Abstract: An arrangement is provided for de-icing pipeline connections of an aircraft, which are connected to all fresh air outlets of an air conditioner, whose construction includes, but is not limited to the functions of multiple turbines and heat exchangers, having a first pipeline, which is connected to a first turbine, and a second pipeline, which is connected to a second turbine, the two pipelines, which are each connected downstream from the two turbines and to which process air is fed at the turbine outlets, being connected at the pipe ends and being continued using a third pipeline. The arrangement is characterized in that a first hot air source is fed hot fresh air from a bleed air system of the aircraft and is connected at its outlet to a fourth pipeline, into which temperature-reduced fresh air is fed from the hot air source.

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: In a method for controlling an aircraft air conditioning system, a correlation is established between a plurality of values of a process air mass flow supplied to an air conditioning unit of the aircraft air conditioning system and the fuel consumption of the aircraft. A correlation is also established between a plurality of values of an ambient air mass flow which is used to cool the process air mass flow supplied to the air conditioning unit of the aircraft air conditioning system and the fuel consumption of the aircraft. The process air mass flow and the ambient air mass flow are controlled in dependence on a predetermined cooling capacity of the aircraft air conditioning system such that the fuel consumption of the aircraft is minimized.

Abstract: An arrangement is provided for de-icing pipeline connections of an aircraft, which are connected to all fresh air outlets of an air conditioner, whose construction includes, but is not limited to the functions of multiple turbines and heat exchangers, having a first pipeline, which is connected to a first turbine, and a second pipeline, which is connected to a second turbine, the two pipelines, which are each connected downstream from the two turbines and to which process air is fed at the turbine outlets, being connected at the pipe ends and being continued using a third pipeline. The arrangement is characterized in that a first hot air source is fed hot fresh air from a bleed air system of the aircraft and is connected at its outlet to a fourth pipeline, into which temperature-reduced fresh air is fed from the hot air source.

Abstract: A system for cooling an aircraft zone includes a mixing chamber (18) which is connected to an air-conditioning assembly (12a, 12b) for making cool air available and/or to a recirculated-air conveying device (20a, 20b) for supplying recirculated air into the mixing chamber (18). The system (10) further includes an aircraft-side air-distribution system (23) which includes at least one line (32) connecting the mixing chamber (18) to the aircraft zone to be cooled and also at least one line (28a, 28b) that is connectable to an aircraft-external air-generating assembly (26a, 26b, 26c, 26d) in order to route air made available by the aircraft-external air-generating assembly (26a, 26b, 26c, 26d) into the aircraft-side air-distribution system (23).

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: A system (10) for cooling a heat exchanger (12) on board an aircraft comprises a process air line (28), a first end of which is connected to an engine (16) of the aircraft in order to supply engine bleed air to the process air line (28). A second end of the process air line 28 is connected to a turbine (30) in order to supply the engine bleed air flowing through the process air line (28) to the turbine (30). A first end of a cooling air line (34) is connected to the turbine (30) in order to supply the cooling air line (34) with cooling air that is produced by expansion of the engine bleed air in the turbine (30). The cooling air line (34) is adapted to supply the cooling air flowing through the cooling air line (34) to the heat exchanger (12) that is to be cooled.

Abstract: The invention relates to an aircraft conduit monitoring system comprising a 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. Said 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.

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: A system (10) for cooling an aircraft region comprises an air-conditioning unit (12a, 12b) for providing cool air, a circulating air conveying device (20a, 20b), and a mixing chamber (18) which is connected to the air conditioning unit (12a, 12b) via an air distribution line (16a, 16b) and to which circulating air can be fed by the circulating air conveying device (20a, 20b). An inlet line (28a, 28b) which is connected to an aircraft-side connection (24a, 24b, 24c, 24d) for an aircraft-external air unit (26a, 26b, 26c, 26d) opens into the air distribution line (16a, 16b) connecting the air conditioning unit (12a, 12b) to the mixing chamber (18).

Abstract: A system (10) for ventilation of an aircraft area (32, 34) comprises a ram-air duct (12) with an air inlet (14), a first ram-air duct branch (16) and a second ram-air duct branch (18) allowing for being flowed parallel to the first ram-air duct branch (16). A supply line (26) connected to the ram-air duct (12) is adapted to supply air flowing through the ram-air duct (12) to the aircraft area (32, 34) to be ventilated. In the first ram-air duct branch (16) a conveying device (24) is arranged. In the second ram-air duct branch (18) a heat exchanger (36) of an aircraft system to be supplied with cooling energy is arranged.

Abstract: A system for the provision of process air comprises a first cooling system (2) with a first heat exchanger, which is arranged in a channel (3) that serves as a cooling sink, and a cooling system (8), integrated in the first cooling system (2), wherein said cooling system (8) comprises a heat exchanger (9) which is integrated in the channel (3) either upstream or downstream of the first heat exchanger.

Abstract: In a method for controlling an aircraft air conditioning system (10) a correlation is established between a plurality of values of a process air mass flow supplyable to an air conditioning unit (12) of the aircraft air conditioning system (10) and the fuel consumption of the aircraft. A correlation is also established between a plurality of values of an ambient air mass flow which is used to cool the process air mass flow supplyable to the air conditioning unit (12) of the aircraft air conditioning system (10) and the fuel consumption of the aircraft. The process air mass flow and the ambient air mass flow are controlled in dependence on a predetermined cooling capacity of the aircraft air conditioning system (10) such that the fuel consumption of the aircraft is minimised.

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 arrangement is provided for de-icing pipeline connections of an aircraft, which are connected to all fresh air outlets of an air conditioner, whose construction includes, but is not limited to the functions of multiple turbines and heat exchangers, having a first pipeline, which is connected to a first turbine, and a second pipeline, which is connected to a second turbine, the two pipelines, which are each connected downstream from the two turbines and to which process air is fed at the turbine outlets, being connected at the pipe ends and being continued using a third pipeline. The arrangement is characterized in that a first hot air source is fed hot fresh air from a bleed air system of the aircraft and is connected at its outlet to a fourth pipeline, into which temperature-reduced fresh air is fed from the hot air source.

Abstract: A system for the provision of process air comprises a first cooling system (2) with a first heat exchanger, which is arranged in a channel (3) that serves as a cooling sink, and a cooling system (8), integrated in the first cooling system (2), wherein said cooling system (8) comprises a heat exchanger (9) which is integrated in the channel (3) either upstream or downstream of the first heat exchanger.

Abstract: A ram air inlet includes a channel with an intake in a wing leading edge, front and rear flaps arranged in the channel for selectively closing or opening the channel, and an actuator connected to the flaps. A front end of the front flap is pivotably connected by a fixed bearing to an aircraft structure adjacent the intake. A rear end of the rear flap is moveably and pivotably mounted to the aircraft structure via a movable bearing arrangement, e.g. a pivot bearing linearly movable in guide tracks, or a flexible lever connected to a fixed pivot bearing, or a swinging bearing pivotably connected to a fixed bearing. The opposite ends of the flaps are pivotably connected to each other by a third bearing. The actuator drives the third bearing to pivot the front flap between opened and closed positions, while the rear flap pivots and moves in the wing chord and/or thickness directions.

Abstract: A ram air inlet includes a channel with an intake in a wing leading edge, front and rear flaps arranged in the channel for selectively closing or opening the channel, and an actuator connected to the flaps. A front end of the front flap is pivotably connected by a fixed bearing to an aircraft structure adjacent the intake. A rear end of the rear flap is moveably and pivotably mounted to the aircraft structure via a movable bearing arrangement, e.g. a pivot bearing linearly movable in guide tracks, or a flexible lever connected to a fixed pivot bearing, or a swinging bearing pivotably connected to a fixed bearing. The opposite ends of the flaps are pivotably connected to each other by a third bearing. The actuator drives the third bearing to pivot the front flap between opened and closed positions, while the rear flap pivots and moves in the wing chord and/or thickness directions.

Abstract: An air discharge valve for an aircraft has an inner valve flap (1) and an outer valve flap (3) which partially overlap each other to form a nozzle of the Laval type with a nozzle inlet (6) converging toward a nozzle neck (S) and with a nozzle outlet (7) diverging away from the nozzle neck (S). The inner valve flap (1) has a trailing edge (8A) hinged to the aircraft body and a first leading edge (8) facing in the flight direction and having a curved sectional configuration. The outer valve flap (3) has a second leading edge (9) hinged to the aircraft body and a trailing edge (9A). Both flaps (1, 3) have a wedge shape. An outwardly facing surface portion (11B) of the inner flap (1) forms an air flow guide for air flowing out of the nozzle outlet (7). An inwardly facing surface portion (15B) of the outer flap (3) forms an air flow guide into the nozzle inlet (6) formed by the curved sectional configuration of the first leading edge (8) and by the inwardly facing surface portion (15B).

Abstract: An air discharge valve for an aircraft has an inner valve flap (1) and an outer valve flap (3) which partially overlap each other to form a nozzle of the Laval type with a nozzle inlet (6) converging toward a nozzle neck (S) and with a nozzle outlet (7) diverging away from the nozzle neck (S). The inner valve flap (1) has a trailing edge (8A) hinged to the aircraft body and a first leading edge (8) facing in the flight direction and having a curved sectional configuration. The outer valve flap (3) has a second leading edge (9) hinged to the aircraft body and a trailing edge (9A ). Both flaps (1, 3) have a wedge shape. An outwardly facing surface portion (11B) of the inner flap (1) forms an air flow guide for air flowing out of the nozzle outlet (7). An inwardly facing surface portion (15B) of the outer flap (3) forms an air flow guide into the nozzle inlet (6) formed by the curved sectional configuration of the first leading edge (8) and by the inwardly facing surface portion (15B).