400 kW 12000 rpm Electric Generator Prototype for Aircraft Hybrid Propulsion System Demonstrator

In recent years, a renewed interest in the development of unmanned air vehicles (UAVs) led to a wide range of interesting applications in the fields of reconnaissance and surveillance. In these types of mission, the noise produced by propeller driven UAVs is a major drawback, which can be partially solved by installing an electric motor to drive the propeller. The evolution of high performance brushless motors makes electric propulsion particularly appealing, at least for small and medium size UAVs. All electric propulsion systems developed to date are though penalized by the limited range/endurance that can be provided by a reasonably sized battery pack. In this paper we propose a hybrid propulsion system based on a recently developed, high efficiency microturbine which can be used to power an electric generator, thus providing a significant range/mission time extension. The UMTG is undergoing operational testing in our Laboratory, to identify its most suitable configuration and to improve its performance: a new compact regenerative combustion chamber was developed and several tests were performed to reduce its weight and size so as to increase the vehicle payload. In a high range/endurance mission the ultramicro turbine drives the electrical motor that powers the propeller only during the cruise phase (the so-called “transfer to target”), while in the final approach, in which a quiet flight attitude is mandatory, a (smaller) battery pack drives the motor directly and the UMTG is turned off. The mission requirements considered for the preliminary design of the UAV consist of a long endurance (> 12 hours) step, with a cruise speed of 33.3 m/s and a dash speed of 45 m/s at an altitude of 5000 meters. The maximum take-off weight is 500 N, with a payload of 80 N. Under the above assumptions, a flying wing configuration for the UAV was defined, with a length of 1.6 meters and a span of 2.5 meters. A system of elevons assures the pitch and roll motion while a double vertical tail, in which a pusher propeller is lodged, guarantees the yaw stability and control.

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A hybrid propulsion system for a high-endurance UAV: configuration selection, aerodynamic study, and gas turbine bench tests

Journal of Unmanned Vehicle Systems ◽

10.1139/juvs-2013-0005 ◽

2014 ◽

Vol 02 (01) ◽

pp. 16-35 ◽

Cited By ~ 10

Author(s):

R. Capata ◽

L. Marino ◽

E. Sciubba

Keyword(s):

Gas Turbine ◽

Electric Propulsion ◽

High Performance ◽

Limited Range ◽

Propulsion System ◽

Major Drawback ◽

Hybrid Propulsion ◽

Electric Generator ◽

Wide Range ◽

Configuration Selection

In recent years, renewed interest in the development of unmanned aerial vehicles (UAVs) has led to a wide range of interesting applications in reconnaissance and surveillance. In these missions, the noise produced by propeller-driven UAVs is a major drawback, which can be partially solved by installing an electric motor to drive the propeller. While the evolution of high performance brushless motors makes electric propulsion particularly appealing, at least for small and medium UAVs, all electric propulsion systems developed to date are penalized by the limited range and endurance that can be provided by a reasonably sized battery pack. In this paper we propose a hybrid propulsion system based on a recently developed ultramicro gas–turbine (UMGT), which can be used to power an electric generator, providing a significant range and (or) mission time extension. The UMGT is undergoing operational testing in our laboratory, to identify the most suitable configuration and to improve performance: a new compact regenerative combustion chamber was developed and several tests are being carried out to reduce its weight and size so as to increase, all other things being equal, the vehicle payload. This paper aims to propose a high endurance UAV, by a preliminary configuration selection and aerodynamic study of its performance.

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Virtual Driver of Hybrid Wheeled Vehicle

Solid State Phenomena ◽

10.4028/www.scientific.net/ssp.180.39 ◽

2011 ◽

Vol 180 ◽

pp. 39-45 ◽

Cited By ~ 2

Author(s):

Gabriel Kost ◽

Andrzej Nierychlok

Keyword(s):

Combustion Engine ◽

Propulsion System ◽

System Structure ◽

Great Contribution ◽

Hybrid Drive ◽

Parallel Connection ◽

Hybrid Propulsion ◽

Electric Generator ◽

Wheeled Vehicle ◽

Wheeled Vehicles

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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Analysis of the possibility of using an engine with a rotating piston as the propulsion of an electric generator in application to a motor glider propulsion

Combustion Engines ◽

10.19206/ce-2019-346 ◽

2019 ◽

Vol 178 (3) ◽

pp. 264-268 ◽

Cited By ~ 2

Author(s):

Marek ORKISZ ◽

Piotr WYGONIK ◽

Michał KUŹNIAR ◽

Maciej KALWARA

Keyword(s):

Engine Speed ◽

Propulsion System ◽

Point Of View ◽

Hybrid Drive ◽

Current Generator ◽

Hybrid Propulsion ◽

Electric Generator ◽

Performance Point ◽

Hybrid Motor ◽

Driving Torque

Analysis of the possibility of using an engine with a rotating piston as the propulsion of an electric generator in application to a motor glider propulsion The paper presents an analysis of the possibilities of application of a rotating piston engine (Wankel type) as a propulsion for an electric generator in the motor glider propulsion system. This generator would be a part of the propulsion system of a hybrid motor glider using the AOS 71 motor glider airframe. In the research, the rotational characteristics of the LCR 407ti engine were determined experimentally. Driving torque run, power and fuel consumption were determined as a function of engine speed. The obtained results are presented in diagrams. The conceptual diagram of the hybrid drive is presented. The current generator was selected and the effectiveness of the generator and the entire propulsion were assessed from the motor gliders performance point of view. On the basis of the conducted research, conclusions were drawn and there were indicated the objectives and directions of further research on hybrid propulsion with specific aerodynamic and mass limitations of the aircraft

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A rotating piston engine with electric generator in serial hybrid propulsion system for use in light aircraft

Combustion Engines ◽

10.19206/ce-141353 ◽

2021 ◽

Author(s):

Maciej KALWARA ◽

Michał KUŹNIAR ◽

Marek ORKISZ

Keyword(s):

Power Input ◽

Propulsion System ◽

Point Of View ◽

Hybrid Propulsion ◽

Electric Generator ◽

Rotary Engine ◽

Performance Point ◽

Wankel Engine ◽

Hybrid Motor ◽

Driving Torque

Analysis of the possibility of using a rotary engine based electric generator to propell a powered sailplane. The paper presents analysis of utilising Wankel type enine as a power input for an electric generator in the motor glider propulsion system. This generator would be a part of the propulsion system of a hybrid motor glider using the AOS 71 motor glider airframe. In the research, the rotational characteristics of the LCR 407ti wankel engine were determined experimentally. Driving torque run, power and fuel consumption were determined as a function of engine speed. The obtained results are presented in diagrams. The conceptual diagram of the hybrid drive is presented. The electric generator was selected and its effectiveness, as well as the effectiveness of entire propulsion system was assessed from the motor glider's performance point of view. Basing on the research conducted, conclusions were drawn and there were indicated the objectives and directions of further research on hybrid propulsion with specific aerodynamic and mass limitations of the aircraft

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Preliminary Design of a Hybrid Propulsion System for High-Endurance UAV

Volume 1: Advances in Aerospace Technology ◽

10.1115/imece2010-38530 ◽

2010 ◽

Author(s):

Roberto Capata ◽

Luca Marino ◽

Enrico Sciubba

Keyword(s):

Electric Propulsion ◽

High Efficiency ◽

Aircraft Design ◽

Propulsion System ◽

Battery Pack ◽

Medium Size ◽

Major Drawback ◽

Hybrid Propulsion ◽

Electric Generator ◽

Wide Range

In recent years, a renewed interest in the development of unmanned air vehicles (UAV’s) led to a wide range of interesting applications in the fields of reconnaissance and surveillance. In these types of mission, the noise produced by propeller driven UAVs is a major drawback, which can be partially solved by installing an electric motor to drive the propeller. The evolution of high performance brushless motors makes electric propulsion particularly appealing, at least for small and medium size UAVs. All electric propulsion systems developed to date are though characterized by the limited range/endurance that can be obtained with a reasonably sized battery pack. In this paper we propose a hybrid propulsion system based on recently developed, high efficiency micro-turbines which can be used to power an electric generator. The UMGT is under evaluation in our department, to achieve the optimal configuration and performances. For this scope a new compact regenerative combustion chamber has been developed and several tests has been carried out, with the aim to reduce weight and dimension and increase vehicle payload. In a high range/endurance mission the ultra-micro-turbine can provide the energy required for the cruise phase (the so-called “transfer to target”), while in the final approach, in which a quiet flight attitude is a demanding item, the battery pack drives the motor. The mission requirements adopted in the preliminary aircraft design presented here consist mainly of a long endurance (> 12 hours) step, with a cruise speed of 33.3 m/s and a dash speed of 45 m/s at an altitude of 5000 meters. The maximum take-off weight is 500 N, with a payload of 80 N. Under the above assumptions, a flying wing configuration for the UAV was defined, with a length of 1.6 meters and a span of 2.5 meters. A system of elevons assures the pitch and roll motion while a double vertical tail, in which a pusher propeller is lodged, guarantees the yaw stability and control.

Download Full-text