Airbus Operations Sl

Airbus Operations Gmbh

Other

Carlos Casado Montero

Pablo Manuel Calderón Gómez

Marcos Javier Chiabrando

Alberto Molina Parga

Juan Manuel Canalejo Bautista

Maria Zamarro Martin

Jose Grana Otero

José Ángel Hernanz Manrique

Ignacio Esteban Parra Fabian

Francisco Manuel Andreu Fernández

Miguel Angel Gallego Lorenzo

Pio Fernandez Lopez

Hugo Casado Abarquero

Jose Angel Hernanz Manrique

Pedro Manuel Martin Candelario

Lucas Granja Parejo

María Cruz Zamarro Martín

Benjamin David

Ignacio Esteban Parra Fabián

José Graña Otero

Alberto Molina

María Cruz Zamarro MARTÍN

Francisco Manuel Andreu FERNÁNDEZ

Pio FERNÁNDEZ LÓPEZ

José ÁNgel Hernanz Manrique

Miguel ÁNgel Gallego Lorenzo

Maria Cruz Zamarro Martin

Pio Fernandez López

An aircraft conditioning system including a fuel tank, including an outlet connected to an Auxiliary Power Unit (APU) fuel inlet, configured to maintain a pressurized gas fuel, a pressure regulator, downstream of the fuel tank, configured to regulate a pressure of the pressurized gas fuel injected to the APU inlet, a first temperature sensor downstream of the pressure regulator and a second temperature sensor upstream of an engine, a first pressure sensor inside the fuel tank, a second pressure sensor downstream of the pressure regulator and a third pressure sensor at an engine inlet, and a controller connected to the pressure sensors and the temperature sensors, the controller receiving temperature and pressure values from the pressure sensors and from the temperature sensors and actuating on at least one of the pressure regulator or the injection position of the pressurized gas fuel inside a plurality of engine combustion chambers.

Conditioning fuel system for an auxiliary power unit of an aircraft

An auxiliary power generator system for an aircraft including an auxiliary power unit (APU) with dual and fully redundant starter and electrical power generation systems that connects independently to a normal electric network or an emergency electric network of an aircraft. A method for supplying electric power to an aircraft by means of the system.

Auxiliary power system

Air conditioning system for a cabinof an aircraft, the air conditioning systemincluding a pressurized air source, a ram air duct, an air amplifierand a heat exchanger. The air amplifierincludes an inletfor work air, a slotsuitable for letting the work air exit the air amplifier, and a main fluid zone. The inletis in fluid communication with the pressurized air sourceand the slotis arranged in fluid communication with the ram air duct, in such a way that the work air exiting from the slotproduces a suction effect in the ambient air in such a way that this ambient air flows along the ram air duct. The air amplifieris arranged so that the ambient air is forced by the suction effect to pass from the inletto the outletof the cold side of the heat exchanger

Air conditioning system

A drain mast for draining liquids from an aircraft, comprising a tube that comprises an internal rim connected to the internal surface of the tube, the internal rim being located in a plane inclined with respect to the horizontal plane of the aircraft and having its lowest part located on the second end of the tube, an aperture for evacuating the liquid, the aperture being located at the lowest part of the internal rim and in the face of the tube facing the incoming airflow, the internal rim and the aperture being configured such that at the second end, the liquid is directed by gravity through the internal rim to the aperture and wherein, in use, the drained liquid flowing from the aperture is pushed by the incoming airflow to the atmosphere.

Drain mast of an aircraft

An air conditioning systemfor a cabinincluding a pressurized air sourcea cooling air sourcea main heat exchangera compressora manifoldand a mixing chamberAn inletto a cold side of the main heat exchangeris in fluid communication with the cooling air sourceAn inletof a hot side of the main heat exchangeris in fluid communication with the pressurized air sourceAn inletof the compressor is in fluid communication with the outletof the cold side of the main heat exchanger

An Auxiliary Power Unit ('APU') for an aircraft with reduced weight, but which at the same time meets all fire-related airworthiness standards. The APU comprises a metallic housing having mounts for attaching the housing to an external structure. The APU further comprises at least one temperature sensor suitable for detecting temperature under fire conditions. The temperature sensor is coupled with the mounts for sensing temperature at the housing.

Auxiliary power unit with integrated fire detection system

A drainage mast able to drain effectively the liquid contained in the compartment of an aircraft when the pressure within the compartment is lower than the outside pressure without using any pressure control active device and without causing any significant perturbation to the aerodynamic behavior of the aircraft. The drainage mast is configured with a cross section area decreasing from its entry section to the compartment to its outlet section and is disposed at an acute angle &#x3b1; relative to the compartment in the airflow direction. The entry and outlet sections have two perpendicular symmetry axes of different length, the entry section is arranged with its longer axis of symmetry substantially parallel to the airflow direction. The drainage mast has a symmetrical configuration with respect to a plane substantially perpendicular to the fuselage envelope passing through the longer axis of symmetry of the entry section.

Drainage mast of the compartment of an aircraft subjected to a negative pressure

An Auxiliary Power Unit (APU) includes a power module () to be supplied with fuel (), a gearbox (), an electric generator (), and an element selected from a compressor (), a hydraulic pump and a combination thereof, in order to provide a functioning mode for production of power selected from electric (), pneumatic (), hydraulic and a combination thereof; the APU presents the novelty of including an electric motor (), integrated into the electric generator (), with the electric motor () and the electric generator () connected to the power module () via the gearbox () and a main clutch (). Moreover, the compressor () and/or the hydraulic pump are also connected to the power module () via the gearbox () and the main clutch (). Also, the compressor () and/or hydraulic pump are connected to the power module () via the gearbox () and the main clutch (). This architecture permits the functioning modes of the APU to be extended, increasing its performance and reducing harmful environmental effects.

Auxiliary power unit (APU) of an aircraft

New ecological operating mode that limits ventilation and air conditioning in the cabin () of the aircraft when the ecological operating mode has been selected, the aircraft is stationed on the ground, the engines are off, the engines' start up system has not been activated, the pneumatic or electrical energy supply system that typically controls ventilation and air conditioning in the aircraft has been activated and is supplying air, to provide a new method of operating at an established minimum limit independent of the difference between the selected temperature and the temperature measured, saving energy, and reducing pollutant emissions and noise.

Device to control the ventilation and air conditioning of aircraft on the ground

Growing community of inventors

Madrid, Spain

Carlos Casado Montero