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Airbus Operations Limited patents


Recent patent applications related to Airbus Operations Limited. Airbus Operations Limited is listed as an Agent/Assignee. Note: Airbus Operations Limited may have other listings under different names/spellings. We're not affiliated with Airbus Operations Limited, we're just tracking patents.

ARCHIVE: New 2018 2017 2016 2015 2014 2013 2012 2011 2010 2009 | Company Directory "A" | Airbus Operations Limited-related inventors


Aircraft fuel vent pipe

An aircraft fuel vent pipe with a pipe body containing a duct which extends along a duct axis between an open end and a closed end. A burst disc closes the closed end of the duct. ... Airbus Operations Limited

Method and apparatus for determining a movement direction of a component of a mechanism

An apparatus for determining a movement direction of a component of a mechanism. The apparatus includes an acoustic emission sensor arranged to detect acoustic emission from the mechanism, and a processor arranged to determine a doppler shift in a frequency characteristic of the measured acoustic emission and to determine a movement direction of a component of the mechanism on the basis of the determined doppler shift. ... Airbus Operations Limited

Rib arrangement in a wing tip device

An aircraft (1) having a wing (3) and a wing tip device (4) at the tip of the wing (3), wherein the wing tip device (4) includes a rib (16) positioned in a span wise region (c) of the wing tip device (4) in which transonic flow occurs when the aircraft (1) is in flight. A method of designing an aircraft (1) including predicting where transonic flow occurs on the wing tip device (4) when the aircraft (1) is in flight, and designing the wing tip device (4) with a rib (16) positioned in the span wise region (c) of the wing tip device (4) in which the predicted transonic flow occurs.. ... Airbus Operations Limited

Ejectable flight data recorder unit

An apparatus for recording aircraft flight data including a primary flight data recorder unit for recording data generated by aircraft systems during operation of an aircraft and a secondary flight data recorder unit in communication with the primary flight data recorder unit. The secondary flight data recorder unit is configured to receive and store data from the primary flight data recorder. ... Airbus Operations Limited

Hydraulic actuator and accumulator arrangement

A landing gear system for an aircraft includes a retractable landing gear assembly, a hydraulic actuator for actuating movement part, for example a bogie of the landing gear assembly, and an accumulator associated with the actuator. The accumulator comprises a volume of pressurised gas separated from hydraulic fluid by a separator piston. ... Airbus Operations Limited

Rotational joint for an aircraft folding wing

An aircraft (2) including a wing (1), the wing (1) having a fixed wing (3) and a wing tip device (4) at the tip of the fixed wing (3), the wing tip device (4) being rotatable relative to the fixed wing (3) between flight and ground configurations, the aircraft including a rotational joint (10) with a rotation mechanism (11) that rotatably couples the wing tip device (4) to the fixed wing (3) and a locking mechanism including a locking bore (53, 54) and a locking pin (51) that is receivable in the locking bore to lock the wing tip device (4) in one of the flight or ground configurations, wherein the rotational joint includes an alignment mechanism including an alignment pin (61) and an alignment bore (62, 63) and at least one of the alignment pin and alignment bore is tapered such that engagement of the alignment pin (61) in the alignment bore acts to guide the locking bore and locking pin into alignment.. . ... Airbus Operations Limited

Fault detection based on brake torque and temperature

A fault detection system for an aircraft braking system including: a controller configured to receive braking demand information; torque information; wear information; wheel speed information; and brake temperature information. The controller is to calculate an expected maximum temperature of the brake based on the torque information, the wear information and the wheel speed information; to determine whether a significant temperature discrepancy exists between the expected maximum temperature and the brake temperature information; to determine whether a significant torque-related discrepancy exists based on the braking demand information and the torque information. ... Airbus Operations Limited

A rotational joint for an aircraft folding wing

A folding wing having a wing tip device (3) rotatable between flight and ground configurations, about an euler axis of rotation (11). The wing tip device (3) and a fixed wing (1) are separated along an oblique cut plane (13) passing through the upper and lower surfaces of the folding wing. ... Airbus Operations Limited

A measuring apparatus for measuring properties of a surface

The present invention provides a measuring apparatus (200) for measuring properties of a surface (101, 103), the apparatus (200) comprising a mounting structure (210) comprising a plurality of segments (211-216) moveably mounted (217) with respect to each other, an actuation mechanism to move the segments of the mounting structure with respect to each other, and a plurality of sensors (220), each sensor being mounted to a segment of the mounting structure (210). The invention also provides a method of measuring properties of a surface (101, 103). ... Airbus Operations Limited

Aircraft seal assembly

An aircraft assembly may have a drag-inducing discontinuity 112. A seal assembly 101 includes a seal body 110 arranged to fair and/or seal the discontinuity 112; and a sealed chamber 114, wherein the sealed chamber 114 being pressurised such that in response to changes in the ambient pressure relative to the internal pressure of the chamber 114 the sealed chamber 114 alters the behaviour of the seal body 110.. ... Airbus Operations Limited

Cap for a fastener

A cap configured for providing a sealed cavity around an end of a fastener and a method of bonding a cap to a structural member in which a contact adhesive is provided for fixing the cap to the structural member and a curable sealant is provided for bonding the cap to the substrate.. . ... Airbus Operations Limited

Landing gear drive systems

A drive system for rotating one or more wheels of an aircraft landing gear for ground taxiing and/or spin-up prior to landing has a motor operable to rotate a first drive pinion via a first drive path, and a driven gear adapted to be fixed to the wheel. The drive system has a first configuration in which the first drive pinion meshes with the driven gear to permit the motor to drive the driven gear via the first drive path. ... Airbus Operations Limited

Locking device

An aircraft wing comprises a fixed wing, and a wing tip device at the tip thereof the wing tip device is configurable between (i) a flight configuration for use during flight, and (ii) a ground configuration for use during ground based operations. In the ground configuration with span of the wing is reduced. ... Airbus Operations Limited

Aircraft autonomous pushback

The invention provides methods and systems for controlling speed of an aircraft during an autonomous pushback manoeuvre, i.e. Under the aircraft's own power without a pushback tractor. ... Airbus Operations Limited

06/07/18 / #20180156696

Actuator testing

An apparatus for in-situ testing of a linear actuator configured to exert an actuation force in an actuation direction by movement of a first part of the actuator relative to a second part of the actuator. The apparatus includes a test device, a test actuator and a measurement device. ... Airbus Operations Limited

06/07/18 / #20180155004

Aerofoil structure components

A component for an aerofoil structure including a unitary member having a spar; a cover panel; and a substantially flat intermediate section which connects the spar to the cover panel. The spar, the cover panel and the intermediate section are integrally formed such that a first angle between the intermediate section and the cover panel and a second angle between the intermediate section and the spar are both in the range 90° to 180°.. ... Airbus Operations Limited

05/31/18 / #20180149498

Fibre-optic communication system, a communication apparatus for the same, and a vehicle

A communication apparatus for a fibre-optic communication system for an aircraft that includes: an optical coupler; an input port optically coupled to the optical coupler via a first waveguide, the input port arranged to receive light; a modulator optically coupled to the optical coupler via a second waveguide, the modulator having a logic input and a fibre having a fibre bragg grating (fbg) receiving light from the input port via the optical coupler, the modulator operable to vary a strain force applied to the fibre according to a logic signal received at the logic input to modulate a wavelength of a modulated light signal reflected by the fbg back to the optical coupler; and an output port optically coupled to the optical coupler via a third waveguide to receive the modulated light signal therefrom, the output port being operable to output the modulated light signal.. . ... Airbus Operations Limited

05/24/18 / #20180145751

Fibre-optic communication system and an aircraft

A fibre-optic communication system for an aircraft including: a light source operable to generate light; a transceiver in optical communication with the light source, the transceiver including a control input and a reflector; an optical fibre in optical communication with the transceiver; and a light detector in optical communication with the optical fibre. The transceiver is operable to generate an amplitude modulated light signal by selectively reflecting the light received from the light source into the optical fibre using the reflector according to information received at the control input. ... Airbus Operations Limited

05/17/18 / #20180135772

Actuator with brushless dc motor

An actuator includes a brushless dc motor, an output device, a reduction system coupled between the brushless dc motor and the output device, and a contactless position sensor configured to sense a position of the output device.. . ... Airbus Operations Limited

05/17/18 / #20180135760

Aircraft gap seal

An aircraft assembly including: first and second external skin panels having opposing edge faces separated by a gap, the gap having a width in a first direction extending between the opposing edge faces and a depth in a second direction generally orthogonal to the first direction; and a gap seal arranged in the gap to at least partially fill the gap, wherein the gap seal is formed of a material configured such that compression of the gap seal in the first direction results in substantially no expansion of the gap seal in the second direction.. . ... Airbus Operations Limited

05/17/18 / #20180135735

Roller components

A roller component configured to engage with a toothed component such that when the roller component is engaged with the toothed component, rotational movement of one of the roller component and the toothed component drives linear movement along an actuation direction of the other one of the roller component and the toothed component. The roller component includes a support member and cantilevered first rollers, each of which has a mounted end connected to a first side of the support member such that each first roller is rotatable relative to the support member about a roller axis perpendicular to the actuation direction, and an unsupported end distal from the mounted end.. ... Airbus Operations Limited

05/17/18 / #20180134365

Aircraft component comprising a chiral lattice

An aircraft protective component for an aircraft module, the aircraft protective component includes: a plurality of cells connected together to form a lattice, each cell having a chiral structure, wherein the lattice of the cells is configured to at least partially surround the aircraft module to provide an energy absorption barrier for the aircraft module. The aircraft protective component enables the energy generated by an impact to the aircraft to be dissipated throughout the lattice of the protective component. ... Airbus Operations Limited

05/03/18 / #20180118333

Landing gear drive system flexible interface

A drive system for an aircraft landing gear, the drive system including a pinion gear, a drive shaft arranged to rotate the pinion gear about a drive axis, a driven gear arranged to mesh with the pinion gear to be rotatable by the pinion gear, the driven gear being connectable to a wheel of the landing gear to be capable of rotating the wheel about a wheel axis; and a flexible interface. The flexible interface includes a plurality of driven gear coupling members, each driven gear coupling member having a first connection portion attached to the driven gear, a second connection portion adapted to be attached to the wheel at an offset distance from the wheel axis, and a joint between the first connection portion and the second connection portion, the joint permitting relative movement between the first connection portion and the second connection portion.. ... Airbus Operations Limited

04/12/18 / #20180099737

Control device for an aircraft

A control device (34) for an aircraft wing (3) including upper and lower spoilers (35, 37) mountable to a wing (3) behind a leading edge slat (26), wherein each of the upper and lower spoilers (35, 37) are movable in a direction towards each other into a wing (3) from a neutral position, to an enabled position to form an airflow slot (52) between the slat (26) and said upper and lower spoilers (35, 37). Each of the upper and lower spoilers (35, 37) may also be movable in a direction away from each other out of a wing (3) from said neutral position.. ... Airbus Operations Limited

04/12/18 / #20180099735

Aircraft wing with aileron

An aircraft wing having a fixed wing with a wing tip device. The wing tip device is movable between a flight configuration for use during flight, and a ground configuration for use during ground-based operations. ... Airbus Operations Limited

04/05/18 / #20180095133

Component monitoring

A component monitoring apparatus [100] including an input [110] to receive sensor data from a sensor arrangement [s1-s4]. The sensor data representative of a use of a respective component [105] during a monitoring interval. ... Airbus Operations Limited

03/29/18 / #20180086439

Aircraft landing detector

Sustained ground contact of an aircraft is determined by detecting a change in a mechanical vibration characteristic of a part of the aircraft. Apparatus for determining sustained ground contact of an aircraft includes an analyser [300] for analysing aircraft vibration signals and a trigger [310] for triggering occurrence of sustained ground contact to an aircraft control system [315] when the analyser [300] detects sustained ground contact.. ... Airbus Operations Limited

02/08/18 / #20180037315

Landing gear drive system

The invention provides a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion, and a driven gear adapted to be mounted to the wheel. ... Airbus Operations Limited

02/08/18 / #20180037314

Landing gear

An aircraft include a landing gear is disclosed. The landing gear comprises a main strut and an inboard stay assembly connected to the aircraft fuselage such that landing gear loads can be transferred from the inboard stay assembly into the fuselage. ... Airbus Operations Limited

01/25/18 / #20180023526

Removing water from fuel tanks

A combination of a fuel tank assembly and a tool for opening an outlet of the fuel tank assembly. The assembly includes a tank for storing a liquid hydrocarbon; and an operator-openable valve arrangement configured to move between a closed flow condition in which flow through the valve arrangement is prevented and an open flow condition in which liquid is allowed to drain out of the tank. ... Airbus Operations Limited

01/25/18 / #20180021880

Method of manufacturing a multi-alloy aerospace component

A method of making an aerospace component such as a spar for an aircraft wing is disclosed. The method includes placing two billets of different alloy in abutting relation, there being no voids or channels formed therebetween, partial penetration friction stir welding together the two billets from opposing sides of the billets, the welds so formed being separated by a central region formed partly by one billet and partly by the other billet, and then machining away material. ... Airbus Operations Limited

01/18/18 / #20180016029

Aircraft landing gear arrangement, a kit therefor, an aircraft comprising the same and a method of determining the angular position of an aircraft wheel

An aircraft landing gear arrangement is provided comprising: a first landing gear portion comprising one or more wheels, a second landing gear portion, the first landing gear portion being rotatable with respect to the second landing gear portion; and a sensor for determining a rotational position of the first landing gear portion in relation to the second landing gear portion, the sensor comprising a first magnetic field generator operable to generate a magnetic field and a first magnetic field modulator for modulating said magnetic field, the sensor being operable to sense the magnetic field as modulated by the first magnetic field modulator, the first landing gear portion comprising the first magnetic field generator or the first magnetic field modulator, the second landing gear portion comprising the other of the first magnetic field generator and the first magnetic field modulator.. . ... Airbus Operations Limited

01/11/18 / #20180009548

Aircraft light

A wingtip device 1 including an upwardly extending winglet 2 and a downwardly extending winglet 4. The downwardly extending winglet 4 is connected to the upwardly extending winglet 2 at a join 6. ... Airbus Operations Limited

12/28/17 / #20170369151

Methods of configuring a wing tip device on an aircraft

A method of configuring a wing tip device (7) on an aircraft (1), including: undertaking ground-based operations at an airport with the wing tip device (7) in a ground configuration, in which the span of the aircraft is within an airport compatibility limit, moving the wing tip device (7) to a take-off configuration in which the wing tip device (7) is moved away from the ground configuration such that the span of the aircraft is increased and such that the wing tip device (7) has a first lift coefficient; taking-off with the wing tip device (7) in the take-off configuration; moving the wing tip device from the take-off configuration to a flight configuration, in which the wing tip device has a second lift coefficient, the second lift coefficient being lower than the first lift coefficient. The lift coefficient may be changed by adjusting the sweep of the wing tip device (7).. ... Airbus Operations Limited

12/28/17 / #20170368769

Method of forming a structural portion of a fuel tank for an aircraft

The present application relates to a method of forming a structural portion of a fuel tank for an aircraft in which the structural portion is formed from a fibre reinforced polymer and a sensor is integrated in the structural portion. The method includes providing a fibre ply which acts as a structural component, and embroidering an electrically conductive wire in a predetermined pattern on the fibre ply to form the sensor. ... Airbus Operations Limited

12/14/17 / #20170355444

Foldable wing and actuator arrangement

A wing arrangement for an aircraft is described including a wing (5) having a base section (5) and a tip section (13), the base section (7) having a first end portion (9) and a second end portion (11), the tip section (13) having a third end portion (15) and a fourth end portion (17), wherein the second end portion (11) and the third end portion (15) are coupled with each other by a coupling arrangement so that the tip section (13) is pivotable with respect to the base section (7) about a pivot axis (19, 19′).. . ... Airbus Operations Limited

12/14/17 / #20170355442

Foldable wing and actuating arrangement

A wing (5) having a base section (5) and a tip section (13), the base section (7) having a first end portion (9) and a second end portion (11), the tip section (13) having a third end portion (15) and a fourth end portion (17), wherein the second end portion (11) and the third end portion (15) are coupled so that the tip section (13) is pivotable with respect to the base section (7) about a pivot axis (19, 19′), and an actuating arrangement having an actuator (21) which is coupled to the base section (7) and the tip section (13) and which is operable to effect a pivotal movement of the tip section (13) relative to the base section (7) between a stowed position and a deployed position.. . ... Airbus Operations Limited

12/14/17 / #20170355440

Rotational joint for an aircraft folding wing and method of assembly

A method of rotatably couple a wing tip device (4) to a fixed wing (3) by a rotational joint (101) having an outer race (8) and an inner race (9) that is received in the outer race (8) one of the inner and outer races comprises a male member (76) and the other is a two-part assembly comprising a first part (9a) and a second part (9b) that together form a female member (72), the method brings the first and second parts together to form the female member (72) about the male member (76) such that the male member (76) is received in the female member (72) and fixing the first and second parts (9a, 9b) such that the race that is rotationally fixed relative to the wing tip device (4) is axially and radially retained relative to the race that is rotationally fixed relative to the fixed wing (3).. . ... Airbus Operations Limited

12/14/17 / #20170355439

Interface between an outer end of a wing and a moveable wing tip device

An aircraft (102) including a wing (101), having a fixed wing (105) with a wing tip device (103) moveably mounted at the outer end thereof. The wing tip device (103) is moveable between: a flight configuration; and a ground configuration. ... Airbus Operations Limited

12/14/17 / #20170355436

Arrangement of ribs at an interface between an outer end of a wing and a moveable wing tip device

An aircraft (102) having a wing assembly (101) including a fixed wing (105) with a wing tip device (103). The wing tip device (103) is moveable between: a flight configuration; and a ground configuration. ... Airbus Operations Limited

11/30/17 / #20170341737

Winglet

A winglet for attachment to a wing portion of an aircraft including a winglet root. The winglet root defines a recess for receiving a connector of the wing portion in use and includes at least one protrusion for receipt into at least one corresponding hole of the wing portion in use. ... Airbus Operations Limited

11/30/17 / #20170341728

Winglet

A winglet for attachment to a wing portion of an aircraft comprises a winglet tip and a winglet root opposite from the winglet tip. The winglet has an opening for receiving therethrough a connector for connecting the winglet to a wing portion in use. ... Airbus Operations Limited

11/23/17 / #20170334543

Folding wing tip and rotating locking member

A rotatable locking member for locking an aircraft wing with a movable wing tip device. The rotatable locking member including a u-shaped receiving portion arranged such that in an unlocked position the locking pin may be moved into and out of the u-shaped receiving portion, and in a locked position the locking pin is not able to be moved out of the u-shaped receiving portion, and the rotatable locking member is configured to be moved between the unlocked and locked position by rotational movement around the longitudinal central axis of the locking pin.. ... Airbus Operations Limited

11/23/17 / #20170334541

Aerofoil body with integral curved spar-cover

An aerofoil shaped body includes a plurality of longitudinal spars, an upper aerofoil cover, and a lower aerofoil cover. The spars and the covers are made of composite laminate material. ... Airbus Operations Limited

11/16/17 / #20170327245

Aircraft joint

An aircraft joint includes a first component having an outer aerodynamic surface and an inner surface, a second component having an outer aerodynamic surface and an inner surface, and a strap assembly bridging between the inner surfaces of the first and second components. The strap assembly has a first strap part attached to the inner surface of the first component, a second strap part attached to the inner surface of the second component, and a third strap part received in the first and second strap parts in a sliding manner. ... Airbus Operations Limited

11/16/17 / #20170327203

Aircraft joint

An aircraft joint between overlapping first and second components includes a fastener assembly. The fastener assembly includes a threaded fastener and a boss having an outer diameter and a threaded internal bore. ... Airbus Operations Limited

11/16/17 / #20170327202

Aircraft joint

An aircraft joint between overlapping first and second components includes a fastener having a head and a shank, and a fastener retainer fixedly attached to the second component at the overlap region. The fastener retainer has a recess and a through hole. ... Airbus Operations Limited

11/16/17 / #20170326927

Tyre deflection monitoring

An apparatus for monitoring deflection of a tyre including a non-transitory memory, storing tyre behavior information which relates tyre deflection to tyre load and tyre pressure; and a controller in communication with the memory. The controller is configured to: receive load information which relates to a load on the tyre; receive pressure information which relates to a pressure of the tyre; and determine a deflection of the tyre based on the received load information, the received pressure information, and the stored tyre behavior information.. ... Airbus Operations Limited

10/26/17 / #20170305763

Fuel flow system

The present application relates to a fuel flow system. In particular, the application relates to a fuel flow system for an aircraft. ... Airbus Operations Limited

10/26/17 / #20170305577

Brake temperature prediction and cooling time functionality

A brake cooling period prediction system for predicting a brake cooling period following a braking event, and including a sensor apparatus in communication with a prediction apparatus. The sensor apparatus has a torque sensor for measuring the torque reacted by a brake during a braking event; a wear sensor for measuring a wear state of the brake; and an environmental sensor for measuring at least one ambient condition of the environment of the brake. ... Airbus Operations Limited

10/26/17 / #20170305536

Landing gear drive systems

A drive system for rotating a wheel of an aircraft landing gear includes a motor operable to rotate a first drive pinion via a first drive path and a driven gear adapted to be fixed to the wheel. The drive system has a first configuration in which the first drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the first drive path. ... Airbus Operations Limited

08/10/17 / #20170227079

Aircraft brake and cooling methods therefor

A method of cooling an aircraft brake including a brake pack and a reservoir in the form of a removable cartridge containing a coolant. The method includes vaporizing the coolant using heat energy from the brake pack.. ... Airbus Operations Limited

07/27/17 / #20170210482

Aircraft fuel system

An aircraft fuel system has a bottom wall, and a rib with a bottom edge joined to the bottom wall. The rib provides a boundary between first and second compartments. ... Airbus Operations Limited

07/27/17 / #20170210458

Aircraft frame structure and associated method

An aircraft frame structure including a grid support (such as a geodetic support) (2) and (i) an impact-resistant barrier (6) including a shear thickening fluid, and (ii) a water-resistant, elastically-deformable cover (4). Methods to make and repair an aircraft using the aircraft frame structure.. ... Airbus Operations Limited

07/13/17 / #20170197707

Drive system for aircraft landing gear

A method of engaging a drive system with a rotating wheel of an aircraft landing gear is disclosed. A motor is operated to apply torque to a pinion so the pinion rotates. ... Airbus Operations Limited

06/22/17 / #20170175895

Seal assembly

. . An aircraft wing has a fixed wing portion and a trailing edge flap movable with respect to the fixed wing portion to define a gap between the fixed wing and the flap. A seal assembly has a first rigid seal member fixed to the fixed wing portion and a second resilient seal member fixed to an upper surface leading edge portion of the flap. ... Airbus Operations Limited

06/22/17 / #20170174329

Aircraft landing gear

The present invention concerns an aircraft landing gear comprising a wheel rotatably mounted on an axle, a first gearing element that rotates with the wheel, a second gearing element configured to mesh with the first gearing element such that rotation of the first gearing element causes rotation of the second gearing element, wherein the second gearing element is connected to a generator, such that rotation of the second gearing element causes the generator to generate electrical energy, further comprising a heat dissipation device connected to the generator wherein the heat dissipation device comprises an electrical heating element connectable to the generator to receive generated electrical energy and convert it to heat energy, and a fluid receptacle adjacent the heating element, such that fluid in the receptacle can be heated. The present invention also concerns an aircraft landing gear comprising a cavitation braking device, an aircraft and a method of braking.. ... Airbus Operations Limited

06/22/17 / #20170174313

Wing structure

A section of an aircraft wing including a leading edge of the aircraft wing. A leading edge part of the section includes ribs; and a skin fixedly attached to the ribs to form a spanwise series of adjacent cells. ... Airbus Operations Limited

06/22/17 / #20170174312

Structure formed from composite material

A structure formed from composite material and method of forming a structure composite material is disclosed in which one or more metal layers are disposed on the composite material.. . ... Airbus Operations Limited

06/22/17 / #20170173919

Structure formed from composite material

A structure formed from composite material and method of forming a composite structure is disclosed in which one or more metal layers are disposed on a composite structural member.. . ... Airbus Operations Limited

06/15/17 / #20170167637

Raceway

A raceway and method of forming a raceway is disclosed in which one or more intumescent layers are disposed on the raceway.. . ... Airbus Operations Limited

06/15/17 / #20170167610

Seal

A seal is disclosed for a wing for providing an aerodynamic seal between a fixed aerofoil and a movable control surface.. . ... Airbus Operations Limited

06/01/17 / #20170152056

Aircraft fuel system

An aircraft fuel tank system including a fuel tank compartment for containing liquid fuel and having a float-activated valve arranged to become positively buoyant when immersed in liquid fuel so that the float moves up to a raised position which causes the valve to close and prevent liquid fuel from flowing out of the fuel tank compartment through the valve. The float is also arranged to move down to a lowered position in response to a level of the liquid fuel in the fuel tank compartment dropping, the movement of the float to the lowered position causing the valve to open and permit liquid fuel to flow out of the fuel tank compartment through the valve. ... Airbus Operations Limited

06/01/17 / #20170152016

Swing wing tip

An aircraft including a wing 10 having a fixed wing 12 and a swing wing tip device 14 pivotably mounted about a pivot 16 at the tip of the fixed wing, wherein the swing wing tip device 14 is configurable between a flight configuration for use during flight and a ground configuration for use during ground-based operations, where the span of the aircraft wing is reduced. The swing wing tip device 14 includes a receiving portion 48 arranged such that in the ground configuration, portions of the upper wing skin and lower wing skin of the fixed wing which are exposed in the flight configuration are at least partially received within the receiving portion 48 of the swing wing 14.. ... Airbus Operations Limited

06/01/17 / #20170152015

Dual-purpose locking and folding arrangement for an aircraft wing tip device

An aircraft (5) including a wing (7) having a wing tip device (1) configurable between: a flight configuration and a ground configuration in which the span of the wing (7) is reduced. The aircraft (5) further includes a lock (13) for locking the wing tip device (1) in the flight configuration, and an actuator (3) for unlocking the lock (13) and for subsequently actuating the wing tip device (1) to the ground configuration. ... Airbus Operations Limited

05/18/17 / #20170137119

Drive system for aircraft landing gear

A drive system for rotating a wheel of an aircraft landing gear. The drive system has a drive pinion and a motor operable to rotate the drive pinion via a drive path. ... Airbus Operations Limited

05/18/17 / #20170137111

Actuation assembly with a track and follower for use in moving a wing tip device on an aircraft wing

An aircraft wing having a wing tip device at the tip thereof is disclosed. The wing tip device is configurable between: a flight configuration for use during flight and a ground configuration for use during ground-based operations to reduce span. ... Airbus Operations Limited

05/18/17 / #20170137110

Articulation mechanism for forming a lock to hold a wing tip device in a ground configuration

An aircraft wing is disclosed having a wing tip device configurable between a flight configuration for use during flight and a ground configuration for use during ground-based operations to reduce the span. The wing includes an actuator and an actuation assembly having an articulation mechanism having a master bell crank connected to the actuator and a slave link connecting the master bell crank with the wing tip device. ... Airbus Operations Limited

05/11/17 / #20170129620

Aircraft fuel system

An aircraft fuel system has a fuel tank for containing liquid fuel, the fuel tank having a base. The aircraft fuel system also has a fuel pump for drawing liquid fuel from the fuel tank, a fuel conduit having a fuel outlet through which fuel is permitted to flow from the fuel tank, and a filter defining a filtered fuel space enclosing the fuel outlet. ... Airbus Operations Limited

05/11/17 / #20170129619

Aircraft fuel system

An aircraft fuel system having a fuel tank and a baffle dividing the fuel tank into a primary fuel containing space and a secondary fuel containing space. A fuel drain is provided through which fuel flows from the primary fuel containing space into the secondary fuel containing space. ... Airbus Operations Limited

05/04/17 / #20170123236

Communication apparatus

A communication apparatus includes an optical fiber along which radiation can be transmitted; an optical fiber grating formed within the optical fiber, the optical fiber grating having a structure, and configured to reflect radiation at a particular wavelength; and an instrument coupled to the grating and configured to controllably modify the structure of the grating, thereby changing the wavelength at which the grating reflects radiation. A communication system including the communication apparatus is also described, along with a method of communicating a signal.. ... Airbus Operations Limited

04/27/17 / #20170113807

Fuel system

A method and apparatus of control of fuel in a fuel tank including use of pneumatics employing a non-reactive gas. The aircraft fuel tank is handled and monitored by a pneumatic apparatus using oxygen depleted air from air separation module or auxiliary power unit of the aircraft. ... Airbus Operations Limited

04/27/17 / #20170113779

Aircraft with a strut-braced foldable wing

An aircraft (1) including a wing (5), the wing having an inner region (5a) and an outer region (5b), the inner and outer regions (5a, 5b) being connected by a hinge (11) defining a hinge line about which the outer region (5b) is foldable to reduce the span of the wing. The aircraft (1) includes an actuator (13) arranged to actuate the folding of the outer region (5b) of the wing with an actuation force. ... Airbus Operations Limited

04/20/17 / #20170109347

Soft schemas for flexible inter-system data modelling

A computer implemented method of defining a data model or schema, and subsequently reading files with said defined data model, the method including: identifying a minimum set of elements required to define the data model; defining the data model having a plurality of elements based on the identified minimum set of elements; for a first data source, or file, having a plurality of elements, and for each of the plurality of elements of the data model determining whether the element of the data model is present in the first data source, or file; and in the event that each element in the data model is identified as being present in the first data source or file, generating an output indicative of the first data source or file conforming to the determined data model.. . ... Airbus Operations Limited

04/20/17 / #20170106974

Drive system for aircraft landing gear

A method of engaging a drive system with a rotating wheel of an aircraft landing gear is disclosed. A motor is operated to apply torque to a pinion so the pinion rotates and moved from a neutral position to a contact position in which it contacts a rotating driven gear at an initial contact time, the rotating driven gear being mounted to a rotating wheel of an aircraft landing gear. ... Airbus Operations Limited

04/13/17 / #20170103590

Aircraft aerodynamic audit system for enhanced fuel efficiency

An aerodynamic audit system is provided for performing an audit process of an aircraft using a computing device via a network. An inspection module inspects at least a portion of the aircraft for locating and measuring any aerodynamic defects present by generating an inspection list having a predetermined inspection path. ... Airbus Operations Limited

04/13/17 / #20170101173

Drive system for aircraft landing gear

A method of engaging a drive system with a rotating wheel of an aircraft landing gear is disclosed. A motor is operated to rotate a pinion which is moved from a neutral position to a contact position in which it contacts a rotating driven gear at an initial contact time, the rotating driven gear being mounted to a rotating wheel of an aircraft landing gear; then after the initial contact time moving the pinion further to a meshing position where the pinion meshes with the driven gear. ... Airbus Operations Limited

04/06/17 / #20170096217

Roller gear for a drive system

A roller gear for use in a roller gear and sprocket configuration of a drive system is disclosed, particularly for use in a landing gear drive system of an aircraft. Alternative embodiments and, in particular, means for permitting removal and replacement of rollers and roller mounting pins in the roller gear are disclosed.. ... Airbus Operations Limited

03/30/17 / #20170088289

Method for detecting leaks in aircraft wings

A method and kit for detecting leaks in an aircraft wing (5) including: providing an aircraft wing structure having at an outboard end a wing tip (11) and at an inboard end a wing root (9) and at least one rib disposed between the wing root (9) and the wing tip (11), there being in a first rib section (13) of the wing (5) a first rib (19) closest to the wing root (9); placing a gas-impermeable bladder (43) over the wing root (9); forming a gas-tight circumferential seal between the bladder (43) and an outer surface of the wing (5) in the first rib section (13); introducing a gas into the aircraft wing (5); and sensing for leaks in the aircraft wing (5).. . ... Airbus Operations Limited

03/30/17 / #20170087943

Aircraft tire pressure monitoring system

A monitoring system, having a processor, provides pressure warnings associated with a tire of an aircraft when the aircraft is stationary, the processor operates in a maintenance mode and receives a first pressure measurement indicating a pressure of the tire; compares the first pressure measurement with a maintenance mode low pressure threshold, and causes the flight deck display to display a low pressure warning associated if the first pressure measurement is below the maintenance mode low pressure threshold. When the aircraft is in motion, the processor operates in a flight mode and receives a second pressure measurement indicating a pressure of the tire, compares the second pressure measurement with an abnormal pressure threshold which is lower than the maintenance mode low pressure threshold, and causes the flight deck display to display an abnormal pressure warning if the second pressure measurement is below the abnormal pressure threshold.. ... Airbus Operations Limited

03/09/17 / #20170067928

Determining rotational speed or direction of a body

A device for use in determining the rotational speed of a body. The device includes a sensor for detecting the strength of a magnetic field, and a body that is rotatable relative to the sensor about an axis. ... Airbus Operations Limited

03/09/17 / #20170066542

Pipe installation

A pipe installation including conductive first and second pipes installed in a fuel tank; and a fitting which connects the first and second pipes and enables fluid to flow through the pipes via a conduit in the fitting. The fitting is attached to the first or second pipe by a flexible joint which permits relative movement between the fitting and the first or second pipe. ... Airbus Operations Limited

03/09/17 / #20170066529

Drive system for landing gear and drive system control method

A method for controlling a separation between rotational axes of a pair of meshing gears is disclosed. A parameter indicative of a transmission error through the gears is measured and the separation is controlled, aiming to minimise variations in the measured signal. ... Airbus Operations Limited

03/09/17 / #20170066528

Wing tip device attachment apparatus and method

A wing tip device for attachment to a wing tip of a powered aircraft including: a first mounting formation, a second mounting formation spaced apart in a spanwise direction relative to the first mounting formation, a third mounting formation spaced apart in a chordwise direction relative to the first and second mounting formations, wherein each of the first, second and third mounting formations are configured for attachment to at least one of a wing spar and a wing rib, and, at least one of the mounting formations is configured to permit movement of a portion of the wing tip device in the spanwise direction relative to a portion of the wing tip.. . ... Airbus Operations Limited

03/02/17 / #20170058971

Landing gear with a bi-directional clutch

An aircraft landing gear including a wheel rotatable about an axle, a motor, and a bi-directional overrunning clutch, such as a roller or sprag clutch, operable to either connect the wheel with the motor or disconnect the wheel from the motor. The bi-directional clutch includes a ring-shaped overrunning track connected to the wheel, a ring-shaped drive track connected to the motor and concentrically aligned with the overrunning track, and a plurality of movable elements retained between the overrunning track and the drive track. ... Airbus Operations Limited

03/02/17 / #20170057667

Pump health monitoring

A pump health monitoring system for an aircraft fuel pump. The health monitoring system compares environmental data to a reference environment and captures pump data when the environmental data matches the reference environment. ... Airbus Operations Limited

02/23/17 / #20170050746

Lobed nut cap

The present invention proposes a cap having a collar portion with three or more contact regions arranged to contact the end of a fastener around which the collar portion is provided, the collar portion having a lobed shape in cross-section such that an outwardly projecting lobe extends between each neighbouring pair of contact regions. An advantage of this lobed arrangement is that the cap can tolerate relatively large manufacturing tolerances at the fastener end. ... Airbus Operations Limited

02/23/17 / #20170050725

Drive system for aircraft landing gear

A drive system for rotating a wheel of an aircraft landing gear is disclosed including a motor operable to rotate a drive pinion via a drive path; and a driven gear adapted to be attached to the wheel so as to be capable of rotating the wheel. The drive system has a drive configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the drive path. ... Airbus Operations Limited

02/23/17 / #20170050724

Drive system for aircraft landing gear

A drive system for rotating a wheel of an aircraft landing gear is disclosed including a motor operable to rotate a drive pinion via a drive path; and a driven gear adapted to be attached to the wheel so as to be capable of rotating the wheel. The drive system has a drive configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the drive path. ... Airbus Operations Limited

02/16/17 / #20170043864

An aircraft with a foldable wing tip device

An aircraft including a wing (1) and a wing tip device (6). The wing tip device (6) is moveable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. ... Airbus Operations Limited

02/02/17 / #20170029096

Drive system for aircraft landing gear

A drive system for an aircraft landing gear is described. The drive system includes a drive pinion, a drive shaft arranged to rotate the drive pinion about a drive axis, and a casing which rotatably supports the drive shaft. ... Airbus Operations Limited

02/02/17 / #20170029094

Aircraft wing with a wing tip device and a strut

An aircraft wing (1) has a wing tip device (3) joined thereto. The root (7) of the wing tip device (3) is joined to the tip of the wing (1) at a first connection (11). ... Airbus Operations Limited

02/02/17 / #20170029090

Control surface for an aircraft

The present application relates to a control surface for an aircraft. The control surface has a leading edge, a trailing edge, and a chord-line defined between the leading edge and the trailing edge. ... Airbus Operations Limited

02/02/17 / #20170029089

An aircraft comprising a foldable aerodynamic structure and a method of manufacturing a foldable aerodynamic structure for an aircraft

A method of manufacturing a foldable aerodynamic structure, such as a wing, for an aircraft. The wing (1) including an inner region (1) and an outer region (3) rotatable relative to the inner region between a flight configuration and a ground configuration. ... Airbus Operations Limited

02/02/17 / #20170028947

Vehicle fairing including an electrical routing

A vehicle fairing including an electrical routing for conducting power and/or control signals between spaced-apart components of a vehicle structure. The vehicle fairing includes an outer surface configured to form part of an outer surface of a vehicle body. ... Airbus Operations Limited

02/02/17 / #20170028670

Composite structure

A structure comprising a stack of composite plies of fiber-reinforced matrix material. The structure includes reinforcing inserts and holes. ... Airbus Operations Limited

01/26/17 / #20170023031

Actuator

An actuator comprising: an inner cylinder received in an outer cylinder and a piston received in the inner cylinder that extends from the inner cylinder and the outer cylinder, the piston being slideable relative to the inner cylinder and the outer cylinder in response to the application of fluid pressure to cause the piston to extend further from the inner cylinder and the outer cylinder; and an auxiliary drive mechanism operable to cause the inner cylinder to extend from the outer cylinder, wherein the piston moves together with the inner cylinder relative to the outer cylinder.. . ... Airbus Operations Limited

01/19/17 / #20170016792

Calibration of transducers

A load measuring sensor set on an aircraft is used under the control of a control unit on the aircraft. The load measuring sensor set is calibrated and there is calibration data associated with it. ... Airbus Operations Limited

01/19/17 / #20170016718

Machine tool control & measurement system

A computer numerical control machine tool with a machine head having one or more process tools. The machine head is moveable with respect to a workpiece. ... Airbus Operations Limited

01/19/17 / #20170015408

Aircraft landing gear

A aircraft landing gear for an aircraft, comprising a plurality of wheels, an electrically powered drive system comprising a drive motor arranged to drive at least one of the plurality of wheels, and an electrically powered braking system comprising a brake arranged to brake at least one of the plurality of wheels. A power supply unit is arranged to provide a supply of power to the electrically powered drive system, and also to the electrically powered braking system.. ... Airbus Operations Limited

01/19/17 / #20170015401

Trussed structure

A trussed structure comprising a frame and at least one strut, wherein the frame is of composite material and includes sockets which are integral with the frame. The invention also provides a process of making the trussed structures. ... Airbus Operations Limited

01/19/17 / #20170015151

Tire pressure sensor device

A tire pressure sensor device (122) for a wheel (112) of an aircraft (102) including a pressure sensor (124) for measuring the internal pressure of a tire, a temperature sensor (126) for measuring a temperature local to the tire (116), a memory unit (131) local to the tire for storing data, and a control unit (128) local to the tire arranged to record in the memory unit (131) data of the readings taken at intervals of time. The data recorded for each reading includes an indication of the time of the reading, the tire pressure and the temperature local to the tire. ... Airbus Operations Limited

01/12/17 / #20170008648

Servicing of landing gear shock absorbers

A method and portable apparatus for servicing a shock absorber on a landing gear assembly of an aircraft in a weight-on-wheels state is disclosed. The shock absorber includes at least one chamber containing both hydraulic fluid and a gas in fluid communication with each other. ... Airbus Operations Limited

01/12/17 / #20170008647

Landing gear shock absorber servicing

A method and apparatus for servicing a shock absorber on a landing gear assembly of an aircraft in a weight-on-wheels state is disclosed. The shock absorber includes at least one chamber containing both hydraulic fluid and a gas in fluid communication with each other. ... Airbus Operations Limited

01/12/17 / #20170008616

Aircraft wing with wing tip device

An aircraft wing assembly including: a wing having a wing box structure with an upper wing cover and a lower wing cover, and a wing tip device attached to the outboard end of the wing, the wing tip device including an upper cover and a lower cover, wherein a gap between opposing edges of the wing tip device lower cover and the lower wing cover is at least 5 mm, a seal assembly aerodynamically seals the gap, wherein the seal assembly includes a bridging component on an interior side of the gap, and a seal which fills the gap and is supported by the bridging component.. . ... Airbus Operations Limited

01/05/17 / #20170003157

Aircraft fuel measurement

A method of estimating a quantity of a liquid fuel in a fuel tank of an aircraft is disclosed. A surface of the fuel is illuminated with light so that the light is reflected or scattered by the surface of the fuel onto an array of sensors. ... Airbus Operations Limited

01/05/17 / #20170001720

Wheel and gear assembly

A wheel assembly is disclosed, in which a ring gear is movably mounted to the rim of the wheel, so that torque can be transmitted between wheel and rim, while the ring gear is isolated from deformations induced in the wheel rim.. . ... Airbus Operations Limited

01/05/17 / #20170001719

Landing gear drive system and method

A drive system for a landing gear is disclosed having a wheel rotatable about a wheel axis, the a drive assembly comprising an input gear rotatable about an input axis by an input shaft, an engagement assembly comprising a first intermediate gear meshed with the input gear and rotatable about a first intermediate axis by a first intermediate shaft, and a first drive pinion mounted on the first intermediate shaft and arranged to rotate in tandem with the first intermediate gear, the engagement assembly being pivotable about the input shaft relative to the drive assembly. A locking device is engageable to prevent rotation of the first intermediate gear about the first intermediate axis. ... Airbus Operations Limited

01/05/17 / #20170001718

Landing gear drive system and method

A drive system for an aircraft landing gear is disclosed having a wheel rotatable about a wheel axis, a driven gear arranged to be attached to the wheel and capable of rotating the wheel about the wheel axis, a drive train comprising an input gear rotatable by an input shaft, an intermediate gear meshed with the input gear and rotatable by an intermediate shaft, and a support member arranged to support the input shaft and intermediate shaft. The support member is arranged to pivot about the input shaft between a neutral configuration in which the drive train is disengaged from the driven gear and a driven configuration in which the drive train is engaged with the driven gear to enable the drive train to rotate the driven gear. ... Airbus Operations Limited








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