scholarly journals Indirect engine sizing via distributed hybrid-electric unmanned aerial vehicle state-of-charge-based parametrisation criteria

2019 ◽  
Vol 233 (14) ◽  
pp. 5360-5368
Author(s):  
S Wang ◽  
JT Economou ◽  
A Tsourdos
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Electric Propulsion ◽  
Combustion Engine ◽  
Electrical Power ◽  
Propulsion System ◽  
State Of Charge ◽  
Electrical System ◽  
Starting Conditions ◽  
Aerial Vehicle ◽  
Hybrid Electric

This paper presents a design process for the challenging problem of sizing the engine pack for a distributed series hybrid-electric propulsion system of unmanned aerial vehicle. Sizing the propulsion system for hybrid-electric unmanned aerial vehicles is a demanding problem because of the two different categories of propulsion (the engine and the motor), and the electrical system characteristics. Furthermore, what adds to the difficulty is that the internal combustion engine does not directly drive the propellers, but it is connected to an electrical generator and therefore provides electrical power to the electric motors and propellers. Hence there is a clear distinction from the traditional engine solutions which are mechanically coupled to the propeller. This paper addresses this specific distinction and proposes an indirect solution based on properties on the electrical part of the system. In particular, a novel parametric characterisation engine sizing approach is presented using the battery pack state-of-charge during a realistic unmanned aerial vehicle flight scenario. Five candidate engine options were considered with different starting conditions for the electrical system. The results show that by using the state-of-charge properties it is possible to select an appropriate size of engine pack while carrying a suitable electrical propulsion pack. However, the solutions are not unique and are appropriate for given design criteria clearly indicated in the paper.

scholarly journals Development of a Lumped Parameter Model for an Aeronautic Hybrid Electric Propulsion System

Aerospace ◽  
2018 ◽  
Vol 5 (4) ◽  
pp. 105 ◽  
Author(s):  
Emma Frosina ◽  
Adolfo Senatore ◽  
Luka Palumbo ◽  
Giuseppe Di Lorenzo ◽  
Ciro Pascarella
Keyword(s):  
Electric Propulsion ◽  
Combustion Engine ◽  
Propulsion System ◽  
General Aviation ◽  
Lumped Parameter Model ◽  
Engine Exhaust ◽  
Electric Propulsion System ◽  
Lumped Parameter ◽  
Hybrid Electric ◽  
The University

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.

scholarly journals Modelling and Experimental Validation of a Hybrid Electric Propulsion System for Light Aircraft and Unmanned Aerial Vehicles

Energies ◽  
2021 ◽  
Vol 14 (13) ◽  
pp. 3969
Author(s):  
Massimo Cardone ◽  
Bonaventura Gargiulo ◽  
Enrico Fornaro
Keyword(s):  
Unmanned Aerial Vehicles ◽  
Model Validation ◽  
Electric Propulsion ◽  
Combustion Engine ◽  
Propulsion System ◽  
Operating Conditions ◽  
Total Power ◽  
Electric Propulsion System ◽  
Aerial Vehicles ◽  
Hybrid Electric

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%.

Performance Assessment of an Integrated Parallel Hybrid-Electric Propulsion System Aircraft

2019 ◽  
Author(s):  
Smruti Sahoo ◽  
Xin Zhao ◽  
Konstantinos G. Kyprianidis ◽  
Anestis Kalfas
Keyword(s):  
Performance Assessment ◽  
Electric Propulsion ◽  
Electrical Power ◽  
Propulsion System ◽  
System Level ◽  
Electric Propulsion System ◽  
The Core ◽  
Parallel Hybrid ◽  
Overall Efficiency ◽  
Hybrid Electric

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.

Experimental evaluation of a hybrid electric propulsion system for small UAVs

2019 ◽  
Vol 92 (5) ◽  
pp. 727-736
Author(s):  
Leonardo Machado ◽  
Jay Matlock ◽  
Afzal Suleman
Keyword(s):  
Fuel Consumption ◽  
Electric Propulsion ◽  
Test Bench ◽  
Combustion Engine ◽  
Propulsion System ◽  
Content Type ◽  
Hybrid Propulsion ◽  
Electric Propulsion System ◽  
Parallel Hybrid ◽  
Hybrid Electric

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.

Simulation of a High Fidelity Turboshaft Engine-Alternator Model for Turboelectric Propulsion System Design and Applications

2018 ◽  
Vol 0 (0) ◽  
Author(s):  
I. Yazar
Keyword(s):  
System Design ◽  
Electric Propulsion ◽  
Combustion Engine ◽  
Open Loop ◽  
Propulsion System ◽  
High Fidelity ◽  
Propulsion Systems ◽  
The Real ◽  
Hybrid Electric ◽  
Turboshaft Engine

Abstract The term sustainability became a popular subject both in the automotive industries and in the aerospace industries. Increasing and threatening environmental pollution problems and reduction in limited fuel sources are motivating either industries and academicians to develop alternative power systems to sustain more healthier and economical life in the long term. One innovation that has been researched in the automotive industry is all electric and hybrid electric propulsion concepts. These concepts have also been proposed as alternative solutions for aviation. These novel propulsion technologies are composed of a gas turbine/internal combustion engine structure (necessary for hybrid electric and turboelectric propulsion systems) and/or energy storage components (battery, fuel cell and so on.) with multiple electric motors respectively. In this paper, simulation of a high fidelity turboshaft engine-alternator model for turboelectric propulsion system is derived. To develop an aero-thermal engine model, GE T700 turboshaft engine data is used and constructed model is connected to an alternator model on MATLAB/Simulink environment. Open-loop simulations are carried out and satisfactory results are obtained.Simulation results are compared to the real engine design point data. Results show that there are acceptable differences between the simulation results and the real engine data. The power balances between compressor - high pressure turbine and power turbine – alternator are proven in the mathematical model. It is expected that the proposed model can be easily extended to power system design and power management studies in turboelectric propulsion systems and also in other suitable novel propulsion systems.

scholarly journals Development of Lumped Parameter Model for an Aeronautic Hybrid-Electric Propulsion System

2018 ◽  
Author(s):  
Emma Frosina ◽  
Adolfo Senatore ◽  
Luca Palumbo ◽  
Giuseppe Di Lorenzo ◽  
Ciro Pascarella
Keyword(s):  
Electric Propulsion ◽  
Combustion Engine ◽  
Propulsion System ◽  
General Aviation ◽  
Lumped Parameter Model ◽  
Engine Exhaust ◽  
Electric Propulsion System ◽  
Lumped Parameter ◽  
Hybrid Electric ◽  
Reduce Emissions

This paper describes a case study for applying of hybrid-electric propulsion system for a general aviation aircraft. The work was performed by a joint team of CIRA and the Department of Industrial Engineering of the University of Naples “Federico II”. Electric and hybrid electric propulsion for aircraft has gained widespread and significant attention over the past decade. The driver for industry interest has principally been the need to reduce emissions of combustion engine exhaust products and noise, but increasingly studies revealed potential for overall improvement in energy efficiency and mission flexibility of new aircraft types. The project goal was to demonstrate feasibility of aeronautic parallel hybrid-electric propulsion for a Light aircraft varying the mission profiles and the electric configuration. Through a creation, and application, of a global model, with software AMESim®, in which it can be represented everything about the components chosen by the industrial partners, some interesting considerations are carried out. In particular, it was confirmed that with the only integration of state of the art technologies, for some particular missions, the advantages of aircraft hybrid-electric propulsion, for light aircraft, are notable.

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