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The objective of this work is to perform a trade-off study between aircraft air conditioning systems based on conventional technology (Engine Pneumatic Bleed based) and the proposed bleedless architecture, based on the MEA (More Electric Aircraft) and Bleedless Engines concept. The pneumatic bleed system components are thus eliminated and a dedicated compressor serves as the main power supply to the air conditioning and pressurization system. Both the conventional and the proposed ECS architecture are described and the system main parameters are calculated. The aircraft used as baseline for the study is a typical regional jet. The operational characteristics and aspects of costs, weight, energy efficiency, maintainability and impacts on other systems of the aircraft were also considered. The proposed air conditioning architecture is compared to a conventional one in terms of weight, system price and power and fuel consumptions.

Nowadays, the most common technologies used in the aircraft ice protection systems use indirect methods that identify atmospheric conditions prone to ice accretion, and not in fact the ice accretion over the surfaces, not measuring this accreted ice. On top of that, the ice protection systems are designed based on a certain flight phase considered the most critical for the system and its operation does not depend on the severity of the ice condition. Using direct methods for detecting the ice accretion on the protected areas and a control system based on the feedback of these sensors, it is possible to reduce the energetic consumption and measuring the ice accreted, optimize it, reducing the penalties for the propulsion system and the aircraft design.