Air conditioning method and system for aircraft

1. Air conditioning system for a pressurised cabin of an aircraft including at least one main engine, said system comprising:

an air withdrawal module including one or more ambient outside air inlets, said withdrawal module withdrawing air which is not withdrawn from the at least one main engine and which is configured for withdrawing one single open ambient air flow from outside the aircraft through said one or more ambient outside air inlets which is formed, either by a dynamic air inlet or by a controllable valve,

an air compression module independent from the at least one main engine configured for compressing the single open ambient air flow withdrawn from outside the aircraft to create a single compressed air flow, and

an air cooling module configured for cooling the single compressed air flow by means of a cryogenic fluid, the air cooling module comprising a condenser for condensing water from the single open ambient air flow, a water extractor for extracting said water, a cooler for cooling said single open ambient air flow emitted by the water extractor and a tank for cryogenic fluid, by means of which the water from the single open ambient air flow is condensed in the condenser and the single open ambient air flow emitted by the water extractor is cooled in the cooler,

wherein the single compressed air flow being either directed to the air cooling module or to a thermal exchange module by means of an air flow orientation module, and

wherein the cooling module is configured for delivering a gaseous fluid produced by a heat exchange between the single compressed air flow and a cryogenic fluid, the gaseous fluid being routed towards the thermal exchange module for supply to a turbine.

2. System according to claim 1 , wherein the cooling module is contained within a housing.

3. System according to claim 1 , in which the thermal exchange module arranged between the air compression module and the cooling module and configured for cooling the single compressed air flow received from the air compression module by means of the flow of gaseous fluid delivered by the cooling module, and for routing, on the one hand, the single compressed air flow thus cooled towards the cooling module and, on the other hand, the flow of gaseous fluid towards a heating module.

4. System according to claim 1 , in which the air flow orientation module arranged between the compression module and the cooling module and configured for orienting the single open ambient air flow compressed by the air compression module towards the air cooling module when a temperature of the single compressed air flow is greater than a temperature required at the inlet of an air conditioning module of the cabin, or towards a heating module when the temperature of the single compressed air flow is lower than the temperature required at the inlet of the air conditioning module of the cabin.

5. System according to claim 1 , said system comprising a heating module configured for receiving, from the thermal exchange module, a flow of gaseous fluid and for routing said flow of gaseous fluid towards a turbine, and for receiving, from the air orientation module, the single compressed air flow to be reheated and for routing said flow of gaseous fluid towards an air conditioning module of the cabin of the aircraft.

6. Aircraft comprising the air conditioning system according to claim 1 .

7. System according to claim 1 , wherein the air compression module is configured for compressing the single open ambient air flow at a low compression rate between 3 or 4.