Aircraft taxiing is conventionally performed using the main engines' inefficient idle thrust. Therefore, in line with greener aviation, the electrification of taxiing is the most viable option to reduce emissions, noise, and fossil fuel consumption during ground operations. This paper studies the potential of hybridising the conventional electric taxiing system, which is currently driven by the Auxiliary Power Unit, with an electrical energy storage system, comprising commercial high-energy and high-power lithium-ion batteries, for the purpose of reducing fuel consumption. Hence, a power distribution optimisation is formulated to minimise fuel consumption over a typical worst-case taxi-out profile. Three different energy management strategies are presented for a narrow-body aeroplane. The optimisation is performed for the selection of off-the-shelf batteries so that their impact on fuel savings can be evaluated in the early design stage.The study showed that a wide range of savings is achievable according to the selected strategy, the added weight allowance and the battery characteristics. Considering a 180 kg added weight allowance and covering the three investigated strategies, up to 72% of taxiing fuel is saved.

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In the literature, there has been thorough research on reliability-based design in different fields. However, aircraft power system investigations have mostly dealt with sub-system optimization. Hence, there is considerable potential to excel innovative formulations that could promote rapid adoption of new technologies, thus favouring continuous novel solution exploration. This paper reviews reliability-based architecture design optimization concepts which have been utilised in alternate applications and could jointly be applied to this MEA problem. Furthermore, it proposes a simplified mathematical formulation to illustrate the ideas behind such approach.