Performance analysis of electrical environmental control and ice protection systems in a commercial transport aircraft

• Published in: Aircraft engineering 2024-03, Vol.96 (2), p.193-204
• Main Authors: Ercan, Hamdi, Öztürk, Cüneyt, Akın, Mustafa
• Format: Article
• Language: English
• Subjects: Aircraft; Aircraft models; Civil aviation; Commercial aircraft; Economic impact; Energy consumption; Engines; Environmental control; Fuel consumption; Heat; Hydraulics; Linear programming; Optimization; Pneumatics; Power; Power consumption; Temperature profiles; Transport aircraft; Weight
• ISSN: 1748-8842; 1758-4213; 1748-8842
• DOI: 10.1108/AEAT-01-2023-0019

Purpose This paper aims to assess the impact of electrifying the environmental control system (ECS) and ice protection system (IPS), the primary pneumatic system consumers in a conventional commercial transport aircraft, on aircraft weight, range, and fuel consumption. Design/methodology/approach The case study was carried out on Airbus A321-200 aircraft. Design, modelling and analysis processes were carried out on Pacelab SysArc software. Conventional and electrical ECS and IPS architectures were modelled and analysed considering different temperature profiles. Findings The simulation results have shown that the aircraft model with ±270 VDC ECS and IPS architecture is lighter, has a more extended range and has less relative fuel consumption. In addition, the simulation results showed that the maximum range and relative fuel economy of all three aircraft models increased slightly as the temperature increased. Practical implications Considering the findings in this paper, it is seen that the electrification of the conventional pneumatic system in aircraft has positive contributions in terms of weight, power consumption and fuel consumption. Social implications The positive contributions in terms of weight, power consumption and fuel consumption in aircraft will be direct environmental and economic contributions. Originality/value Apart from the conventional ECS and IPS of the aircraft, two electrical architectures, 230 VAC and ±270 VDC, were modelled and analysed. To see the effects of the three models created in different temperature profiles, analyses were done for cold day, ISA standard day and hot day temperature profiles.