Abstract: The various embodiments herein disclosed include a method wherein an integrated circuit (100) may receive a code image from an external device (127), encrypt the code image using a cryptographic logic (113) with a Hardware Unique Key to create a Hardware Unique Code Image (119) where the Hardware Unique Key is inaccessible to the external device (127). The integrated circuit (100) will then store the Hardware Unique Code Image wherein the Hardware Unique Code Image is executable only after decryption using the Hardware Unique Key. The method also includes sending a command to a cryptographic logic (113) to request decryption of the Hardware Unique Code Image by the cryptographic logic (113) using the Hardware Unique Key and executing the Hardware Unique Code Image by the boot software (103) after the decryption.

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: A cooling system (10) for the cooling of heat producing devices (44, 46, 48) in an aircraft is designed with a central cold producing device (12), at least one cold consumer (44, 46, 48) and a cold conveyance system (14) which connects the cold producing device (12) and the cold consumer (44, 46, 48). With this cooling system, the cold conveyance system (14) has at least one cooling circuit which supplies a cooled cold carrier medium from the cold producing device (12) to at least one cold consumer (44, 46, 48) and brings this back to the cold producing device (12), so that at least one cold consumer (44, 46, 48) is supplied with the cold produced in the cold producing device (12) by means of the cold carrier medium circulating in the cooling circuit.

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: The invention relates to a cooling system (20) for an aircraft, comprising a number of refrigeration devices (1) which produce refrigeration and transmit this refrigeration to a cooling medium, and a circuit (21), containing at least one refrigeration consumer (22), for the cooling medium, for supplying the refrigeration consumer(s) (22) with refrigeration. Each refrigeration device (1) is a modular unit coupled to the circuit (21) and having a pump (10), which conveys the cooling medium through the circuit (21).

Abstract: An arrangement for supplying humidified ambient air for an aircraft comprises a first line arrangement (22), which brings up supply air and from which the supply air is blown into the aircraft interior (10). This arrangement further comprises an evaporating device (32), which supplies a steam flow, the pressure of which corresponds at least approximately to a predetermined pressure value lying above a requisite interior pressure of the aircraft. A second line arrangement (36, 38, 40), which opens into the first line arrangement (22), carries the steam flow. Disposed in the second line arrangement (36, 38, 40) is an optionally adjustable aperture arrangement (52) for lowering the pressure of the steam flow.

Abstract: The present invention relates to a bus system for transmitting a data packet between multiple devices in an aircraft, which is based on the CAN data bus system, but has an expanded identification field, in which a fixed region is designed for identification of the manifold aircraft systems, through which each aircraft system may be addressed uniquely. According to an exemplary embodiment, the data packet may be sent with different priorities, through which “important” data packets have priority on the transmission medium.

Abstract: The present invention relates to an evaporator arrangement for an air conditioning system of an aircraft, wherein a bypass conduit is provided which can be connected such that if required at least part of the airflow bypasses an evaporator. Advantageously this makes it possible in the case of malfunction of the evaporator to maintain the functionality of the air conditioning system.

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

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 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 process for temperature regulation of sections of the interior of an aircraft with the following steps: recording of the respective actual temperatures and the respective nominal temperatures in the individual sections; mixing of engine bleed air and air which is cooler than the engine bleed air in order to obtain pre-tempered mixed air at a temperature which essentially corresponds to the lowest of the nominal temperatures recorded; distribution of the pre-tempered mixed air to all sections; and post-tempering of the mixed air distributed to the sections with higher nominal temperature corresponding to the differences between the respective nominal temperatures and the respective actual temperatures can be carried out in a device with 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; to a distribution line connected to the outlet of the mixer valve which is connected to the r

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.

Abstract: A method and a line system for the air-conditioning of a freight compartment or a cabin of an aircraft envisage that at sites (A, B, C, D) remote from passengers air that is at a temperature different from that at sites (E, F, G, H) closer to passengers is introduced into the freight compartment (12, 14) or into the cabin.

Abstract: A home product includes a container and a plastic liner. The container includes an interior surface. The plastic liner is integrally conformed and attached to a substantial portion of the interior surface of the container to seal and protect the container. The plastic liner is conformed and attached to the container via a thermoforming or blow molding-process.

Abstract: The invention relates to a turbine or pump or pump turbine, comprising a rotor which has a plurality of rotating blades and a hub, a housing which has a distributor for regulating the currents flowing into the rotor, and an induction pipe for guiding the water flowing out of the rotor, comprising an inlet diffusor. The inventive turbine or pump or pump turbine is characterized by the following characteristics; an elongate displacement body is arranged in the induction pipe and the upstream end of the displacement body is arranged in the region of the hub of the rotor.