http://dx.doi.org/10.1049/cp.2012.0205.

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Jones, Catherine E., Kieran Millar, Kenny Fong, Rafael Pena Alzola, Patrick Norman, and Graeme Burt. "A Modelling Design Framework for Integrated Electrical Power and Non-Electrical Systems Design on Electrical Propulsion Aircraft." In 2022 IEEE/AIAA Transportation Electrification Conference and Electric Aircraft Technologies Symposium (ITEC+EATS). IEEE, 2022. http://dx.doi.org/10.1109/itec53557.2022.9813810.

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