scholarly journals 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

2019 ◽  
Vol 178 (3) ◽  
pp. 264-268 ◽  
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

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

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

Virtual Driver of Hybrid Wheeled Vehicle

2011 ◽  
Vol 180 ◽  
pp. 39-45 ◽  
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.

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

2021 ◽  
Vol 14 (5) ◽  
pp. 249
Author(s):  
Anton Varyukhin ◽  
Viktor Zakharchenko ◽  
Vladimir Lomazov ◽  
Denis Zhuravlev ◽  
Flyur Ismagilov ◽  
...  
Keyword(s):  
Propulsion System ◽  
Hybrid Propulsion ◽  
Electric Generator

A Hybrid Propulsion System for a High-Endurance UAV: Configuration Selection and Aerodynamic Study

2011 ◽  
Author(s):  
Roberto Capata ◽  
Luca Marino ◽  
Enrico Sciubba
Keyword(s):  
Electric Propulsion ◽  
High Performance ◽  
High Efficiency ◽  
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 (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.

Economic Benefits of Hybrid Drive Propulsion for DDG-51 Class Ships

2008 ◽  
Author(s):  
Fred T. Willett ◽  
Greg Reed ◽  
Gene Castles
Keyword(s):  
Performance Optimization ◽  
Electrical Power ◽  
Economic Benefits ◽  
Propulsion System ◽  
Permanent Magnet Motors ◽  
Hybrid Drive ◽  
Hybrid Propulsion ◽  
Low Speed ◽  
Fuel Savings ◽  
Turbine Generators

The typical operating profile for destroyers and other marine vessels includes a large portion of low-speed activity. Low-speed operation is accompanied by propulsion system inefficiency, as the propulsion turbines are operating off-design. Low speeds are further enabled by propeller pitch variation, which exacerbates system inefficiency. A hybrid propulsion system scheme is proposed that will allow propulsion by either mechanical or electrical drive. Electrical power generated by the ship service turbine-generators (SSTGs) is used to drive large permanent magnet motors. The motors then drive the propeller shafts during low speed operation. This scheme allows the propulsion turbines to be shut down and the ship service turbine-generators to run closer to design point, resulting in fuel savings. Additional savings are possible at higher speeds by operating the motor(s) in generation mode, enabling SSTG shut down and propulsion turbine performance optimization. This paper describes in detail the concept of hybrid drive operation and demonstrates the economic justification for such a system.

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

2014 ◽  
Vol 02 (01) ◽  
pp. 16-35 ◽  
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.

scholarly journals Energy Balance of a Vehicle Equipped with Hybrid Propulsion System Fuelled with Alternative Fuels

2019 ◽  
Vol 26 (4) ◽  
pp. 91-96
Author(s):  
Mirosław Karczewski ◽  
Leszek Szczęch ◽  
Filip Polak
Keyword(s):  
Alternative Fuels ◽  
Internal Combustion Engines ◽  
Power Transmission ◽  
Diesel Oil ◽  
Propulsion System ◽  
Total Efficiency ◽  
Hybrid Drive ◽  
Power Generator ◽  
Hybrid Propulsion ◽  
Hybrid Power

AbstractArticle presents the energetic balance of small-unmanned vehicle hybrid power transmission. The vehicle equipped with serial hybrid transmission consisted of electric engines connected to the battery pack and small Diesel power generator. In mentioned construction, battery is used as energy buffer and combustion engine is used more as emergency power supply, and is turned on when battery is depleted. In other condition, power generator can be turned off, without reducing power of transmission parameters, except its range. Vehicles with hybrid drive are very common chosen vehicles by users. More and more often, we also talk about searching for replacement fuels for internal combustion engines, so also for those with hybrid drive. The research was carried out on an unmanned land platform equipped with a hybrid propulsion system supplied as standard with Diesel oil. The article presents the problems of comparing the efficiency of a hybrid vehicle fuelled with Diesel oil, but also with alternative fuels based on kerosene and other components. For test, three types of fuels were used, standard Diesel oil, F-34 and with experimental mixture of Jet A-1 fuel with 10% of 2-ethylhexanol. Energy used for charging of the battery, from tank-to-wheel, was calculated. This also enables to calculate total efficiency of such hybrid power transmission, powered with different fuels.

scholarly journals Hybrid Propulsion System: Novel Propellant Design for Mars Ascent Vehicles

2021 ◽  
Author(s):  
Ozan Kara ◽  
Arif Karabeyoglu
Keyword(s):  
Low Cost ◽  
Flame Temperature ◽  
Propulsion System ◽  
Hybrid Rocket ◽  
General Audience ◽  
Hybrid Propulsion ◽  
Test Setup ◽  
Rocket Propulsion ◽  
Hybrid Motor

This chapter briefly introduces hybrid rocket propulsion for general audience. Advantageous of hybrid rockets over solids and liquids are presented. This chapter also explains how to design a test setup for hybrid motor firings. Hybrid propulsion provides sustainable, safe and low cost systems for space missions. Therefore, this chapter proposes hybrid propulsion system for Mars Ascent Vehicles. Paraffin wax is the fuel of the rocket. Propulsion system uses CO2/N2O mixture as the oxidizer. The goal is to understand the ignition capability of the CO2 as an in-situ oxidizer on Mars. CO2 is known as major combustion product in the nature. However, it can only burn with metallic powders. Thus, metallic additives are added in the fuel grain. Results show that CO2 increase slows down the chemical kinetics thus reduces the adiabatic flame temperature. Maximum flammability limit is achieved at 75% CO2 by mass in the oxidizer mixture. Flame temperature is 1700 K at 75% CO2. Ignition quenches below the 1700 K.

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

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.

Modeling and Control of Hybrid Propulsion System for Ground Vehicles

2018 ◽  
Author(s):  
Yuan Zou ◽  
Junqiu Li ◽  
Xiaosong Hu ◽  
Yann Chamaillard
Keyword(s):  
Propulsion System ◽  
Ground Vehicles ◽  
Hybrid Propulsion ◽  
Modeling And Control ◽  
And Control
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