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 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%.

scholarly journals Design and Optimization of Ram Air-Based Thermal Management Systems for Hybrid-Electric Aircraft

Aerospace ◽  
2020 ◽  
Vol 8 (1) ◽  
pp. 3
Author(s):  
Hagen Kellermann ◽  
Michael Lüdemann ◽  
Markus Pohl ◽  
Mirko Hornung
Keyword(s):  
Thermal Management ◽  
Sensitivity Analyses ◽  
Management Systems ◽  
Dimensional System ◽  
System Sensitivity ◽  
Design And Optimization ◽  
Fuel Burn ◽  
Electric Aircraft ◽  
Power Split ◽  
Hybrid Electric

Ram air-based thermal management systems (TMS) are investigated herein for the cooling of future hybrid-electric aircraft. The developed TMS model consists of all components required to estimate the impacts of mass, drag, and fuel burn on the aircraft, including the heat exchangers, coldplates, ducts, pumps, and fans. To gain a better understanding of the TMS, one- and multi-dimensional system sensitivity analyses were conducted. The observations were used to aid with the numerical optimization of a ram air-based TMS towards the minimum fuel burn of a 180-passenger short-range turboelectric aircraft with a power split of up to 30% electric power. The TMS was designed for the conditions at the top of the climb. For an aircraft with the maximum power split, the additional fuel burn caused by the TMS is 0.19%. Conditions occurring at a hot-day takeoff represent the most challenging off-design conditions for TMS. Steady-state cooling of all electric components with the designed TMS is possible during a hot-day takeoff if a small puller fan is utilized. Omitting the puller fan and instead oversizing the TMS is an alternative, but the fuel burn increase on the aircraft level grows to 0.29%.

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