Airbus Operations Gmbh

Airbus Deutschland Gmbh

Recaro Aircraft Seating Gmbh & Co. Kg

Andreas Frey

Matthias Reiss

Ahmet Kayihan Kiryaman

Ozan Uluc

Wolfgang Ebigt

Wilson Willy Casas Noriega

Carsten Colberg

Markus Kerber

Michael Dreyhaupt

Peter Schwebke

Dirk Kastell

Stefan Repp

Sven Reisbach

Frank Bliemeister

Willy Casas Noriega

The invention discloses the multistage cooling of an aircraft electronic system () with at least one electronic component which delivers heat. The multistage feature results from the use of a plurality of circuits for transferring the waste heat. An internal coolant () circulating in a closed circuit which is thermally coupled to the electronic component carries heat from the at least one electronic component to a heat exchanger () which delivers the heat to an external coolant which flows and/or circulates from a source outside of the aircraft electronic system () through the heat exchanger () to a sink outside of the aircraft electronic system (). The internal coolant flows from the heat exchanger () in the direction of the at least one electronic component and/or circulates in a closed circuit.

Multistage cooling of electronic components of an aircraft

The invention relates to an improved aircraft electronics cooling system for an aircraft having a liquid cooling system, the aircraft electronics cooling system providing a thermal coupling between an electronic device to be cooled and the liquid cooling system of the aircraft. A coolant delivered by the liquid cooling system may flow through a board of the electronic device, through a heat sink on which the electronic device is arranged and/or through a housing in which the electronic device is arranged. The coolant may be permanently in the liquid state in a cooling circuit. The coolant may vaporize at least partially while cooling the electronic device.

Aircraft electronics cooling apparatus for an aircraft having a liquid cooling system

An aircraft cooling system includes a first coolant stream which cools at least one first heat load and a second coolant stream which cools at least one second heat load. The aircraft cooling system is formed such that the first heat load and the second heat load are thermally coupled together. The first heat load and the second heat load can be formed by two mutually redundant aircraft components. A third coolant stream thermally couples the first heat load and the second heat load together. The third coolant stream can be cooled by a heat sink, such as the outer skin of the aircraft in a bilge region.

Redundant aircraft cooling system for redundant aircraft components

A seat fixing device for fixing an air passenger seat to a floor of an aircraft includes at least one fastening rail () in the form or a hollow profile, which is provided with a longitudinal channel () delimiting the free flanks () of the profile on the top part thereof () oriented to the seat. The channel includes through openings () located in a predetermined modular dimension, which enlarge the free input section and are used for inserting at least one snap-locking part () of a locking body (). The looking body () is movable to a clamping position with the profile () of the hollow profile () by the relative displacement of each snap-locking part () in a perpendicular direction with respect to the longitudinal axis () of the fastening rail (). The fixing device provides an eccentric drive () of the locking body () for carrying out relative displacement, which reduces assembly costs.

Seat fixing device

An aircraft air-conditioning system is disclosed, which includes at least one heat exchanger to which coolant circulating in a cooling circuit of a cooling system and air are fed. The coolant cools the fed air in the heat exchanger, and the air leaving the heat exchanger enters the aircraft cabin. The coolant of the cooling system is always in the liquid state in the cooling circuit. The liquid coolant can also cool an aircraft seat or a sitting area of the aircraft seat.

Aircraft air-conditioning system for the individual air conditioning of regions of an aircraft cabin with a liquid coolant

An aircraft cooling system for cooling heat loads on board an aircraft includes a cold producing device, a first cold carrier fluid circuit thermally coupled to the cold producing device and connected to a first heat load in order to carry off heat from the first heat load, a second cold carrier fluid circuit connected to a second heat load in order to carry off heat from the second heat load, a heat exchanger disposed in the second cold carrier fluid circuit and configured to thermally couple the second cold carrier fluid circuit to an ambient temperature surrounding the aircraft, and a coupling system configured to selectively thermally couple the first cold carrier fluid circuit to the second cold carrier fluid circuit or thermally uncouple it from the second cold carrier fluid circuit.

Cooling system for cooling heat loads on board an aircraft and method for operating such a cooling system

A cooling system () for cooling an aircraft device () comprises an evaporator () for receiving a fluid (F) which is to be evaporated, a first adsorber () which contains a medium () for the adsorption of the fluid (F) which is evaporated in the evaporator (), as well as a second adsorber () which contains a medium for the adsorption of the fluid (F) which is evaporated in the evaporator (). A control system () is adapted to establish or to interrupt a fluid connection between the evaporator () and the first and/or the second adsorber(s) ().

Cooling system and method for cooling an aircraft device

A system () for cooling freight goods on board an aircraft comprises a refrigerating apparatus and a cooling station () to which cooling energy generated by said refrigerating apparatus is fed by means of a refrigerating medium and which is connected to an air infeed line () of an air-conditioning installation of the aircraft, wherein an air outlet aperture () of the cooling station () is connectable to a freight compartment () of the aircraft in order to discharge into said freight compartment () air which has been cooled down to a desired temperature.

Cooling system and freight container

The invention relates to an improved aircraft electronics cooling system for an aircraft having a liquid cooling system (), the aircraft electronics cooling system providing a thermal coupling between an electronic device () to be cooled and the liquid cooling system () of the aircraft. A coolant delivered by the liquid cooling system () may flow through a board of the electronic device (), through a heat sink on which the electronic device () is arranged and/or through a housing in which the electronic device () is arranged. The coolant may be permanently in the liquid state in a cooling circuit. The coolant may vaporize at least partially while cooling the electronic device.

A passenger seat, an aircraft passenger seat in particular, has seat components such as a seat frame (), a backrest (), and a seat cushion carrier () with seat cushion (). The seat depth between backrest () and a seat front edge () can be varied by an adjustment mechanism () with an energy accumulator, such that the seat depth is adjustable and fastenable in desired adjustment positions. The adjustment mechanism has at least one variable-volume energy accumulator. An adjustment position of the seat depth may be associated with each volume level. The seat depth adjustment may be effected essentially free of mechanical components such as sets of levers.

Passenger seat with adjustable seat depth

The invention relates to a seat securing system for securing air passenger seats to a securing rail (), whereby the system permits a relative motion between a mounting part () and a base body () that, in the longitudinal direction of said securing rail (), can be brought into a fixed position. In this securing position, a locking body (), which can pivot from a release position and into a locking position and which is subjected to the action of an energy storage device (), secures the respective detent parts () and thus the base body () and mounting part () on the securing rail (). Said energy storage device permits a compensation of tolerances so that the inventive fitting always rests securely against the rail().

Seat securing system

A seat, in particular an aircraft passenger seat, has a seat component () and a backrest component () made at least in part of shell components. One shell component () is detachably connected to other components of the seat by a fastening mechanism. In the event of sudden introduction of force, as in the event of a crash, the shell component () is detached from the other components of the seat. A passive element is created by the shell component. When normal operating forces are present, that is, in the normal operating state of the seat, the passive element retains its position and shape. In the event of introduction of large force impulses, such as in sudden introduction of force in the event of a crash, the passive element is detached from the remaining shell structure of the seat without significant reaction forces being generated, which might cause injury of the seat occupant, and creates a free space in the seat.

Growing community of inventors

Immenstaad, Germany

Andreas Frey