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 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: 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 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: 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.

Abstract: A bipolar optical plug-and-socket connector for connecting two optical fibers with other optical fibers and electro-optical transmission and receiving devices includes an optical housing for holding two fiber end sleeves in which each sleeve terminates a fiber. The optical housing includes first and second housing portions which have different external forms from one another. The housing portions hold respective ones of the sleeves when the sleeves are inserted into the housing portions along a plugging direction. The housing portions join to one another in a direction running perpendicular to the plugging direction to place the optical housing in a fully assembled position while the housing portions hold the sleeves. Each housing portion includes an end lock for locking the sleeves in the housing portions. The end locks of the housing portions lock the sleeve held in the other of the housing portions when the housing portions are joined together.

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: An improved organizer is provided that may be hung on a CPU, cubicle partition, file cabinet or other structure commonly found in an office or work place. The organizer may include a single backing member connected to a variety of organizing elements or may be of a saddle-type where two backing members are connected together by one or more overhang straps thereby providing organizing elements on either side of the structure, such as a CPU. The organizing elements include pockets, trays, baskets, bulletin boards, dry erase boards and other types of display surfaces.

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: An air dispersion system has a main supply line, a plurality of air outlets, which are connected via respective air exhaust routes to the main supply line, and at least one heating element, which is associated with at least one of the air outlets and can temper the air in the exhaust route of this air outlet.

Abstract: A laundry basket has a bottom panel with a perimeter. A contiguous side wall extends generally upward from the perimeter of the bottom panel and terminates at an upper end. A basket interior is defined above the bottom panel and bounded by the side wall. A curved wall section of the side wall is curved concavely inward toward the basket interior. The bottom panel and the contiguous side wall, including the curved wall section, are formed of a primary material. A cushion pad is positioned generally at the upper end of the curved wall section and is formed from a secondary material that is softer than the primary material of the curved wall portion.

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: A bipolar optical plug-and-socket connector for connecting two optical fibers with other optical fibers and electro-optical transmission and receiving devices includes an optical housing for holding two fiber end sleeves in which each sleeve terminates a fiber. The optical housing includes first and second housing portions which have different external forms from one another. The housing portions hold respective ones of the sleeves when the sleeves are inserted into the housing portions along a plugging direction. The housing portions join to one another in a direction running perpendicular to the plugging direction to place the optical housing in a fully assembled position while the housing portions hold the sleeves. Each housing portion includes an end lock for locking the sleeves in the housing portions. The end locks of the housing portions lock the sleeve held in the other of the housing portions when the housing portions are joined together.

Abstract: A removable container liner for a rigid insulating container includes a bottom portion and a wall portion formed as a single unitary body. The body may be composed of a stain resistant and odor resistant plastic. The liner may be configured to be used within an insulated container such as a cooler or water jug.

Abstract: A freezable container includes a base portion and may include a lid. The base portion may include a cold-retaining medium layer and be configured to be freezable to maintain a chilled environment for stored content. The freezable container may be configured to fit inside an insulated container such as a cooler.

Abstract: An air conditioning system for an aircraft includes a first rotatable shaft with a first compressor, a first turbine, a cooling air fan, and an auxiliary compressor connected for rotation therewith, and preferably further includes a second rotatable shaft with a second compressor and a second turbine connected for rotation therewith. A compression, cooling, and expansion cycle driven by at least the first compressor and the first turbine provides a principle flow of air conditioning air. The auxiliary compressor draws in outside air and provides a redundant auxiliary ventilation air flow, which is supplied into the installation space in which the air conditioning unit is installed, or another space in the aircraft that requires a reliable constant ventilation and cooling whenever the air conditioning unit is operational. The auxiliary ventilation air may be connected to a common air distribution network with other air conditioning units.

Abstract: In an air conditioning system for an aircraft, two pre-mixing units respectively mix cold air from two air conditioning units with recirculated fuselage interior air from two recirculation units, to prepare two pre-mixed air flows that are both directed into and mixed together in a common air distribution mixing chamber, from which mixed air distribution lines branch off to respectively associated separate air conditioning zones within the fuselage. Post-mixing units are respectively interposed in the mixed air distribution lines and respectively mix additional quantities of recirculated fuselage interior air into the mixed air distribution lines. Thereby, the admixture of recirculated air is divided into at least two stages, the system provides redundant failure tolerant operation, and the danger of ice formation in the air lines is reliably prevented even while the air conditioning units provide cold air at a temperature below the water freezing point.

Abstract: In an air conditioning system for an aircraft, two pre-mixing units respectively mix cold air from two air conditioning units with recirculated fuselage interior air from two recirculation units, to prepare two pre-mixed air flows that are both directed into and mixed together in a common air distribution mixing chamber from which mixed air distribution lines branch off to respectively associated separate air conditioning zones within the fuselage. Post-mixing units are respectively interposed in the mixed air distribution lines and respectively mix additional quantities of recirculated fuselage interior air into the mixed air distribution lines. Thereby, the admixture of recirculated air is divided into at least two stages, the system provides redundant failure tolerant operation, and the danger of ice formation in the air lines is reliably prevented even while the air conditioning units provide cold air at a temperature below the water freezing point.