scholarly journals Influence of Novel Airframe Technologies on the Feasibility of Fully-Electric Regional Aviation

Aerospace ◽  
2021 ◽  
Vol 8 (6) ◽  
pp. 163
Author(s):  
Stanislav Karpuk ◽  
Ali Elham
Keyword(s):  
Energy Density ◽  
Active Flow Control ◽  
Aircraft Design ◽  
Operating Costs ◽  
Mission Analysis ◽  
Novel Technologies ◽  
Electric Aircraft ◽  
And Performance ◽  
Battery Energy ◽  
Active Flow

The feasibility of regional electric aviation to reduce environmental impact highly depends on technological advancements of energy storage techniques, available battery energy density, and high-power electric motor technologies. However, novel airframe technologies also strongly affect the feasibility of a regional electric aircraft. In this paper, the influence of novel technologies on the feasibility of regional electric aviation was investigated. Three game-changing technologies were applied to a novel all-electric regional aircraft: active flow control, active load alleviation, and novel materials and structure concepts. Initial conceptual design and mission analysis of the aircraft was performed using the aircraft design framework SUAVE, and the sensitivity of the most important technologies on the aircraft characteristics and performance were studied. Obtained results were compared against a reference ATR-72 aircraft. Results showed that an all-electric aircraft with airframe technologies might be designed with the maximum take-off weight increase of 50% starting from the battery pack energy density of 700 Wh/kg. The overall emission level of an all-electric aircraft with novel technologies is reduced by 81% compared to the ATR-72. On the other hand, novel technologies do not contribute to the reduction in Direct Operating Costs (DOC) starting from 700 Wh/kg if compared to an all-electric aircraft without technologies. An increase in DOC ranges from 43% to 30% depending on the battery energy density which creates a significant market obstacle for such type of airplanes. In addition, the aircraft shows high levels of energy consumption which concerns its energy efficiency. Finally, the sensitivity of DOC to novel technologies and sensitivities of aircraft characteristics to each technology were assessed.

Limitations and Challenges in Designing an All-Electric Aircraft: Analytical Study

2019 ◽  
Vol 11 (5) ◽  
Author(s):  
Suddunuri Sumanth Siddhartha ◽  
Jigme Tsering ◽  
B.G. Charishma Reddy
Keyword(s):  
Energy Density ◽  
Combustion Engine ◽  
Renewable Energy Resources ◽  
Jet Propulsion ◽  
Free Jet ◽  
Ducted Fan ◽  
Sufficient Energy ◽  
Battery Capacity ◽  
Electric Aircraft ◽  
Battery Energy

Driven by rapid depletion of non-renewable energy resources, emission reduction of combustion engine exhaust, noise reduction and in-efficiency of combustion engine demand and production of electric vehicle has seen a significant growth in recent years. However, when it comes to electrification of the aircraft technology, there are a number of challenges and technological limitations faced by the designer such as vicious weight cycle, in-sufficient energy density and power constraints in batteries. This paper outlines those challenges in design and manufacturing of a manned electric aircraft. Using MATLAB, a mathematical model of the electric aircraft is created considering parameters like power required, battery capacity, battery weight and total weight of the aircraft. Range and endurance of an electric aircraft for different variations in payload or passenger capacity will be determined. This detailed study will give a picture on what is achievable using current technology (battery energy density, combustion free jet propulsion etc.) and what can be achieved based on the limitations in developing a electric ducted fan engines. This paper also outlines design challenges being faced in combustion free jet propulsion namely electric ducted fan engines which is needed for propelling the electric aircraft. This paper is concluded with design recommendations and parameters to be considered during design process for a fully electric aircraft.

scholarly journals Multi-Fidelity Design Optimization of a Long-Range Blended Wing Body Aircraft with New Airframe Technologies

Aerospace ◽  
2020 ◽  
Vol 7 (7) ◽  
pp. 87
Author(s):  
Stanislav Karpuk ◽  
Yaolong Liu ◽  
Ali Elham
Keyword(s):  
Long Range ◽  
New Technologies ◽  
Active Flow Control ◽  
Preliminary Investigation ◽  
Aircraft Design ◽  
Fuel Burn ◽  
Aircraft Fuel ◽  
Computational Fluid Dynamics Cfd ◽  
Blended Wing Body ◽  
Active Flow

The German Cluster of Excellence SE²A (Sustainable and Energy Efficient Aviation) is established in order to investigate the influence of game-changing technologies on the energy efficiency of future transport aircraft. In this paper, the preliminary investigation of the four game-changing technologies active flow control, active load alleviation, boundary layer ingestion, and novel materials and structure concepts on the performance of a long-range Blended Wing Body (BWB) aircraft is presented. The BWB that was equipped with the mentioned technologies was designed and optimized using the multi-fidelity aircraft design code SUAVE with a connection to the Computational Fluid Dynamics (CFD) code SU2. The conceptual design of the BWB aircraft is performed within the SUAVE framework, where the influence of the new technologies is investigated. In the second step, the initially designed BWB aircraft is improved by an aerodynamic shape optimization while using the SU2 CFD code. In the third step, the performance of the optimized aircraft is evaluated again using the SUAVE code. The results showed more than 60% reduction in the aircraft fuel burn when compared to the Boeing 777.

Enhancements in conceptual electric aircraft design

2019 ◽  
Vol 91 (6) ◽  
pp. 851-856
Author(s):  
Jacek Mieloszyk ◽  
Andrzej Tarnowski
Keyword(s):  
Numerical Models ◽  
Aircraft Design ◽  
Performance Estimation ◽  
Design Parameters ◽  
Content Type ◽  
Improve Design ◽  
Design Variables ◽  
Electric Aircraft ◽  
Wing Geometry ◽  
And Performance

PurposeThis paper aims to describe the enhancement of the numerical method for conceptual phase of electric aircraft design.Design/methodology/approachThe algorithm provides a balance between lift force and weight of the aircraft, together with drag and thrust force equilibrium, while modifying design variables. Wing geometry adjustment, mass correction and performance estimation are performed in an iterative process.FindingsAircraft numerical model, which is most often very simplified, has a number of new improvements. This enables to make more accurate analyses and to show relationships between design parameters and aircraft performance.Practical implicationsThe presented approach can improve design results.Originality/valueThe new methodology, which includes enhanced numerical models for conceptual design, has not been presented before.

Computational analysis of the aerodynamic performance of a jet-flap airfoil in transonic flow

2012 ◽  
Vol 226 (6) ◽  
pp. 664-678 ◽  
Author(s):  
V Mantič-Lugo ◽  
G Doulgeris ◽  
A Gohardani ◽  
R Singh
Keyword(s):  
Flow Control ◽  
Active Flow Control ◽  
Angle Of Attack ◽  
Aircraft Design ◽  
Civil Aviation ◽  
Commercial Aircraft ◽  
Angle Variation ◽  
Distributed Propulsion ◽  
Lift And Drag ◽  
Active Flow

The needed shift in next generation aircraft design is expected to bring novel concepts for civil aviation as the jet-flap wing. The aircraft efficiency improvements with the jet-flap wing directs its use for future aircraft designs reinforced by the tendency for more synergistic systems as active flow control, boundary layer ingestion and distributed propulsion, making the jet-flap wing a very suitable option for the latter concept. The analysis carried out in this paper is aimed at the application of the jet-flap wing concept for manoeuvrability and cruise efficiency improvement of an airliner. A 2D computational model of a jet-flapped transonic airfoil is developed in order to assess the jet-flap wing technology for a commercial aircraft at cruise conditions. This paper provides an insight into the parameters that affect the performance of a jet-flap under various flight conditions. To do this, a general parametrical analysis is performed, studying numerically the influences of main flow parameters like Mach number, Reynolds number, angle of attack, jet deflection angle and jet thickness. Changes in pressure distribution and flow circulation around the airfoil yield strong modifications in lift and drag due to jet angle variation. Improvements are encountered in the performance of an airfoil with a jet-flap system compared with a standard airfoil with no jet. Enhancements in lift and reduction in drag, as well as an increase of the lift-to-drag ratio is possible with a proper combination of the jet deflection and the angle of attack of the airfoil. In summary, this paper shows the conditions under which the benefits of the jet-flapped wing, for lift enhancement and manoeuvrability as an active flow control are promising.

scholarly journals Design of a Four-Seat, General Aviation Electric Aircraft

2021 ◽  
Vol 8 (2) ◽  
pp. 139-168
Author(s):  
Priya Chouhan ◽  
Nikos J. Mourtos
Keyword(s):  
Energy Density ◽  
Fossil Fuels ◽  
Aircraft Design ◽  
General Aviation ◽  
Aviation Fuel ◽  
Control Analysis ◽  
Hybrid Propulsion ◽  
Fuel Prices ◽  
Electric Aircraft ◽  
General Aviation Aircraft

Financial and environmental considerations continue to encourage aircraft manufacturers to consider alternate forms of aircraft propulsion. On the financial end, it is the continued rise in aviation fuel prices, as a result of an increasing demand for air travel, and the depletion of fossil fuel resources; on the environmental end, it is concerns related to air pollution and global warming. New aircraft designs are being proposed using electrical and hybrid propulsion systems, as a way of tackling both the financial and environmental challenges associated with the continued use of fossil fuels. While battery capabilities are evolving rapidly, the current state-of-the-art offers an energy density of ~ 250 Wh/kg. This is sufficient for small, general aviation electric airplanes, with a modest range no more than 200 km. This paper explores the possibility of a medium range (750 km) electric, four-seat, FAR-23 certifiable general aviation aircraft, assuming an energy density of 1500 Wh/kg, projected to be available in 2025. It presents the conceptual and preliminary design of such an aircraft, which includes weight and performance sizing, fuselage design, wing and high-lift system design, empennage design, landing gear design, weight and balance, stability and control analysis, drag polar estimation, environmental impact and final specifications. The results indicate that such an aircraft is indeed feasible, promising greener general aviation fleets around the world. Keywords: general aviation aircraft, electric aircraft, aircraft design

Sign in / Sign up

Export Citation Format

Share Document