Статті в журналах: "Parallel Hybrid-Electric Propulsion System"

1

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.

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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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2

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.

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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.

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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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4

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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5

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.

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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.

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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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7

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.

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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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8

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.

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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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9

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.

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10

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.

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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.

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11

Gesell, Hendrik, Florian Wolters, and Martin Plohr. "System analysis of turbo-electric and hybrid-electric propulsion systems on a regional aircraft." Aeronautical Journal 123, no. 1268 (August 1, 2019): 1602–17. http://dx.doi.org/10.1017/aer.2019.61.

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ABSTRACTThe increasing environmental requirements in the air transport sector pose great challenges to the aviation industry and are key drivers for innovation. Besides various approaches for increasing the efficiency of conventional gas turbine engines, electric propulsion systems have moved into the focus of aviation research. The first electric concepts are already in service in general aviation. This study analyses the potentials of electric and turbo hybrid propulsion systems for commercial aviation. Its purpose is to compare various architectures of electrical powertrains with a conventional turboprop on a regional aircraft, similar to the ATR 72, on engine and flight mission levels. The considered architectures include a turbo-electric (power controlled and direct driven), hybrid-electric (serial and parallel) and a pure electric concept. Their system weights are determined using today’s technology assumptions. With the help of performance models and flight mission calculations the impact on fuel consumption, CO ${}_{2}$ emissions and aircraft performance is evaluated.

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12

Litwin, Wojciech, Wojciech Leśniewski, Daniel Piątek, and Karol Niklas. "Experimental Research on the Energy Efficiency of a Parallel Hybrid Drive for an Inland Ship." Energies 12, no. 9 (May 2, 2019): 1675. http://dx.doi.org/10.3390/en12091675.

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The growing requirements for limiting the negative impact of all modes of transport on the natural environment mean that clean technologies are becoming more and more important. The global trend of e-mobility also applies to sea and inland water transport. This article presents the results of experimental tests carried out on a life-size, parallel diesel-electric hybrid propulsion system. The efficiency of the propulsion system was analysed for two modes of operation (electric and diesel) and for different engine speeds and loads. Analysis of the impact of using a hybrid propulsion system on fuel consumption was carried out on a case study vessel and for six actual journeys. The use of hybrid propulsion in “zero emission” mode enables up to four times higher energy efficiency when compared to a conventional drive, while reducing CO2 emissions and air pollution to zero, as well as a hundred-fold reduction in noise emissions. High flexibility in the operation of such a drive enables the use of intelligent power control technology (smart propulsion). This article shows that the use of hybrid propulsion reduces the negative impact on the environment to a minimum and allows for a significant reduction in the vessel’s operating costs.

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13

Zong, Jianan, Bingjie Zhu, Zhongxi Hou, Xixiang Yang, and Jiaqi Zhai. "Evaluation and Comparison of Hybrid Wing VTOL UAV with Four Different Electric Propulsion Systems." Aerospace 8, no. 9 (September 9, 2021): 256. http://dx.doi.org/10.3390/aerospace8090256.

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Electric propulsion technology has attracted much attention in the aviation industry at present. It has the advantages of environmental protection, safety, low noise, and high design freedom. An important research branch of electric propulsion aircraft is electric vertical takeoff and landing (VTOL) aircraft, which is expected to play an important role in urban traffic in the future. Limited by battery energy density, all electric unmanned aerial vehicles (UAVs) are unable to meet the longer voyage. Series/parallel hybrid-electric propulsion and turboelectric propulsion are considered to be applied to VTOL UAVs to improve performances. In this paper, the potential of these four configurations of electric propulsion systems for small VTOL UAVs are evaluated and compared. The main purpose is to analyze the maximum takeoff mass and fuel consumption of VTOL UAVs with different propulsion systems that meet the same performance requirements and designed mission profiles. The differences and advantages of the four types propulsion VTOL UAV in the maximum takeoff mass and fuel consumption are obtained, which provides a basis for the design and configuration selection of VTOL UAV propulsion system.

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Frosina, Emma, Adolfo Senatore, Luka Palumbo, Giuseppe Di Lorenzo, and Ciro Pascarella. "Development of a Lumped Parameter Model for an Aeronautic Hybrid Electric Propulsion System." Aerospace 5, no. 4 (October 4, 2018): 105. http://dx.doi.org/10.3390/aerospace5040105.

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This paper describes a case study for applying a hybrid electric propulsion system for general aviation aircraft. The work was performed by a joint team from the Centro Italiano Ricerche Aerospaziali (CIRA) and the Department of Industrial Engineering of the University of Naples Federico II. The use of electric and hybrid electric propulsion for aircraft has gained widespread and significant attention over the past decade. The driver of industry interest has principally been the need to reduce the emissions of combustion engine exhaust products and noise; however, studies have revealed the potential for overall improvement in the energy efficiency and mission flexibility of new aircraft types. The goal of the present study was to demonstrate the feasibility of aeronautic parallel hybrid electric propulsion for light aircraft, varying mission profiles and electric configurations. Through the creation and application of a global model with AMESim® software, in which every aspect of the components chosen by the industrial partners can be represented, some interesting studies were carried out. The numerical model used was more complete and more accurate compared to some others available in the literature. In particular, it was confirmed that, for particular missions, integrating state-of-the-art technologies provides notable advantages for aircraft hybrid electric propulsion for light aircraft.

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Jimenez, Darwin, Esteban Valencia, Ariel Herrera, Edgar Cando, and Marcelo Pozo. "Evaluation of Series and Parallel Hybrid Propulsion Systems for UAVs Implementing Distributed Propulsion Architectures." Aerospace 9, no. 2 (January 25, 2022): 63. http://dx.doi.org/10.3390/aerospace9020063.

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Current environmental policies for the aviation sector motivate the use of cleaner propulsion alternatives in order to reduce their CO2 footprint and noise pollution in the coming years. In this context, hybrid propulsion systems have emerged as a potential solution, as they have demonstrated a good trade-off between performance and low pollutant emissions. The present work carries out a comparison between parallel and series hybrid propulsion systems using heterogeneous and homogeneous distributed propulsion architectures. In order to highlight the opportunities of distributed propulsion systems and validate the methodology developed, a single propulsion hybrid configuration is used as baseline case for this study. For the propulsion system sizing, this work uses a parametric modelling tool, which includes a constraint analysis coupled with a weight estimation module to determine suitable configurations for a environmental monitoring mission. The latter module includes semi-empirical correlations to size the electric and mechanical components for each propulsion setup. From the results, it has been found that for the representative case of monitoring in the Galapagos Islands, which requires an endurance of approximate 7 h, the parallel hybrid system using three distributed propulsors presents the best performance features in terms of fuel savings, showing a 34% reduction compared with the baseline case. To summarize, the main contribution of this study lies on the development of a methodology to set potential hybrid distributed propulsion configurations for UAVs aimed for determined monitoring missions.

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Spada Chi̇odo, Ludovica, Teresa Donateo, and Antonio Ficarella. "Effect of Coordination on Transient Response of a Hybrid Electric Propulsion System." Volume 03 Issue 01 vm03, is01 (June 28, 2022): 4–12. http://dx.doi.org/10.23890/ijast.vm03is01.0101.

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Thanks to its typical limited speeds and altitudes, Urban Air Mobility represents an interesting application for electric and hybrid-electric power systems. In addition, short-range requirements are compatible with the limited performance of today’s batteries, conversely to their current inapplicability for commercial aviation purposes. For the present study, a parallel Hybrid Electric Propulsion System for a coaxial-rotor Air Taxi has been implemented in Simulink and tested on four different sets of operating conditions, with a transient signal as input for the Power Lever Angle command. The goal of this investigation is to analyze the transient behavior of the hybrid-electric propulsion system in question, to underline the role of electric motors in assisting thermal engine during transients, and, in particular, focuses on the benefits deriving from the adoption of a coordination block which adapts torque split between the two power sources on the basis of actual engine response.

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17

Xiao, Nengqi, Xiang Xu, and Baojia Chen. "Research on Simulation and Experiment of Ship Complex Diesel-Electric Hybrid Propulsion System." Journal of Ship Research 64, no. 02 (June 1, 2020): 171–84. http://dx.doi.org/10.5957/jsr.2020.64.2.171.

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This article introduces the composition and 12 operating conditions of a four-engine two-propeller hybrid power system. Through the combination of gearbox clutch and disconnection, the propulsion system has four single-engine operation modes, two double-engine parallel operation modes, and six PTI operation modes. Because the propulsion system has a variety of operating conditions, each operating condition has a form of energy transfer. As a result, its energy management and control are more complicated. To study the energy management and control strategy of a diesel- electric hybrid propulsion system, this work mainly studies the simulation model and sub-models of a diesel-electric hybrid propulsion system. In this study, MATLAB/ SIMULINK software is used to build the diesel engine model, motor model, and ship engine system mathematical model. The test and analysis were carried out on the test bench of the diesel-electric hybrid power system. By comparing the theoretical value of the SIMULINK simulation model with the test value of the test bench system, the correctness of each sub-model modeling method is verified. On the one hand, research on the text lays a theoretical foundation for the subsequent implementation of the conventional energy management and control strategy based on state identification on the unified management and distribution of the diesel-electric hybrid power system. At the same time, energy management of the diesel-electric hybrid system is also carried out. Optimization research provides theoretical guidance.

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Kowalski, Jakub, Wojciech Leśniewski, and Wojciech Litwin. "Multi-source-supplied parallel hybrid propulsion of the inland passenger ship STA.H. Research work on energy efficiency of a hybrid propulsion system operating in the electric motor drive mode." Polish Maritime Research 20, no. 3 (September 1, 2013): 20–27. http://dx.doi.org/10.2478/pomr-2013-0031.

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Abstract In the Faculty of Ocean Engineering and Ship Technology, Gdansk University of Technology, design has recently been developed of a small inland ship with hybrid propulsion and supply system. The ship will be propelled by a specially designed so called parallel hybrid propulsion system. The work was aimed at carrying out the energy efficiency analysis of a hybrid propulsion system operating in the electric motor drive mode and at performing the noise pollution measurements. The performed investigations have shown that a significant impact on the efficiency and on the acoustic emission has the type of belt transmission applied.

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19

Marzougui, Taher, Kolja Neuhaus, Laurent Labracherie, and Gianmarco Scalabrin. "Optimal sizing of hybrid electric propulsion system for eVTOL." IOP Conference Series: Materials Science and Engineering 1226, no. 1 (February 1, 2022): 012070. http://dx.doi.org/10.1088/1757-899x/1226/1/012070.

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Abstract Electric propulsion unmanned aerial vehicles (UAVs) attract much attention in aviation industry, with electric vertical take-off and landing (eVTOL) aircraft tending to gain ground. The current development of hybrid eVTOL aircraft intended for urban air mobility is facing many technical challenges. Among these challenges rises the optimal sizing of its hybrid power system (HPS). The latter requires an energy management strategy (EMS). In this paper, the adopted management strategy is based on filtering techniques using frequency-separation. The EMS ensures the optimal distribution of the load power requirement between the different sources while considering their limits. In addition, the optimal sizing allows to strengthen the complementarity between sources and to indirectly reduce their mass. In this work, the studied HPS consists of a fuel cell associated with an energy storage system (ESS), composed of lithium polymer batteries (Li-Po) and supercapacitors. The onboard sources are connected in parallel on the power bus through three DC-DC converters. The results of this study are presented and discussed to highlight the relevance of the proposed approach.

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Machado, Leonardo, Jay Matlock, and Afzal Suleman. "Experimental evaluation of a hybrid electric propulsion system for small UAVs." Aircraft Engineering and Aerospace Technology 92, no. 5 (November 18, 2019): 727–36. http://dx.doi.org/10.1108/aeat-06-2019-0120.

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Purpose This paper aims to experimentally evaluate the performance of a parallel hybrid propulsion system for use in small unmanned aerial vehicles (UAVs). Design/methodology/approach The objective is to combine all the individual components of the hybrid electric propulsion system (HEPS) into a modular test bench to characterize the performance of a parallel hybrid propulsion system, and to evaluate a rule-based controller based on the ideal operating line concept for the control of the power plant. Electric motor (EM) designed to supplement the power of the internal combustion engine (ICE) to reduce the overall fuel consumption, with the supervisory controller optimizing ICE torque. Findings The EM was able to supplement the power of the ICE to reduce fuel consumption, and proved the capability of acting as a generator to recharge the batteries drawing from ICE power. Furthermore, the controller showed that it is possible to reduce the fuel consumption with a HEPS when compared to its gasoline counterpart by running simulated representative UAV missions. The findings also highlighted the challenges to build and integrate the HEPS in small UAVs. Originality/value The modularity of the test bench allows each component to be changed to assess its impact on the performance of the system. This allows for further exploration and improvements of the HEPS in a controlled environment.

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Boggero, Luca, Sabrina Corpino, Andrea De Martin, Giuseppe Evangelista, Marco Fioriti, and Massimo Sorli. "A Virtual Test Bench of a Parallel Hybrid Propulsion System for UAVs." Aerospace 6, no. 7 (July 2, 2019): 77. http://dx.doi.org/10.3390/aerospace6070077.

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The article proposes the design of a test bench simulator to test a parallel hybrid propulsion architecture for aeronautical applications. The virtual test bench simulates, in a scaled version, the real test bench, designed for a power of about 0.4 MW. After presenting the architecture of the real propulsion system, the virtual test bench is described. The real system is basically composed by a paralleled electric motor and thermal engine which provide mechanical power to the propeller. Saving cost and volume the test bench is composed by electric motors simulates the behaviors of the real propulsion system despite their differences. The dynamic relationships expressing the transmission of torque between the components, and the method of down-sizing the power delivered are highlighted. Particular attention is given to the real inertia actions that must be simulated on the virtual test bench. An application of the proposed methodology is then presented through the simulation of the take-off phase, and the torque time histories, angular velocities and powers generated on the virtual test bench are used to verify the corresponding time histories expected in the real system.

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B Basavaradder, Arun, Dayananda Pai K., and Chethan K N. "Review on alternative propulsion in automotives -hybrid vehicles." International Journal of Engineering & Technology 7, no. 3 (July 8, 2018): 1311. http://dx.doi.org/10.14419/ijet.v7i3.11455.

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The dynamic diminishing in overall oil stores and proximity of stringent outflows runs the world over, have made a desperate prerequisite for the making of automobiles with upgraded effectiveness. This is the change time frame to move with elective powertrains as an Electric driven, hybrid, fuel cell models are being produced. Energy Management System (EMS) are given significance for capacity and improving the effectiveness of machines. The operation of Hybrid Electric Vehicles (HEVs) in different landscape with their fuel utilization is accounted. Hybrid powertrain like series, parallel and mixed are clarified. Testing undertaking is the appropriation of charging station situation for India and compelling use of hybrid vehicles. Battery management is the key part in HEV which require search for various methodologies are taken into for creating. The correlation of the customary motors finished with hybrid vehicles.

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Ray, Richik. "Series-Parallel Hybrid Electric Vehicle Parameter Analysis using MATLAB." International Journal for Research in Applied Science and Engineering Technology 9, no. 10 (October 31, 2021): 421–28. http://dx.doi.org/10.22214/ijraset.2021.38433.

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Abstract: In this paper, a MATLAB based Simulink model of a Series-Parallel Hybrid Electric Vehicle is presented. With the advent of Industry 4.0, the usage of Big Data, Machine Learning, Internet of Things, Artificial Intelligence, and similar groundbreaking domains of technology have usurped manual supervision in industrial as well as personal scenarios. This is aided by the drastic shift from orthodox and conventional Internal Combustion Engine based vehicles fuelled by fossil fuels in the order of petrol, diesel, etc., to fully functional electric vehicles developed by renowned companies, for example Tesla. Alongside 100% electric vehicles are hybrid vehicles that function on a system based on the integration of the conventional ICE and the modern Electric Propulsion System, which is referred to as the Hybrid Vehicle Drivetrain. Designs for modern HEVs and EVs are developed on computer software where simulations are run and all the essential parameters for the vehicle’s performance and sustainability are run and observed. This paper is articulated to discuss the parameters of a series-parallel HEV through an indepth MATLAB Simulink design, and further the observations are presented. Keywords: ICE (Internal Combustion Engine), HEV (Hybrid Electric Vehicle), Drivetrain, MATLAB, Simulink, PSD (Power Split Device), Vehicle Dynamics, SOC (State-of-Charge)

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Liu, Zhen Tong, Hong Wen He, and Wei Qing Li. "Optimization of Economy Shift Schedule for Automated Mechanical Transmission in a Parallel Hybrid Electric Vehicle." Applied Mechanics and Materials 260-261 (December 2012): 331–36. http://dx.doi.org/10.4028/www.scientific.net/amm.260-261.331.

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Power train of hybrid electric vehicle (HEV) equipped with automated mechanical transmission (AMT) is made up of engine, electric motor, batteries and propulsion system. Shift schedule can’t be worked out with the same way of conventional AMT vehicle. Based on the optimal torque distribution strategy and analysis of the driving efficiency for parallel hybrid electric vehicle (PHEV), a new economy shift schedule for PHEVs equipped with AMT is proposed to maximize the driving efficiency. The MATLAB/CRUISE co-simulation results show that the proposed shift schedule can more efficiently improve the fuel economy performance.

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He, Yapeng, Ailong Fan, Zheng Wang, Yuanchang Liu, and Wengang Mao. "Two-phase energy efficiency optimisation for ships using parallel hybrid electric propulsion system." Ocean Engineering 238 (October 2021): 109733. http://dx.doi.org/10.1016/j.oceaneng.2021.109733.

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Spinelli, Andrea, Luchien Anderson, Hossein Balaghi Enalou, Bahareh Zaghari, Timoleon Kipouros, and Panagiotis Laskaridis. "Application of Probabilistic principles to Set-Based Design for the optimisation of a hybrid-electric propulsion system." IOP Conference Series: Materials Science and Engineering 1226, no. 1 (February 1, 2022): 012064. http://dx.doi.org/10.1088/1757-899x/1226/1/012064.

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Abstract Current research in hybrid-electric aircraft propulsion has outlined the increased complexity in design when compared with traditional propulsion. However, current design methodologies rely on aircraft-level analysis and do not include the consideration of the impact of new technologies and their uncertainty. This can be a key factor for the development of future hybrid-electric propulsion systems. In this paper, we present a methodology for exploring the design space using the principles of Set-Based Design, which incorporates probabilistic assessment of requirements and multidisciplinary optimisation with uncertainty. The framework can explore every design parameter combination using a provided performance model of the system under design and evaluate the probability of satisfying a minimum required figure of merit. This process allows to quickly discard configurations incapable of meeting the goals of the optimiser. A multidisciplinary optimiser then is used to obtain the best points in each surviving configuration, together with their uncertainty. This information is used to discard undesirable configurations and build a set of Pareto optimal solutions. We demonstrate an early implementation of the framework for the design of a parallel hybrid-electric propulsion system for a regional aircraft of 50 seats. We achieve a considerable reduction to the required function evaluations and optimisation run time by avoiding the ineffective areas of the design space but at the same time maintaining the optimality potential of the selected sets of design solutions.

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Matlock, Jay, Stephen Warwick, Philipp Sharikov, Jenner Richards, and Afzal Suleman. "Evaluation of energy efficient propulsion technologies for unmanned aerial vehicles." Transactions of the Canadian Society for Mechanical Engineering 43, no. 4 (December 1, 2019): 481–89. http://dx.doi.org/10.1139/tcsme-2018-0231.

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The transition to cleaner, more efficient and longer-endurance aircraft is at the forefront of research and development in air vehicles. The focus of this research is to experimentally evaluate hybrid propulsion and energy harvesting systems in unmanned aerial vehicles (UAVs). Hybrid systems offer benefits over conventional gasoline and electric systems including lower environmental impacts, reduced fuel consumption, redundancy, and distributed propulsion. Additional energy efficiency can be achieved by harvesting some of the thermal energy of the exhaust gases. The development and experimental evaluation of a hybrid propulsion UAV was carried out at the University of Victoria Center for Aerospace Research (UVIC-CfAR) in the framework of the Green Aviation Research & Development Network (GARDN) grant. The work involved the development of a framework to evaluate UAV hybrid propulsion efficiency, and to predict the amount of power harvestable from thermoelectric generators (TEGs). The objective was to combine all of the components into a modular test bench that will allow the performance of the parallel hybrid system to be characterized and compared with theoretical results. Several experiments were performed to collect performance data of various components including a triple-TEG system connected to an engine, and system variables were modified to simulate flight profiles.

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28

Boggero, Luca, Marco Fioriti, and Sabrina Corpino. "Development of a new conceptual design methodology for parallel hybrid aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 3 (December 14, 2017): 1047–58. http://dx.doi.org/10.1177/0954410017745569.

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In this paper, an innovative methodology for the conceptual design of hybrid-powered airplanes is proposed. In particular, this work focuses on parallel hybrid architectures, in which the thermal engine is mechanically coupled to an electric motor, both supplying propulsive power during a limited number of flight phases, e.g. during takeoff and climb. This innovative solution is the subject of several studies being carried out since the current decade. In this paper, a brief overview of the works conducted by other researchers is provided. Then, an overall aircraft design methodology is proposed, which is derived from the most renewed design algorithms. The original contribution of this work is represented by the development of a methodology for the design of hybrid propulsion systems. Moreover, the proposed method is integrated within a global aircraft design methodology. In particular, several effects of the innovative system on the entire aircraft are considered, for instance the variation of the empty mass or the impacts on fuel consumption. The paper ends with some case studies of the proposed design methodology, and a discussion of the obtained results is provided.

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Finger, D. Felix, Carsten Braun, and Cees Bil. "Comparative Assessment of Parallel-Hybrid-Electric Propulsion Systems for Four Different Aircraft." Journal of Aircraft 57, no. 5 (September 2020): 843–53. http://dx.doi.org/10.2514/1.c035897.

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Zulkifli, S. A. M., M. H. Hamdan, N. Saad, and A. R. A. Aziz. "System Integration in a Through-the-Road, In-Wheel Motor Hybrid Electric Vehicle Using FPGA-Based CompactRIO and LabVIEW." Journal of the Society of Automotive Engineers Malaysia 1, no. 3 (April 28, 2021): 216–27. http://dx.doi.org/10.56381/jsaem.v1i3.68.

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A through-the-road (TTR) hybrid electric vehicle (HEV) is a sub-type of the parallel hybrid, in which the internal combustion engine (ICE) and electric motor provide propulsion power to different axles. TTR architecture allows for hybrid conversion of an existing vehicle using in- wheel motors (IWM), as alternative to on-board motor. Operation requires different types of signals to be acquired and processed: hardwire low- voltage analog signals, digital pulse-train and CAN-bus signals. This work discusses system integration in a TTR hybrid: motor controller, engine control unit (ECU) and energy management system (EMS), using FPGA- based CompactRIO controller. The EMS needs to generate an enhanced throttle signal to the ECU - bypassing the original signal from the throttle position sensor - to gain control of the internal combustion engine for proper hybrid operation.

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Sun, Xiao Xia, Yi Chun Wang, Chun Ming Shao, Yu Feng Wu, and Guo Zhu Wang. "Study of Thermal Management System for a Series-Parallel Hybrid Electric Vehicle Using Numerical Simulation." Applied Mechanics and Materials 300-301 (February 2013): 932–37. http://dx.doi.org/10.4028/www.scientific.net/amm.300-301.932.

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Advanced thermal management system (TMS) has the potential to increase the life of the vehicle’s propulsion, and meanwhile, decrease fuel consumption and pollutant emission. In this paper, an advanced TMS which is suitable for a series-parallel hybrid electric vehicle (SPHEV) is presented. Then a numerical TMS model which can predict the thermal responses of all TMS components and the temperatures of the engine and electric components is developed. By using this model, the thermal response of the TMS over a realistic driving cycle is simulated. The simulation result shows that the TMS can fulfill the heat dissipation requirement of the whole vehicle under different driving conditions. It also demonstrates that a numerical model of TMS for SPHEV is an effective tool to assess design concepts and architectures of the vehicle system during the early stage of system development.

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Lorena, Rafael Garbelini, and Eduardo Kazumi Yamakawa. "Overview of the main powertrain architectures for hybrid and electric vehicles." Semina: Ciências Exatas e Tecnológicas 42, no. 2 (December 1, 2021): 201. http://dx.doi.org/10.5433/1679-0375.2021v42n2p201.

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The research for alternative solutions to assist the propulsion, fuel converters and energy storage systems (ESS) in vehicular applications has become the focus of many institutions and mainly in the automotive industry, aiming to reduce the impacts caused by the emission of gases in the exhaust pipe and to improve energy efficiency in the worldwide vehicle fleet. Hybrid Electric Vehicles (HEV) and Electric Vehicles (EV) are currently a reality and meet this requirement to build a greener and less polluting society. In this context, this paper describes the operational characteristics of the different powertrain architectures employed in hybrid electric vehicles, including series, parallel and series-parallel topologies, as well as battery-powered and fuel cell electric vehicles. Finally, some of the elementary issues facing these advanced vehicular technologies, including the challenges for market penetration are highlighted.

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Donateo, Teresa, Ludovica Spada Chiodo, Antonio Ficarella, and Andrea Lunaro. "Improving the Dynamic Behavior of a Hybrid Electric Rotorcraft for Urban Air Mobility." Energies 15, no. 20 (October 14, 2022): 7598. http://dx.doi.org/10.3390/en15207598.

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A rising number of aerospace manufacturers are working on the development of new solutions in the field of Urban Air Mobility with increasing attention addressing electric and hybrid electric propulsive systems. Hybrid electric propulsive systems potentially offer performance improvements during transient maneuvers, as well as sustaining the engine during flight phases characterized by high power demands. Among the challenges of hybridization in rotorcraft, there is the necessity to predict the dynamic behavior and its effect on the control of rotor shaft speed. In the present study, the dynamic behavior of a parallel hybrid electric propulsive system for a coaxial-rotor air taxi is analyzed in response to a typical sequence of pilot commands that encompasses the range of operations from hover to forward flight. The system is modeled with a dynamic approach and includes sub-models for the coaxial rotors, the turboshaft engine, the electric machine, and the battery. The results of the investigation show a better performance during transients of the hybrid system than a conventional turboshaft configuration, especially if the electric contribution to the power request is coordinated to account for the lag due to slower engine dynamic response.

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Vouros, Stavros, Mavroudis Kavvalos, Smruti Sahoo, and Konstantinos Kyprianidis. "Enabling the potential of hybrid electric propulsion through lean-burn-combustion turbofans." Journal of the Global Power and Propulsion Society 5 (September 16, 2021): 164–76. http://dx.doi.org/10.33737/jgpps/140592.

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Hybrid-electric propulsion has emerged as a promising technology to mitigate the adverse environmental impact of civil aviation. Boosting conventional gas turbines with electric power improves mission performance and operability. In this work the impact of electrification on pollutant emissions and direct operating cost of geared turbofan configurations is evaluated for an 150-passenger aircraft. A baseline two-and-a-half-shaft geared turbofan, representative of year 2035 entry-into-service technology, is employed. Parallel hybridization is implemented through coupling a battery-powered electric motor to the engine low-speed shaft. A multi-disciplinary design space exploration framework is employed comprising modelling methods for multi-point engine design, aircraft sizing, performance and pollutant emissions, mission and economic analysis. A probabilistic approach is developed considering uncertainties in the evaluation of direct operating cost. Sensitivities to electrical power system technology levels, as well as fuel price and emissions taxation are quantified at different time-frames. The benefits of lean direct injection are explored along short-, medium-, and long-range missions, demonstrating 32% NO<italic><sub>x</sub></italic> savings compared to traditional rich-burn, quick-mix, lean-burn technologies in short-range operations. The impact of electrification on the enhancement of lean direct injection benefits is investigated. For hybrid-electric powerplants, the take-off-to-cruise turbine entry temperature ratio is 2.5% lower than the baseline, extending the corresponding NO<italic><sub>x</sub></italic> reductions to the level of 46% in short-range missions. This work sheds light on the environmental and economic potential and limitations of a hybrid-electric propulsion concept towards a greener and sustainable civil aviation.

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35

Fornaro, Enrico, Massimo Cardone, and Adolfo Dannier. "A Comparative Assessment of Hybrid Parallel, Series, and Full-Electric Propulsion Systems for Aircraft Application." IEEE Access 10 (2022): 28808–20. http://dx.doi.org/10.1109/access.2022.3158372.

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36

Bajec, P., B. Pevec, and D. Miljavec. "Optimal control of brushless PM motor in parallel hybrid propulsion system." Mechatronics 20, no. 4 (June 2010): 464–73. http://dx.doi.org/10.1016/j.mechatronics.2010.04.004.

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Cardone, Massimo, Bonaventura Gargiulo, and Enrico Fornaro. "Modelling and Experimental Validation of a Hybrid Electric Propulsion System for Light Aircraft and Unmanned Aerial Vehicles." Energies 14, no. 13 (July 1, 2021): 3969. http://dx.doi.org/10.3390/en14133969.

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This article presents a numerical model of an aeronautical hybrid electric propulsion system (HEPS) based on an energy method. This model is designed for HEPS with a total power of 100 kW in a parallel configuration intended for ultralight aircraft and unmanned aerial vehicles (UAV). The model involves the interaction between the internal combustion engine (ICE), the electric motor (EM), the lithium battery and the aircraft propeller. This paper also describes an experimental setup that can reproduce some flight phases, or entire missions, for the reference aircraft class. The experimental data, obtained by reproducing two different take-offs, were used for model validation. The model can also simulate anomalous operating conditions. Therefore, the tests chosen for the model validation are characterized by the EM flux weakening (“de-fluxing”). This model is particularly suitable for preliminary stages of design when it is necessary to characterize the hybrid system architecture. Moreover, this model helps with the choice of the main components (e.g., ICE, EM, and transmission gear ratio). The results of the investigation conducted for different battery voltages and EM transmission ratios are shown for the same mission. Despite the highly simplified model, the average margin of error between the experimental and simulated results was generally under 5%.

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Yezeguelian, Axel, and Askin T. Isikveren. "Methods to improve UAV performance using hybrid-electric architectures." Aircraft Engineering and Aerospace Technology 92, no. 5 (April 16, 2020): 685–700. http://dx.doi.org/10.1108/aeat-11-2019-0227.

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Purpose When comparing and contrasting different types of fixed-wing military aircraft on the basis of an energetic efficiency figure-of-merit, unmanned aerial vehicles (UAVs) dedicated to tactical medium-altitude long-endurance (MALE) operations appear to have significant potential when hybrid-electric propulsion and power systems (HEPPS) are implemented. Beginning with a baseline Eulair drone, this paper aims to examine the feasibility of retro-fitting with an Autarkic-Parallel-HEPPS architecture to enhance performance of the original single diesel engine. Design/methodology/approach In view of the low gravimetric specific energy performance attributes of batteries in the foreseeable future, the best approach was found to be one in which the Parallel-HEPPS architecture has the thermal engine augmented by an organic rankine cycle (ORC). For this study, with the outer mould lines fixed, the goal was to increase endurance without increasing the Eulair drone maximum take-off weight beyond an upper limit of +10%. The intent was to also retain take-off distance and climb performance or, where possible, improve upon these aspects. Therefore, as the focus of the work was on power scheduling, two primary control variables were identified as degree-of-hybridisation for useful power and cut-off altitude during the en route climb phase. Quasi-static methods were used for technical sub-space modelling, and these modules were linked into a constrained optimisation algorithm. Findings Results showed that an Autarkic-Parallel-HEPPS architecture comprising an ORC thermal energy recovery apparatus and high-end year-2020 battery, the endurance of the considered aircraft could be increased by 11%, i.e. a total of around 28 h, including de-icing system, in-flight recharge and emergency aircraft recovery capabilities. The same aircraft with the de-icing functionality removed resulted in a 20% increase in maximum endurance to 30 h. Practical implications Although the adoption of Series/Parallel-HEPPS only solutions do tend to generate questionable improvements in UAV operational performance, combinations of HEPPS with energy recovery machines that use, for example, an ORC, were found to have merit. Furthermore, such architectural solutions could also offer opportunity to facilitate additional functions like de-icing and emergency aircraft recovery during engine failure, which is either not available for UAVs today or prove to be prohibitive in terms of operational performance attributes when implemented using a conventional PPS approach. Originality/value This technical paper highlights a new degree of freedom in terms of power scheduling during climbing transversal flight operations. A control parameter of cut-off altitude for all types of HEPPS-based aircraft should be introduced into the technical decision-making/optimisation/analysis scheme and is seen to be a fundamental aspect when conducting trade-studies with respect to degree-of-hybridisation for useful power.

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Redkin, A. V., Yu A. Yaloza, and I. E. Kovalev. "Reliability assessment of convertible aircraft with hybrid propulsion system and multirotor lifting system." Civil Aviation High Technologies 23, no. 5 (October 28, 2020): 76–96. http://dx.doi.org/10.26467/2079-0619-2020-23-5-76-96.

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Projects and experimental models of innovative concepts of VTOL aircraft with a hybrid propulsion system are attracting great interest and investment inflow all over the world. In this regard, when developing new concepts, it is important to understand how much better they will be than the currently operated rotorcraft and convertible aircraft in terms of reliability and flight safety, to be able to use them for passenger transportation in the future. In addition, when designing and choosing the optimal layout, it is necessary to know the contribution of each element and unit to the reliability of the aircraft as a whole in order to meet the requirements. To calculate the reliability indicators, the method of structural diagrams was chosen, and the calculation methodology was developed. The general classification of modern innovative concepts of convertible aircraft is considered, schematic diagram of hybrid propulsion system and its main parameters are determined. The article discusses the influence of the number of lifting rotor groups and their location on the possibility to continue the flight in hover mode in case of failure of one rotor group, the necessary power reserve of lifting electric motors is determined to ensure the given safety condition. In accordance with the adopted structural diagram, the main functional groups of the hybrid propulsion system of convertible aircraft operating in different flight modes are determined. The basic modes of a typical flight profile of a convertible aircraft are considered, time intervals characteristic for each mode are set. For each flight mode, a structural scheme of reliability of functional groups of a hybrid propulsion system is constructed, having a serial or parallel connection of elements, depending on their influence on the consequences of failure, the equation for calculating the probability of fail-free operation is derived. For lifting rotor groups, a combination of critical failures of more than one group is considered, and the equation is composed to calculate the probability of a catastrophic event in hover mode. Based on the obtained equations, the resulting calculation of the probability of fail-free operation, the probability of failure per flight hour for each flight mode was carried out separately and in total for the entire flight. Thus, for all flight modes, the probabilities of a catastrophic and emergency event, as well as a difficult situation in flight, are considered. A comprehensive analysis of the obtained results of reliability indicators calculation for convertible aircraft with six lifting rotors and two turboprop engines made it possible to conclude that it meets the requirements of the 25th part of aviation regulations for transport aircraft. A good potential margin of up to 10-2 was determined for the probability of a catastrophic failure in take-off, landing and transitional modes. The elements and subsystems that are critical for fail-free operation are identified, and ways to improve their reliability and the aircraft as a whole are proposed.

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40

Harmon, Frederick G., Andrew A. Frank, and Sanjay S. Joshi. "The control of a parallel hybrid-electric propulsion system for a small unmanned aerial vehicle using a CMAC neural network." Neural Networks 18, no. 5-6 (July 2005): 772–80. http://dx.doi.org/10.1016/j.neunet.2005.06.030.

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41

Wang, B.-H., J.-W. Zhang, and Y.-G. Luo. "The rapid development of a parallel hybrid propulsion control system by an online calibrating system." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 221, no. 12 (December 2007): 1555–56. http://dx.doi.org/10.1243/09544070jauto278.

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42

Nasoulis, Christos P., Georgios Protopapadakis, Vasilis G. Gkoutzamanis, and Anestis I. Kalfas. "The impact of propulsive architecture on the design of a 19-passenger hybrid-electric aircraft." IOP Conference Series: Materials Science and Engineering 1226, no. 1 (February 1, 2022): 012074. http://dx.doi.org/10.1088/1757-899x/1226/1/012074.

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Abstract The electrification of aircraft is an on-going endeavor, currently examined intensively in the general aviation class. However, for the commuter class, the proper selection of the hybrid-electric propulsive architecture is instrumental, to fully exploit the electrification benefit. Within this work, a comparison of two 19-seater aircraft with different hybrid-electric propulsive components is made, using an in-house aircraft conceptual design tool. The first aircraft is based on a twin-turboprop parallel-hybrid configuration that cruises at low Mach number speeds and altitude. On the other hand, the second aircraft variant is based on a tri-fan series/parallel-hybrid configuration with an aft Boundary Layer Ingestion system that operates at both higher altitude and Mach numbers. A design space exploration is performed where different degrees of hybridization and batteries specific energy are considered, to define the technological requirements for each architecture. The evaluation of the propulsive architectures is based on block fuel reduction, overall mission duration, direct operating costs and total environmental impact. The results aim to quantify the benefits of each configuration and determine the one with the closest entry into service. Finally, it is observed that the overall environmental impact reduces by 26 % and 17 % for the turboprop and turbofan variants respectively.

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Duan, Buren, Haonan Zhang, Lizhi Wu, Zuohao Hua, Zijing Bao, Ning Guo, Yinghua Ye, and Ruiqi Shen. "Acceleration characteristics of laser ablation Cu plasma in the electrostatic field." European Physical Journal Applied Physics 93, no. 2 (February 2021): 20802. http://dx.doi.org/10.1051/epjap/2021200349.

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As a new concept of space propulsion system, laser-ablation propulsion has attracted more and more attention due to its characteristics of low power consumption, high specific impulse, variable and controllable thrust. With an aim to further raise up the movement velocity of plasma, we combine the laser with high-voltage electrostatic field to accelerate the Cu plasma induced by laser ablation. To demonstrate the acceleration characteristics of plasma under different electric field intensity, the plasma conductivity, plasma shockwave intensity and plasma plume movement process were tested using parallel electrode plate device, self-made torsion pendulum impulse test bench and high-speed ICCD camera. The results showed that the conductive current and impulse formed by the plasma obviously increased under the applied electric field. The images captured by high-speed ICCD camera showed the plasma cross-sectional area was 0.194 mm2 at 900 ns and 0.217 mm2 at 1600 ns when the electric field intensity was 0 V/mm. With the electric field intensity increased to 30 V/mm, the plasma cross-sectional area elevated to 0.280 mm2 at 900 ns and 0.288 mm2 at 1600 ns. The acquisitions prove that the idea of this paper is feasible and favorable, which provide a theoretical basis for the combination of laser ablation propulsion and electric field.

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Ionaş, M., V. Argeşanu, and N. Lontiş. "Comparative numerical evaluation of ECE-EUDC cycle performances of a hypothetical car equipped with three types of propulsion systems: conventional, series hybrid and parallel hybrid." IOP Conference Series: Materials Science and Engineering 1220, no. 1 (January 1, 2022): 012019. http://dx.doi.org/10.1088/1757-899x/1220/1/012019.

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Abstract This publication refers to the studies which were made to a compact car model to observe the behavior of the three drivetrain versions that the car can be equipped with: the version in which the vehicle model is equipped only with a Diesel engine (classic), a plug-in hybrid version with the combustion engine placed in a series circuit (pSHEV) and a second plug-in hybrid variant, where the thermal engine is arranged in parallel (pPHEV) with the electric motor (EM). The study emphasizes the behavior of three different vehicle propulsion systems equipped on the compact car on a standardized road cycle condition defined by the Urban Driving Cycle (UDC) referred as ECE 15 cycle combined with the Extra-Urban Driving Cycle (EUDC). The scope is to set up the three different powertrain systems through numerical modeling and to generate the conclusions based on the simulations results obtained in ADvanced VehIcle SimulatOR (ADVISOR).

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Spinelli, Andrea, Hossein Balaghi Enalou, Bahareh Zaghari, Timoleon Kipouros, and Panagiotis Laskaridis. "Application of Probabilistic Set-Based Design Exploration on the Energy Management of a Hybrid-Electric Aircraft." Aerospace 9, no. 3 (March 8, 2022): 147. http://dx.doi.org/10.3390/aerospace9030147.

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The energy management strategy of a hybrid-electric aircraft is coupled with the design of the propulsion system itself. A new design space exploration methodology based on Set-Based Design is introduced to analyse the effects of different strategies on the fuel consumption, NOx and take-off mass. Probabilities are used to evaluate and discard areas of the design space not capable of satisfying the constraints and requirements, saving computational time corresponding to an average of 75%. The study is carried on a 50-seater regional turboprop with a parallel hybrid-electric architecture. The strategies are modelled as piecewise linear functions of the degree of hybridisation and are applied to different mission phases to explore how the strategy complexity and the number of hybridised segments can influence the behaviour of the system. The results indicate that the complexity of the parametrisation does not affect the trade-off between fuel consumption and NOx emissions. On the contrary, a significant trade-off is identified on which phases are hybridised. That is, the least fuel consumption is obtained only by hybridising the longest mission phase, while less NOx emissions are generated if more phases are hybridised. Finally, the maximum take-off mass was investigated as a parameter, and the impact to the trade-off between the objectives was analysed. Three energy management strategies were suggested from these findings, which achieved a reduction to the fuel consumption of up to 10% and a reduction to NOx emissions of up to 15%.

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Łosiewicz, Zbigniew, Waldemar Mironiuk, Witold Cioch, Ewelina Sendek-Matysiak, and Wojciech Homik. "Application of Generator-Electric Motor System for Emergency Propulsion of a Vessel in the Event of Loss of the Full Serviceability of the Diesel Main Engine." Energies 15, no. 8 (April 13, 2022): 2833. http://dx.doi.org/10.3390/en15082833.

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Oil tanker disasters have been a cause of major environmental disasters, with multi-generational impacts. One of the greatest hazards is damage to the propulsion system that causes the ship to turn sideways to a wave and lose stability, which in storm conditions usually leads to capsizing and sinking Despite the perceived consequences of maritime disasters in the current solutions for the propulsion of oil tankers, there are no legal or real solutions for independent emergency main propulsion in this type of ship. Stressing that the reliability of the propulsion system has a significant impact on the ship’s safety at sea, the authors presented a new solution in the form of a power take-off/power take-in (PTO/PTI) system. This is the emergency use of a shaft generator as the main electric motor, operating in parallel in a situation when the main engine (ME), (the main engine of the ship’s direct high-power propulsion system that is slow-speed) loses the operational capability to propel the ship. Since one cause of wear, or failure, of the main engines is improper operational decisions, the paper shows the wear mechanism in relation to the accuracy of operational decisions. Using classical reliability theory, it also shows that the use of the proposed system results in an increase in the reliability of the propulsion system. The main topic of the paper was the use of an electrical system called PTO/PTI as an emergency propulsion system on the largest commercial vessels, such as bulk carriers and crude oil tankers, which has not been used before in maritime technical solutions. Semi-Markov processes, continuous in time, discrete in states, and which are used in technology, were also proposed as a tool describing the process of the operation of such a ship propulsion system, and they are useful to support operational decisions affecting the state of the technical condition of the engine. There are two ship operation strategies that can be adopted: the four-state model, for normal operation, and the three-state model, which operates with the occurrence of failure. For these types of models, their limiting distributions were defined in the form of probabilities. It was also demonstrated that faster than expected engine wear and the occurrence of inoperability of the main engine can be caused by wrong operational decisions made by the shipowner or crew. Using this type of main engine operating methodology, it is possible to support the decision of the engineer to stop the main engine and to subject it to the process of restoration to an acceptable state of technical condition (before the failure or during the failure in severe storm conditions), with the parallel use of the proposed electric propulsion (PTO/PTI) as an emergency propulsion, giving the crew a chance to maintain the steering necessary to maintain safe lateral stability.

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Adler, Eytan J., Benjamin J. Brelje, and Joaquim R. R. A. Martins. "Thermal Management System Optimization for a Parallel Hybrid Aircraft Considering Mission Fuel Burn." Aerospace 9, no. 5 (April 26, 2022): 243. http://dx.doi.org/10.3390/aerospace9050243.

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Electrified aircraft propulsion enables new aircraft designs with fewer emissions. One challenge of electrified architectures is handling the electrical components’ waste heat. This is because batteries and other electrical components are sensitive to high temperatures and accumulate heat within their structure. In this work, we investigate using a thermoacoustic refrigerator to cool the battery of a parallel hybrid single-aisle commercial transport aircraft. This thermoacoustic refrigeration system is powered by waste heat from the turbofan engine core, whereas a conventional refrigerator consumes electricity from the battery or shaft power offtakes. Compared to a conventional vapor cycle refrigerator, the thermoacoustic refrigeration system results in greater mission fuel burn because of pressure losses attributable to the extraction of heat from the turbofan to drive the thermoacoustic refrigerator. Heat exchangers with very low pressure losses may render the thermoacoustic refrigeration system beneficial compared to conventional refrigeration in certain use cases, such as low-altitude missions.

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Adler, Eytan J., Benjamin J. Brelje, and Joaquim R. R. A. Martins. "Thermal Management System Optimization for a Parallel Hybrid Aircraft Considering Mission Fuel Burn." Aerospace 9, no. 5 (April 26, 2022): 243. http://dx.doi.org/10.3390/aerospace9050243.

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Electrified aircraft propulsion enables new aircraft designs with fewer emissions. One challenge of electrified architectures is handling the electrical components’ waste heat. This is because batteries and other electrical components are sensitive to high temperatures and accumulate heat within their structure. In this work, we investigate using a thermoacoustic refrigerator to cool the battery of a parallel hybrid single-aisle commercial transport aircraft. This thermoacoustic refrigeration system is powered by waste heat from the turbofan engine core, whereas a conventional refrigerator consumes electricity from the battery or shaft power offtakes. Compared to a conventional vapor cycle refrigerator, the thermoacoustic refrigeration system results in greater mission fuel burn because of pressure losses attributable to the extraction of heat from the turbofan to drive the thermoacoustic refrigerator. Heat exchangers with very low pressure losses may render the thermoacoustic refrigeration system beneficial compared to conventional refrigeration in certain use cases, such as low-altitude missions.

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He, Xu, Hongming Xu, Huw Williams, Quan Zhou, and Ji Li. "Fuzzy Logic based Power-Split Hybrid Propulsion Control System using Digital Twin Assisted Parallel Learning." International Journal of Powertrains 11, no. 4 (2022): 1. http://dx.doi.org/10.1504/ijpt.2022.10048469.

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50

Li, Ji, Quan Zhou, Huw Williams, Hongming Xu, and Xu He. "Fuzzy logic based power-split hybrid propulsion control system using digital twin assisted parallel learning." International Journal of Powertrains 11, no. 4 (2022): 288. http://dx.doi.org/10.1504/ijpt.2022.127858.

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