scholarly journals Analysis and design of hybrid electric regional turboprop aircraft

2017 ◽  
Vol 9 (1) ◽  
pp. 15-25 ◽  
Author(s):  
Mark Voskuijl ◽  
Joris van Bogaert ◽  
Arvind G. Rao
Keyword(s):  
Electric Propulsion ◽  
Environmental Benefits ◽  
Analysis And Design ◽  
Electric Aircraft ◽  
Shaft Power ◽  
Hybrid Electric ◽  
And Performance ◽  
Battery Technology ◽  
Range Equation ◽  
Technology Level

Abstract The potential environmental benefits of hybrid electric regional turboprop aircraft in terms of fuel consumption are investigated. Lithium–air batteries are used as energy source in combination with conventional fuel. A validated design and analysis framework is extended with sizing and analysis modules for hybrid electric propulsion system components. In addition, a modified Bréguet range equation, suitable for hybrid electric aircraft, is introduced. The results quantify the limits in range and performance for this type of aircraft as a function of battery technology level. A typical design for 70 passengers with a design range of 1528 km, based on batteries with a specific energy of 1000 Wh/kg, providing 34% of the shaft power throughout the mission, yields a reduction in emissions by 28%.

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.

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

2020 ◽  
Author(s):  
Vasilis G. Gkoutzamanis ◽  
Arjun Srinivas ◽  
Doukaini Mavroudi ◽  
Anestis I. Kalfas ◽  
Mavroudis D. Kavvalos ◽  
...  
Keyword(s):  
Energy Storage ◽  
Conceptual Design ◽  
Electric Propulsion ◽  
Co2 Reduction ◽  
Requirements Definition ◽  
Operational Characteristics ◽  
Electric Aircraft ◽  
Design Requirements ◽  
Hybrid Electric ◽  
Battery Technology

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 some dominating 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 that are under research and development. After the requirements definition, the first level of conceptual design is employed. Based on 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, to highlight the multidisciplinary aspects between the sizing of an aircraft, the selected architecture (series/parallel partial hybrid) and the energy storage operational characteristics. 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 fulfill 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 (targeted range, payload, battery technology). Finally, the lower degree of hybridization (40%) is observed to have a 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.

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.

Design Exploration and Performance Assessment of Advanced Recuperated Hybrid-Electric UAM Rotorcraft

2021 ◽  
Author(s):  
Chana Anna Saias ◽  
Ioannis Roumeliotis ◽  
Ioannis Goulos ◽  
Vassilios Pachidis ◽  
Marko Bacic
Keyword(s):  
Environmental Impact ◽  
Electric Propulsion ◽  
Simulation Framework ◽  
Design Exploration ◽  
Rotor Aerodynamics ◽  
Fuel Burn ◽  
Trade Offs ◽  
Parallel Hybrid ◽  
Hybrid Electric ◽  
And Performance

Abstract The design of efficient, environmentally friendly and quiet powerplant for rotorcraft architectures constitutes a key enabler for Urban Air Mobility application. This work focuses on the development and application of a generic methodology for the design, performance and environmental impact assessment of a parallel hybrid-electric propulsion system, utilizing simple and advanced recuperated engine cycles. A simulation framework for rotorcraft analysis comprising models for rotor aerodynamics, flight dynamics and hybrid-electric powerplant performance is deployed for the design exploration and optimization of a hybrid-electric rotorcraft, modelled after the NASA XV-15, adapted for civil applications. Optimally designed powerplants for payload-range capacity, energy efficiency and environmental impact have been obtained. A comparative evaluation has been performed for the optimum designs. The respective trade-offs between engine, heat exchanger weight, thermal efficiency, as well as mission fuel burn and environmental impact have been quantified. It has been demonstrated that a recuperated gas turbine based hybrid-electric architecture may provide improvements of up to 6% in mission range capability without sacrificing useful load. At the same time, analyses performed for a representative 100 km mission suggest reductions in fuel burn and NOX emissions of up to 12.9% and 5.2% respectively. Analyses are carried at aircraft and mission level using realistic UAM mission scenarios.

Sizing, Integration and Performance Evaluation of Hybrid Electric Propulsion Subsystem Architectures

2017 ◽  
Author(s):  
Gokcin Cinar ◽  
Dimitri N. Mavris ◽  
Mathias Emeneth ◽  
Alexander Schneegans ◽  
Carsten Riediger ◽  
...  
Keyword(s):  
Performance Evaluation ◽  
Electric Propulsion ◽  
Hybrid Electric ◽  
And Performance

scholarly journals Parallel hybrid electric propulsion architecture for single aisle aircraft - powertrain investigation

2019 ◽  
Vol 304 ◽  
pp. 03008 ◽  
Author(s):  
Jos Vankan ◽  
Wim Lammen
Keyword(s):  
Electric Propulsion ◽  
Environmental Control ◽  
System Modelling ◽  
Fuel Saving ◽  
Electric Motors ◽  
Energy Saving Potential ◽  
Electric Aircraft ◽  
Parallel Hybrid ◽  
Hybrid Electric ◽  
More Electric Aircraft

This paper presents an investigation of the fuel- and energy-saving potential through the introduction of several hybrid electric propulsion (HEP) and more electric aircraft (MEA) systems on single aisle aircraft. More specifically, for an A320NEO the following main electric systems are considered: electric motors, batteries and power electronics for parallel HEP, electric components for replacement of the main pneumatic and hydraulic non-propulsive systems like environmental control system and actuators, and electric power transport and supply. The power sizing of the electric components, as well as their mass effects on overall aircraft mission performance are evaluated by system modelling of the aircraft, turbofan and the considered electric components. It is found for the considered aircraft and missions that the fuel saving potential of parallel HEP systems alone is very limited or absent. Typically the combination of HEP and MEA technologies shows potential for improved energy efficiency due to synergies of the involved systems and their operation.

scholarly journals Range Equation for Hybrid-Electric Aircraft with Constant Power Split

2020 ◽  
Vol 57 (3) ◽  
pp. 552-557 ◽  
Author(s):  
Reynard de Vries ◽  
Maurice F. M. Hoogreef ◽  
Roelof Vos
Keyword(s):  
Constant Power ◽  
Electric Aircraft ◽  
Power Split ◽  
Hybrid Electric ◽  
Range Equation

scholarly journals Review of State-of-the-Art Green Monopropellants: For Propulsion Systems Analysts and Designers

Aerospace ◽  
2021 ◽  
Vol 8 (1) ◽  
pp. 20
Author(s):  
Ahmed E. S. Nosseir ◽  
Angelo Cervone ◽  
Angelo Pasini
Keyword(s):  
Environmental Sustainability ◽  
Electric Propulsion ◽  
High Performance ◽  
Systems Design ◽  
Propulsion Systems ◽  
Space Applications ◽  
Analysis And Design ◽  
Research Activities ◽  
Systems Analysts ◽  
And Performance

Current research trends have advanced the use of “green propellants” on a wide scale for spacecraft in various space missions; mainly for environmental sustainability and safety concerns. Small satellites, particularly micro and nanosatellites, evolved from passive planetary-orbiting to being able to perform active orbital operations that may require high-thrust impulsive capabilities. Thus, onboard primary and auxiliary propulsion systems capable of performing such orbital operations are required. Novelty in primary propulsion systems design calls for specific attention to miniaturization, which can be achieved, along the above-mentioned orbital transfer capabilities, by utilizing green monopropellants due to their relative high performance together with simplicity, and better storability when compared to gaseous and bi-propellants, especially for miniaturized systems. Owing to the ongoing rapid research activities in the green-propulsion field, it was necessary to extensively study and collect various data of green monopropellants properties and performance that would further assist analysts and designers in the research and development of liquid propulsion systems. This review traces the history and origins of green monopropellants and after intensive study of physicochemical properties of such propellants it was possible to classify green monopropellants to three main classes: Energetic Ionic Liquids (EILs), Liquid NOx Monopropellants, and Hydrogen Peroxide Aqueous Solutions (HPAS). Further, the tabulated data and performance comparisons will provide substantial assistance in using analysis tools—such as: Rocket Propulsion Analysis (RPA) and NASA CEA—for engineers and scientists dealing with chemical propulsion systems analysis and design. Some applications of green monopropellants were discussed through different propulsion systems configurations such as: multi-mode, dual mode, and combined chemical–electric propulsion. Although the in-space demonstrated EILs (i.e., AF-M315E and LMP-103S) are widely proposed and utilized in many space applications, the investigation transpired that NOx fuel blends possess the highest performance, while HPAS yield the lowest performance even compared to hydrazine.

scholarly journals The potential of full-electric aircraft for civil transportation: from the Breguet range equation to operational aspects

2021 ◽  
Author(s):  
Ingo Staack ◽  
Alejandro Sobron ◽  
Petter Krus
Keyword(s):  
Electric Propulsion ◽  
Air Transportation ◽  
High Expectations ◽  
Free Air ◽  
Electric Aircraft ◽  
Short And Long Term ◽  
Conceptual Study ◽  
Key Enabling Technologies ◽  
Range Equation

AbstractThe decades-old idea of electric-powered commercial flight has re-emerged alongside high expectations for greener CO2 emission-free air transportation. But to what extent can electric aircraft reduce the energy and environmental footprint of aviation? What should such aircraft look like, and how does their operation compare to conventional jet aircraft? What technologies are needed and which of them are already in place? This paper goes back to the basics of flight physics and critically analyzes some of the unresolved challenges that lay ahead. Current commercial operations are examined and the short-term effects of any electrification of short-range flights are quantified. Fundamental system components and basic design and operating concepts are analysed to highlight unavoidable constraints that often seem to be misunderstood or overlooked. These limitations are illustrated with a conceptual study of a full-electric FAR/CS-23 commuter aircraft and realistic estimations of its performance. It becomes clear that electric propulsion alone will not fully meet society’s expectations, even if key enabling technologies continue to develop as forecast. Nevertheless, this paper suggests that electrification may instead become one piece of a propulsion-technology mix that would more effectively address our short- and long-term emission goals.

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