Abstract: An energy recovery assembly, fuel cell system and vehicle, with an electrolyzer configured to provide a fuel and an oxidant, a fuel cell configured to convert the fuel and an oxidant to electrical energy, a tank configured to store the fuel or the oxidant, and a conduction pathway connecting the tank to the electrolyzer and the fuel cell. The assembly also includes: an expansion machine disposed in the conduction pathway and configured to expand a fluid flowing through the expansion machine and to obtain mechanical energy; and a valve arrangement configured to put the pathway in a first mode in which the fuel or the oxidant is guided to the tank, or in a second mode in which the fuel cell or the oxidant is guided to the fuel cell, wherein the fuel or the oxidant in the first and second modes flows through the expansion machine.

Abstract: An aircraft tail region including a cooling system installed in the aircraft tail region. The cooling system comprises a cooler, which forms a section of an outer skin of the aircraft tail region, and includes coolant channels allowing a flow of ambient air therethrough, and extending from a first surface of the cooler to a second surface of the cooler. The cooling system also includes a fan system, which is adapted to convey ambient air through the coolant channels of the cooler at least in specified operating phases of the cooling system, and a first opening, which is formed in the outer skin of the aircraft tail region, and which allows, in conveying operation of the fan system, ambient air which is supplied through the coolant channels of the cooler into an interior of the aircraft tail region to be discharged back into the aircraft environment.

Abstract: The invention pertains to a de-icing system for an aircraft with at least one heat source and at least one air delivery means for delivering air into regions of the aircraft to be de-iced. In comparison with the prior art, the invention is characterized in that the air delivery means is connected to an air-conditioning system of the aircraft for discharging air from the cabin of the aircraft via an air heating device, wherein the air heating device is connected to at least one heat source in order to heat the air from the cabin of the aircraft. The de-icing system according to the invention is able to realize a wing de-icing that not only fulfills an anti-icing function, but also a de-icing function on the ground without additional expenditure of energy.

Abstract: An aircraft tail region including a cooling system installed in the aircraft tail region. The cooling system comprises a cooler, which forms a section of an outer skin of the aircraft tail region, and includes coolant channels allowing a flow of ambient air therethrough, and extending from a first surface of the cooler to a second surface of the cooler. The cooling system also includes a fan system, which is adapted to convey ambient air through the coolant channels of the cooler at least in specified operating phases of the cooling system, and a first opening, which is formed in the outer skin of the aircraft tail region, and which allows, in conveying operation of the fan system, ambient air which is supplied through the coolant channels of the cooler into an interior of the aircraft tail region to be discharged back into the aircraft environment.

Abstract: An aircraft cooling system (10) comprises a cooling element (12), which comprises a housing (14), a cooling air inlet (18) formed in the housing (14) and a plurality of heat exchangers (32, 34, 36, 38), which are disposed on lateral surfaces (24, 26, 28, 30) of the housing (14) and through which cooling air supplied through the cooling air inlet (18) may flow. A cooling air supply channel (40, 40?) connects a cooling air supply opening (44, 44?) formed in a tail section of an aircraft to the cooling air inlet (18) of the cooling element (12). A cooling air outlet channel (46) connects the heat exchangers (32, 34, 36, 38) of the cooling element (12) to a cooling air discharge opening (50).

Abstract: The invention pertains to a de-icing system for an aircraft with at least one heat source and at least one air delivery means for delivering air into regions of the aircraft to be de-iced. In comparison with the prior art, the invention is characterized in that the air delivery means is connected to an air-conditioning system of the aircraft for discharging air from the cabin of the aircraft via an air heating device, wherein the air heating device is connected to at least one heat source in order to heat the air from the cabin of the aircraft. The de-icing system according to the invention is able to realize a wing de-icing that not only fulfills an anti-icing function, but also a de-icing function on the ground without additional expenditure of energy.

Abstract: An aircraft cooling system (10) comprises a cooling element (12), which comprises a housing (14), a cooling air inlet (18) formed in the housing (14) and a plurality of heat exchangers (32, 34, 36, 38), which are disposed on lateral surfaces (24, 26, 28, 30) of the housing (14) and through which cooling air supplied through the cooling air inlet (18) may flow. A cooling air supply channel (40, 40?) connects a cooling air supply opening (44, 44?) formed in a tail section of an aircraft to the cooling air inlet (18) of the cooling element (12). A cooling air outlet channel (46) connects the heat exchangers (32, 34, 36, 38) of the cooling element (12) to a cooling air discharge opening (50).