Airbus Operations Gmbh

Sebastian Roering

Wilson Willy Casas Noriega

Markus Piesker

Matthias Reiss

Ozan Uluc

Jan Dittmar

Carsten Colberg

Marc Hoelling

Werner Rothammer

Holger Wolf

Ullrich Hesse

Ahmet Kayihan Kiryaman

Dirk Kastell

Martin Sieme

Georg Muehlthaler

Gerd Wedler

Philipp Goldmann

Cherif Terzi

Anja Erdle

Jean Blenner

A storage assembly, which is in particular suitable for use in a cooling system designed for an operation with a two-phase coolant medium, comprising a storage container with a receiving area for receiving a coolant medium and a conveying device for conveying coolant medium from the receiving area of the storage container. The conveying device is formed integral with the storage container of the storage assembly.

Storage assembly with a conveying device integrated into a storage container

A system for controlling a cooling system comprises an operating state detection unit adapted to detect operating signals characteristic of the operating state of the cooling system and/or the operating state of a plurality of cooling energy consumers to be supplied with cooling energy by the cooling system and a database in which priority data dependent on the operating state and characteristic of the priority to be given to the cooling energy consumers in terms of the cooling energy to be supplied in various operating states of the cooling system and/or of the cooling energy consumers, is stored for a plurality of cooling energy consumers to be supplied with cooling energy by the cooling system.

System and method for controlling an aircraft cooling system

A system for cooling and/or heating aircraft devices to be cooled and/or heated includes a first individual cooling and/or heating system associated with a first aircraft device to be cooled and/or heated, a second individual cooling and/or heating system associated with a second aircraft device to be cooled and/or heated, a cooling and/or heating energy supply apparatus adapted to supply cooling and/or heating energy generated by the first and/or the second individual cooling and/or heating system to the first and/or the second aircraft device to be cooled and/or heated, a control device adapted to receive and process signals characteristic of the cooling and/or heating requirements of the first and/or the second aircraft device to be cooled and/or heated and of the load condition of the first and/or the second individual cooling and/or heating system.

System and method for cooling and/or heating aircraft devices

A cooling system for cooling food on board an aircraft includes a cooling circuit adapted to supply cooling energy to at least one cooling station, a refrigerant circulating in the cooling circuit selected such that it is convertible at least partially from the liquid to the gaseous state of aggregation on releasing its cooling energy to the at least one cooling station and subsequently convertible back at least partially to the liquid state of aggregation again by an appropriate pressure and temperature control in the cooling circuit, and a refrigerant container including a receiving space arranged in an interior space of the refrigerant container which receives the refrigerant circulating in the cooling circuit, the receiving space of the refrigerant container connected to the cooling circuit by a flow line for discharging the refrigerant from the receiving space and by a return line for returning the refrigerant into the receiving space.

Cooling system and method for operating a cooling system

A sealing system () for use in an aircraft facility to be sealed from the environment comprises a closing element () which can be connected to a housing () of the aircraft facility in order to seal an opening () formed in the housing () of the aircraft facility. Furthermore, the sealing system () comprises a receiving device (), and a sealing element () received in the receiving device (). A transfer device () is adapted to transfer the sealing element () between an inactive state, in which the sealing element () is shaped and/or positioned such that it cannot be brought into sealing contact with a sealing surface (), and an active state, in which the sealing element () is shaped and/or positioned such that it can be brought into sealing contact with the sealing surface ().

Sealing system

An air duct for supplying ambient air in an aircraft includes an air inlet, a flow duct portion and a feed device that is devised to feed ambient air through the air inlet and the flow duct portion. A flow control flap closes the air inlet in a first position, releases a first flow cross-section of the air inlet in a second position and releases a larger second flow cross-section of the air inlet in a third position. The flow control flap is designed to not increase drag significantly in the second position while still enabling flow through the flow duct portion, while increasing drag to increase air fow through the flow duct portion in the third position.

Air duct for supplying ambient air in an aircraft

In a method of the application, cooling energy is produced by a refrigerating device. The cooling energy produced by the refrigerating device is supplied to at least one cooling station by a cooling circuit, circulating in which is a refrigerant, which upon release of its cooling energy to the at least one cooling station is converted from the liquid to the gaseous state and is then converted back to the liquid state by corresponding pressure- and temperature control in the cooling circuit. Upon transfer of the cooling system to its state of rest, a control value disposed in the cooling circuit is controlled in such a way that a desired operating pressure (&#x3c1;) arises in the cooling circuit downstream of the control valve. Refrigerant cooled by the refrigerating device is received in a reservoir disposed upstream of the control valve in the cooling circuit.

Method of operating a cooling system and cooling system

An aircraft signal computer system includes a plurality of modular signal computer units and a liquid cooling device for cooling the modular signal computer units. The liquid cooling device includes a coolant line, which is connectable to a central liquid cooling system of an aircraft in order to supply a liquid coolant medium at a desired low temperature to the liquid cooling device. The coolant line of the liquid cooling device is in thermal surface contact with the modular signal computer units in order to dissipate heat from the modular signal computer units. A heat-emitting component of the modular signal computer units may be in thermal contact with a coolant bath or an internal heat conductor for removing heat energy.

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Hamburg, Germany

Sebastian Roering