Abstract: A method for controlling an aircraft air conditioning system includes the steps of detecting an operating state of an air conditioning unit of the aircraft air conditioning system and controlling the temperature of a process air mass flow supplied to the air conditioning unit in dependence on the operating state of the air conditioning unit.

Abstract: An aircraft air conditioning system comprises a plurality of temperature zones and at least one door. Comprises an air-conditioning unit configured to condition and provide air to at least one of the plurality of temperature zones, temperature zone sensors each associated with a temperature zone for measuring the temperature therein, and a control unit. The control unit receives information representing the closing state of a cabin door, and is coupled to the temperature zone sensors and configured to control the temperature of the conditioned air provided to at least one of the plurality of temperature zones in two operation modes. In a first mode, when doors are closed, the temperature control depends on the measured temperatures in the temperature zones. In the second mode, it depends on a set-temperature, independent of the measured temperature in a temperature zone affected by an open door.

Abstract: In a method for controlling an aircraft air conditioning system, a heating or cooling demand of an aircraft region to be air conditioned is determined. A volume flow of recirculation air discharged from the aircraft region to be air conditioned and a volume flow of compressed air into a mixing chamber of the aircraft air conditioning system is controlled such that the heating or cooling demand of the aircraft region to be air conditioned is met, while the volume flow of compressed air into the mixing chamber of the aircraft air conditioning system is minimized.

Abstract: The invention pertains to a relief valve (10) for being arranged on an opening (10) of a fuselage shell of an aircraft, wherein the opening (10) has a front opening edge (9a) and a rear opening edge (9a), and wherein the relief valve (10) features: a cover (13) that is arranged on the fuselage shell by means of an opening and closing device in order to open and close the opening (10) of the fuselage shell, and a prestressing device for prestressing the cover (13) into an initial position, wherein a guide plate (23) is arranged on the cover (13) by means of a mounting device (20), wherein the guide plate is spaced apart from the cover (13) and extends along the cover (13), and wherein the invention furthermore pertains to a fuselage part with such a relief valve (10) for being installed into an aircraft fuselage with a fuselage shell and a plurality of fuselage frames arranged on the inside of the fuselage shell, as well as to an aircraft fuselage with such a fuselage part.

Abstract: A system for cooling an aircraft zone includes a mixing chamber which is connected to an air-conditioning assembly for making cool air available and/or to a recirculated-air conveying device for supplying recirculated air into the mixing chamber. The system further includes an aircraft-side air-distribution system which includes at least one line connecting the mixing chamber to the aircraft zone to be cooled and also at least one line that is connectable to an aircraft-external air-generating assembly in order to route air made available by the aircraft-external air-generating assembly into the aircraft-side air-distribution system.

Abstract: A system for cooling a heat exchanger on board an aircraft includes an engine bleed air line connected to an engine of the aircraft and adapted to supply engine bleed air to the heat exchanger. The system further includes a process air line branching off from the engine bleed air line such that the engine bleed air is supplied to the process air line and connecting to an input side of a turbine. The system also includes a cooling air line connected to an output side of the turbine such that cooling air produced by an expansion of the engine bleed air supplied to the turbine is supplied to the cooling air line and then to the heat exchanger. The heat exchanger is adapted to transfer cooling energy from the cooling air to the engine bleed air supplied to the heat exchanger from the engine bleed air line.

Abstract: The invention relates to a compressor/turbine arrangement for use in an air conditioning unit of an aircraft air conditioning system comprising a process air supply line which is designed to supply process air generated by a process air source to a compressor. A detection device is designed to detect a characteristic signal for the temperature of the process air flowing through the process air supply line. A turbine is designed to drive the compressor. A cooling device is disposed in a process air line connecting the compressor to the turbine and is designed to cool the process air coming out of the compressor and flowing through the process air line in the direction of the turbine. Downstream of the cooling device a connecting line branches off from the process air line and opens into the process air supply line. A control device is designed to control a process air flow through the connecting line in dependence on the signal detected by the detection device.

Abstract: A system for cooling an aircraft region includes an air-conditioning unit for providing cool air, a circulating air conveying device, and a mixing chamber which is connected to the air conditioning unit via an air distribution line and to which circulating air can be fed by the circulating air conveying device. An inlet line which is connected to an aircraft-side connection for an aircraft-external air unit opens into the air distribution line connecting the air conditioning unit to the mixing chamber. Therefore, air flows from the aircraft-external air unit and air flow from the air-conditioning unit are simultaneously provided to the mixing unit and then to the aircraft region.

Abstract: A ventilation system for ventilation of an aircraft area includes a ram-air duct with an air inlet, a first ram-air duct branch and a second ram-air duct branch parallel to the first ram-air duct branch. A supply line connected to the ram-air duct is adapted to supply air flowing through the ram-air duct to the aircraft area to be ventilated. In the first ram-air duct branch a conveying device is arranged. In the second ram-air duct branch a heat exchanger of an aircraft system to be supplied with cooling energy is arranged. The ventilation system provides ventilation to the aircraft area during ground operation without requiring the conveying device to flow air through the heat exchanger.

Abstract: A system for air conditioning an aircraft cabin includes an air conditioning unit connected to a central mixer in order to supply the central mixer with air at a desired low temperature. A first recirculation system is designed to remove exhaust air from a first aircraft cabin region and is connected to the central mixer in order to lead the exhaust air into the central mixer. A second recirculation system is designed to remove exhaust air from a second aircraft cabin region and is connected to first and second local mixers in order to lead the exhaust air into the local mixers, the local mixers also receiving mixed air flow from the central mixer. The second recirculation system includes a cooling unit which is designed to cool the recirculation air removed from the second aircraft cabin region before delivery to the first and second local mixers.

Abstract: An aircraft air conditioning system comprises a plurality of temperature zones and at least one door. Comprises an air-conditioning unit configured to condition and provide air to at least one of the plurality of temperature zones, temperature zone sensors each associated with a temperature zone for measuring the temperature therein, and a control unit. The control unit receives information representing the closing state of a cabin door, and is coupled to the temperature zone sensors and configured to control the temperature of the conditioned air provided to at least one of the plurality of temperature zones in two operation modes. In a first mode, when doors are closed, the temperature control depends on the measured temperatures in the temperature zones. In the second mode, it depends on a set-temperature, independent of the measured temperature in a temperature zone affected by an open door.

Abstract: A method and a device determines an air mass flow flowing through a ram air channel having disposed therein a feed device adapted in a first operating state of the ram air channel to feed air through the ram air channel and further adapted in a second operating state of the ram air channel to be set in rotation by an air mass flow flowing through the ram air channel. The method includes the step of detecting an actual operational characteristic of the feed device that is characteristic of the air mass flow flowing through the ram air channel in the second operating state of the ram air channel as well as the step of determining the air mass flow flowing through the ram air channel on the basis of the detected actual operational characteristic of the feed device.

Abstract: The invention pertains to a relief valve (10) for being arranged on an opening (10) of a fuselage shell of an aircraft, wherein the opening (10) has a front opening edge (9a) and a rear opening edge (9a), and wherein the relief valve (10) features: a cover (13) that is arranged on the fuselage shell by means of an opening and closing device in order to open and close the opening (10) of the fuselage shell, and a prestressing device for prestressing the cover (13) into an initial position, wherein a guide plate (23) is arranged on the cover (13) by means of a mounting device (20), wherein the guide plate is spaced apart from the cover (13) and extends along the cover (13), and wherein the invention furthermore pertains to a fuselage part with such a relief valve (10) for being installed into an aircraft fuselage with a fuselage shell and a plurality of fuselage frames arranged on the inside of the fuselage shell, as well as to an aircraft fuselage with such a fuselage part.

Abstract: An aircraft air conditioning system comprising a compressor adapted to generate compressed process air, an air conditioning unit adapted to cool and expand compressed process air supplied to the air conditioning unit from the compressor, and an energy converter adapted to convert hydraulic energy into electric energy. The compressor is supplied with electric energy generated by the energy converter by converting hydraulic energy supplied to the energy converter.

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: A method and a device determines an air mass flow flowing through a ram air channel having disposed therein a feed device adapted in a first operating state of the ram air channel to feed air through the ram air channel and further adapted in a second operating state of the ram air channel to be set in rotation by an air mass flow flowing through the ram air channel. The method includes the step of detecting an actual operational characteristic of the feed device that is characteristic of the air mass flow flowing through the ram air channel in the second operating state of the ram air channel as well as the step of determining the air mass flow flowing through the ram air channel on the basis of the detected actual operational characteristic of the feed device.

Abstract: A method for controlling an aircraft air conditioning system includes the steps of detecting an operating state of an air conditioning unit of the aircraft air conditioning system and controlling the temperature of a process air mass flow supplied to the air conditioning unit in dependence on the operating state of the air conditioning unit.

Abstract: In a method for controlling an aircraft air conditioning system, a heating or cooling demand of an aircraft region to be air conditioned is determined. A volume flow of recirculation air discharged from the aircraft region to be air conditioned and a volume flow of compressed air into a mixing chamber of the aircraft air conditioning system is controlled such that the heating or cooling demand of the aircraft region to be air conditioned is met, while the volume flow of compressed air into the mixing chamber of the aircraft air conditioning system is minimized.

Abstract: The present invention relates to a circuit for detecting a functional status of an electro-motor. Typical electro-motors need additional components to identify the functional status of the motor. This means additional weight for such motors determining the functional status. According to the present invention, a circuit is provided using a part of a motor as a sensor for detecting the functional status of the electro-motor.

Abstract: An aircraft conduit monitoring system includes conduit that conducts gas from a source to a point of application. A flow sensing device and a pressure sensing device are provided within the conduit. At least one set value of a gas mass flow rate and at least one set value of a pressure are sensed in a learning mode of operation. The set values are compared with sensed actual values in the normal mode of operation. A gas volume flow rate can also be sensed and processed instead of a gas mass flow rate.