Abstract
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.
Highlights
In response to the ongoing strong growth in air traffic (e.g. [1]) and its impact on the natural environment, ambitious targets and roadmaps for future aviation have been defined (e.g. [2], [3])
This paper focuses on the power management and system sizing of a so-called parallel Hybrid electric propulsion (HEP) architecture
The following main electric systems are considered: electric motors, batteries and power electronics for parallel HEP, electric components for replacement of the main hydraulic and pneumatic non-propulsive systems like the environmental control system (ECS), flight control system (FCS), ice protection system (IPS) and landing gear (LG) actuation. Besides these electric system models, models of the aircraft, turbofan engine and flight mission are used to quantify the power and fuel needs and account for system mass changes involved with the electric components replacements
Summary
In response to the ongoing strong growth in air traffic (e.g. [1]) and its impact on the natural environment, ambitious targets and roadmaps for future aviation have been defined (e.g. [2], [3]). HEP systems were first introduced on a large scale in the automotive sector and are making their way to the aviation industry These HEP systems attempt to reduce fuel consumption and emissions of traditional combustion engines through hybridisation via electrical energy sources. Another trend in the aviation industry is the electrification of aircraft subsystem architectures. The following main electric systems are considered: electric motors, batteries and power electronics for parallel HEP, electric components for replacement of the main hydraulic and pneumatic non-propulsive systems like the environmental control system (ECS), flight control system (FCS), ice protection system (IPS) and landing gear (LG) actuation Besides these electric system models, models of the aircraft, turbofan engine and flight mission are used to quantify the power and fuel needs and account for system mass changes involved with the electric components replacements. The results in terms of fuel- and energy consumption for the considered missions are reported
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