scholarly journals X-57 Power and Command System Design

2017 ◽  
Author(s):  
Sean Clarke ◽  
Matthew Redifer ◽  
Kurt Papathakis ◽  
Aamod Samuel ◽  
Trevor Foster
Keyword(s):  
Power Distribution ◽  
Electric Propulsion ◽  
High Speed ◽  
New Technologies ◽  
Propulsion System ◽  
General Aviation ◽  
Efficiency Gain ◽  
Critical Systems ◽  
Electric Power Distribution ◽  
Entire Vehicle

This paper describes the power and command system architecture of the X‑57 Maxwell flight demonstrator aircraft. The X-57 is an experimental aircraft designed to demonstrate radically improved aircraft efficiency with a 3.5 times aero-propulsive efficiency gain at a “high‑speed cruise” flight condition for comparable general aviation aircraft. These gains are enabled by integrating the design of a new, optimized wing and a new electric propulsion system. As a result, the X‑57 vehicle takes advantage of the new capabilities afforded by electric motors as primary propulsors. Integrating new technologies into critical systems in experimental aircraft poses unique challenges that require careful design considerations across the entire vehicle system, such as qualification of new propulsors (motors, in the case of the X-57 aircraft), compatibility of existing systems with a new electric power distribution bus, and instrumentation and monitoring of newly qualified propulsion system devices.

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 Comparative Analysis and Optimization of Technical and Weight Parameters of Turbo-Electric Propulsion Systems

Aerospace ◽  
2020 ◽  
Vol 7 (8) ◽  
pp. 107 ◽  
Author(s):  
Mykhaylo Filipenko ◽  
Stefan Biser ◽  
Martin Boll ◽  
Matthias Corduan ◽  
Mathias Noe ◽  
...  
Keyword(s):  
Electric Propulsion ◽  
Propulsion System ◽  
Aviation Industry ◽  
Total Efficiency ◽  
Efficiency Gain ◽  
Propulsion Systems ◽  
Electric Propulsion System ◽  
Reduce Emissions ◽  
Passenger Aircraft ◽  
Mission Profile

According to Flightpath 2050, the aviation industry is aiming to substantially reduce emissions over the coming decades. One possible solution to meet these ambitious goals is by moving to hybrid-electric drivetrain architectures which require the electric components to be extremely lightweight and efficient at the same time. It has been claimed in several publications that cryogenic and in particular superconducting components can help to fulfill such requirements that potentially cannot be achieved with non-cryogenic components. The purpose of this work was to make a fair comparison between a cryogenic turbo-electric propulsion system (CEPS) and a non-cryogenic turbo-electric propulsion system (TEPS) on a quantitative level. The results on the CEPS were presented in detail in a previous publication. The focus of this publication is to present the study on the TEPS, which in conclusion allows a direct comparison. For both systems the same top-level aircraft requirements were used that were derived within the project TELOS based on an exemplary mission profile and the physical measures of a 220-passenger aircraft. Our study concludes that a CEPS could be 10% to 40% lighter than a TEPS. Furthermore, a CEPS could have a total efficiency gain of up to 18% compared to a similar TEPS.

scholarly journals Analysis of Electric Propulsion System for Exploration of Saturn

2009 ◽  
Vol 2009 ◽  
pp. 1-14 ◽  
Author(s):  
Carlos Renato Huaura Solórzano ◽  
Antonio Fernando Bertachini de Almeida Prado ◽  
Alexander Alexandrovich Sukhanov
Keyword(s):  
Electric Propulsion ◽  
New Technologies ◽  
Propulsion System ◽  
Keplerian Orbit ◽  
Low Thrust ◽  
Propulsion Systems ◽  
New Horizons ◽  
Outer Planets ◽  
Electric Propulsion System ◽  
Solar Electric Propulsion

Exploration of the outer planets has experienced new interest with the launch of the Cassini and the New Horizons Missions. At the present time, new technologies are under study for the better use of electric propulsion system in deep space missions. In the present paper, the method of the transporting trajectory is used to study this problem. This approximated method for the flight optimization with power-limited low thrust is based on the linearization of the motion of a spacecraft near a keplerian orbit that is close to the transfer trajectory. With the goal of maximizing the mass to be delivered in Saturn, several transfers were studied using nuclear, radioisotopic and solar electric propulsion systems.

scholarly journals Application-optimised propulsion systems for energy-efficient operation

2011 ◽  
Vol 5 (9) ◽  
pp. 87
Author(s):  
Stefan Kaul ◽  
Paul Mertes ◽  
Lutz Müller
Keyword(s):  
Power Distribution ◽  
Energy Efficient ◽  
Electric Propulsion ◽  
Propulsion System ◽  
Propulsion Systems ◽  
Systematic Analysis ◽  
Efficient Operation ◽  
Economic Operation ◽  
Distributed Propulsion ◽  
Optimal Adaptation

Today, optimal propellers are designed by using advanced numerical methods. Major revolutionary improvements cannot be expected. More essential are the design conditions and the optimal adaptation of the propulsion system according to the operational requirements. The selection and optimisation of the propulsion system based on a systematic analysis of the ship’s requirements and the operation profile are the prerequisites for reliable and energy-efficient propulsion. Solutions are presented, which accommodate these issues with a focus on steerable rudderpropellers. Considerations include the efficiency potential of the propulsor itself, optimisation of the engine propeller interaction, and optimisation of a demandresponsive energy supply. The propeller-thruster interaction is complex, but offers some potential for optimisation. Results of examinations show this. The power distribution between multiple propellers at high loads of limited propeller diameters increases the efficiency. This can be done by double-propeller systems like the SCHOTTEL TwinPropeller or by distributing the power on several thrusters. This distributed propulsion offers economic operation and an increased lifetime by means of the demandresponsive use of energy. An efficiency-optimized electric motor instead of the upper gear box reduces the mechanical losses in the case of diesel-electric propulsion. An example: the SCHOTTEL CombiDrive.

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.

Proposal of a Method for Implementing Infrared Scanning Inspection Programs in Merchant Vessels

2004 ◽  
Vol 41 (01) ◽  
pp. 1-6
Author(s):  
M. Salvá ◽  
R. Hernández ◽  
C. Sanz
Keyword(s):  
Power Distribution ◽  
High Speed ◽  
New Technologies ◽  
Electrical Power ◽  
Predictive Maintenance ◽  
Infrared Thermal Imaging ◽  
Infrared Scanning ◽  
Maintenance Program ◽  
Bad Weather ◽  
Pressurized Fluids

This paper summarizes a proposal for implementing a predictive maintenance program based on infrared scanning inspection in merchant vessels. Current use of infrared inspection in merchant vessels is discussed, with an analysis of the problems and the benefits. Finally, a method for developing an inspection plan is proposed. The method consists of a selection of parameters, with consideration of infrared thermography and which general and specific criteria must be followed. Infrared thermal imaging is currently used for many engineering activities, mainly in industrial plants, in which predictive maintenance is widely used. However, this technique is being applied only in some types of merchant vessels, such as fast ferries and, in general, high-speed crafts. The main objective of the maintenance program proposed in this paper is prevention of loss by reducing the risks of fire and explosion. Twenty percent of the world ship losses in the last 25 years were caused by fire or explosions, the second most common cause of loss after bad weather. The proposed method consists of inspection and diagnostic tasks done on a systematic basis. The measurements of surface temperatures can detect hot spots and, subsequently, potential ignition sources. All the electrical power, distribution, and receptor devices; insulations; and any hot surface in the engine room, such as boiler casings and exhaust pipes, are included in the maintenance program. The second objective is related to the savings achieved by preventive maintenance reduction and the benefits of healthy facilities. Thermal scanning can detect small temperature differences between close points on a surface. This capability allows the detection of potential failures, such as cracks and lack of insulation in pipes and casings, thermal isolations, and small leaks of pressurized fluids such as steam, compressed air, and nonvisible fluids. The authors are currently working on a research project sponsored by the Spanish Maritime Authority within the scope of the development of new technologies focused on increasing maritime safety. One of the tasks of that project is the method of carrying out the inspection programs presented in this paper.

Rendez vous with Saturn's rings

1984 ◽  
Vol 75 ◽  
pp. 743-759 ◽  
Author(s):  
Kerry T. Nock
Keyword(s):  
Solar Energy ◽  
Electric Propulsion ◽  
Power Source ◽  
Propulsion System ◽  
Low Thrust ◽  
Ring Plane ◽  
The Earth ◽  
Total Impulse ◽  
Saturn's Rings

ABSTRACTA mission to rendezvous with the rings of Saturn is studied with regard to science rationale and instrumentation and engineering feasibility and design. Future detailedin situexploration of the rings of Saturn will require spacecraft systems with enormous propulsive capability. NASA is currently studying the critical technologies for just such a system, called Nuclear Electric Propulsion (NEP). Electric propulsion is the only technology which can effectively provide the required total impulse for this demanding mission. Furthermore, the power source must be nuclear because the solar energy reaching Saturn is only 1% of that at the Earth. An important aspect of this mission is the ability of the low thrust propulsion system to continuously boost the spacecraft above the ring plane as it spirals in toward Saturn, thus enabling scientific measurements of ring particles from only a few kilometers.

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