Next Article in Journal
A Multi-Scale Modeling Approach for Simulating Crack Sensing in Polymer Fibrous Composites Using Electrically Conductive Carbon Nanotube Networks. Part II: Meso- and Macro-Scale Analyses
Previous Article in Journal
The Development of an Ordinary Least Squares Parametric Model to Estimate the Cost Per Flying Hour of ‘Unknown’ Aircraft Types and a Comparative Application
Article Menu

Export Article

Open AccessArticle
Aerospace 2018, 5(4), 105; https://doi.org/10.3390/aerospace5040105

Development of a Lumped Parameter Model for an Aeronautic Hybrid Electric Propulsion System

1
University of Naples “Federico II”, Via Claudio 21, 80125 Naples, Italy
2
Centro Italiano Ricerca Aerospaziale, Via Maiorise, 81043 Capua (CE), Italy
These authors contributed equally to this work.
*
Author to whom correspondence should be addressed.
Received: 29 June 2018 / Revised: 27 August 2018 / Accepted: 3 September 2018 / Published: 4 October 2018
(This article belongs to the Special Issue Computational Mechanics in Aerospace Engineering)
Full-Text   |   PDF [9547 KB, uploaded 12 October 2018]   |  

Abstract

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. View Full-Text
Keywords: lumped parameter simulation; aircraft hybrid propulsion; fuel economy; propulsion and propellant systems lumped parameter simulation; aircraft hybrid propulsion; fuel economy; propulsion and propellant systems
Figures

Figure 1

This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited (CC BY 4.0).
SciFeed

Share & Cite This Article

MDPI and ACS Style

Frosina, E.; Senatore, A.; Palumbo, L.; Di Lorenzo, G.; Pascarella, C. Development of a Lumped Parameter Model for an Aeronautic Hybrid Electric Propulsion System. Aerospace 2018, 5, 105.

Show more citation formats Show less citations formats

Note that from the first issue of 2016, MDPI journals use article numbers instead of page numbers. See further details here.

Related Articles

Article Metrics

Article Access Statistics

1

Comments

[Return to top]
Aerospace EISSN 2226-4310 Published by MDPI AG, Basel, Switzerland RSS E-Mail Table of Contents Alert
Back to Top