Abstract: A system for controlling a cooling system comprises an operating state detection unit adapted to detect operating signals characteristic of the operating state of the cooling system and/or the operating state of a plurality of cooling energy consumers to be supplied with cooling energy by the cooling system and a database in which priority data dependent on the operating state and characteristic of the priority to be given to the cooling energy consumers in terms of the cooling energy to be supplied in various operating states of the cooling system and/or of the cooling energy consumers, is stored for a plurality of cooling energy consumers to be supplied with cooling energy by the cooling system.

Abstract: An air conditioning system for an aircraft for the individual air conditioning of regions of a cabin of an aircraft includes a central air conditioning device, which provides a pressurized and temperature-controlled central air flow. A part of the central air flow is supplied to a first cabin region. Another part of the central air flow is heated in a heating device or cooled in a cooling device and supplied to another cabin region. Water evaporates in the cooling device, in order to cool the air flow to be supplied to the cabin region.

Abstract: A system for cooling and/or heating aircraft devices to be cooled and/or heated includes a first individual cooling and/or heating system associated with a first aircraft device to be cooled and/or heated, a second individual cooling and/or heating system associated with a second aircraft device to be cooled and/or heated, a cooling and/or heating energy supply apparatus adapted to supply cooling and/or heating energy generated by the first and/or the second individual cooling and/or heating system to the first and/or the second aircraft device to be cooled and/or heated, a control device adapted to receive and process signals characteristic of the cooling and/or heating requirements of the first and/or the second aircraft device to be cooled and/or heated and of the load condition of the first and/or the second individual cooling and/or heating system.

Abstract: An aircraft battery exhaust system comprises a fluid discharge opening formed in an aircraft outer skin and a fluid discharge line having a first end connected to the fluid discharge opening and a second end. A first fluid discharge branch line has a first end connected to the second end of the fluid discharge line and a second end connected to a first battery in such a manner that a fluid leaking from the first battery is directed into the first fluid discharge branch line. A second fluid discharge branch line has a first end connected to the second end of the fluid discharge line and a second end connected to a second battery in such a manner that a fluid leaking from the second battery is directed into the second fluid discharge branch line.

Abstract: An air conditioning system in an aircraft is provided. The system comprises at least one air cycle air-conditioning pack with a compressor comprising a bleed air outlet and with a compressed-air line connected to the bleed air connection, which compressed-air line is connectable to a starter turbine for a main engine. With the use of air from a compressor of an air conditioning pack it is not necessary to switch off the air conditioning pack; bleed air removal from the auxiliary power units becomes obsolete; and, since there is no unnecessary discharge of compressed air from a bleed air system, noise pollution on the ground is reduced.

Abstract: A process for management of thermal effluents of an aircraft that includes an airframe (110) and at least one propulsion system (112), whereby the at least one propulsion system (112) includes a gas turbine engine (116) that is supplied with fuel via a fuel supply circuit (122) that extends from a reservoir (124) that is arranged at the airframe (110), whereby the airframe (110) includes at least one source of thermal effluents (134), wherein the process includes at least partially dissipating—at the level of at least one propulsion system (112)—the thermal effluents that are generated at the airframe (110) by using as coolant the fuel that is used for supplying the gas turbine engine (116).

Abstract: A cooling air inlet which is particularly suitable for use in an engine bleed air system of an aircraft air conditioning system. The cooling air inlet comprises a cooling air inlet opening which opens into an inlet portion of a cooling air line. A cooling air inlet valve which is positionable in a first open position or a second open position is arranged in the inlet portion of the cooling air line. The cooling air inlet valve is adapted to effect the build-up of a first cooling air admission pressure in the inlet portion of the cooling air line in its first open position and the build-up of a second cooling air admission pressure in the inlet portion of the cooling air line in its second open position. The second cooling air admission pressure is greater than the first cooling air inlet pressure.

Abstract: An energy supply system for operating at least one air conditioning system of an aircraft, comprises at least one air line network and at least one electric line network. The air line network is connected to the air conditioning system and at least one bleed air connection for routing bleed air to the air conditioning system. The electric line network is connected to the air conditioning system and at least one electrical energy source for routing electrical energy to the air conditioning system. The air conditioning system has an electrically operable cooling device. By means of the energy supply system according to the invention the energy withdrawn from the power units is better adapted to the energy necessary for operating the air conditioning system and other systems—such as, for example, wing de-icing—and therefore reduces the excess fuel consumption of the aircraft.

Abstract: A system for cooling and/or heating aircraft devices to be cooled and/or heated includes a first individual cooling and/or heating system associated with a first aircraft device to be cooled and/or heated, a second individual cooling and/or heating system associated with a second aircraft device to be cooled and/or heated, a cooling and/or heating energy supply apparatus adapted to supply cooling and/or heating energy generated by the first and/or the second individual cooling and/or heating system to the first and/or the second aircraft device to be cooled and/or heated, a control device adapted to receive and process signals characteristic of the cooling and/or heating requirements of the first and/or the second aircraft device to be cooled and/or heated and of the load condition of the first and/or the second individual cooling and/or heating system.

Abstract: A system for controlling a cooling system comprises an operating state detection unit adapted to detect operating signals characteristic of the operating state of the cooling system and/or the operating state of a plurality of cooling energy consumers to be supplied with cooling energy by the cooling system and a database in which priority data dependent on the operating state and characteristic of the priority to be given to the cooling energy consumers in terms of the cooling energy to be supplied in various operating states of the cooling system and/or of the cooling energy consumers, is stored for a plurality of cooling energy consumers to be supplied with cooling energy by the cooling system.

Abstract: A system is provided for cooling at least one heat producing device in an aircraft that includes, but is not limited to at least one coolant circuit. A coolant absorbs heat from the heat producing device and dissipates heat, by way of a heat dissipation device, to the surroundings of the aircraft. A temperature spreading device reduces the temperature of the coolant in a feed line of the coolant circuit and increases the heat dissipation temperature of the heat dissipation device relative to the temperature of the coolant in a return line of the coolant circuit. In this manner ram air ducts that are commonly used in the state of the art or systems that consume pre-cooled air can be avoided, which in particular when the aircraft is situated on the ground on hot days can render avionics cooling or the like difficult.

Abstract: The present invention relates to a method for insulating an aircraft cabin 6 and for the cooling or heating of cabin air in an aircraft, respectively with the method comprising the steps of: introducing aircraft cabin air into an aircraft cabin wall 6; guiding this aircraft cabin air along a section of this aircraft cabin wall 6; and leading this aircraft cabin air away from the aircraft cabin wall 6.

Abstract: An energy supply system for operating at least one air conditioning system of an aircraft, comprises at least one air line network and at least one electric line network. The air line network is connected to the air conditioning system and at least one bleed air connection for routing bleed air to the air conditioning system. The electric line network is connected to the air conditioning system and at least one electrical energy source for routing electrical energy to the air conditioning system. The air conditioning system has an electrically operable cooling device. By means of the energy supply system according to the invention the energy withdrawn from the power units is better adapted to the energy necessary for operating the air conditioning system and other systems—such as, for example, wing de-icing—and therefore reduces the excess fuel consumption of the aircraft.

Abstract: An air conditioning system for an aircraft for the individual air conditioning of regions of a cabin of an aircraft includes a central air conditioning device, which provides a pressurized and temperature-controlled central air flow. A part of the central air flow is supplied to a first cabin region. Another part of the central air flow is heated in a heating device or cooled in a cooling device and supplied to another cabin region. Water evaporates in the cooling device, in order to cool the air flow to be supplied to the cabin region.

Abstract: A process for management of thermal effluents of an aircraft that includes an airframe (110) and at least one propulsion system (112), whereby the at least one propulsion system (112) includes a gas turbine engine (116) that is supplied with fuel via a fuel supply circuit (122) that extends from a reservoir (124) that is arranged at the airframe (110), whereby the airframe (110) includes at least one source of thermal effluents (134), wherein the process includes at least partially dissipating—at the level of at least one propulsion system (112)—the thermal effluents that are generated at the airframe (110) by using as coolant the fuel that is used for supplying the gas turbine engine (116).

Abstract: A device for temperature regulation of sections of the interior of an aircraft includes a controlled mixer valve for the mixing of engine bleed air and air that is cooler than the engine bleed air in order to obtain pre-tempered mixed air flowing out of the mixer valve; a distribution line connected to the outlet of the mixer valve which is connected to the respective sections by at least two supply lines; individual heating units assigned to the respective sections; sensors assigned to the individual sections for the respective actual temperatures; transmitters for the respective nominal temperatures; and a regulator unit which controls the mixer valve dependent upon the respective nominal temperatures and the respective actual temperatures in the individual areas.

Abstract: The present invention relates to a method for insulating an aircraft cabin 6 and for the cooling or heating of cabin air in an aircraft, respectively with the method comprising the steps of: introducing aircraft cabin air into an aircraft cabin wall 6; guiding this aircraft cabin air along a section of this aircraft cabin wall 6; and leading this aircraft cabin air away from the aircraft cabin wall 6.