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: 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 system (10) for cooling a thermally loaded device on board an aircraft comprises a distribution line (12) which is in communication with an installation space (14) of the thermally loaded device, a coolant supply line (20) which is in communication with a coolant source, and a heat removal line (28) which is in communication with a source of pressure below atmospheric pressure. A shut-off control device (34) is adapted so as, in a first position, to separate the distribution line (12) from the coolant supply line (20) and connect the distribution line (12) to the heat removal line (28) and, in a second position, to connect the distribution line (12) to the coolant supply line (20) and separate the distribution line (12) from the heat removal line (28).

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: Nowadays in aircraft on-board inert gas generation systems (OBIGGS) are used to generate inert gases. Cooled bleed air of engines or auxiliary turbines is fed to said OBIGGS systems. According to an embodiment of the present invention, an air supply device for an OBIGGS system in an aircraft is proposed that comprises a bleed position (1,2). By way of the bleed position (1,2), air from an air conditioning unit (4,5) on board the aircraft can be bled and can be fed to the OBIGGS system. There is thus no need for an additional heat exchanger and an additional ram-air channel. Maintenance expenditure and air resistance are thus reduced.

Abstract: Aircraft air-conditioning system (1) for an aircraft having a plurality of zones (2, 4), comprising a first line (6) for feeding cold air at an actual temperature T1act., a second line (14) which branches off a portion of the air from the first line (6) at a branching point (10) and feeds the air to a plurality of zones (2, 4) of an aircraft, wherein warm air is fed through a first trim valve (12) into the second line (14) so that the air in the second line (14) is heated to the actual temperature T2act., and a first zone feed line (24) feeding the air downstream of the first trim valve (12) to a first zone (2), wherein a second trim valve (26) is arranged in the first zone feed line (24), through which valve warm air is fed into the first zone feed line (24) so that the air in the first zone feed line (24) is heated to the actual temperature Tzf1act., and the first line (6) downstream and/or upstream of the branching point (1) feeds cold air at least to one further zone.

Abstract: An air guiding flap of an aircraft wherein one surface thereof faces an air duct and is exposed to a prevailing pressure in the air duct and whose opposite surface is exposed to the pressure of the relative wind flowing past the aircraft. The air guiding flap comprises an actuator for automatically opening and closing the air guiding flap which actuator cooperates with a device for controlling the position of the air guiding flap. In order to keep the stress on the air guiding flap low a force detecting device is provided which detects the force impinging on the actuator base don a difference between the prevailing pressure in the air duct and the pressure of the relative wind flowing past the aircraft. The controlling device adjusts the position of the air guiding flap such that the force impinging on the actuator at any one time is at least essentially zero.

Abstract: A system (10) for cooling a thermally loaded device on board an aircraft comprises a distribution line (12) which is in communication with an installation space (14) of the thermally loaded device, a coolant supply line (20) which is in communication with a coolant source, and a heat removal line (28) which is in communication with a source of pressure below atmospheric pressure. A shut-off control device (34) is adapted so as, in a first position, to separate the distribution line (12) from the coolant supply line (20) and connect the distribution line (12) to the heat removal line (28) and, in a second position, to connect the distribution line (12) to the coolant supply line (20) and separate the distribution line (12) from the heat removal line (28).

Abstract: Nowadays in aircraft on-board inert gas generation systems (OBIGGS) are used to generate inert gases. Cooled bleed air of engines or auxiliary turbines is fed to said OBIGGS systems. According to an embodiment of the present invention, an air supply device for an OBIGGS system in an aircraft is proposed that comprises a bleed position (1,2). By way of the bleed position (1,2), air from an air conditioning unit (4,5) on board the aircraft can be bled and can be fed to the OBIGGS system. There is thus no need for an additional heat exchanger and an additional ram-air channel. Maintenance expenditure and air resistance are thus reduced.

Abstract: Nowadays in aircraft so-called on-board inert gas generation systems (OBIGGS) are used to generate inert gases, to which OBIGGS cooled bleed air of engines or auxiliary power units is fed. According to an embodiment of the present invention, an air cooling device for an OBIGGS system in an aircraft is proposed that comprises a bleed position. By way of the bleed position, cooling air from an air conditioning unit on board the aircraft can be bled, which cooling air can subsequently be used for cooling supply air for the OBIGGS system. Thus, there is no need for an additional ram-air inlet channel for cooling the supply air. Air resistance and weight are thus reduced, and the stability of the primary structure is enhanced.

Abstract: The invention relates to an air guiding flap of an aircraft wherein one surface thereof faces an air duct and is exposed to a prevailing pressure in the air duct and whose opposite surface is exposed to the pressure of the relative wind flowing past the aircraft. The air guiding flap comprises an actuator for automatically opening and closing the air guiding flap which actuator cooperates with a device for controlling the position of the air guiding flap. In order to keep the stress on the air guiding flap low a force detecting device is provided which detects the force impinging on the actuator based on a difference between the prevailing pressure in the air duct and the pressure of the relative wind flowing past the aircraft. The controlling device adjusts the position of the air guiding flap such that the force impinging on the actuator at any one time is at least essentially zero.

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, ie. 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: A cooling air supply system (10) for an aircraft in order to supply cooling air from the aircraft surrounds to at least two devices requiring cooling air (38, 44, 56) within the aircraft, is designed with an air inlet (12), an air channel (16) communicating with the air inlet (12) and with an air distribution device (30, 32, 34) for the distribution of air to at least two devices requiring cooling air (38, 44, 56), whereby the air inlet (12) is proportioned in such a way that it covers the maximum cooling air requirement of at least two devices requiring cooling air (38, 44, 56).

Abstract: In a fiber optic display system an array of pixels form a continuous viewable surface. Each pixel is formed by a bundle of one or more optical fibers which vector light to the pixels from one or more light sources. High density of pixels at the viewable surface is achieved by bundling small diameter optical fibers adapted for vectoring light from low density light sources. The two-dimensional geometry of the viewable surface is de-coupled from the light source which is arranged in a three dimensional space. The arrangement of light source into three dimensional space is accomplished by partitioning the light source into an array of light source planes. The arrangement of light source into a three dimensional array allows for the combined surface area of the planes to substantially exceed the display area of the viewable surface.

Abstract: In a fiber optic display system an array of pixels form a continuous viewable surface. Each pixel is formed by a bundle of one or more optical fibers which vector light to the pixels from one or more light sources. High density of pixels at the viewable surface is achieved by bundling small diameter optical fibers adapted for vectoring light from a low density light sources. The two-dimensional geometry of the viewable surface is de-coupled from the light source which is arranged in a three dimensional space.