Abstract: A regulating system for the regulation of the cabin pressure PC of an aircraft, includes at least one cabin pressure regulator unit, which is so configured that, by controlling at least one air outflow or air inflow device of the aircraft, it can set the cabin pressure Pc within the aircraft fuselage with the latter supplied with fresh air and subjected to pressure at a pressure level or a cabin height defined by the cabin regulator unit. If there are changes to be made to the pressure level or the cabin height, for example while the aircraft is climbing or descending, the cabin regulator unit maintains the quotient of the time-related change of the cabin pressure Pc in the aircraft cabin and the cabin pressure Pc constant. The result is that the gas expansion rate, or the gas compression rate in a passenger's middle ear, remains constant, so that during the entire climbing or descending stage no varying or increasing discomfort is experienced by the passengers.

Abstract: The present invention provides a method for controlling an internal pressure in an aircraft or spacecraft, the method comprising the following steps: detecting the internal pressure in the craft and an external pressure Pa outside of the craft and comparing said pressures with each other; and adjusting a flap of at least one outflow valve to a blade position, in which the flap directs air flowing past an outer surface of the craft into the craft to increase the internal pressure, if the external pressure exceeds the internal pressure by a predetermined value during the descent of the craft. The idea, on which the present invention is based, is to assign a double function to the outflow valve: during normal flight the positive pressure in the craft is relieved by means of the outflow valve.

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 device for temperature control in an aircraft cabin includes a first supply control arrangement and a first pressure control arrangement. The first supply control arrangement includes an air duct and a valve arrangement that controls a supply of heated air delivered to a first temperature area of the aircraft cabin such that a first specified temperature for the first temperature zone is achieved. When the valve arrangement fails, the first pressure control arrangement operates to control a pressure of heated air supplied into the first temperature area such that the first specified temperature for the first temperature zone is achieved.

Abstract: A regulating system for the regulation of the cabin pressure PC of an aircraft, includes at least one cabin pressure regulator unit, which is so configured that, by controlling at least one air outflow or air inflow device of the aircraft, it can set the cabin pressure Pc within the aircraft fuselage with the latter supplied with fresh air and subjected to pressure at a pressure level or a cabin height defined by the cabin regulator unit. If there are changes to be made to the pressure level or the cabin height, for example while the aircraft is climbing or descending, the cabin regulator unit maintains the quotient of the time-related change of the cabin pressure Pc in the aircraft cabin and the cabin pressure Pc constant. The result is that the gas expansion rate, or the gas compression rate in a passenger's middle ear, remains constant, so that during the entire climbing or descending stage no varying or increasing discomfort is experienced by the passengers.

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: The present invention provides a method for controlling an internal pressure in an aircraft or spacecraft, the method comprising the following steps: detecting the internal pressure in the craft and an external pressure Pa outside of the craft and comparing said pressures with each other; and adjusting a flap of at least one outflow valve to a blade position, in which the flap directs air flowing past an outer surface of the craft into the craft to increase the internal pressure, if the external pressure exceeds the internal pressure by a predetermined value during the descent of the craft. The idea, on which the present invention is based, is to assign a double function to the outflow valve: during normal flight the positive pressure in the craft is relieved by means of the outflow valve.

Abstract: Device and method for temperature control in an aircraft cabin (104) wherein is controlled with a first supply control arrangement the supply of heated air from a first source into a first temperature area (106) of the aircraft cabin (104) depending upon a specified first temperature for the first temperature area and with a first pressure control arrangement (176) a current pressure in the first supply control arrangement in the event of a malfunction of the first supply control arrangement depending upon the specified first temperature.