Ideas for future electric aircraft system

The present trend of aerospace industries is being shifted towards a “More Electric Aircraft” system which needs to be high power dense. For this purpose, the integration technologies have gained massive interest, providing the benefits of reduced losses, weight, volume and cost. In this article, the integration concept of a passive filter inductor is presented for a permanent magnet synchronous motor. The integrated motor eliminates the need of an external inductor, thus, eliminates the added inductor losses, mass, volume and cost associated with it. The motor utilizes its’s inherent inductance to use it as a filter inductor instead of implementing a discrete inductor that is commonly placed between inverter and the motor terminals. Optimization study is carried out, where the filter branch windings are tapped, in terms of improving mass and volume and performance parameters such as power losses and torque ripple. From the optimization study, the motor with minimum weight and volume is experimentally validated at the rated conditions, in order to prove the concept feasibility. Total system weight and volume of integrated and traditional motor drives are compared, which gives the minimum weight of 2.26 kg and 3.14 kg respectively, and the minimum volume of 0.54 L and 1.1 L respectively.

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Design and realisation of a two-seater aircraft powered by fuel cell electric propulsion

The Aeronautical Journal ◽

10.1017/s0001924000003730 ◽

2010 ◽

Vol 114 (1155) ◽

pp. 281-297 ◽

Cited By ~ 12

Author(s):

Giulio Romeo ◽

Fabio Borello

Keyword(s):

Fuel Cell ◽

Electric Motor ◽

Electric Propulsion ◽

High Performance ◽

Flight Test ◽

Cell System ◽

Electric Aircraft ◽

New Energy ◽

Aircraft System ◽

Continuous Power

Abstract The main objective of the project is to develop and validate the use of a fuel cell based power system for the propulsion of more/all electric aircraft. The Rapid 200-FC two-seater electric-motor-driven aeroplane which is powered by fuel cells is at present being completed and will be validated during a flight test in Autumn 2009. Several configurations have been evaluated in order to install the new energy and propulsion system on board while maintaining the centre of gravity within allowable limits. The fuel cell system and the electric motor are being integrated on board. The FC stack will be able to deliver a maximum continuous power of 20kW. A battery pack has to guarantee another 20kW of maximum continuous power for a limited time period (15 minutes), during take-off, climbing and, in the case of emergency, during landing. The main goal of the project is to validate the overall high performance of an all electric aircraft system which is capable of remaining aloft for one hour. A parametric analysis has also been carried out to evaluate which key technologies influence the performance of future aircraft to the greatest extent.

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ANFIS-SCC Control of Shunt Active Power Filter for Minimization of Harmonics for More Electric Aircraft System

Applications of Artificial Intelligence in Electrical Engineering - Advances in Computational Intelligence and Robotics ◽

10.4018/978-1-7998-2718-4.ch001 ◽

2020 ◽

pp. 1-22

Author(s):

Saifullah Khalid ◽

Shailendra Kumar

Keyword(s):

Harmonic Distortion ◽

Active Power Filter ◽

Active Power ◽

Current Control ◽

Nonlinear Load ◽

Shunt Active Power Filter ◽

Power Filter ◽

Electric Aircraft ◽

Aircraft System ◽

More Electric Aircraft

A growth of computational intelligence techniques is the motivation to propose an intelligent controller in this chapter to minimize the harmonics in a more electric aircraft systems due to the presence of nonlinear load applied in aircraft system. Conventional PI controller is implemented in the system and the compensated reference current is generated by sinusoidal current control theory. Shunt active power filter is mainly used to minimize the harmonics in the aircraft system feeding the nonlinear load. The proposed system uses conventional SCC- and ANFIS-based controller and the results are compared. The simulation result of total harmonic distortion (THD) is demonstrated through MATLAB/SIMULINK.

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A Practical Approach From the MEE Toward Hybrid Propulsion

Volume 6: Ceramics; Controls, Diagnostics and Instrumentation; Education; Manufacturing Materials and Metallurgy ◽

10.1115/gt2017-63222 ◽

2017 ◽

Author(s):

Noriko Morioka ◽

Hitoshi Oyori ◽

Tomoaki Asako ◽

Katsuyuki Takahashi ◽

Takumi Ando

Keyword(s):

Electrical Power ◽

Electrical Energy ◽

Propulsion System ◽

Commercial Aircraft ◽

Hybrid Propulsion ◽

Electric Aircraft ◽

Aircraft System ◽

System Configurations ◽

Electric Engine ◽

More Electric Aircraft

The MEA (More Electric Aircraft)/AEA (All Electric Aircraft) and MEE (More Electric Engine) is representative of system evolution, contributing to improved energy management of the entire aircraft system and reducing fuel consumption of aircraft. Looking at future aviation, it is necessary to have further evolution beyond the MEA/AEA and MEE to achieve further improvement of aircraft efficiency and “greener aviation”. The electrified propulsion system, which uses electrical energy as propulsive power, would be a possible option, and various kinds of configurations have been studied and developed. Small one- or two-seater airplanes have already successfully flown with the all-electrified propulsion; however, there are a lot of perspectives for the system configuration for larger-sized commercial aircraft. It is considered that a hybrid propulsion system, in which the E3M (Engine Embedded Electric Machine) provides assisting power to the engine shafts, would be one of the probable configurations. The authors are currently developing the E3M as an LP (Low Pressure) spool-driven generator, and the approach is considered to be practical because E3M technology can be commonly applicable for both large electrical power generation and hybrid propulsion. In this paper, several advanced propulsion system configurations are compared, and perspectives of the hybrid propulsion for future commercial aircraft are described. Also technical challenges for the MEE/E3M, continuing toward future hybrid propulsion, are outlined and further R&D steps are considered.

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