This thesis develops a mathematical optimization model to optimize charging schedules and energy management for electrified aircraft at Rotterdam The Hague Airport (RTHA), addressing research gaps in adapting airport infrastructure for electric aviation. Based on a real-life flight schedule from 2019, the model determines a Battery Energy Storage System (BESS) size while minimizing operational costs, such as grid electricity, photovoltaic (PV) use, BESS degradation, and flight delay/cancellation penalties, while trying to maintain the schedule as closely as possible. Five electric aircraft types, ranging from a 2-seater flight school aircraft, to a 90-seater commercial aviation model, were considered with a Constant Power - Constant Voltage (CPCV) charging profile, alongside a detailed mission energy analysis. Seasonal simulation for January, April, July, and October 2019 showed delays averaging from 2 minutes in July while peaking at 45 in January, alongside three flight cancellations due to high energy demands. Optimized BESS sizes range from 7 MWh to 12 MWh. Optimization of the model showed a reduction of up to €500,000 weekly when compared to a baseline case. Sensitivity analysis showed that increasing the grid import limits from 3.5 MW to 5 MW gave better grid reliability, with less delays and cancellations, while a decrease to 2 MW showed increases in delay times and cancellations. When the export limit was reduced from 7.5 MW to 5 MW, the delays increased due to constrained energy offloading, while increasing it to 10 MW decreased the delays and cancellations by one. A 1 MWh BESS increase reduced cancellations by one and total delay time by up to 5 hours. Adjusting the turnaround times by ± 15 minutes demonstrated the model’s resilience to stricter turnaround times, but a 4-hour delay increase was present with extensions. The findings of the thesis show the critical role that BESS capacity and grid limits play in ensuring operational efficiency for the electric aviation infrastructures of the future, but also the cost and delay reduction by optimizing charging schedules.

Aviation is a growing industry responsible for over 2% of the energy-related CO2 emissions in 2021. To achieve the 'Net Zero Emission by 2050 scenario', the aviation industry is turning towards modern propulsion technologies that reduce carbon and NOx emissions. Research is taking place on many prospective aircraft designs, such as hybrid/turbo-electric powertrains, fuel cell/liquid hydrogen-powered aircraft and fully electric aircraft. Although fully electric aircraft offer the cleanest possible air travel, these aircraft are considered the solution for short-haul flights due to the range extension issue caused by the deficient specific energy of batteries compared to currently used aviation fuel. The electric aircraft concept designers rely on the potential development in battery technology while proposing their designs, and sporadic state-of-the-art battery designs are present concerning electric aviation.

The concept of reconfigurable battery packs involves using power switches to modify the arrangement of connected battery cells based on specific requirements. This innovative technique can potentially significantly reduce the weight of battery packs. The primary objective of this thesis was to conduct a comprehensive analysis and comparison between fixed configuration and reconfigurable battery packs in the context of electric aviation. It was imperative first to design these battery packs to facilitate this comparison. Given the limited availability of open data on electric aircraft designs, the power profile was estimated using available reference aircraft specifications and reasonable assumptions. The literature review on power systems in aircraft revealed a significant correlation between system-level voltage and the weight of power cables. This discovery led to estimating an optimal system-level voltage, a critical constraint in battery sizing. For the fixed configuration battery pack, sizing was conducted using both a high-specific energy cell and a high-specific power cell. The design of a reconfigurable battery pack involved strategically leveraging both cell types. This innovative approach created a reconfigurable battery pack capable of dynamically connecting and disconnecting an internal high-specific energy battery pack called the 'primary battery pack' and a high-specific power battery pack known as the 'secondary battery pack' through power switches, allowing them to complement each other during high-power demand phases of flight, such as take-off and climbing.

Software simulations were conducted for the validation of this technique. These simulations revealed that the reconfigurable battery pack experienced higher C-rates than the fixed configuration battery pack. Given that higher C-rates can impact battery health by inducing capacity loss over multiple cycles, a preliminary ageing analysis was performed to quantitatively assess the adverse effects of higher C-rates on the reconfigurable battery pack.

The results quantified that around 400 kg of potential weight savings is possible by employing reconfigurable battery packs over fixed configuration battery packs at only 0.4% more capacity loss over 500 charging-discharging cycles. The weight savings can be translated into three different scenarios. Firstly, payload weight capacity can be enhanced. Secondly, flying with lesser weight will offset the power profile, saving energy. Lastly, an additional number of cells equivalent to the mass saved can realise the range extension of the electric aircraft.