scholarly journals Design of hybrid electric heavy fuel MALE ISR UAV enabling technologies for military operations

2020 ◽  
Vol 92 (5) ◽  
pp. 745-755
Author(s):  
Marco Fioriti ◽  
Silvio Vaschetto ◽  
Sabrina Corpino ◽  
Giovanna Premoli
Keyword(s):  
Propulsion System ◽  
Military Operations ◽  
Safety Level ◽  
Content Type ◽  
Hybrid Propulsion ◽  
Electric System ◽  
Operating Modes ◽  
Enabling Technologies ◽  
Aerial Vehicle ◽  
Hybrid Electric

Purpose This paper aims to present the main results achieved in the frame of the TIVANO national-funded project which may anticipate, in a stepped approach, the evolution and the design of the enabling technologies needed for a hybrid/electric medium altitude long endurance (MALE) unmanned aerial vehicle (UAV) to perform persistent intelligence surveillance reconnaissance (ISR) military operations. Design/methodology/approach Different architectures of hybrid-propulsion system are analyzed pointing out their operating modes to select the more suitable architecture for the reference aircraft. The selected architecture is further analyzed together with its electric power plant branch focusing on electric system architecture and the selected electric machine. A final comparison between the hybrid and standard propulsion is given at aircraft level. Findings The use of hybrid propulsion may lead to a reduction of the total aircraft mass and an increase in safety level. However, this result comes together with a reduced performance in climb phase. Practical implications This study can be used as a reference for similar studies and it provides a detailed description of propulsion operating modes, power management, electric system and machine architecture. Originality/value This study presents a novel application of hybrid propulsion focusing on a three tons class MALE UAV for ISR missions. It provides new operating modes of the propulsion system and a detailed electric architecture of its powertrain branch and machine. Some considerations on noise emissions and infra-red traceability of this propulsion, at aircraft level.

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.

Life Cycle Analysis for a Powertrain in a Concept for Electric Power Generation in a Hybrid Electric Aircraft

2020 ◽  
Author(s):  
Michael Schneider ◽  
Jens Dickhoff ◽  
Karsten Kusterer ◽  
Wilfried Visser
Keyword(s):  
Life Cycle ◽  
Gas Turbine ◽  
Electric Propulsion ◽  
Aircraft Engine ◽  
Propulsion System ◽  
Civil Aviation ◽  
Propulsion Systems ◽  
Hybrid Propulsion ◽  
Hybrid Electric ◽  
The Impact

Abstract In the recent decades, civil aviation was growing 4.7% per annum. In order to reduce emissions promoting the global warming process, alternative propulsion systems are needed. Full-electric propulsion systems in aviation might have the potential for emission-free flights using renewable energy. However, several research efforts indicate electric propulsion only seems feasible for small aircraft. Especially due to the low energy density of batteries compared to fossil fuels. For this reason, hybrid propulsion systems came into focus, combining the benefits of all-electric and conventional propulsion system concepts. It is also considered as bridging technology, system test and basis for component development — and therewith paves the way towards CO2 free aviation. In the ‘HyFly’ project (supported by the German Luftfahrtforschungsprogramm LuFo V-3), the potential of a hybrid electric concept for a short/mid-range 19 PAX aircraft is assessed — not only on system but also on single component basis. In a recent study, the propulsion architecture and the operating mode of the gas turbine and the electric components have been defined [1]. In this paper, the advantages of the hybrid propulsion architecture and a qualitative assessment of component life are presented. Methods for life time prediction for the aircraft engine, the electric motor, the reluctance generator and the battery are discussed. The impact of turbine inlet temperature on life consumption is analyzed. The life cycle of the aircraft engine and the electric components including gradual component deterioration and consequent performance degradation is simulated by using an in-house gas turbine simulation tool (GTPsim). Therefore, various effects on electric propulsion system can be predicted for the entire drivetrain system in less than one hour.

Conceptual study of a mechanically integrated parallel hybrid electric turbofan

2018 ◽  
Vol 232 (14) ◽  
pp. 2688-2712 ◽  
Author(s):  
Arne Seitz ◽  
Markus Nickl ◽  
Anne Stroh ◽  
Patrick C Vratny
Keyword(s):  
Power Plant ◽  
Distribution System ◽  
Power Plants ◽  
Selection Procedure ◽  
Performance Study ◽  
Hybrid Propulsion ◽  
Electric System ◽  
Parallel Hybrid ◽  
Hybrid Electric ◽  
Aircraft Application

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.

Ground simulation of fuel cell/battery hybrid propulsion system for small unmanned air vehicles

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Sinan Keiyinci ◽  
Kadir Aydin
Keyword(s):  
Fuel Cell ◽  
Energy Density ◽  
Hybrid System ◽  
Proton Exchange ◽  
Propulsion System ◽  
Unmanned Air Vehicles ◽  
Power Sources ◽  
Content Type ◽  
Hybrid Propulsion ◽  
Air Vehicles

Purpose The endurance of small unmanned air vehicles (UAVs) is directly associated with the energy density of the propulsion system used. As the batteries commonly used in small UAVs have a relatively low energy density, they are not sufficient for long-term endurance tasks. The purpose of this paper is to offer a solution to increase the endurance of a concept small UAV with combination of different power sources. The design, construction and ground tests of fuel cell-powered hybrid propulsion systems are presented in this paper. Design/methodology/approach The power requirements of a concept UAV were calculated according to aerodynamic calculations and then, hybrid propulsion system sources are determined. The hybrid system consists of a 100 W scale proton-exchange membrane (PEM) type fuel cell stack, lithium-polymer battery, solar cells and power management system (PMS). Subsequently, this hybrid power system was integrated with the new design of PMS and then series of ground tests were carried out. Findings This experimental study proved that it is theoretically possible to obtain an endurance of around 3 h for concept UAV with the proposed hybrid system. Practical implications The research study shows that fuel cell-based hybrid propulsion system with the proposed PMS can be widely used to obtain extended endurance in small UAVs. Originality/value A hybrid propulsion system with a novel PMS unit is proposed for small UAVs and the ground tests were implemented.

Energy management-based design of a Wankel hybrid-electric UAV

2019 ◽  
Vol 92 (5) ◽  
pp. 701-715
Author(s):  
Teresa Donateo ◽  
Antonio Ficarella ◽  
Claudia Lucia De Pascalis
Keyword(s):  
Energy Management ◽  
Thermal Power ◽  
Fuel Saving ◽  
Energy Management Strategy ◽  
Content Type ◽  
Operating Modes ◽  
Point Analysis ◽  
Maximum Payload ◽  
Hybrid Electric ◽  
Wankel Engine

Purpose The purpose of this study is to investigate the optimization of design and energy management in a parallel hybrid-electric powertrain to replace the conventional engine of an existing tactical unmanned aerial vehicle (UAV) equipped with a Wankel engine with a pre-defined flight mission. The proposed powertrain can work in four different operating modes: electric, thermal, power-assist and charging. Design/methodology/approach The power request at propeller axis of each flight segment is used as input for an in-house model that calculates the overall fuel consumption throughout the mission (Mfuel) and the maximum payload weight (Wpay) by means of an average-point analysis. These outputs depend on the energy management strategy that is expressed by the power-split ratio between engine and electric phase (Uphase) of each mission phase, according to which the components of the hybrid system are sized. The in-house model is integrated into an optimization framework to find the optimal set of Uphase and battery size that minimizes Mfuel and maximizes Wpay. Findings It was found a 3.24% saving of the fuel mass burned throughout the mission (or, alternative an improvement of endurance by 4.3%) with about the same maximum-payload mass (+0.2%) of the original configuration, or a smaller fuel saving with +11% more payload. The fuel saving of 3.24% corresponds to −3.25% in total emissions of CO2 and a 2.34% reduction of the cost-per-mission. Practical implications This study demonstrates that environmental advantages, even if limited, can be already obtained from optimal design and management of the hybrid power system with today technologies while waiting for further benefits from the introduction of advanced technologies for batteries and electric machines. Originality/value The main novelties are the design of the powertrain on the basis of the energy management and the application of scalability and hybridization to Wankel engines.

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.

Evaluating the Performances of Advanced Powertrains

Volume 2 ◽  
2004 ◽  
Author(s):  
Massimo Feola ◽  
Fabrizio Martini ◽  
Stefano Ubertini
Keyword(s):  
Fuel Consumption ◽  
Electric Vehicle ◽  
Electric Vehicles ◽  
Hybrid Electric Vehicle ◽  
Hybrid Electric Vehicles ◽  
Hybrid Vehicles ◽  
Propulsion System ◽  
Road Vehicles ◽  
Hybrid Propulsion ◽  
Hybrid Electric

Over the last few decades a tremendous effort has been made to reduce road vehicles engines contribution to air pollution and fuel consumption. Due to the more stringent limits imposed by governments, various manufactures started working in the incorporation of alternative powertrain configurations, such as pure electric vehicles (EV), hybrid electric vehicles (HEV) and fuel cell vehicles (FCV), in the automotive consumer market. In order to appreciate the advantages and disadvantages of these new vehicles over conventional vehicles a comparison must be performed in terms of efficiency and pollutant emissions. However, hybrid vehicles comprise many components with at least two different energy conversion devices (i.e. internal combustion engine and electric machine) drawing energy from at least two different energy storage devices (i.e. fuel tank and battery). In recent times, many hybrid propulsion system configurations have emerged and many others can be imagined comprising multiple reversible and irreversible energy paths. Therefore, considering that in a hybrid vehicle at least two different forms of energy (i.e. fuel chemical energy and electricity) are consumed, fuel consumption alone is no more sufficient to give a measure of the effectiveness of a hybrid propulsion system. This paper presents a first attempt to give a general mathematical form of the traction energy, the global efficiency and the specific fuel consumption of a hybrid electric vehicle that recovers as particular cases the thermal vehicle and the series hybrid electric vehicle. To evaluate the efficiency of the generic propulsion system the complete process from fuel energy and electricity to power available at the wheels is considered. The introduced concept of equivalent fuel consumption can be the basis for the comparison between road vehicles whatever the powertrain is pure thermal or hybrid. In order to get a better understanding of the mathematical analysis and its potential effectiveness some numerical simulations of hybrid vehicles virtual prototypes are performed through a suitable simulation model. The aim of the present analysis is to provide an instrument that allow a quick evaluation of the performances of hybrid electric vehicles.

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