Abstract: This invention relates to a powder comprising a carrier material which is in powdery form and selected from the group consisting of a water-soluble polymer, a water-insoluble polymer, and an inert inorganic material, and a mixture containing at least about 5 wt. % of a compound having the formula (1-a) and at least about 5 wt. % of a compound having the formula (1-b), HO—(R2O)m—H (1-a), R1aO—(R2aO)n—H (1-b). Claimed also are a process to make the powder, its use, as well as a dry mortar formulation containing the same.

Abstract: A cooling system for the cooling of heat producing devices in an aircraft is designed with a central cold producing device, at least one cold consumer and a cold conveyance system which connects the cold producing device and the cold consumer. With this cooling system, the cold conveyance system has at least one cooling circuit which supplies a cooled cold carrier medium from the cold producing device to at least one cold consumer and brings the cold carrier medium back to the cold producing device, so that at least one cold consumer is supplied with the cold produced in the cold producing device.

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: The present application describes an arrangement and a method for utilizing the heat of waste air for heating the bilge area of aircraft, wherein the bilge area is connected to a heat transfer unit via a first air supply pipe, through which a bilge air flow drawn in from the bilge area flows into the heat transfer unit, wherein the heat transfer unit comprises a second air supply pipe, through which a waste air heat flow to be cooled that is created at another location in the aircraft flows into the heat transfer unit in order to heat the drawn-in bilge air flow, wherein the heat transfer unit comprises a first air discharge pipe, through which the cooled waste air heat flow is discharged, and a second air discharge pipe with a bilge inlet section, and wherein at least a portion of the heated bilge flow is returned to the bilge area via the air discharge pipe and the bilge inlet section.

Abstract: The present application describes an arrangement and a method for utilizing the heat of waste air for heating the bilge area of aircraft, wherein the bilge area is connected to a heat transfer unit via a first air supply pipe, through which a bilge air flow drawn in from the bilge area flows into the heat transfer unit, wherein the heat transfer unit comprises a second air supply pipe, through which a waste air heat flow to be cooled that is created at another location in the aircraft flows into the heat transfer unit in order to heat the drawn-in bilge air flow, wherein the heat transfer unit comprises a first air discharge pipe, through which the cooled waste air heat flow is discharged, and a second air discharge pipe with a bilge inlet section, and wherein at least a portion of the heated bilge flow is returned to the bilge area via the air discharge pipe and the bilge inlet section.

Abstract: The invention relates to a window glazing comprising at least two window panes with an intermediate ventilated space arranged therebetween, wherein at least one window pane is provided with a layer which is arranged on the interior side therefore and whose transmission is controllable. More specifically, said invention relates to a multilayer glazing comprising corresponding intermediate spaces in which a sweeping gas circulates, wherein said sweeping gas consists of a mixture of air and other gaseous components in which the sweeping gas content is adjustable.

Abstract: The present invention provides an air intake valve for an aircraft and a method for the production of an air intake valve. The air intake valve has an opening region for letting ambient air through into a fuselage inner region of the aircraft and a flap for opening and closing the opening region, the opening region and the flap each having a shape which is capable of forming air vortices on edges of the opening region when ambient air flows through the air intake valve.

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 method and a line system for the air-conditioning of a cabin of an aircraft envisage that at sites remote from passengers air that is at a temperature lower than air at sites closer to passengers is introduced into the cabin.

Abstract: A ram air channel (10) for the supply of ambient air in an aircraft includes a first air inlet (12) and a main flow channel (16) which extends downstream of the first air inlet (12). In order to guarantee that the systems on board the aircraft are supplied, in a simple and reliable way, with the required ambient air in any operational state of the aircraft, i.e. both during the flight and on the ground, the ram air channel (10) has a second air inlet (24) which is independent from the first air inlet (12).

Abstract: With a method for controlling the temperature of feed air which is injected into the cabin zone of a passenger aircraft, the cabin of which is sub-divided into several cabin zones supplied respectively with specially temperature-controlled feed air, the temperature of the injected feed air is controlled for each cabin zone, dependent upon the deviation of an injection temperature actual value for the feed air injected into the cabin zone in question, measured by sensors, in relation to an injection temperature optimum value. If there is no, or at least no usable reading of the ambient temperature of this cabin zone for a cabin zone, an optimum value for the injection temperature of this cabin zone can be established in accordance with a variation, whereby it is determined upon the basis of the injection temperature optimum values and/or the injection temperature actual values of other cabin zones, whereby the measurement by sensors of the cabin temperature works reliably.

Abstract: A ram air outlet duct (10) for removing air from an aircraft includes a ram air outlet duct wall (20) bounding an interior (16) of the ram air outlet duct (10), a ram air outlet (12), and a ram air outlet duct flap (22) for adjusting a flow cross-section of the ram air outlet (12). To minimise additional drag caused by the ram air outlet duct (10) when it is mounted in an aircraft and the aircraft is flying, a flap area of to the ram air outlet duct flap (22) is smaller than a cross-sectional area of the ram air outlet (12) and/or the ram air outlet duct wall (20) has a rounded shape in a section (26) adjoining the ram air outlet (12).

Abstract: A ram-air duct (10) includes a ram-air inlet duct (20) and a ram-air outlet duct (30) arranged downstream of the ram-air inlet duct (20) and in fluid communication with the ram-air inlet duct (20). At an inlet (22) of the ram-air inlet duct (20) a movable element is arranged and adapted to set an inlet parameter (E) of the inlet (22). At an outlet (32) of the ram-air outlet duct (30) a movable element is arranged and adapted to set an outlet parameter (A) of the outlet (32). The outlet parameter (A) and the inlet parameter (E) are linked together by a function (ƒ), so that an outlet parameter (A) corresponding to a value (f(E)) of the function (ƒ) is assigned to each inlet parameter (E).

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: In a cooling system (10) for cooling heat-generating installations (44, 46, 48) in an aircraft, with a refrigerating installation (12), at least one refrigeration consumer (44, 46, 48) and a refrigeration transport system (14) connecting the refrigerating installation (12) and the refrigeration consumer (44,46, 48), it is provided that the refrigerating installation (12) comprises at least one refrigeration machine (18, 20) which covers the maximum refrigeration requirement of the at least one refrigeration consumer (44, 46, 48) and in that the at least one refrigeration consumer (44, 46, 48) is supplied with cold generated in the refrigerating installation (12) via a refrigerating agent circulating in the refrigeration transport system (14).

Abstract: With a method for controlling the temperature of feed air which is injected into the cabin zone of a passenger aircraft, the cabin of which is sub-divided into several cabin zones supplied respectively with specially temperature-controlled feed air, the temperature of the injected feed air is controlled for each cabin zone, dependent upon the deviation of an injection temperature actual value for the feed air injected into the cabin zone in question, measured by sensors, in relation to an injection temperature optimum value. If there is no, or at least no usable reading of the ambient temperature of this cabin zone for a cabin zone, an optimum value for the injection temperature of this cabin zone can be established in accordance with a variation, whereby it is determined upon the basis of the injection temperature optimum values and/or the injection temperature actual values of other cabin zones, whereby the measurement by sensors of the cabin temperature works reliably.

Abstract: Aircraft fuselage with an upper deck, constructed as a passenger area, and a lower deck, including a freight area, and with a ventilation installation for the upper deck and lower deck, wherein a bilge area is constructed as a vacuum chamber against the freight area and is connected to the lower deck solely via flow orifices in the abutment area between a lower floor and the fuselage wall.

Abstract: A hose fitting and a method for fastening a hose fitting to a hose end section are disclosed. The hose fitting includes a connecting element and holding sleeve. The connecting element includes an insert section configured to be inserted into the hose end section. The holding sleeve includes a fixing section with a fixing part to engage a fixing counter part of the connecting element to fix the holding sleeve to the connecting element. A holding section of the holding sleeve may include radially inward projecting holding projections. The fixing and holding sections may be connected via an intermediate section arranged therebetween. In the fastened state, where the hose fitting is fastened to the hose end section, the holding projection may intrude into an outer sheathing of the hose end section. A clearance can be created between the hose end and the fixing part in the fastened state.

Abstract: The invention concerns a cooling system for an aircraft with an air inlet (4) through which air from the environment of the aircraft enters a ram air channel (2), and an air outlet (6) through which air emerges from the ram air channel (2). A heat exchanger (10) is arranged in the ram air channel (2). A ventilation device (8) is in fluid communication with the ram air channel (2). Also connected to the ram air channel (2) is a distribution line (12) to cool at least one heat-loaded component of the aircraft, in particular a cabin air conditioning system, and/or to ventilate an installation space of the at least one heat-loaded component.

Abstract: The invention relates to a window glazing comprising at least two window panes with an intermediate ventilated space arranged therebetween, wherein at least one window pane is provided with a layer which is arranged on the interior side thereof and whose transmission is controllable. More specifically, said invention relates to a multilayer glazing comprising corresponding intermediate spaces in which a sweeping gas circulates, wherein said sweeping gas consists of a mixture of air and other gaseous components in which the sweeping gas content is adjustable.