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Статті в журналах з теми "Parallel Hybrid-Electric Propulsion System"
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Lents, Charles E. "Hybrid Electric Propulsion." Mechanical Engineering 142, no. 06 (June 1, 2020): 54–55. http://dx.doi.org/10.1115/1.2020-jun5.
Повний текст джерелаАнотація:
Abstract Electrified propulsion holds the promise of reducing aviation’s CO2 emissions footprint through three means: access to green grid electric energy, improvements in aircraft performance through new airframe and propulsion system architectures and enabling further optimization of the gas turbine cycle. Charging an aircraft battery pack with green electric energy and using this energy to drive electric propulsors results in a zero emissions vehicle. This is practical for light aircraft and short missions. Boosting a Jet-A burning gas turbine with green electric energy (again stored in a ground charged battery), in either a parallel or series turbo-electric architecture can yield a net reduction in CO2 emissions, as long as the fuel burn required to carry the weight of a discharged battery pack does not overcome the reduction in fuel burn afforded by the ground charged battery. Several studies have indicated that a net savings is possible with cell level energy densities approach ∼ 500 whr/kg, a reasonable target for the 2030 time frame. Electrified propulsion can also enable unique aircraft configurations, employing a veryhigh efficiency prime mover (gas turbine) designed for running only a generator at peak efficiency, and/or distributing the propulsors throughout the aircraft, for improvement in L/D and propulsive efficiency.
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Leśniewski, Wojciech, Daniel Piątek, Konrad Marszałkowski, and Wojciech Litwin. "Small Vessel with Inboard Engine Retrofitting Concepts; Real Boat Tests, Laboratory Hybrid Drive Tests and Theoretical Studies." Energies 13, no. 10 (May 20, 2020): 2586. http://dx.doi.org/10.3390/en13102586.
Повний текст джерелаАнотація:
The development of modern technologies and their increasing availability, as well as the falling costs of highly efficient propulsion systems and power sources, have resulted in electric or hybrid propulsions systems’ growing popularity for use on watercraft. Presented in the paper are design and lab tests of a prototype parallel hybrid propulsion system. It describes a concept of retrofitting a conventionally powered nine meter-long vessel with the system, and includes results of power and efficiency measurements, as well as calculations of the vessel’s operating range under the propulsion of its electric motor. The concept of adding of a solar panels array was studied.
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Rizzo, Gianfranco, Shayesteh Naghinajad, Francesco Tiano, and Matteo Marino. "A Survey on Through-the-Road Hybrid Electric Vehicles." Electronics 9, no. 5 (May 25, 2020): 879. http://dx.doi.org/10.3390/electronics9050879.
Повний текст джерелаАнотація:
Hybrid Electric Vehicles (HEVs) can be divided into three categories according to how the two propulsion systems (the thermal and the electric ones) supply the driving torque to the vehicle. When the torque is supplied only by an electric propulsion system, while the heat engine takes care of generating the electricity needed to operate the system, it is called a hybrid-series. Conversely, when both propulsion systems provide torque, the vehicle is identified with parallel hybrid wording. Among the parallel hybrids there is a particular configuration called Through-the-Road (TTR). In this configuration, the two propulsion systems are not mechanically connected to each other, but it is precisely the road that allows hybrid propulsion. This architecture, dating back to the early twentieth century, is still used by several manufacturers and carries with it peculiar configurations and control methods. It is also a configuration that fits well with the transformation of conventional vehicles into a hybrid. The paper presents a survey of the TTR HEV solution, evidencing applications, potentialities and limits.
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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.
Повний текст джерелаАнотація:
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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Litwin, Wojciech, Wojciech Leśniewski, and Jakub Kowalski. "Energy Efficient and Environmentally Friendly Hybrid Conversion of Inland Passenger Vessel." Polish Maritime Research 24, no. 4 (December 20, 2017): 77–84. http://dx.doi.org/10.1515/pomr-2017-0138.
Повний текст джерелаАнотація:
Abstract The development and growing availability of modern technologies, along with more and more severe environment protection standards which frequently take a form of legal regulations, are the reason why attempts are made to find a quiet and economical propulsion system not only for newly built watercraft units, but also for modernised ones. Correct selection of the propulsion and supply system for a given vessel affects significantly not only the energy efficiency of the propulsions system but also the environment - as this selection is crucial for the noise and exhaust emission levels. The paper presents results of experimental examination of ship power demand performed on a historic passenger ship of 25 m in length. Two variants, referred to as serial and parallel hybrid propulsion systems, were examined with respect to the maximum length of the single-day route covered by the ship. The recorded power demands and environmental impact were compared with those characteristic for the already installed conventional propulsion system. Taking into account a high safety level expected to be ensured on a passenger ship, the serial hybrid system was based on two electric motors working in parallel and supplied from two separate sets of batteries. This solution ensures higher reliability, along with relatively high energy efficiency. The results of the performed examination have revealed that the serial propulsion system is the least harmful to the environment, but its investment cost is the highest. In this context, the optimum solution for the ship owner seems to be a parallel hybrid system of diesel-electric type
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Litwin, Wojciech, Daniel Piątek, Wojciech Leśniewski, and Konrad Marszałkowski. "50’ Sail Catamaran with Hybrid Propulsion, Design, Theoretical and Experimental Studies." Polish Maritime Research 29, no. 2 (June 1, 2022): 12–18. http://dx.doi.org/10.2478/pomr-2022-0012.
Повний текст джерелаАнотація:
Abstract The development of modern lithium batteries and propulsion systems now allows the use of complex propulsion systems for vessels of various sizes. As part of the research and implementation project, a parallel hybrid drive system was designed, built and then tested in the laboratory. The experimental studies conducted allowed for the measurements of power, fuel consumption and electric power distribution in various operating modes of the propulsion system. The research proves that in the analysed case, the hybrid parallel system meets the demand for electric energy during a typical cruise scenario, and thus there is no need to install a power generator on the yacht.
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Figueiras, Iara, Maria Coutinho, Frederico Afonso, and Afzal Suleman. "On the Study of Thermal-Propulsive Systems for Regional Aircraft." Aerospace 10, no. 2 (January 24, 2023): 113. http://dx.doi.org/10.3390/aerospace10020113.
Повний текст джерелаАнотація:
Life without mobility is inconceivable. To enable this connectivity, one must find a way to progress towards a more sustainable transportation. In the aviation industry, a comprehensive understanding of greening technologies such as electrification of the propulsion system for commercial aircraft is required. A hybrid-electric propulsion concept applied to a regional aircraft is studied in the context of the FutPrInt50 project. To this end, the hybrid-electric propulsive system components are modeled, validated, and evaluated using computational and experimental data presented in the literature. The components are then assembled to construct the three powertrains for the hybrid-electric propulsion systems (Series, Parallel and Turboelectric) and parametric studies are carried out to study the influence of various battery parameters and hybridization factor. The performance results for a simple mission profile are generated. Together with a thermal management system, multi-objective optimization studies for the different architectures are then performed, with the power hybridization factor as the design variable and minimization of total mass and emissions as objective functions.
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Kost, Gabriel, and Andrzej Nierychlok. "Virtual Driver of Hybrid Wheeled Vehicle." Solid State Phenomena 180 (November 2011): 39–45. http://dx.doi.org/10.4028/www.scientific.net/ssp.180.39.
Повний текст джерелаАнотація:
This paper presents the application of wheeled vehicle based on a hybrid propulsion system. Describes control system structure and communication between different units of propulsion, intermediary devices and the fundamental issues of building such a network. Virtual propulsion of a wheeled vehicle hybrid drive designed for parallel connection structure of the drive units. This enabled the propulsion work more efficiently through the synergy of energy units – ICE and electric motor, and allowed ICE unit turn off in built-up areas. In the presented research results can be seen as a great contribution to the work of the propulsion system has an internal combustion engine, which not only drives the electric generator, but also a wheeled vehicles.
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Hung, J. Y., and L. F. Gonzalez. "On parallel hybrid-electric propulsion system for unmanned aerial vehicles." Progress in Aerospace Sciences 51 (May 2012): 1–17. http://dx.doi.org/10.1016/j.paerosci.2011.12.001.
Повний текст джерела
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Seitz, Arne, Markus Nickl, Anne Stroh, and Patrick C. Vratny. "Conceptual study of a mechanically integrated parallel hybrid electric turbofan." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 14 (July 27, 2018): 2688–712. http://dx.doi.org/10.1177/0954410018790141.
Повний текст джерелаАнотація:
In the paper, options for mechanically integrated parallel hybrid propulsion are evaluated, and a conceptual sizing and performance study of a mechanically integrated parallel hybrid electric turbofan engine for a short-range aircraft application is presented and discussed. Through a methodical down-selection procedure, a most promising power plant system architectural concept is identified from an initial cloud of concept candidates. The design of the preferred configuration is conceptualized including initial performance analyses, both at the isolated power plant as well as at the integrated aircraft level. Beside the basic power plant definition, the multidisciplinary concept elaboration includes solutions proposed for the electric systems architectural layout, the major electrical components involved as well as important airframe integration aspects. The components of the electrical power management and distribution system are sized, and efficiency and weights are evaluated under special consideration of thermal management requirements. In result, a best and balanced degree of power hybridization is determined for the studied mechanically integrated parallel hybrid power plants taking account of electric system design and weight impacts as well as power plant operational robustness in case of electric system failure. The overall system assessment includes the evaluation of fuel reduction potentials through a parametric aircraft sizing study including the derivation of key technological requirements for onboard electrical energy storage. In the paper, essential design and sizing strategies for mechanically integrated parallel hybrid aero propulsion systems are derived, and a brief characterization of the associated key technological challenges is provided.
Дисертації з теми "Parallel Hybrid-Electric Propulsion System"
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Harmon, Frederick G. "Neural network control of a parallel hybrid-electric propulsion system for a small unmanned aerial vehicle /." For electronic version search Digital dissertations database. Restricted to UC campuses. Access is free to UC campus dissertations, 2005. http://uclibs.org/PID/11984.
Повний текст джерела
2
Kaloun, Adham. "Conception de chaînes de traction hybrides et électriques par optimisation sur cycles routiers." Thesis, Centrale Lille Institut, 2020. http://www.theses.fr/2020CLIL0019.
Повний текст джерелаАнотація:
La conception des chaînes de traction hybrides est une tâche complexe, qui fait appel à des experts de différents domaines s'appuyant sur des compétences et des outils distincts. En plus de cela, la recherche d'une solution optimale nécessite un retour système. Cela peut être, selon la granularité des modèles de composants, très coûteux en temps de calcul. Ceci est d'autant plus vrai lorsque la performance du système est déterminée par sa commande, comme c'est le cas du véhicule hybride. En fait, différentes possibilités peuvent être sélectionnées pour fournir le couple requis aux roues pendant le cycle de conduite. Ainsi, le principal obstacle est d'atteindre l'optimalité tout en conservant une méthodologie rapide et robuste. Dans ces travaux de thèse, de nouvelles approches visant à exploiter le potentiel complet de l'hybridation sont proposées et comparées. La première stratégie est une approche bi-niveaux composée de deux blocs d'optimisation imbriqués: un processus d'optimisation des paramètres de design externe qui calcule la meilleure valeur de consommation de carburant à chaque itération en se basant sur une version améliorée de la programmation dynamique pour l'optimisation de la commande. Deux stratégies de conception systémique différentes basées sur le schéma itératif sont également proposées. La première approche est basée sur la réduction de modèle tandis que la seconde se repose sur des techniques précises de réduction de cycle. Cette dernière permet l'utilisation de modèles de haute précision sans pénaliser le temps de calcul. Une approche simultanée est ensuite mise en œuvre, qui optimise à la fois les variables de conception et les paramètres d'une nouvelle stratégie efficace à base de règles. Cette dernière permettra une optimisation plus rapide par rapport à l'optimisation directe de toutes les variables de décision. Enfin, une technique basée sur l'utilisation des méta-modèles est exploréeDesigning hybrid powertrains is a complex task, which calls for experts from various fields. In addition to this, finding the optimal solution requires a system overview. This can be, depending on the granularity of the models at the component level, highly time-consuming. This is even more true when the system’s performance is determined by its control, as it is the case of the hybrid powertrain. In fact, various possibilities can be selected to deliver the required torque to the wheels during the driving cycle. Hence, the main obstacle is to achieve optimality while keeping the methodology fast and robust. In this work, novel approaches to exploit the full potential of hybridization are proposed and compared. The first strategy is a bi-level approach consisting of two nested optimization blocks: an external design optimization process that calculates the best fuel consumption value at each iteration, found through control optimization using an improved version of dynamic programming. Two different systemic design strategies based on the iterative scheme are proposed as well. The first approach is based on model reduction while the second approach relies on precise cycle reduction techniques. The latter enables the use of high precision models without penalizing the calculation time. A co-optimization approach is implemented afterwards which adjusts both the design variables and parameters of a new efficient rule-based strategy. This allows for faster optimization as opposed to an all-at-once approach. Finally, a meta-model based technique is explored
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BOGGERO, LUCA. "Design techniques to support aircraft systems development in a collaborative MDO environment." Doctoral thesis, Politecnico di Torino, 2018. http://hdl.handle.net/11583/2710702.
Повний текст джерелаАнотація:
The aircraft design is a complex multidisciplinary and collaborative process. Thousands of disciplinary experts with different design competences are involved within the whole development process. The design disciplines are often in contrast with each other, as their objectives might be not coincident, entailing compromises for the determination of the global optimal solution. Therefore, Multidisciplinary Design and Optimization (MDO) algorithms are being developed to mathematically overcome the divergences among the design disciplines. However, a MDO formulation might identify an optimal solution, but it could be not sufficient to ensure the success of a project. The success of a new project depends on two factors. The first one is relative to the aeronautical product, which has to be compliant with all the capabilities actually demanded by the stakeholders. Furthermore, a “better” airplane may be developed in accordance with customer expectations concerning better performance, lower operating costs and fewer emissions. The second important factor refers to the competitiveness among the new designed product and all the other competitors. The Time-To-Market should be reduced to introduce in the market an innovative product earlier than the other aeronautical industries. Furthermore, development costs should be decreased to maximize profits or to sell the product at a lower price. Finally, the development process must reduce all the risks due to wrong design choices.
These two main motivations entail two main objectives of the current dissertation. The first main objective regards the assessment and development of design techniques for the integration of the aircraft subsystems conceptual design discipline within a collaborative and multidisciplinary development methodology. This methodology shall meet all the necessities required to design an optimal and competitive product. The second goal is relative to the employment of the proposed design methodology for the initial development of innovative solutions. As the design process is multidisciplinary, this thesis is focused on the on-board systems discipline, without neglecting the interactions among this discipline with all the other design disciplines. Thus, two kinds of subsystems are treated in the current dissertation. The former deals with hybrid-electric propulsion systems installed aboard Remotely Piloted Aerial Systems (RPASs) and general aviation airplanes. The second case study is centered on More and All Electric on-board system architectures, which are characterized by the removal of the hydraulic and/or pneumatic power generation systems in favor of an enhancement of the electrical system.
The proposed design methodology is based on a Systems Engineering approach, according to which all the customer needs and required system functionalities are defined since the earliest phase of the design. The methodology is a five-step process in which several techniques are implemented for the development of a successful product. In Step 1, the design case and the requirements are defined. A Model Based Systems Engineering (MBSE) approach is adopted for the derivation and development of all the functionalities effectively required by all the involved stakeholders. All the design disciplines required in the MDO problem are then collected in Step 2. In particular, all the relations among these disciplines – in terms of inputs/outputs – are outlined, in order to facilitate their connection and the setup of the design workflow. As the present thesis is mainly focused on the on-board system design discipline, several algorithms for the preliminary sizing of conventional and innovative subsystems (included the hybrid propulsion system) are presented. In the third step, an MDO problem is outlined, determining objectives, constraints and design variables. Some design problems are analyzed in the present thesis: un-converged and converged Multidisciplinary Design Analysis (MDA), Design Of Experiments (DOE), optimization. In this regard, a new multi-objective optimization method based on the Fuzzy Logic has been developed during the doctoral research. This proposed process would define the “best” aircraft solution negotiating and relaxing some constraints and requirements characterized by a little worth from the user perspective. In Step 4, the formulation of the MDO problem is then transposed into a MDO framework. Two kinds of design frameworks are here considered. The first one is centered on the subsystems design, with the aim of preliminarily highlighting the impacts of this discipline on the entire Overall Aircraft Design (OAD) process and vice-versa. The second framework is distributed, as many disciplinary experts are involved within the design process. In this case, the level of fidelity of the several disciplinary modules is higher than the first framework, but the effort needed to setup the entire workflow is much higher. The proposed methodology ends with the investigation of the design space through the implemented framework, eventually selecting the solution of the design problem (Step 5).
The capability of the proposed methodology and design techniques is demonstrated by means of four application cases. The first case study refers to the initial definition of the physical architecture of a hybrid propulsion system based on a set of needs and capabilities demanded by the customer. The second application study is focused on the preliminary sizing of a hybrid-electric propulsion system to be installed on a retrofit version of a well-known general aviation aircraft. In the third case study, the two kinds of MDO framework previously introduced are employed to design conventional, More Electric and All Electric subsystem architectures for a 90-passenger regional jet. The last case study aims at minimizing the aircraft development costs. A Design-To-Cost approach is adopted for the design of a hybrid propulsion system.
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Kaloun, Adham. "Conception de chaînes de traction hybrides et électriques par optimisation sur cycles routiers." Thesis, Ecole centrale de Lille, 2020. http://www.theses.fr/2020ECLI0019.
Повний текст джерелаАнотація:
La conception des chaînes de traction hybrides est une tâche complexe, qui fait appel à des experts de différents domaines s'appuyant sur des compétences et des outils distincts. En plus de cela, la recherche d'une solution optimale nécessite un retour système. Cela peut être, selon la granularité des modèles de composants, très coûteux en temps de calcul. Ceci est d'autant plus vrai lorsque la performance du système est déterminée par sa commande, comme c'est le cas du véhicule hybride. En fait, différentes possibilités peuvent être sélectionnées pour fournir le couple requis aux roues pendant le cycle de conduite. Ainsi, le principal obstacle est d'atteindre l'optimalité tout en conservant une méthodologie rapide et robuste. Dans ces travaux de thèse, de nouvelles approches visant à exploiter le potentiel complet de l'hybridation sont proposées et comparées. La première stratégie est une approche bi-niveaux composée de deux blocs d'optimisation imbriqués: un processus d'optimisation des paramètres de design externe qui calcule la meilleure valeur de consommation de carburant à chaque itération en se basant sur une version améliorée de la programmation dynamique pour l'optimisation de la commande. Deux stratégies de conception systémique différentes basées sur le schéma itératif sont également proposées. La première approche est basée sur la réduction de modèle tandis que la seconde se repose sur des techniques précises de réduction de cycle. Cette dernière permet l'utilisation de modèles de haute précision sans pénaliser le temps de calcul. Une approche simultanée est ensuite mise en œuvre, qui optimise à la fois les variables de conception et les paramètres d'une nouvelle stratégie efficace à base de règles. Cette dernière permettra une optimisation plus rapide par rapport à l'optimisation directe de toutes les variables de décision. Enfin, une technique basée sur l'utilisation des méta-modèles est exploréeDesigning hybrid powertrains is a complex task, which calls for experts from various fields. In addition to this, finding the optimal solution requires a system overview. This can be, depending on the granularity of the models at the component level, highly time-consuming. This is even more true when the system’s performance is determined by its control, as it is the case of the hybrid powertrain. In fact, various possibilities can be selected to deliver the required torque to the wheels during the driving cycle. Hence, the main obstacle is to achieve optimality while keeping the methodology fast and robust. In this work, novel approaches to exploit the full potential of hybridization are proposed and compared. The first strategy is a bi-level approach consisting of two nested optimization blocks: an external design optimization process that calculates the best fuel consumption value at each iteration, found through control optimization using an improved version of dynamic programming. Two different systemic design strategies based on the iterative scheme are proposed as well. The first approach is based on model reduction while the second approach relies on precise cycle reduction techniques. The latter enables the use of high precision models without penalizing the calculation time. A co-optimization approach is implemented afterwards which adjusts both the design variables and parameters of a new efficient rule-based strategy. This allows for faster optimization as opposed to an all-at-once approach. Finally, a meta-model based technique is explored
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Ren, Zhongling. "Optimization Methods for Hybrid Electric Vehicle Propulsion System." Thesis, KTH, Energiteknik, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-235932.
Повний текст джерелаАнотація:
Design of hybrid vehicles is a hot topic because of the strict restriction on the emissions of the vehicle. The optimal design of hybrid vehicles becomes necessary to reduce the cost or emissions of the vehicle. The propulsion system of a hybrid electric vehicle is inherently more complex than that of a conventional vehicle as an electric power supply branch is added. The design involves topology design, component design and control design, where all phases are interrelated. The idea to handle all the three design phases together is called system level design. Due to its complexity, it is not possible time wise to evaluate all possible design options. Optimization algorithms are therefore needed to speed up the process. The variable types that appear in each design phase are different and multiple algorithms are needed. In this thesis, different algorithms are studied for their robustness for both continuous variables and discrete variables, as well as benchmarked for the Volvo internal optimization platform afterwards. Standard test cases are used to validate the algorithms and several features are added to an algorithm to make it more generic and efficient. Based on theoretical and experimental studies, recommendations for the selection of algorithms are proposed based on different types of variables.Based on the optimization platform, several different optimization coordination architectures for system level design are introduced and simultaneous and nested coordination architectures are tested by one specific industrial case in the second part of the thesis. Both methods appeared to be promising according to the result of the test case and they managed to reduce the convergence time dramatically. The vehicle model used was not precise enough to prove which method is the superior one but a more precise model can be introduced in the future to facilitate such a conclusion.Hybridfordon är ett aktuellt ämne, på grund av den strikta regleringen gällande fordonsutsläpp. Den optimala designen av hybridfordon är nödvändig för att reducera kostnaden eller utsläppen. Motorsystemet hos ett elektriskt hybridfordon blir mer komplicerat än det hos ett konventionellt fordon, eftersom man måste ta hänsyn till försörjningen av elektrisk energi. Designprocessen involverar design av topologi, design av komponenter samt design av kontrollsystem. Idéen om att sammanfoga alla tre designfaser kallas systemnivådesign. På grund av komplexiteten är det tidsmässigt inte möjligt att evaluera samtliga möjliga designval. Därför behövs optimeringsalgoritmer för att snabba på processen. Olika typer av variabler berörs i de olika designfaserna och därför behövs olika algoritmer. I avhandlingen undersöks olika algoritmers robusthet för kontinuerliga och diskreta variabler samt deras prestanda mot en intern optimeringsplattform. Standardiserade testfall används för att validera algoritmerna vartefter algoritmerna görs mer effektiva och generella. Baserat på teoretiska och experimentella studier föreslås rekommendationer för val av algoritmer baserat på olika typer av variabler. Baserat på optimeringsplattformen introduceras flera olika optimeringskoordinationsarkitekturer för systemnivådesign, och samtidiga och samordnade koordinationsarkitekturer testas för ett specifikt industrifall i den andra delen av avhandlingen. Båda metoderna tycktes vara lovande enligt resultatet av testfallet, och de lyckades sänka konvergensperioden dramatiskt. Den använda fordonsmodellen var inte tillräckligt exakt för att bevisa vilken metod som är den överlägsna, men en mer exakt modell kan introduceras i framtiden för att underlätta en sådan slutsats.
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Dreier, Dennis. "Assessing the potential of fuel saving and emissions reduction of the bus rapid transit system in Curitiba, Brazil." Thesis, KTH, Energi och klimatstudier, ECS, 2015. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-176398.
Повний текст джерелаАнотація:
The transport sector contributes significantly to global energy use and emissions due to its traditional dependency on fossil fuels. Climate change, security of energy supply and increasing mobility demand is mobilising governments around the challenges of sustainable transport. Immediate opportunities to reduce emissions exist through the adoption of new bus technologies, e.g. advanced powertrains. This thesis analysed energy use and carbon dioxide (CO2) emissions of conventional, hybrid-electric, and plug-in hybrid-electric city buses including two-axle, articulated, and biarticulated chassis types (A total of 6 bus types) for the operation phase (Tank-to-Wheel) in Curitiba, Brazil. The systems analysis tool – Advanced Vehicle Simulator (ADVISOR) and a carbon balance method were applied. Seven bus routes and six operation times for each (i.e. 42 driving cycles) are considered based on real-world data. The results show that hybrid-electric and plug-in hybrid-electric two-axle city buses consume 30% and 58% less energy per distance (MJ/km) compared to a conventional two-axle city bus (i.e. 17.46 MJ/km). Additionally, the energy use per passenger-distance (MJ/pkm) of a conventional biarticulated city bus amounts to 0.22 MJ/pkm, which is 41% and 24% lower compared to conventional and hybrid-electric two-axle city buses, respectively. This is mainly due to the former’s large passenger carrying capacity. Large passenger carrying capacities can reduce energy use (MJ/pkm) if the occupancy rate of the city bus is sufficient high. Bus routes with fewer stops decrease energy use by 10-26% depending on the city bus, because of reductions in losses from acceleration and braking. The CO2 emissions are linearly proportional to the estimated energy use following from the carbon balance method, e.g. CO2 emissions for a conventional two-axle city bus amount to 1299 g/km. Further results show that energy use of city bus operation depends on the operation time due to different traffic conditions and driving cycle characteristics. An additional analysis shows that energy use estimations can vary strongly between considered driving cycles from real-world data. The study concludes that advanced powertrains with electric drive capabilities, large passenger carrying capacities and bus routes with a fewer number of bus stops are beneficial in terms of reducing energy use and CO2 emissions of city bus operation in Curitiba.
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Lundin, Johan. "Flywheel in an all-electric propulsion system." Licentiate thesis, Uppsala universitet, Elektricitetslära, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-222030.
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Energy storage is a crucial condition for both transportation purposes and for the use of electricity. Flywheels can be used as actual energy storage but also as power handling device. Their high power capacity compared to other means of storing electric energy makes them very convenient for smoothing power transients. These occur frequently in vehicles but also in the electric grid. In both these areas there is a lot to gain by reducing the power transients and irregularities. The research conducted at Uppsala university and described in this thesis is focused on an all-electric propulsion system based on an electric flywheel with double stator windings. The flywheel is inserted in between the main energy storage (assumed to be a battery) and the traction motor in an electric vehicle. This system has been evaluated by simulations in a Matlab model, comparing two otherwise identical drivelines, one with and one without a flywheel. The flywheel is shown to have several advantages for an all-electric propulsion system for a vehicle. The maximum power from the battery decreases more than ten times as the flywheel absorbs and supplies all the high power fluxes occuring at acceleration and braking. The battery delivers a low and almost constant power to the flywheel. The amount of batteries needed decreases whereas the battery lifetime and efficiency increases. Another benefit the flywheel configuration brings is a higher energy efficiency and hence less need for cooling. The model has also been used to evaluate the flywheel functionality for an electric grid application. The power from renewable intermittent energy sources such as wave, wind and current power can be smoothened by the flywheel, making these energy sources more efficient and thereby competitive with a remaining high power quality in the electric grid.
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Lin, Qing. "Small-Signal Modeling and Stability Specification of a Hybrid Propulsion System for Aircrafts." Thesis, Virginia Tech, 2021. http://hdl.handle.net/10919/103515.
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This work utilizes the small-signal impedance-based stability analysis method to develop stability assessment criteria for a single-aisle turboelectric aircraft with aft boundary-layer propulsion (STARC-ABL) system. The impedance-based stability analysis method outperforms other stability analysis methods because it does not require detailed information of individual components for system integration, therefore, a system integrator can just require the vendors to make the individual components meet the impedance specifications to ensure whole system stability. This thesis presents models of a generator, motor, housekeeping loads, and battery all with power electronics interface which form an onboard electrical system and analyzes the relationship between the impedance shape of each component and their physical design and control loop design. Based on the developed small-signal model of the turbine-generator-rectifier subsystem and load subsystem, this thesis analyzes the impact of electromechanical dynamics of the turbofan passed through the generator on the dc distribution system, concluding that the rectifier can mitigate the impact. Finally, to ensure the studied system stable operation during the whole flying profile, the thesis provides impedance specifications of the dc distribution system and verifies the specifications with several cases in time-domain simulations.M.S.
Electric aircraft propulsion (EAP) technologies have been a trend in the aviation industry for their potential to reduce environmental emissions, increase fuel efficiency and reduce noise for commercial airplanes. Achieving these benefits would be a vital step towards environmental sustainability. However, the development of all-electric aircraft is still limited by the current battery technologies and maintenance systems. The single-aisle turboelectric aircraft with aft boundary-layer (STARC-ABL) propulsion concept is therefore developed by NASA aiming to bridge the gap between the current jet fuel-powered aircraft and future all-electric vehicles. The plane uses electric motors powered by onboard gas turbines and transfers the generated power to other locations of the airplane like the tail fan motor to provide distributed propulsion. Power electronics-based converter converts electricity in one form of electricity to another form, for example, from ac voltage to dc voltage. This conversion of power is very important in the whole society, from small onboard chips to Mega Watts level electrical power system. In the aircraft electrical power system context, power electronics converter plays an important role in the power transfer process especially with the recent trend of using high voltage dc (HVDC) distribution instead of conventional ac distribution for the advantage of increased efficiency and better voltage regulation. The power generated by the electric motors is in ac form. Power electronics converter is used to convert the ac power into dc power and transfer it to the dc bus. Because the power to drive the electric motor to provide distributed propulsion is also in ac form, the dc power needs to be converted back into ac power still through a power electronics converter. With a high penetration of power electronics into the onboard electrical power system and the increase of electrical power level, potential stability issues resulted from the interactions of each subsystem need to be paid attention to. There are mainly two stability-related studies conducted in this work. One is the potential cross-domain dynamic interaction between the mechanical system and the electrical system. The other is a design-oriented study to provide sufficient stability margin in the design process to ensure the electrical system’s stable operation during the whole flying profile. The methodology used in this thesis is the impedance-based stability analysis. The main analyzing process is to find an interface of interest first, then grouped each subsystem into a source subsystem and load subsystem, then extract the source impedance and load impedance respectively, and eventually using the Nyquist Criterion (or in bode plot form) to assess the stability with the impedance modeling results. The two stability-related issues mentioned above are then studied by performing impedance analysis of the system. For the electromechanical dynamics interaction study, this thesis mainly studies the rotor dynamics’ impact on the output impedance of the turbine-generator-rectifier system to assess the mechanical dynamics’ impact on the stability condition of the electrical system. It is found that the rotor dynamics of the turbine is masked by the rectifier; therefore, it does not cause stability problem to the pre-tuned system. For the design-oriented study, this thesis mainly explores and provides the impedance shaping guidelines of each subsystem to ensure the whole system's stable operation. It is found that the stability boundary case is at rated power level, the generator voltage loop bandwidth is expected to be higher than 300Hz, 60˚ to achieve a 6dB, 45˚ stability margin, and load impedance mainly depends on the motor-converter impedance.
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Nakka, Sai Krishna Sumanth. "Co-design of Hybrid-Electric Propulsion System for Aircraft using Simultaneous Multidisciplinary Dynamic System Design Optimization." University of Cincinnati / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1602153187738909.
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Geiß, Ingmar [Verfasser]. "Sizing of the Series Hybrid-electric Propulsion System of General Aviation Aircraft / Ingmar Geiß." München : Verlag Dr. Hut, 2021. http://nbn-resolving.de/urn:nbn:de:101:1-2021100123334382521757.
Повний текст джерелаКниги з теми "Parallel Hybrid-Electric Propulsion System"
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Simpson, Andrew. Energy storage system considerations for grid-charged hybrid electric vehicles. Washington, D.C.]: U.S. Dept. of Energy, National Renewable Energy Laboratory, Office of Energy Efficiency & Renewable Energy, 2005.
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Min-Huei, Kim, and Lewis Research Center, eds. Advanced propulsion power distribution system for next generation electric/hybrid vehicle: Phase I, preliminary system studies : final report. Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1995.
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Bose, Bimal K. Advanced propulsion power distribution system for next generation electric/hybrid vehicle: Phase I, preliminary system studies : final report. Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1995.
Знайти повний текст джерелаЧастини книг з теми "Parallel Hybrid-Electric Propulsion System"
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Pettes-Duler, Matthieu, Xavier Roboam, and Bruno Sareni. "Integrated Design Process and Sensitivity Analysis of a Hybrid Electric Propulsion System for Future Aircraft." In Lecture Notes in Electrical Engineering, 71–85. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-37161-6_6.
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Bancă, Gheorghe, Florian Ivan, Gheorghe Frățilă, and Valentin Nișulescu. "Modeling the Performances of a Vehicle Provided with a Hybrid Electric Diesel Propulsion System (HEVD)." In CONAT 2016 International Congress of Automotive and Transport Engineering, 415–26. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-45447-4_46.
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Lee, Bohwa, Poomin Park, and Chuntaek Kim. "Power Managements of a Hybrid Electric Propulsion System Powered by Solar Cells, Fuel Cells, and Batteries for UAVs." In Handbook of Unmanned Aerial Vehicles, 495–524. Dordrecht: Springer Netherlands, 2014. http://dx.doi.org/10.1007/978-90-481-9707-1_115.
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Thomas, Jose, Allen Thomas, Akhil Biju, Aswin Mathew, C. Parag Jose, and K. M. Haneesh. "A GPS-Gradient Mapped Database-Based Fuzzy Energy Management System for a Series—Parallel Hybrid Electric Vehicle." In Advances in Electrical Control and Signal Systems, 515–27. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5262-5_38.
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Yamin, Mohamad, Cokorda P. Mahandari, and Rasyid H. Sudono. "Dynamic Simulation of Wheel Drive and Suspension System in a Through-the-Road Parallel Hybrid Electric Vehicle." In Proceedings of Second International Conference on Electrical Systems, Technology and Information 2015 (ICESTI 2015), 263–70. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-287-988-2_28.
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"Electric drive system technologies." In Propulsion Systems for Hybrid Vehicles, 243–324. Institution of Engineering and Technology, 2010. http://dx.doi.org/10.1049/pbrn007e_ch5.
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"Design of electromechanical system for parallel hybrid electric vehicle." In Energy Efficiency Improvement of Geotechnical Systems, 39–46. CRC Press, 2013. http://dx.doi.org/10.1201/b16355-6.
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Serpi, Alessandro, Mario Porru, and Alfonso Damiano. "A Novel Highly Integrated Hybrid Energy Storage System for Electric Propulsion and Smart Grid Applications." In Advancements in Energy Storage Technologies. InTech, 2018. http://dx.doi.org/10.5772/intechopen.73671.
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Jeevan Danaraj, Edgar. "Electrification for Aero-Engines: A Case Study of Modularization in New Product Development." In Advances in Turbomachinery [Working Title]. IntechOpen, 2022. http://dx.doi.org/10.5772/intechopen.109006.
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Modularization of hybrid-electric propulsion for commercial aircraft is becoming a reality in air transportation. The main intent of an electric architecture is to produce less carbon emissions and advance towards sustainability in the aeronautics industry. Due to regulatory and customer requirements for new technologies aimed at climate change and pollution, the integration of hybrid electric engine design become more challenging. Conceptual modular and integral product architectures are being compared with conventional and new constructions. A Design Structure Matrix (DSM) model is developed to analyze configuration of sub-component and their relationships through interaction between system elements. The DSM model includes product decomposition and cyclic task interdependencies to understand the extent of modularity in the product life cycle. The traditional turbofan engine architecture will be compared with hybrid electric propulsion engine architecture. The analysis indicates that the electric engine configuration constitutes a shift to a more distributed and less modular architecture. The DSM model reported a 19% increase in density of connectivity between components and 58% decrease in terms of structural complexity. The significance of these changes demonstrates that the more distributed architecture of the fully electric engine architecture requires less effort in system integration than the geared traditional turbofan architecture.
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Belvisi, Daniele, Raphael Zaccone, Massimo Figari, Sergio Simone, and Bruno Spanghero. "BESS-Based Hybrid Propulsion: An Application to a Front Line Naval Vessel Preliminary Design." In Progress in Marine Science and Technology. IOS Press, 2022. http://dx.doi.org/10.3233/pmst220020.
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The paper conceives a flexible new generation naval ship Destroyer (DDX, Destroyer, Experimental) with a primary focus on low environmental footprint, high efficiency, and reliability. The ship implements an innovative propulsion power generation and storage system based on a CODOGOL (COmbined Diesel Or Gas Or eLectric) architecture and a Battery Energy Storage System (BESS). The proposed modular solution is also suitable for retrofitting applications and represents an innovation in the state of the art of hybrid propulsion systems for big, front-line naval ships. The shipboard BESS is used as a backup power source to ensure minimum generator operation (MGO) mode reliability requirements. The benefits of the proposed solution are discussed in detail, highlighting a reduction of the operating costs and fuel consumption, as well as low pollutant emissions and Life Cycle Costs. Eventually, dynamical simulation is used to assess the effectiveness of the proposed solution in critical conditions.
Тези доповідей конференцій з теми "Parallel Hybrid-Electric Propulsion System"
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Papadopoulos, Konstantinos I., Christos P. Nasoulis, Elissaios G. Ntouvelos, Vasilis G. Gkoutzamanis, and Anestis I. Kalfas. "Power Flow Optimization for a Hybrid-Electric Propulsion System." In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-84037.
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Abstract The present study deals with the optimization of performance for a hybrid-electric propulsion system. It focuses on the modeling and power management frameworks, while evaluation is done on a single flight basis. The main objective is to extract the maximum out of the novel powertrain archetype. Two hybridization factors are considered. The pair helps to describe the degree of hybridization at the power supply and power consumption levels. Their revised mathematical definition facilitates a unique method of hybrid-electric propulsion system modeling, that maximizes the conveyed amount of information. An in-house computational tool is developed. It employs a genetic algorithm optimizer in the interest of managing power usage during flight. Energy consumption is set as the objective function. The operation of a 19-seater, commuter aircraft is investigated. Turbo-electric, series-hybrid, parallel-hybrid and series-parallel variants are derived from a generic composition. An analysis on their optimized performance, with different technological readiness levels for 2020 and 2035, is aimed at identifying where each system performs best. Considering 2020 technology, it does not yield a viable hybrid-electric configuration, without suffering significant payload penalties. Architectures relying on mechanical propulsors show promise of 15% reduction to energy consumption, accounting for 2035 readiness levels. The concepts of Boundary Layer Ingestion and Distributed Propulsion display the potential to boost electrified propulsion. The series-hybrid and series-parallel configurations are the primary beneficiaries of these concepts, displaying up to 30% reduction in fuel and 20% reduction in energy consumption.
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Sahoo, Smruti, Xin Zhao, Konstantinos G. Kyprianidis, and Anestis Kalfas. "Performance Assessment of an Integrated Parallel Hybrid-Electric Propulsion System Aircraft." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-91459.
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Abstract Hybrid-electric propulsion system promises avenues for a greener aviation sector. Ground research work was performed in the past for the feasibility assessment, at the system level, for such novel concepts and the results showed were promising. Such designs, however, possess unique challenges from an operational point of view, and for sizing of the sub-system components; necessitating further design space exploration for associating with an optimal operational strategy. In light of the above, the paper aims at presenting an operational analysis and performance assessment study, for a conceptualised parallel hybrid design of an advanced geared turbofan engine, based on 2035 timeframe technology level. It is identified that the hybrid power operation of the engine is constrained with respect to the requirement of maintaining an adequate surge margin for the low pressure side components; however, a core re-optimised engine design with consideration of electrical power add-in for the design condition, relieves such limit. Therefore such a design, makes it suitable for implementation of higher degree of hybridisation. Furthermore, performance assessment is made both at engine and engine-aircraft integrated level for both scenarios of hybrid operation and the benefits are established relative to the baseline engine. The performance at engine level engine specific fuel consumption (SFC), thrust specific power consumption (TSPC), and overall efficiency, shows improvement in both hybridised scenarios. Improvement in SFC is achieved due to supply of the electrical power, whereas, the boost in TSPC, and overall efficiency is attributed to the use of higher efficiency electrical drive system. Furthermore, it is observed that while the hybridised scenario performs better at engine level, the core re-optimised design exhibits a better saving for block fuel/energy consumption, due to the considerable weight savings in the core components.
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Marto, Diogo, and Francisco Brójo. "Hybrid-Electric Propulsion Solutions for UAV Application." In ASME 2022 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/imece2022-95375.
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Abstract Due to the rapid growth of the aviation industry, the concentrations of hazardous pollutants in the atmosphere are rising and the need for more environment-friendly solutions is higher than ever. This study aims to test and show the benefits of hybrid-electric propulsion systems in UAVs in two possible configurations, parallel and series. The hybrid propulsion system combines a 28-cc 2-stroke internal combustion engine with a 200-watt frameless generator. As a primary approach, the engine alone with a 16-inch diameter and 12-inch pitch propeller is characterized by its torque, power and specific fuel consumption throughout the engine’s operating range. In a second approach, the hybrid component is added and a comparison between both results taken is made. Preliminary results show that parallel configuration offers lower specific fuel consumption in comparison with the engine alone. Also, the higher load on the engine used as the primary powerplant seems to promote a more stable operation, with higher throttle control and lower vibrations. In a final remark, considerations regarding the two configurations are made. These considerations aim to establish the best points to operate each architecture and which one is best suited to be implemented on a UAV depending on the mission profile.
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Sahoo, Smruti, Mavroudis D. Kavvalos, Dimitra Eirini Diamantidou, and Konstantinos G. Kyprianidis. "System-Level Assessment of a Partially Distributed Hybrid Electric Propulsion System." In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-81917.
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Abstract Hybrid electric propulsion system based aircraft designs are paving the path towards a future greener aviation sector and thus, have been the major focus of the aeronautical community. The fuel efficiency improvements of such propulsion system configurations are realized at the aircraft level. In order to assess such benefits, a radical shift in the sub-system modeling requirements and an integrated conceptual aircraft design environment is necessary. This work highlights performance model development work pertaining to different hybrid electric propulsion system components and development of a design platform which facilitates tighter integration of different novel propulsion system disciplines at aircraft level. Furthermore, a serial/parallel partially distributed hybrid electric propulsion system is chosen as the candidate configuration to assess the potential benefits and associated trade-offs by conducting multidisciplinary design space exploration studies. It is established that the distributed hybrid electric configurations pose the potential for aircraft structural weight reduction benefits. The study further illustrates the impacts from onboard charging during the low thrust requirement segments, quantitatively. It is highlighted that the amount of off-take power extraction for onboard charging of the battery is limited due to engine operability and higher specific fuel consumption issues. Though provisioning of onboard charging lowers the potential for block fuel savings, improvement in battery specific energy can make it more promising, which is also dependent on the hybridization power level. It is established that distributed propulsion system configurations particularly benefit from a high aspect ratio wing structure, which manifests for high hybridization power levels. A high voltage level transmission system with more efficient electrical components, enhances opportunities for achieving block fuel saving benefits.
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Ghelani, Raj, Ioannis Roumeliotis, Chana Anna Saias, Christos Mourouzidis, Vassilios Pachidis, Justin Norman, and Marko Bacic. "Design Methodology and Mission Assessment of Parallel Hybrid Electric Propulsion Systems." In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-82478.
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Abstract An integrated engine cycle design methodology and mission assessment for parallel hybrid electric propulsion architectures are presented in this paper. The aircraft case study considered is inspired by Fokker 100, boosted by an electric motor on the low-pressure shaft of the gas turbine. The fuel burn benefits arising from boosting the low-pressure shaft are discussed for two different baseline engine technologies. A three-point engine cycle design method is developed to redesign the engine cycle according to the degree of hybridization. The integrated cycle design and power management optimization method is employed to identify potential fuel burn benefits from hybridization for multiple mission ranges. Genetic algorithm-based optimizer has been used to identify optimal power management strategies. The sensitivity of these mission results has also been analyzed for different assumptions on the electric powertrain. With 1 MW motor power and a battery pack of 2307 kg, a maximum of 3% fuel burn benefit can be obtained by retrofitting the gas turbine for 400 nm mission range. Optimizing the power management strategy can improve this fuel burn benefit by 0.2–0.3%. Redesigning the gas turbine and optimizing the power management strategy, finally provides a maximum fuel benefit of 4.2% on 400 nm. The results suggest that a high hybridization by power, low hybridization by energy, and ranges below 700 nm are the only cases where the redesigned hybrid electric aircraft has benefits in fuel burn and energy consumption relative to the baseline aircraft. Finally, it is found that the percentage of fuel burn benefits from the hybrid electric configuration increases with the improvement in engine technology.
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Yan, Xingda, James Fleming, and Roberto Lot. "Modelling and Energy Management of Parallel Hybrid Electric Vehicle with Air Conditioning System." In 2017 IEEE Vehicle Power and Propulsion Conference (VPPC). IEEE, 2017. http://dx.doi.org/10.1109/vppc.2017.8330923.
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Li, Xuefang, Simos A. Evangelou, and Roberto Lot. "Integrated Management of Powertrain and Engine Cooling System for Parallel Hybrid Electric Vehicles." In 2018 IEEE Vehicle Power and Propulsion Conference (VPPC). IEEE, 2018. http://dx.doi.org/10.1109/vppc.2018.8604994.
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Finger, D. Felix, Carsten Braun, and Cees Bil. "Comparative Assessment of Parallel-Hybrid-Electric Propulsion Systems for Four Different Aircraft." In AIAA Scitech 2020 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-1502.
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Ochiai, Kazuki, Yusuke Wada, Yushi Kamiya, Yasuhiro Daisho, and Kenji Morita. "Power system modeling and performance evaluation of series/ parallel-type plug-in hybrid electric vehicles." In 2010 IEEE Vehicle Power and Propulsion Conference (VPPC). IEEE, 2010. http://dx.doi.org/10.1109/vppc.2010.5729241.
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Sun, Xiaoxia, Chunming Shao, Guozhu Wang, Rongpeng Li, Danhua Niu, and Jun Shi. "Global Energy Management for Propulsion, Thermal Management System of A Series-parallel Hybrid Electric Vehicle." In 3rd International Conference on Vehicle Technology and Intelligent Transport Systems. SCITEPRESS - Science and Technology Publications, 2017. http://dx.doi.org/10.5220/0006370403320338.
Повний текст джерелаЗвіти організацій з теми "Parallel Hybrid-Electric Propulsion System"
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Richter, Tim, Lee Slezak, Chris Johnson, Henry Young, and Dan Funcannon. Advanced Hybrid Propulsion and Energy Management System for High Efficiency, Off Highway, 240 Ton Class, Diesel Electric Haul Trucks. Office of Scientific and Technical Information (OSTI), December 2008. http://dx.doi.org/10.2172/1092149.
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