Session: 01-02 Conceptual Design and Optimization I

Paper Number: 126483

126483 - Advanced Power Management Strategies for Complex Hybrid-Electric Aircraft 

Aircraft electrification for propulsion is a promising way to alleviate the negative environmental impact of conventional carbon-powered aviation. Inclusion of the electrical powertrain aims to enhance design freedom allowing for more efficient and flexible power systems and operational schemes, which can be the gateway to sustainable propulsion.

In this work a design space exploration is performed aiming to derive power management guidelines based on aircraft environmental performance. Different component and system technologies are assessed in parallel with intrinsic system design constraints and aircraft-level customer requirements. Care is given to the link between electrical power system and the constraints and synergies that arise at the integrated system-level design, due to available and projected battery and electrical drive technology and topologies.

A 19-passenger commuter aircraft employing the series/parallel partial hybrid-electric architecture is examined. Two underwing-mounted turboprop engines act as the main propulsors. These are assisted by a boundary layer ingestion fan mounted in the aft of the aircraft and powered by an electrical drive. The primary electrical energy source is a battery system. Coupling of thermal engines with electrical generators allows for power extraction and conversion from chemical to electrical for propulsion and battery charging. A multi-disciplinary framework is utilized, comprising modelling approaches for multi-point thermal engine design, physics-based electrical component sizing and performance, aircraft sizing, mission design, and environmental assessment.

The investigation revealed a Pareto front where designs of high and low degree of hybridization yield different positive outcomes. Moreover, the level of utilization of the electrical power system generates further trade-offs with respect to overall efficient system performance. Low degrees of hybridization were favoured by designs that minimized battery weight and as an outcome achieved environmental benefits by reduced aircraft weight. Designs of high degree of hybridization suffered by increased battery and aircraft mass but capitalized on electrification more, yielding greater emissions reduction. Finally, designs that did not deplete the battery fully, still lead to reduced environmental impact, showcasing the potential for multiple flights between on-ground battery charging. This work showcases potential power management strategies in complex hybrid-electric architectures and correlates them with the integrated system design and aircraft requirements.

Presenting Author: Dimitrios Bermperis Mälardalen University

Presenting Author Biography: Dimitrios Bermperis holds a Diploma in Mechanical Engineering from the Aristotle University of Thessaloniki. He is currently working as a PhD candidate at Mälardalen University focusing on modelling and simulation of novel hybrid-electric and hydrogen-fired power systems with the goal of sustainable aviation.

Authors:

Dimitrios Bermperis Mälardalen University
Mavroudis D. Kavvalos German Aerospace Center (DLR)
Stavros Vouros Mälardalen University
Konstantinos Kyprianidis Mälardalen University