scholarly journals Aeroelastic Stability Analysis of Electric Aircraft Wings with Distributed Electric Propulsors

Aerospace ◽  
2021 ◽  
Vol 8 (4) ◽  
pp. 100
Author(s):  
Mohammadreza Amoozgar ◽  
Michael I. Friswell ◽  
Seyed Ahmad Fazelzadeh ◽  
Hamed Haddad Khodaparast ◽  
Abbas Mazidi ◽  
...  
Keyword(s):  
Angular Momentum ◽  
Electric Propulsion ◽  
Aeroelastic Stability ◽  
Concentrated Mass ◽  
High Lift ◽  
Aircraft Wings ◽  
Time Space ◽  
Beam Equations ◽  
Geometrically Exact Beam ◽  
Electric Aircraft

In this paper, the effect of distributed electric propulsion on the aeroelastic stability of an electric aircraft wing was investigated. All the electric propulsors, which are of different properties, are attached to the wing of the aircraft in different positions. The wing structural dynamics was modelled by using geometrically exact beam equations, while the aerodynamic loads were simulated by using an unsteady aerodynamic theory. The electric propulsors were modelled by using a concentrated mass attached to the wing, and the motor’s thrust and angular momentum were taken into account. The thrust of each propulsor was modelled as a follower force acting exactly at the centre of gravity of the propulsor. The nonlinear aeroelastic governing equations were discretised using a time–space scheme, and the obtained results were verified against available results and very good agreement was observed. Two case studies were considered throughout the paper, resembling two flight conditions of the electric aircraft. The numerical results show that the tip propulsor thrust, mass, and angular momentum had the most impact on the aeroelastic stability of the wing. In addition, it was observed that the high-lift motors had a minimal effect on the aeroelastic stability of the wing.

Research on Parameters Matching of Ultralight Electric Aircraft Propulsion System

2013 ◽  
Vol 732-733 ◽  
pp. 1212-1215
Author(s):  
Gui Wen Kang ◽  
Yu Hu ◽  
Ya Dong Li ◽  
Wen Hui Jiang
Keyword(s):  
Electric Propulsion ◽  
High Energy ◽  
Low Noise ◽  
Electric Power System ◽  
Propulsion System ◽  
Heat Radiation ◽  
Design Parameters ◽  
Electric Propulsion System ◽  
Electric Aircraft ◽  
Parameter Matching

The propulsion system of ultralight electric aircraft is one of the general aviation technology development directions. It has the advantages such as light pollution, low noise, high energy utilization ratio, simple structure, easy maintenance, high reliability, less heat radiation, little operation cost and so on. Combined with the certain type of ultralight aircraft design parameters, the layout of aircraft electric propulsion, the principles and steps of the parameter matching of electric propulsion system were presented. The method of parameter matching and performance verification of electric propulsion system was put forward. The feasibility of the system is verified from the point of dynamic property. The study of parameter matching of electric propulsion system could not only provide basis for the integrated optimization for electric power system, but also evaluate the performance of the system simulation as reference.

scholarly journals Transition of Space Propulsion and Challenge to the Future -Breakthrough of Propulsion Technology

2019 ◽  
Vol 3 (1) ◽  
pp. 1
Author(s):  
Yoshinari Minami
Keyword(s):  
Electric Propulsion ◽  
Stellar System ◽  
Theoretical Method ◽  
Space Propulsion ◽  
Ion Thruster ◽  
Space Navigation ◽  
The Earth ◽  
Time Space ◽  
New Space ◽  
Historical Transition

The distance to a stellar system is very immense, therefore the travel to the fixed star nearest to the Earth using the present propulsion technology will require tens of thousands years. In order to overcome such a limit of the space travel between fixed stars, research and development of a new propulsion theory and navigation theory are indispensable.This paper describes the historical transition and future prospects of space propulsion technology, that is, new space propulsion and space navigation concept (Laser thruster, Continuum mechanics of Space-Time, Space drive propulsion, Hyper-Space navigation etc.) based on the published article so far by author. The prospects of various applications of laser thruster, ion thruster as electric propulsion and solar sail are introduced. A field propulsion which surpasses conventional propulsion is then discussed as well as the possibility of realistic interstellar travel by applying field propulsion to navigation theory.Space propulsion physics such as propulsion theory and navigation theory give us a concrete theoretical method toward galaxy exploration.

scholarly journals Perspectives and Development of Electrical Systems in More Electric Aircraft

2021 ◽  
Vol 2021 ◽  
pp. 1-14
Author(s):  
Ahmet Yigit Arabul ◽  
Emre Kurt ◽  
Fatma Keskin Arabul ◽  
İbrahim Senol ◽  
Martin Schrötter ◽  
...  
Keyword(s):  
Power Systems ◽  
Electric Propulsion ◽  
State Of The Art ◽  
Aircraft Design ◽  
The State ◽  
Total Change ◽  
Profound Change ◽  
Electrical Systems ◽  
Electric Aircraft ◽  
More Electric Aircraft

On-board electrical systems are the key components of each modern aircraft. They enable its safer, more comfortable, and environmentally friendlier operation. The strict regulations to reduce pollution and noise are produced by aircraft eventuated in projects like Clean Sky or ICAO Global Coalition for Sustainable Aviation. One solution to environmentally friendlier operation is the full electric propulsion of the aircraft, which enables the reduction of both noise and pollution. Such a concept requires a total change of all on-board power systems and enables the profound change in aircraft design. This paper presents the evolution of aircraft power systems into the so-called more electric aircraft (MEA) and discusses the state-of-the-art electrical systems. Furthermore, the concept of all-electric aircraft (AEA) is presented here.

scholarly journals Aeroelastic stability analysis of aircraft wings with initial curvature

2020 ◽  
Vol 107 ◽  
pp. 106241
Author(s):  
M.R. Amoozgar ◽  
S.A. Fazelzadeh ◽  
H. Haddad Khodaparast ◽  
M.I. Friswell ◽  
J.E. Cooper
Keyword(s):  
Stability Analysis ◽  
Aeroelastic Stability ◽  
Aircraft Wings ◽  
Initial Curvature

DESIGN AND ANALYSIS OF RIGID-BODY SHAPE-CHANGE MECHANISM FOR AIRCRAFT WINGS

2015 ◽  
Vol 77 (21) ◽  
Author(s):  
Mohammad Hazrin Ismail ◽  
Shamsul Anuar Shamsudin ◽  
Mohd Nizam Sudin
Keyword(s):  
Shape Change ◽  
Rigid Bodies ◽  
Main Body ◽  
Programming Technique ◽  
High Lift ◽  
Airframe Noise ◽  
Aircraft Wings ◽  
Prismatic Joints ◽  
A Chain ◽  
Fixed End

Airframe noise reduction becomes a main interest among researchers who study the performance of aircrafts. The airframe noise can occur between the high-lift systems and main body of the airfoil. The proposed shape-changing airfoil is one of many ideas to reduce airframe noise by eliminating the gap between the main body and high-lift systems. This paper presents a new design of 30P30N airfoil, which converts the three-element airfoil (slat, main body and flap) into two-element airfoil (combination of slat and main body as an element and flap) by installing a shape-changing slat into the systems. This work applies a chain of rigid bodies connected by revolute and prismatic joints that are capable of approximating a shape change defined by a set of morphed slat design profiles. To achieve a single degree of freedom (DOF), a building-block approach is employed to mechanize the fixed-end shape-changing chain with the helped of Geometric Constraint Programming technique as an effective method to develop the mechanism. The conventional and shape-change 30P30N airfoils are compared to study the performances of airfoils with the velocity and angle of attack are constant.

scholarly journals THEA-CODE: a design tool for the conceptual design of hybrid-electric aircraft with conventional or unconventional airframe configurations

2021 ◽  
Vol 22 ◽  
pp. 19
Author(s):  
Giuseppe Palaia ◽  
Davide Zanetti ◽  
Karim Abu Salem ◽  
Vittorio Cipolla ◽  
Vincenzo Binante
Keyword(s):  
Conceptual Design ◽  
Electric Propulsion ◽  
Greenhouse Gas Emission ◽  
State Of The Art ◽  
Design Tool ◽  
Current State ◽  
Electric Aircraft ◽  
Potential Benefits ◽  
Hybrid Electric ◽  
Critical Requirement

The aviation world is dealing with the development of new and greener aviation. The need for reducing greenhouse gas emission as well as the noise is a critical requirement for the aviation of the future. The aviation world is struggling with it, and a compelling alternative can be the electric propulsion. This work aims to present THEA-CODE, a tool for the conceptual design of hybrid-electric aircraft. The tool evaluates the potential benefits of the electric propulsion in terms of fuel burnt and direct and indirect CO2 emissions. THEA-CODE is suitable not only for conventional “wing-tube” configurations but also for unconventional ones, such as the box-wing. The results show a significant reduction of fuel burnt adopting batteries with energy density higher than the current state of the art. A procedure to find the potential best compromise configurations is presented as well.

Conceptual Design and Energy Storage Positioning Aspects for a Hybrid-Electric Light Aircraft

2021 ◽  
Author(s):  
Vasilis Gkoutzamanis ◽  
Mavroudis D. Kavvalos ◽  
Arjun Srinivas ◽  
Doukaini Mavroudi ◽  
George Korbetis ◽  
...  
Keyword(s):  
Energy Storage ◽  
Conceptual Design ◽  
Electric Propulsion ◽  
Co2 Reduction ◽  
Requirements Definition ◽  
Electric Aircraft ◽  
Design Requirements ◽  
Hybrid Electric ◽  
Battery Technology ◽  
Aircraft Configurations

Abstract This work focuses on the feasibility of a 19-passenger hybrid-electric aircraft, to serve the short-haul segment within the 200-600 nautical miles. Its ambition is to answer to research questions, during the evaluation and design of aircraft based on electric propulsion architectures. The potential entry into service of such aircraft is foreseen in 2030. A literature review is performed, to identify similar concepts developed globally. After the requirements' definition, the first level of conceptual design is employed. Following a set of assumptions, a methodology for the sizing of the hybrid-electric aircraft is described, to explore the basis of the design space. Additionally, a methodology for the energy storage positioning is provided, highlighting the multidisciplinary aspects between the sizing of an aircraft, the selected architecture (series/parallel partial hybrid) and the energy storage specifications. The design choices are driven by the aim to reduce CO2 emissions and accommodate boundary layer ingestion engines, with aircraft electrification. The results show that it is not possible to fulfil the initial design requirements (600 nmi) with a fully-electric aircraft configuration, due to the far-fetched battery necessities. It is also highlighted that compliance with airworthiness certifications is favored by switching to hybrid-electric aircraft configurations and relaxing the design requirements (range, payload, battery technology). Finally, the lower degree of hybridization (40%) is observed to have higher energy efficiency (12% lower energy consumption and larger CO2 reduction), compared to the higher degree of hybridization (50%), with respect to the conventional configuration.

Geometrically exact beam equations in the adaptive DCA framework

2019 ◽  
Vol 47 (1) ◽  
pp. 1-19 ◽  
Author(s):  
Jeremy J. Laflin ◽  
Kurt S. Anderson
Keyword(s):  
Beam Equations ◽  
Geometrically Exact Beam

scholarly journals Annoyance to Noise Produced by a Distributed Electric Propulsion High-Lift System

2017 ◽  
Author(s):  
Stephen A. Rizzi ◽  
Daniel L. Palumbo ◽  
Jonathan Rathsam ◽  
Andrew W. Christian ◽  
Menachem Rafaelof
Keyword(s):  
Electric Propulsion ◽  
High Lift
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