AIRBUS OPERATIONS LIMITED Patent applications |
Patent application number | Title | Published |
20160068504 | CYCLIC ORTHO ESTER FUEL ADDITIVE - The invention relates to liquid hydrocarbons containing cyclic ortho esters as dehydrating dehydrating icing inhibitors and to methods of using the compounds. The liquid hydrocarbons include fuels such aviation fuels, lubricants, hydraulic fluids and hydrocarbon solvents. | 03-10-2016 |
20150360765 | DOWNWARDLY EXTENDING WING TIP DEVICE - An aircraft including a wing, the end of the wing having a wing tip device, wherein the wing tip device includes a moveable region that is rotatable, about an axis of rotation extending out of the plane of the wing tip device, between: (i) a high-altitude cruise configuration in which the moveable region extends downwardly below the wing; and (ii) a ground-operating configuration in which the moveable region extends rearwardly behind the wing such that the ground clearance of the wing tip device is increased. | 12-17-2015 |
20150231835 | FIBRE ORIENTATION OPTIMISATION - The present application is concerned with methods of determining optimised fibre paths for complex composite components manufactured from multiple layers of composite material, particularly such components manufactured using an automated fibre placement (AFP) process. One aspect provides a method of determining an optimised fibre path for a geometrical feature of a composite component comprising a plurality of layers of composite material, each layer of composite material comprising a plurality of unidirectional fibres embedded in a matrix. The method includes manufacturing a test piece by: laying up a plurality of composite plies to form a planar charge, each composite ply comprising a plurality of unidirectional fibres embedded within a matrix; and shaping the planar charge by forming it over a mandrel using a hot drape forming process, the shaped charge having a shape corresponding to the geometrical feature of the composite component. Then, at each of one or more datum points, measuring a direction of the unidirectional fibres of one of the plurality of composite plies of the manufactured test piece with respect to a local coordinate system of said datum point. An optimised fibre path for the geometrical feature is determined based on the one or more measured fibre directions of said one of the plurality of composite plies. | 08-20-2015 |
20150219602 | RADIUS INSPECTION TOOLS - An ultrasonic inspection tool has a chassis with a two part body, an aperture for providing a clear line of sight between an array and a workpiece, and a series of feet for sliding along the workpiece. | 08-06-2015 |
20150122951 | MORPHING AEROFOIL - A morphing aerofoil comprising: a leading edge; a trailing edge; and upper and lower surfaces extending between the leading and trailing edges. An upper thermal actuation member is provided proximate the upper surface; and a lower thermal actuation member is provided proximate the lower surface opposite the upper thermal actuator. The upper and lower thermal actuation members have different thermal expansion coefficients and are positioned such that they cause the trailing edge to deflect when they expand or contract by different amounts in response to a change in ambient temperature, thereby changing a camber of the aerofoil. | 05-07-2015 |
20150122948 | AIRCRAFT FUEL TANK ARRANGEMENT - An aircraft fuel tank arrangement for the relief of a pressure differential between the interior of the aircraft fuel tank and the ambient atmosphere is provided. The aircraft fuel tank arrangement comprises a removable cartridge received within a cartridge-receiving body located at least partially in the fuel tank, said cartridge comprising a first burstable member operable to rupture in the presence of a pressure differential between the interior of the aircraft fuel tank and the ambient atmosphere which is greater than a predetermined pressure differential. | 05-07-2015 |
20150101403 | MEASURING THE VOLUME OF FLUID IN A VESSEL - A method and apparatus is disclosed for measuring the volume of fluid in a variable volume vessel. | 04-16-2015 |
20150090007 | METHOD FOR DETECTING LEAKS IN AIRCRAFT WINGS - A method is provided for detecting leaks in the wing of an aircraft prior to the fitting of the wing to the rest of the aircraft. A wing sealing assembly for sealing the wing of an aircraft so that the wing may be leak-tested is also described. | 04-02-2015 |
20150030380 | FASTENER RECEPTACLE STRIP - A structural assembly comprising a first component having a ramped surface, and a fastener assembly for fastening the first component to a second component, the fastener assembly including a receptacle strip of resiliently deformable material attached to the ramped surface of the first component so as to assume the contour of the ramped surface, and a plurality of fastener receptacles attached to the receptacle strip for receiving respective fasteners. Also, a method of fastening a first component to a second component using the fastener assembly. | 01-29-2015 |
20140341675 | INJECTABLE NUT CAP - The description provides a method of forming a seal around an end of a fastener protruding from a structure. The cap includes a cap body with a cavity; a sealing material inlet comprising an opening in the cap body; three or more ridges protruding from the cap body into the cavity; and three or more channels between the ridges. The method includes: installing the cap body over the end of the fastener so that it is enclosed within the cavity and contacted by the ridges; injecting sealing material into the cavity via the sealing material inlet so that the sealing material flows along the channels, fills the cavity, contacts the end of the fastener, and contacts the structure; and curing the sealing material to form the seal. | 11-20-2014 |
20140263833 | LANDING GEAR - In the retracted position, aircraft landing gear of an aircraft is supported by an uplock hook. The deployment of the aircraft landing gear includes the steps of supporting at least part of the weight of the landing gear by a releasable catch in the form of an uplock hook, applying a lifting force to the landing gear to remove at least part of the load sustained by the releasable catch, releasing the catch and effecting the downward movement of the landing gear to the deployed position. | 09-18-2014 |
20140263829 | APPARATUS FOR USE ON AN AIRCRAFT - An actuator is arranged to move an aircraft component such as a landing gear leg, flap or aileron between a first position and a second position, net load from external forces acting on the aircraft component tending to drive it towards the first position. The actuator comprises a threaded screw and a threaded nut. A main prime mover is configured to apply torque to the screw or nut acting in opposition to the net load under normal operating conditions. An emergency prime mover is configured to apply torque to the screw or nut acting in the same sense as the net load under emergency operating conditions in which the interface between the nut and the screw has become partially jammed to the extent that the component cannot be moved from the second position to the first position by operation of the net load alone. | 09-18-2014 |
20140263828 | TELESCOPIC STRUT - A telescopic strut for electrically connecting a fixed structure of an aircraft to a movable structure mounted to the fixed structure, wherein the strut is adapted to be mechanically connected to the fixed structure by its one end and to be mechanically connected to the movable structure by its opposite end, the strut comprising a plurality of telescopic elements and containing a helically coiled electrical cable, wherein the cable is adapted to move between retracted and extended positions with the telescoping of the strut. Also, a method of operating an aircraft having a movable structure mounted to a fixed structure, and one or more of the telescopic struts mechanically and electrically connected between the fixed and movable structures. | 09-18-2014 |
20140246539 | 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. One of the first drive pinion and the driven gear comprises a first sprocket and the other of the first drive pinion and the driven gear comprises a series of rollers arranged to form a ring. Each roller being rotatable about a roller axis at a fixed distance from an axis of rotation of the first drive pinion or driven gear, respectively. | 09-04-2014 |
20140245853 | 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. One of the first drive pinion and the driven gear comprises a first sprocket and the other of the first drive pinion and the driven gear comprises a series of rollers arranged to form a ring. Each roller being rotatable about a roller axis at a fixed distance from an axis of rotation of the first drive pinion or driven gear, respectively. | 09-04-2014 |
20140238610 | ASSEMBLING AND SHAPING LAMINATE PANEL - A method of assembling and shaping a laminate panel. An intermediate member is mounted on a lay-up table and a lay-up is assembling by laying a series of plies onto the intermediate member on the lay-up table. The intermediate member and the lay-up are then removed from the lay-up table and placed them on a shaped surface. The lay-up is then forced against the shaped surface, via the intermediate member, in a manner that modifies the shape of the lay-up to form a shaped laminate panel. Finally the shaped laminate panel is removed from the intermediate member. The lay-up table can thus support the flexible intermediate member during assembly, and can be relatively flat to enable the lay-up to assembled by an automated process. | 08-28-2014 |
20140238501 | AIRCRAFT INERTING SYSTEM - A method of controlling a flow rate of inerting gas introduced into a vented aircraft fuel tank, the method comprising: monitoring changes in a quantity of a fuel in the aircraft fuel tank; monitoring changes in the ambient air pressure external to the aircraft fuel tank; and actively controlling a flow rate of inerting gas, {dot over (m)}(I), introduced into the aircraft fuel tank based upon changes in the quantity of fuel in the fuel tank and changes in the ambient air pressure, p. Also, an aircraft including a vented fuel tank, a supply of inerting gas for rendering inert the fuel tank ullage, and a controller for performing the method. | 08-28-2014 |
20140231592 | LEADING EDGE RIB ASSEMBLY - An aircraft wing comprising a main wing element with a spar and a leading edge rib which is supported by the spar and extends forward of the spar; a high lift device which is movably mounted to the main wing element; and an actuation mechanism comprising a drive shaft and a gear train. The gear train comprising a drive cog which is carried by the drive shaft, an actuator cog which is coupled to the high lift device, and one or more intermediate cogs which are mounted to the rib and coupled in series with the drive cog and the actuator cog so as to transmit torque from the drive cog to the actuator cog which moves the high lift device between a retracted position and an extended position in which the high lift device increases the camber of the wing. The sizes of the cogs in the gear train are selected so that the drive shaft rotates at a higher rate than the high lift device. | 08-21-2014 |
20140209749 | FUEL PRESSURE SENSOR LINE RESERVOIR - The present invention concerns a device for use in an aircraft fuel pressure sensor line. More particularly, but not exclusively, this invention concerns a fuel pressure sensor line connecting an aircraft fuel pump to a pressure sensor. The invention also concerns a fuel pressure sensor line reservoir for use with a sensor line connecting an aircraft fuel pump to a pressure sensor. An aircraft fuel pump system comprises an aircraft fuel pump and a pressure sensor connected the aircraft fuel pump via a sensor line. The sensor line includes a reservoir located between the aircraft fuel pump and the pressure sensor. The reservoir acts to prevent liquid contacting the pressure switch when the fuel pump is not active. | 07-31-2014 |
20140208576 | FASTENER ASSEMBLY - A fastener assembly for mounting a component to a bracket attached to an inner surface of the skin of an aircraft wing such that the component is thermally and electrically isolated from the bracket is disclosed. The component and bracket each having mounting holes and the fastener assembly comprises a fastening element having a shaft to extend through said holes, first and second isolating members mountable on the shaft on either side of the bracket such that the bracket is sandwiched between said first and second isolating members and, a retaining element threadingly engageable with the shaft protruding through the second isolating member to clamp said first and second isolating members together against said bracket. One of the isolating members has a central portion that protrudes through said mounting hole in the bracket and the other isolating member comprises a recess to receive said central portion. | 07-31-2014 |
20140190007 | ELECTRICAL CONNECTOR - An aircraft pressure bulkhead electrical connector comprising a first connection terminal proximate at least one side of the electrical connector and a pressure seal arranged to maintain an applied air pressure differential across the electrical connector in use. | 07-10-2014 |
20140168219 | METHOD, APPARATUS AND COMPUTER PROGRAM PRODUCT FOR MODELLING THE NON-LINEAR STRUCTURAL RESPONSE OF A COMPONENT - A method, apparatus and computer program product for modeling the non-linear structural response of a component. The non-linear structural response is modeled using a two-step global-local finite element analysis method, which employs a linear global analysis step, a linear intermediate analysis step and a non-linear local analysis step. The boundary conditions applied in the intermediate step are derived in part from the linear global analysis and the boundary conditions applied in the local analysis are derived in part from the global and intermediate analyses. | 06-19-2014 |
20140158822 | SUPPORT ASSEMBLY - An assembly to support a wing leading or trailing edge device during deployment and retraction of the device includes a fixed support member attachable to the support structure of an aircraft wing, an intermediate link arm having one end pivotally mounted for rotation relative to the support member about a first axis and, a primary link arm having a first end pivotally mounted to the opposite end of the intermediate link arm for rotation relative to the intermediate link arm about a second axis. A second end of the primary link arm is for attachment to the device via a bearing element so that the device can move relative to the primary link arm in any direction when the intermediate and primary link arms rotate about the first and second axes, respectively, during deployment or retraction of the device from the aircraft wing. | 06-12-2014 |
20140158820 | AIRCRAFT LANDING GEAR - An aircraft landing gear comprising: a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un-sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a drive transmission mounted externally on the sprung part, or on the un-sprung part, of the main leg, the drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and an actuator for lifting the drive transmission into and out of driving engagement with the toothed ring and for maintaining the driving engagement as the landing gear deflects during a ground taxiing operation. Also, a method of operating the aircraft landing gear. | 06-12-2014 |
20140158294 | ORIENTATION OF INTERFACING PROJECTIONS - A method of joining a first component to a second component, the method comprising preparing the first component by forming an array of elongate projections on a bond surface of the component, each projection having a centreline, a tip, and a base. The centreline at the tip of each projection is oriented at an angle with respect to the normal to the bond surface at its base, and the angular orientation of the tip centrelines varies across the array of projections. Next, the first component and a flexible layer are brought together so as to embed the projections in the flexible layer before hardening the flexible layer to form the second component. Also, a joint so formed. | 06-12-2014 |
20140144005 | FASTENING DEVICE - The present invention concerns fastening devices. More particularly, but not exclusively, this invention concerns a fastening device suitable for fastening two or more separate items together. The invention provides a fastening device comprising: a first fixing element | 05-29-2014 |
20140138487 | RETRACTABLE INFILL PANEL FOR HIGH-LIFT DEVICE - The present invention provides an aircraft assembly with a fixed structure and a high-lift device. The fixed structure has a spar, a forward part which provides a foremost edge of an aircraft wing, and a lower part which provides a lower surface of the aircraft wing. A high-lift device is downwardly movable relative to the fixed structure from a stowed configuration to a deployed configuration. The high-lift device has a forward part which provides a foremost edge of the aircraft wing and a lower part which provides a lower surface of the aircraft wing. Downward movement of the high-lift device causes progressive opening of a lateral gap between the lower part of the high-lift device and the lower part of the fixed structure. A retractable infill panel is arranged to progressively extend from a retracted configuration to an extended configuration to fill the lateral gap. | 05-22-2014 |
20140138485 | MODULAR STRUCTURAL ASSEMBLY - A modular structural assembly to form part of an aircraft wing that has an outer skin and a plurality of stringers is disclosed. The assembly includes a plurality of panels, each panel having a portion that forms part of the outer skin and at least one stringer integrally formed with said portion. | 05-22-2014 |
20140138481 | DEPLOYMENT MECHANISM - The invention provides a deployment mechanism | 05-22-2014 |
20140131528 | MOUNT FOR CABLE HARNESS - The present application relates to a mount ( | 05-15-2014 |
20140117158 | AIRCRAFT WING WITH WING TIP DEVICE - An aircraft wing assembly comprising a wing ( | 05-01-2014 |
20140084516 | CURE TOOL - The invention provides a cure tool | 03-27-2014 |
20140053645 | FUEL QUANTITY MEASUREMENT - The present invention provides a method, device and apparatus for determining a quantity of fuel within a fuel tank having a drain valve penetrating a lower boundary of the fuel tank. The method includes inserting a pressure measurement probe having a pressure sensor into the drain valve to permit contact between the pressure sensor and fuel within the tank, and measuring a pressure of the fuel with the pressure sensor. The measured pressure is used to determine the quantity of fuel within the tank, e.g. by consulting look-up tables comprising data indicating the relationship between measured pressure and fuel quantity, or by using one or more conversion equations. | 02-27-2014 |
20140048651 | RIB FOR AN AIRCRAFT WING - A method of installing fuel system components in an aircraft wing is disclosed. An aircraft wing having a plurality of structural elements such as ribs which are joined together during assembly. The method includes the step of attaching at least some of the fuel system components to at least one of the structural elements prior to joining said structural elements together to assemble a wing. Also disclosed is a structural rib for an aircraft wing, configured to receive one or more fuel system components, and a combined structural rib and fuel system assembly. | 02-20-2014 |
20140048198 | FLANGED CAP FOR FORMING SEALED CAVITY AROUND FASTENER - A cap has a body portion forming a central cavity, and an annular flange which extends outwardly from the body portion. The body portion is deformable between a first configuration in which the annular flange is inclined upwardly, and a second configuration in which the annular flange is inclined downwardly. A method includes applying a quantity of sealant to the annular flange in the first configuration; fitting the cap over the end of the fastener so that the fastener is enclosed by the cap; and turning down the annular flange such that the cap assumes the second configuration in which an annular pocket is formed between the flange and the base, and the sealant material fills the annular pocket; and bonding the cap to the structure with the sealant material. | 02-20-2014 |
20140042276 | SLAT SUPPORT AND DEPLOYMENT COUPLING - A slat support and deployment apparatus comprising a master slat support and deployment assembly and a slave slat support and deployment assembly is disclosed. The master and the slave slat support and deployment assembly each include an arm having a free end attachable to the same slat at spaced locations along its length for deployment and retraction of said slat in a direction generally parallel to a wing in response to simultaneous movement of said arms. The master and the slave slat support assemblies each include a coupling for attaching said free end of each arm to a slat and the coupling that couples the free end of the arm of each slat support and deployment assembly to a slat is configured to allow movement of that slat relative to said free end of said arm of each slat support and deployment assembly during deployment and retraction of said slat. | 02-13-2014 |
20140023830 | METHOD OF MANUFACTURING A STRUCTURE - A method of manufacturing a structure, the method comprising: forming a panel assembly by bonding a stack of thickness control plies of composite material to a laminar composite panel, the stack of thickness control plies having a first edge proximate an edge of the laminar composite panel, a second edge opposite the first edge, and a ramp where the thickness of the stack of thickness control plies decreases towards the first or second edge; measuring the thickness of the laminate composite panel or the panel assembly; controlling the number of thickness control plies in accordance with the measured thickness; attaching a first component to the panel assembly, the first component having a surface which engages the laminar composite panel and a ramp which engages the ramp in the stack of thickness control plies; and attaching the laminar composite panel at or near its edge to a further component. | 01-23-2014 |
20140020826 | HEIGHT TAILORING OF INTERFACING PROJECTIONS - A method of joining a first component to a second component, the method comprising forming an array of projections extending from a bond surface of the first component, the projections having a plurality of different profiles; and embedding the array of projections in the second component formed of a plurality of laminate plies, wherein each projection profile is adapted to best transfer load into a respective one of the laminate plies. The resultant joint is able to transfer load more progressively between the two components leading to improved tensile strength. | 01-23-2014 |
20140007689 | ULTRASONIC WHEEL SCANNER - A scanner comprises a scanning array mounted within a rotatable assembly having a first wheel on a first side, a second wheel on a second side and a membrane forming a drum around the array wherein a load path is provided between the wheels to divert load from the membrane such that it can be made thinner. | 01-09-2014 |
20140002947 | AIRCRAFT BONDING NETWORK | 01-02-2014 |
20140000370 | INSPECTION OF COMPOSITE COMPONENTS | 01-02-2014 |
20130336795 | METHOD OF COUPLING AEROFOIL SURFACE STRUCTURES AND AN AEROFOIL ASSEMBLY - A method of attaching first and second aerofoil sections to each other is disclosed. The method comprises the steps of: positioning one aerofoil section in an initial assembly orientation with respect to the other aerofoil section so that hinge elements on each aerofoil section are in alignment with each other, inserting a hinge shaft through said aligned hinge elements to initially couple the aerofoil sections together whilst the aerofoil sections are in their initial assembly orientation; and rotating one aerofoil section relative to the other aerofoil section about a compound angle defined by the hinge shaft into a second orientation in which the aerofoil sections are in their final, assembled orientation relative to each other. An aerofoil assembly is also disclosed. | 12-19-2013 |
20130322982 | CAP FOR FORMING SEALED CAVITY AROUND FASTENER - A joint comprising: a structure; and a fastener passing through the structure. The cap has a body portion with an annular base terminating at an edge, the body portion forming an enclosure around an end of the fastener. The cap also has an annular flange which extends outwardly from the body portion and is set back from the edge of the base so as to define a pocket between the flange and the base. A sealant is provided in the pocket between the flange and the base, the sealant bonding the cap to the structure via a sealant/cap interface with the cap and a sealant/structure interface with the structure. The surface area of the sealant/cap interface is greater than the surface area of the sealant/structure interface. | 12-05-2013 |
20130320141 | SEAL ASSEMBLY FOR AN AIRCRAFT WING - A wing assembly for an aircraft comprising a spar, a wing cover and a rib; wherein the spar has a web portion and a flange portion joined by a radius corner; wherein a gap is formed at an interface between the spar, the wing cover and the rib; wherein the assembly further comprises a seal member which substantially covers the gap, and sealant provided between the seal member and the rib and/or the wing cover and/or the spar so as to seal the gap. Also a method for sealing a gap in an aircraft wing assembly. | 12-05-2013 |
20130316147 | STRINGER, AIRCRAFT WING PANEL ASSEMBLY, AND METHOD OF FORMING THEREOF - Embodiments of the invention relate to a stringer ( | 11-28-2013 |
20130313273 | AIRCRAFT FUEL TANK SYSTEM - An aircraft fuel tank system is disclosed in which a vent tank is provided with an additional ullage vent for use, in combination with an eternal flame barrier means, when refuelling. | 11-28-2013 |
20130301049 | SYSTEM FOR DETECTING MISALIGNMENT OF AN AERO SURFACE - A system for detecting misalignment of an aero surface relative to other aero surfaces during simultaneous deployment of said aero surfaces is disclosed. It comprises a generator configured to shine a laser through aligned apertures in a series of aero surfaces towards a reflector during deployment of said aero surfaces, a receptor to detect reflection of said laser from said reflector back through said apertures to the generator and, a controller operable to terminate further deployment of said aero surfaces in the event that no reflection is detected by said receptor, or if an actual time taken for the reflected beam of light to be detected by the receptor differs from a predetermined time. In a preferred embodiment the aero sufaces are slats extending from the leading edge of an aircraft wing. | 11-14-2013 |
20130285292 | MICROWAVE CURING OF COMPOSITE MATERIAL - A method of curing a composite material. A tool is heated using microwaves. At least a part of the composite material is shielded by reflecting microwaves away from the composite material with a shield. Heat is transferred from the tool through the shield to the composite material. The tool comprises a material which is sensitive to microwaves so that, when microwaves are incident upon the tool, some of the microwaves are absorbed by the microwave-sensitive material, thereby heating the tool. | 10-31-2013 |
20130269421 | SENSOR DEVICE AND METHOD FOR COMMUNICATING WITH SENSOR DEVICES - A sensor device for a fuel system, the sensor device comprising sensing means configured to sense a property of fuel within the fuel system, and transmitting means configured to wirelessly transmit a signal representative of the sensed fuel property to a remote receiver. Also a sensor device comprising a photo-diode which is operable to function as an antenna or part of an antenna for the device. Also a method for communicating with a plurality of sensor devices. | 10-17-2013 |
20130264002 | INTEGRAL STIFFENER - An integral composite wing spar ( | 10-10-2013 |
20130263934 | AIRCRAFT FUEL TANK VENT PROTECTOR - An aircraft fuel tank vent ( | 10-10-2013 |
20130240130 | MOULDING TOOL AND METHOD OF MANUFACTURING A PART - A tool set comprising: a moulding tool comprising a moulding surface and a mandrel recess in the moulding surface; a first mandrel configured to fit into the mandrel recess and form a first component; and a second mandrel configured to fit into the mandrel recess and form a second component which has a different shape or size to the first component. A method of manufacturing a part, the method comprising: arranging a set of components on one or more inner mould line tools; forming a layer around the inner mould line tool(s); fitting a pair of outer mould line tools on opposite sides of the inner mould line tool(s); moulding the part by compressing the layer and the components between the inner and outer mould line tools; and removing the inner mould line tool(s) from the part. | 09-19-2013 |
20130236038 | WIRELESS POWER TRANSMISSION - A method, apparatus and software are disclosed for wireless power transmission in which the power transmission frequency is optimised. | 09-12-2013 |
20130233082 | ULTRASONIC INSPECTION TOOL - An ultrasonic inspection probe comprising: a flexible ultrasonic array, a flexible coupling component arranged to ultrasonically couple the flexible ultrasonic array to a workpiece at a coupling boundary surface, a loading component arranged to apply a pressure to the coupling component to a surface opposite the coupling boundary surface to maintain contact between the coupling boundary surface and a workpiece. | 09-12-2013 |
20130220124 | FILTER FOR A PIPE - The invention provides a filter for a pipe, the filter comprising an attachment portion for attaching to the pipe, and a filter surface for presentation to and filtering of an oncoming flow of the pipe, wherein the filter surface has at least one pointed apex for protruding into the oncoming flow. The invention also provides a pipe for transporting an oncoming flow, wherein the pipe is provided with a filter surface across the cross-sectional area of the pipe and wherein the filter surface has at least one pointed apex protruding along the longitudinal axis of the pipe. The invention also provides an aircraft with such a filter or pipe and a method of filtering an oncoming flow of a pipe. | 08-29-2013 |
20130220024 | TEST APPARATUS FOR PROVIDING AXIAL STRESSES IN A STRUCTURE - The invention provides a test apparatus for providing axial stresses in a structure, comprising a first set of formations for abutting a first surface of the structure at a first plurality of locations, a second set of formations for abutting a second surface of the structure at a second plurality of locations, and a force actuator, and wherein each set of formations comprises at least three formations and wherein at least two formations in each set of formations are aligned with a notional alignment line along the structure and at least one formation in each set of formations is out of alignment along the structure with said notional alignment line, such that when the force actuator applies a force, loads are applied at different locations, causing the structure to bend biaxially and thereby providing biaxial stresses in the structure. | 08-29-2013 |
20130214100 | CLAMP BLOCK ASSEMBLY - A clamp block assembly for securing hydraulic pipes, the clamp block assembly comprising one or more unitary clamp blocks of deformable material each having a through hole for receiving a respective pipe, and a clamp adapted to apply a predetermined load around the clamp block(s). | 08-22-2013 |
20130214096 | SEAL ASSEMBLY - A seal assembly for closing an aperture in an aerodynamic surface of a structure, the seal assembly comprising: a track for attachment to the structure; and a retractable seal including a flexible substrate and a plurality of rods connected to the substrate, wherein at least one of the rods is mounted for running movement along the track, and the seal is moveable between an extended position and a retracted position by moving the at least one rod along the track accompanied by folding/unfolding of the seal substrate, and wherein the seal is biased to its extended position. | 08-22-2013 |
20130209854 | BATTERY CASE - A battery case for a power tool, comprising a body defining a cavity configured to receive a battery, a body surface of the battery case being formed to have a curved outward profile. | 08-15-2013 |
20130209764 | COMPOSITE LAMINATE WITH SELF-HEALING LAYER - A composite structure comprising: a first stack comprising a plurality of plies of composite material and at least one ply of self-healing material, the ply of self-healing material comprising a plurality of containers each containing a curable healing liquid; and a second stack comprising a plurality of plies of composite material, the stacks being joined together at a bond line. By placing a ply of self-healing material in one of the stacks (preferably relatively close to the bond line) the ply of self-healing material can resist the propagation of cracks between the first stack and the second stack. Preferably the global strength of the first stack is greater than the global strength of the second stack. | 08-15-2013 |
20130206926 | AIRCRAFT ELECTRICAL CABLE RACEWAY - An electrical cable raceway for an aircraft, the electrical cable raceway being formed at least in part from a ceramic material. | 08-15-2013 |
20130205190 | ONTOLOGY DRIVEN REQUIREMENTS ENGINEERING SYSTEM AND METHOD - A computer system comprising a processor and memory, wherein the system is programmed to provide a metamodel comprising a plurality of predefined fields relating to requirements engineering and ontological relationships between at least some of the predefined fields, and is programmed to prompt a user to enter information into the predefined fields in order to create a requirements specification. | 08-08-2013 |
20130193273 | WINGTIP FIN OF AN AIRCRAFT - A wingtip fin of an aircraft comprising an upstanding fin body, the fin body having an inboard face and an outboard face and a recess defined there within, a display screen assembly in the recess in the fin body, the display screen assembly comprising a translucent face, substantially flush with and forming at least part of the inboard face or the outboard face of the fin body, and a display screen arranged in the recess such that images displayed on the display screen are visible through the translucent face. | 08-01-2013 |
20130193268 | BLUFF BODY NOISE CONTROL - An aircraft noise-reduction apparatus comprise a flow-facing element ( | 08-01-2013 |
20130192892 | ELECTRICAL CABLE PROTECTOR - A cable protector for connection to an aircraft electrical cable raceway, comprising a flexible conductive body defining a conduit through which an electrical cable can pass and an electrically conductive connection arrangement configured to enable connection of the body of the protector to a raceway in an electrically conductive manner. | 08-01-2013 |
20130187012 | CABLE RETAINER - A device and method for securing a plurality of electrical conductors in a bundle. The device ( | 07-25-2013 |
20130183082 | PROFILE OF INTERFACING PROJECTIONS - A method of joining a first component to a second component, the method comprising preparing the first component by forming an array of projections extending from a bond surface of the first component, each projection having a base, a tapered tip and a tapered overhang beneath the tip, wherein the overhang has an undercut surface which is inclined and faces towards the local bond surface; bringing the components together so as to embed the projections in the second component; and hardening the second component after the array of projections has been embedded into it. Also, a joint so formed. | 07-18-2013 |
20130180312 | CALIBRATION BLOCK AND METHOD - A calibration block and method for sensitivity calibration. The calibration block has a curved calibration surface having a central axis and a surface for coupling to a transducer element of an angular scanning phased array ultrasonic testing scanner. The block is configured such that the surface positions the transducer such that its scanning axis is coaxial with the central axis of the curved calibration surface. | 07-18-2013 |
20130174663 | TOOL AND METHOD FOR MANIPULATING A TRANSDUCER ASSEMBLY - A tool for manipulating a transducer assembly. The tool had a shaft to space the transducer assembly from a handle end. The tool rotatably mounts the transducer assembly so that the transducer assembly can transmissively coupled to and follow an arcuate scanning path. The tool includes a guide member for following an edge of a component to be tested. | 07-11-2013 |
20130173828 | REMOTE DATA CONCENTRATOR - A remote data concentrator (RDC) for an avionics network, the RDC comprising an input/output interface (I/O) for connection to one or more input/output devices, and a network interface for connection to a remote processor, wherein the RDC is operable to provide communication between the input/output device(s) and the remote processor, and wherein the RDC further comprises a set of instructions for autonomously driving an output device connected to the I/O. Also, an avionics network including the RDC; an aircraft including the RDC; and a method of operating the RDC. | 07-04-2013 |
20130171852 | MULTI-INTERFACE - A line replaceable unit (LRU) for an integrated modular avionics (IMA) architecture, the LRU comprising at least one input/output interface and a plurality of connectors, wherein each connector includes at least one pin and each connector is adapted for connection to a single segregated wire route bundle, and wherein hardware of one interface is electrically connected within the LRU to one or more pins of each of at least two of the connectors. Also, an IMA architecture including the LRU, and an aircraft including the LRU or the IMA architecture. | 07-04-2013 |
20130169036 | AIRCRAFT POWER DISTRIBUTION NETWORK - An aircraft power distribution network comprising first and second galvanically isolated power bus bars, and first and second remote data concentrators (RDCs), each RDC having an input/output interface (I/O) and a power supply, the first RDC power supply being connected to the first power bus bar, the second RDC power supply being connected to the second power bus bar, an input/output device being connected to the I/O of the first RDC and to the I/O of the second RDC, each RDC being adapted to supply electrical power to the input/output device through its respective I/O, wherein each RDC includes a switch for isolating the input/output device, and the switches being operatively coupled such that electrical power cannot be supplied to the input/output device by both RDCs simultaneously. Also, a method of operating the network. | 07-04-2013 |
20130164489 | STIFFENER RUN-OUT - A panel assembly comprising: a panel ( | 06-27-2013 |
20130160295 | METHOD, APPARATUS AND COMPUTER PROGRAM PRODUCT FOR DETERMINING THE STRAIN INDUCED AT A SELECTED POINT IN A STIFFENED PANEL STRUCTURE IN RESPONSE TO A LOAD, TAKING INTO ACCOUNT ONE OR MORE OUT OF PLANE (OOP) EFFECTS - A method, apparatus and computer program product is disclosed for determining the strain induced at a selected point in a stiffened panel structure in response to a load, taking into account one or more out of plane (OOP) effects. | 06-27-2013 |
20130153802 | SHAFT LOCKING DEVICE - The present application relates to a shaft locking device. The device has an locking element configured to be mounted on a shaft in a first position so that the locking element indicates the angular position of the shaft. The locking element is also configured to be mounted on a shaft in a second position so that the locking element is locatable against a stop to prevent rotation of the shaft. The present application also relates to a device for determining the angular position of a shaft, a valve assembly and an actuating unit for a valve. | 06-20-2013 |
20130153713 | TRANSLATING CABLE DEVICE SEALING - An aircraft wing assembly, comprising a wing having a fixed leading edge, a slat mounted for movement between a retracted position and an extended position with respect to the fixed leading edge, and a translating cable device for electrically connecting the slat to the wing and having a strut coupled at one end to the slat, the fixed leading edge having an aperture to accommodate the strut, and a seal assembly for sealing between the strut and the aperture. | 06-20-2013 |
20130153712 | AIRCRAFT WING ASSEMBLY - An aircraft wing assembly, comprising a wing having a fixed leading edge, a slat mounted upon a slat deployment mechanism for moving the slat between a retracted position and an extended position with respect to the fixed leading edge, the fixed leading edge having an aperture to accommodate the slat deployment mechanism, and a closing plate mounted off the slat deployment mechanism for closing a gap between a lower trailing edge of the slat and a lower edge of the aperture when the slat is retracted. The closing plate can include a first portion and a second portion, and a hinge connecting the first and the second portions. The closing plate can include a plurality of integrally formed spacer elements for positioning the closing plate with respect to the slat deployment mechanism. Also, a method of removing an access panel in an aircraft wing assembly. | 06-20-2013 |
20130152398 | HOLE DEPTH MEASUREMENT DEVICE - A plastic hand-held measuring device, can measure the depth of a hole or bore or the length of a fixing, having particular application with composite aircraft components. A hook or tang, at the end of an elongate portion, can engage with the far end of the bore allowing the depth ascertained from a first measurement scale. A first formation can engage with a fixing, allowing measurement of the length of the fixing from a second measurement scale. A plastic slide can abut against a portion of the component to be measured and indicate the distance on the measurement scale that corresponds to the length of the dimension being measured. The slide may be arranged to engage with successive indexed formations along the length of the device, so that it is inclined to remain in a position corresponding to an indexed formation. | 06-20-2013 |
20130146712 | APPARATUS FOR ATTACHMENT OF WING PANELS - A shroud panel ( | 06-13-2013 |
20130146711 | AIRCRAFT RIB ASSEMBLY - A spoiler rib assembly ( | 06-13-2013 |
20130146707 | METHOD AND APPARATUS FOR PROVIDING POWER IN AN AIRCRAFT TO ONE OR MORE AIRCRAFT SYSTEMS - A method and apparatus is disclosed in which an aircraft system such as the landing gear system or braking system is operated at least partially under power provided by a generator driven by the wheels of the landing gear. | 06-13-2013 |
20130139421 | WINGTIP FIN OF AN AIRCRAFT - A wingtip fin of an aircraft comprising an upstanding fin body, the fin body having an inboard face and an outboard face, a sign assembly in the fin body, the assembly comprising a translucent, graphic bearing face, substantially flush with and forming at least part of the inboard face or the outboard face of the fin body, a recess in the fin body behind the graphic-bearing face, and a light source arranged in the recess to illuminate the graphic-bearing face from inside the fin body. | 06-06-2013 |
20130129526 | WRINKLE CONTROL METHOD AND TOOL THEREFOR - A method for forming a laminate component, the method comprising the steps of: a) providing a tool having a moulding surface; b) arranging a stack of ply layers on the moulding surface of the tool; and c) moulding the stack of ply layers over the moulding surface in a moulding process, wherein the tool has a wrinkle control feature in its moulding surface for managing the development of wrinkle in the ply layers during the moulding process, and wherein the wrinkle control feature cooperates with the stack of ply layers during the moulding process to produce a local surface undulation in a nominal surface of the laminate component nearest the tool to either prevent wrinkling in the ply layers or initiate wrinkling in one or more of the ply layers at a predetermined location. Also, a tool having a wrinkle control feature, and a laminate component so formed. | 05-23-2013 |
20130128914 | THERMAL TEST APPARATUS AND METHOD - Thermal test apparatus comprising a specimen supported by a fixture, a thermal shroud comprising a flexible insulating fabric forming an enclosure around at least a portion of the specimen, and a temperature controlled air supply connected to an opening formed in the enclosure for delivering a supply of temperature controlled air into the enclosure. Also, a method of conducting a thermal test. | 05-23-2013 |
20130127152 | AIRCRAFT TOOL - The invention relates to the installation of pipes, for example aircraft fuel pipes and fuel systems, in an aircraft. The invention further relates to guidance tool for restricting the potential angular misalignment between the axial centrelines of a pipe end and corresponding socket arrangement during a pipe installation process. The guidance tool may comprise a sleeve and a clamp. The clamp may be configured to removably engage the sleeve with an external surface of a pipe end, such that at least part of the sleeve and pipe end may be inserted into a corresponding socket arrangement. | 05-23-2013 |
20130126670 | DEPLOYMENT SYSTEM - A deployment mechanism is disclosed for deploying a deployable member supported on tracks relative to a base member and comprising a brake system operable in response to relative skewing of the tracks. | 05-23-2013 |
20130125375 | FASTENER JOINT WITH SEALING GASKET - A joint comprising: a first component having a face and a bore defined by a bore wall; a second component; a fastener joining the first component to the second component, the fastener comprising a head and a shaft protruding from the head; and a polysulphide gasket comprising a ring which is compressed between the head of the fastener and the face of the first component; and a collar between the shaft of the fastener and the bore wall. The gasket comprises a ring of sealing material surrounding a hole for receiving a fastener, the sealing material comprising an at least partially cured polysulphide sealant. The gasket has a region of increased thickness positioned towards the inner periphery of the ring which flows to form the collar. | 05-23-2013 |
20130125374 | FASTENER JOINT WITH SEALING GASKET - A joint comprising: a first component having a face and a bore defined by a bore wall; a second component; a fastener joining the first component to the second component, the fastener comprising a head and a shaft protruding from the head; and a polysulphide gasket comprising a ring which is compressed between the head of the fastener and the face of the first component; and a collar between the shaft of the fastener and the bore wall. The gasket comprises a ring of sealing material surrounding a hole for receiving a fastener, the sealing material comprising an at least partially cured polysulphide sealant. The gasket has a region of increased thickness positioned towards the inner periphery of the ring which flows to form the collar. | 05-23-2013 |
20130124107 | FUEL TANK CONTAMINANT PREDICTION - A method for predicting a quantity of a contaminant in a fuel tank at the end of a time period, the method comprising the steps of: determining a quantity of the contaminant in the fuel tank at the start of the time period; determining at least one operating condition of the fuel tank during the time period; using information relating to the at least one operating condition of the fuel tank to generate a predicted quantity of the contaminant accumulated in the fuel tank during the time period; and calculating, based upon the quantity of the contaminant at the start of the time period and the predicted quantity of the contaminant accumulated during the time period, a predicted quantity of the contaminant at the end of a time period. | 05-16-2013 |
20130119202 | REFUEL CONTROL SYSTEM AND METHOD OF REFUELLING - The invention provides a refuel control system for controlling refuel of at least one tank ( | 05-16-2013 |
20130118612 | CLACK VALVE ASSEMBLY - A clack valve assembly comprising: a valve seat comprising an opening; a bearing comprising a recess with a base, a mouth, and a pair of side walls between the base and the mouth; a lid comprising a lid plate and a shaft, the shaft being received in the recess of the bearing; and a shaft retaining member which closes the mouth of the recess in the bearing, thus retaining the shaft within the recess. The shaft and the lid plate are integrally formed elements of a single part. The shaft can rotate within the recess to enable the lid to rotate from a closed position in which the lid engages the valve seat and covers the opening, to an open position in which the lid lifts away from the valve seat enabling fluid to flow through the opening in the valve seat. | 05-16-2013 |
20130108828 | AIRCRAFT PROTECTION DEVICE | 05-02-2013 |
20130104375 | PLAIN JOURNAL BEARING | 05-02-2013 |
20130092267 | FUEL TANK INSTALLATION - A fuel tank installation comprising: a fuel tank for holding fuel, the fuel tank comprising a fuel tank wall formed with a hole; a fuel pump assembly fitted into the hole in the fuel tank wall with an inner part of the fuel pump assembly protruding from an inner side of the hole and an outer part of the fuel pump assembly protruding from an outer side of the hole; a cage surrounding the outer part of the fuel pump assembly; and a mounting piece which attaches both the cage and the fuel pump assembly to the fuel tank wall. | 04-18-2013 |
20130091955 | METHOD AND APPARATUS FOR MEASURING RESIDUAL STRESSES IN A COMPONENT - A process for measuring the through stress distribution ( | 04-18-2013 |
20130087662 | FLAP SUPPORT - A flap support structure for an aircraft wing having a trailing edge flap, the flap support structure comprising: a flap support beam including an aerodynamic fairing; and a drive unit including a universal support structure which rotatably receives a drive shaft connected to a drive arm for moving the trailing edge flap, wherein the universal support structure also forms part of the flap support beam and supports the aerodynamic fairing. | 04-11-2013 |
20130080137 | CONVERSION METHOD AND SYSTEM - A computer-implemented method for converting a representation of a system into a behaviour model of the system is provided. The method can be used to convert a schematic diagram into a behavioural model. | 03-28-2013 |
20130076767 | INSTALLATION OPTIMISATION - A computer-implemented method for determining a configuration of a plurality of components in a systems installation which satisfies one or more constraints. | 03-28-2013 |
20130067882 | BLEED AIR DUCT JOINT INSULATION MEANS - A bleed air duct joint insulation means is disclosed in which a leak vent comprises valve means. | 03-21-2013 |
20130067746 | METHOD AND DEVICE FOR REMOVING A SLEEVE FROM A BORE - A method of removing a metal sleeve from a bore formed in one or more elements is disclosed. The sleeve may be a cold-expanded sleeve secured within the bore by means of an interference fit. The method includes removing material from the internal surface of the sleeve by means of cutting along a line to a depth less than the thickness of the sleeve, and subsequently urging the sleeve from the bore. | 03-21-2013 |
20130062467 | AIRCRAFT WING BOX JOINT - An aircraft wing box spanwise joint, comprising a rib having a web, and a pair of rib fittings joined together, each rib fitting forming a closed loop around the periphery of the rib, wherein the rib is integrally formed with one of the rib fittings. Also, an aircraft wing including two or more of the joints. Also, a method of forming an aircraft wing box spanwise joint, the method comprising forming a pair of rib fittings, wherein one of the rib fittings is integrally formed with a rib having a web, each rib fitting forming a closed loop around the periphery of the rib, bringing the rib fittings together, and joining the rib fittings together. | 03-14-2013 |
20130048187 | CURABLE ASSEMBLY AND A FILLER COMPONENT - A curable assembly which upon the application of curing conditions will form a completed component or part component comprises two pieces of composite fibre-reinforced, resin matrix material, with filler component of relatively rigid material arranged therebetween. The intermediate component is arranged to be secured between the two pieces. The filler component has a body with first and second opposing surface profiles. The filler component can be used to transmit or react a consolidating load during curing. | 02-28-2013 |
20130045075 | FITTING, CRANE HOOK, AND CRANE HOOK ASSEMBLY - A method of lifting an aircraft at a lifting location, the method comprising: securing a fitting to the aircraft when the aircraft is at the lifting location; engaging the fitting with a crane hook; transmitting lifting load from the crane hook to the aircraft via the fitting; and removing the fitting from the aircraft. | 02-21-2013 |
20130037655 | METHOD OF SEALING A GAP - A method of sealing a gap between first and second aerodynamic surfaces. The width of the gap between the two surfaces is measured to obtain a gap measurement. The width of a seal member is pre-formed in accordance with the gap measurement. The seal member is fitted into the gap such that the seal member is substantially flush with the first and second aerodynamic surfaces. Apparatus for performing the method is also described. The apparatus comprising: a metrology device adapted to measure the width of the gap between the first and second aerodynamic surfaces; a seal member dispenser for dispensing a seal member; and a cutter adapted to cut the seal member to size in accordance with the measurements obtained by the metrology device. | 02-14-2013 |
20130034684 | COMPOSITE STRUCTURE - A structure comprising a plurality of plies of fibre-reinforced composite material, each ply having a ply orientation defined by a principal stiffness direction of the ply. The structure has a first region and a second region, each region comprising N1 primary plies, N4 cross plies with a ply orientation substantially perpendicular to the primary plies, N2 positive-angled bias plies with a ply orientation at a positive acute angle to the primary plies, and N3 negative-angled bias plies with a ply orientation substantially perpendicular to the positive-angled bias plies. The ply orientation of the primary plies in each region is more closely aligned with a primary axis of the structure than the cross plies or the bias plies. N1=N4 in the first region but not in the second N region, and N2=N3 in the second region but not in the first region. In each of the two regions, one ply set is balanced and the other ply set is un-balanced. This provides a compromise between the advantages of using un-balanced ply sets, for instance to provide bending torsion coupling, and the disadvantage that un-balanced ply sets can introduce thermally induced distortion during manufacture. | 02-07-2013 |
20130027835 | JOINT - A joint with a first component; a second component; and an electrical assembly which provides an electrical pathway between the first and second components with an electrical resistance between 100 kΩ and 10 MΩ. The electrical assembly comprises a bonding lead; and a pair of connection assemblies each connecting the bonding lead to a respective one of the components. Each connection assembly comprises: a fastener with a shaft which passes through a hole in the component and a hole in the bonding lead, the hole in the bonding lead passing between an inner face of the bonding lead which faces towards the component and an outer face of the bonding lead which faces away from the component, and a washer which is carried by the shaft of the fastener and engages the component and the inner face of the bonding lead. Each washer provides the path of least electrical resistance between the bonding lead and a respective one of the components, each said path having an electrical resistance between 50 kΩ and 5 MΩ. | 01-31-2013 |
20130025963 | AIR CONDITIONING SYSTEM EXHAUST SILENCER FOR AN AIRCRAFT - An exhaust silencer for the air conditioning system of an aircraft is disclosed. | 01-31-2013 |
20130025219 | AIRCRAFT GLAZING ATTACHMENT - A glazing unit is provided in which a two part bush is provided such that relative movement between a fastener, a glazing component and a wing skin is permitted, thus avoiding stress concentrations and lowering risk of damage in use. | 01-31-2013 |
20130009000 | METHOD AND APPARATUS FOR OPERATING AN AIRCRAFT LANDING SYSTEM - A method and apparatus is disclosed in which an aircraft landing system is at least partly primarily powered by power provided by a ram air turbine (RAT). | 01-10-2013 |
20130001893 | SPLIT GROMMET ASSEMBLY - A split grommet assembly comprising a grommet and a clamping ring. The grommet has a body portion with a peripheral edge and a sealing groove round the peripheral edge of the body portion. The grommet also has a gland portion with a peripheral edge, and a hole passing through the body and gland portions. The body and gland portions are each split along a split line which runs from the hole to their peripheral edges. The clamping ring encircles the peripheral edge of the gland portion and can be opened to permit an elongate object to be fitted into the hole via the split line, and closed to apply a compressive load to the peripheral edge of the gland portion which resists opening of the body along the split line. | 01-03-2013 |
20130001459 | VALVE APPARATUS - Valve apparatus for converting a direct water drain valve into an indirect water drain valve, the direct water drain valve having at least one drain conduit, the apparatus including: a part having an inner volume and a fluid transfer aperture for fluid to enter the inner volume, the part being arranged to be connected, directly or indirectly, to the direct water drain valve so as to convert at least some of the inner volume into a substantially fluid-tight passageway between the fluid transfer aperture and the at least one drain conduit of the direct water drain valve. | 01-03-2013 |
20130000142 | FUEL SYSTEM AND METHOD - A fuel system comprising a fuel tank, a vent tank having a duct open to the ambient atmosphere, a first vent line fluidically connecting the fuel tank ullage to the vent tank, a gas drying system including a pump and a dehumidifying device disposed within the vent tank, and a second vent line fluidically connecting a dry gas outlet of the dehumidifying device to the ullage, wherein the pump is operable to maintain a higher pressure within the ullage than in the vent tank so as to drive vapour rich gas from the ullage into the vent tank via the first vent line. Also, a method of operating the fuel system and a method of retro-fitting the gas drying system in an existing fuel system. The gas drying system may optionally be a gas drying/inerting system. | 01-03-2013 |
20120324707 | PIVOT JOINT ASSEMBLY - A pivot joint assembly has a first part with a hole. A pivot pin passes through the hole. A second part is carried by the pivot pin to be rotatable relative to the first part. A bush has an annular sleeve with an inner face engaging the pivot pin and an outer face engaging a bore wall of the first part. A sealing ring between the bush and the first part. The sealing ring has a body attached to the first part, and a sealing member extending away from the body in a radial direction to a sealing lip which engages the bush without being attached thereto. The sealing member is resiliently compressed to urge the sealing lip towards the bush to maintain engagement with the bush in the event that the bush moves away from the body in the radial direction. | 12-27-2012 |
20120312022 | COALESCING FILTER - A fuel system comprising a liquid fuel tank, an engine, and a coalescing filter adapted to separate water from fuel, the filter having an inlet fluidically connected to the fuel tank, a first outlet fluidically connected to a fuel feed system for the engine, and a second outlet fluidically connected to the fuel tank, wherein the coalescing filter is adapted to discharge fuel filtrate from the second outlet and filtrand from the first outlet. Also, a method of removing water or ice from a fuel tank, the method comprising directing a flow of fuel from a fuel tank to a coalescing filter adapted to separate water from fuel, discharging filtrand from a first outlet of the coalescing filter to a fuel feed system for consumption by an engine, and discharging fuel filtrate from a second outlet of the coalescing filter and returning the fuel filtrate to the fuel tank. | 12-13-2012 |
20120292828 | METHOD OF MANUFACTURING COMPOSITE MATERIAL - Disclosed is a method of manufacturing a composite sheet. The method comprises (a) irradiating a sheet of fibres and a matrix film at an irradiation zone with a plasma at substantially atmospheric pressure, and (b) impregnating the sheet of fibres with the matrix at an adhesion zone. The processes (a) and (b) are performed simultaneously, and the matrix film is irradiated with a plasma at said irradiation zone after being unwound from a roller and prior to entering said adhesion zone. | 11-22-2012 |
20120292452 | AIRCRAFT WING ASSEMBLY - An aircraft wing assembly, comprising: a fixed wing portion; a first and second flight control surfaces; a first and second actuators operatively coupled to the first and second flight control surfaces for moving respective first and second flight control surfaces with respect to the fixed wing portion; a control system operatively coupled to the first and second actuators for controlling movement of the first and second flight control surfaces; and a third actuator selectively engaged with the second flight control surface for engaging and moving the second flight control surface out of a path of movement of the first flight control surface only in the event of a failure in the second actuator or its control, so as to avoid direct contact between the first and second flight control surfaces. | 11-22-2012 |
20120279395 | FUEL SYSTEM INERTING - A fuel system comprising a fuel tank, a catalytic inerting device for producing oxygen depleted air (ODA) by reaction of fuel vapour from the fuel tank with air, and a separator device for separating carbon dioxide from the ODA gas before feeding the carbon dioxide depleted ODA gas to the fuel tank so as to render the fuel tank ullage atmosphere inert. Also, a method of reducing the carbon dioxide content of oxygen depleted air (ODA) produced by a catalytic inerting device for inerting a fuel tank ullage atmosphere, the method comprising separating carbon dioxide from the ODA gas before feeding the carbon dioxide depleted ODA gas to the fuel tank. The system may be installed in an aircraft. | 11-08-2012 |
20120273995 | METHOD OF SEALING A GAP - A sealing unit for sealing a gap between a pair of surfaces includes a nozzle for injecting sealant into the gap, rollers, an endless track round the rollers, and a curing device. The sealing unit is moved along the length of the gap. A sealant is injected into the gap from the nozzle and the track is rotated around the rollers as they are moved along the length of the gap. The track is pressed onto first and second surfaces so the sealant in the gap is constrained by the track to lie substantially flush with the first and second surfaces. The sealing unit is moved along the length of the gap at a rate such that the sealant becomes sufficiently cured when it is in contact with the track so that the track can be peeled away from the sealant as the track rotates round the second roller. | 11-01-2012 |
20120273619 | AIRCRAFT AERIAL REFUELLING SYSTEM - An aircraft aerial refueling system including at least one pressure controlled fuel pump having a control system adapted to regulate the pump outlet fuel pressure using an outlet fuel pressure signal as control feedback. Also, methods of operating an aircraft aerial refueling system. | 11-01-2012 |
20120248251 | CONDUIT PROTECTION SYSTEM AND METHOD - A conduit protection system, comprising: a conduit for carrying a fluid; a sealed vessel surrounding the conduit along a protected zone of the conduit; and a valve moveable between a first position for obstructing fluid flow through the protected zone of the conduit and a second position for enabling fluid flow through the protected zone of the conduit, wherein the valve is biased to the first position, and wherein the valve is fluidically coupled to the sealed vessel such that a positive pressure within the sealed vessel is operable to move the valve to the second position against the bias. Also, a method for protecting a fluid carrying conduit. | 10-04-2012 |
20120217347 | AIRCRAFT FUEL TANK ACCESS COVER AND AN AIRCRAFT FUEL TANK - An aircraft fuel tank access cover comprises an inner door, an outer door and a clamping arrangement for clamping the doors together about an access aperture in the skin of the fuel tank. The clamping arrangement comprises a bolt in-moulded in a generally central part of the inner door and or external nut. The doors have reinforcing rib arrangements to spread the clamping load to the peripheral edges thereof. | 08-30-2012 |
20120213640 | COMPOSITE STRUCTURE - A composite structure has a first section, a second section, and a curved corner joining the first and second sections. The structure has a stack of fibre-reinforced plies including first and second external plies which run from the first section into the second section on an inside and an outside of the corner, respectively. A discontinuous first internal ply is sandwiched between the first and second external plies so that more of the first internal ply is located within the first section than within the second section. A second internal ply is sandwiched between the first and second external plies. The fibres of the first internal ply run at an angle θ to the fibres of the second internal ply. In some embodiments the angle θ is greater than 3° but less than 20°. In one embodiment the angle θ is between 35° and 42°. | 08-23-2012 |
20120211607 | COMPOSITE STRUCTURE - A composite structure has first and second sections, and a curved corner joining the first and second sections. The structure includes a stack of fibre-reinforced plies. First and second external plies run from the first section into the second section round an inside and an outside of the corner, respectively. First and second internal plies are sandwiched between the first and second external plies, and run from the first section into the second section round the corner. The first internal fly is dropped off inside the second section. The second internal ply is dropped off inside the first section. The structure has an increased thickness where the first and second internal plies overlap. | 08-23-2012 |
20120205490 | AIRCRAFT HORIZONTAL STABILISER FITTED WITH LEADING-EDGE STRAKE - An adjustable, or all-moving, horizontal stabiliser for an aircraft, the stabiliser having a leading edge, a trailing edge, a root and a tip, and a strake fixed with respect to the stabiliser and attached to, or integrally formed with, the stabiliser leading edge adjacent the root. | 08-16-2012 |
20120195056 | AIRCRAFT LIGHTING DEVICE - An aircraft wingtip device comprises illumination means arranged to project light onto interior and exterior surfaces of the wingtip device. | 08-02-2012 |
20120193479 | AIRCRAFT FUEL SYSTEM - An aircraft fuel system has a fuel tank with first and second cells separated by one or more baffles. A venting system reduces pressure difference between the interior and exterior of the fuel tank, and an inerting system supplies oxygen-depleted gas to the fuel tank. The baffles permit the flow of fluid between the cells. The venting system has one or more vent nozzles within the fuel tank and in fluid communication with one or more vent ports. The inerting system has one or more inerting nozzles for injecting oxygen-depleted gas into the first and second cells. A control device varies the ratio between the total flow rates of the oxygen-depleted gas into the first and second cells. | 08-02-2012 |
20120193120 | CABLE RACEWAY - A cable raceway assembly is provided having channel sections with protrusions and clamp insertable with recesses engageable with the protrusions provide a snap-fit ratchet-type engagement. | 08-02-2012 |
20120187253 | LEADING EDGE DEVICE FOR AN AIRCRAFT - A leading edge section of an aircraft wing comprises a main wing body portion, a droop nose high-lift device mounted adjacent to the fore region of the main wing body portion, and a door. The droop nose high-lift device is moveable between a stowed position and a first deployed position. When the droop nose high-lift device is in the first deployed position and the door is in an open position, an air flow region is exposed such that, during use, air flows through the air flow region from the lower surface to the wing upper surface of the wing. The door is also arranged to be moved during flight to control the amount of airflow through said air flow region. | 07-26-2012 |
20120181730 | CUTTING TOOL AND METHOD - A cutting tool has: a rotatable hollow tube with an inlet at a distal end of the tube and a cutting edge at the perimeter of the inlet, the tube being arranged so as to rotate when in use so as to cut a work piece with the cutting edge; and an auger housed within the hollow tube, the auger being arranged so as to rotate when in use so as to feed cut material from the inlet along the hollow tube, wherein a distal end of the auger is set back from the cutting edge of the tube. | 07-19-2012 |
20120168567 | ELECTRICAL POWER TRANSFER ASSEMBLY - An assembly for an aircraft including a first structure mounted to a second structure, and a power transfer assembly electrically connecting the first and second structures. The first structure is movable relative to the second structure between a retracted and an extended position. The power transfer assembly includes a housing, a spool mounted for rotation relative to the housing and biased to rotate in a first direction, and an electrical cable adapted to be wound around the spool when the spool rotates, such that movement of the first structure from its retracted to its extended position causes the cable to be unwound from the spool by rotation of the spool in a second direction opposite the first. Also, a method of electrically connecting the first and second structures. The invention may be applied to an aircraft wing to electrically connect a leading edge slat to a fixed aerofoil portion. | 07-05-2012 |
20120154177 | METHOD OF MONITORING AIRCRAFT BRAKE PERFORMANCE AND APPARATUS FOR PERFORMING SUCH A METHOD - A brake performance monitoring system operates by an energy differential calculated from brake demand energy and energy absorbed during a braking operation. A significant differential would be reported as a possible problem with the braking system. | 06-21-2012 |
20120153075 | AIRCRAFT LANDING GEAR - An aircraft landing gear comprising: a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un-sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a drive transmission mounted externally on the sprung part, or on the un-sprung part, of the main leg, the drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and an actuator for lifting the drive transmission into and out of driving engagement with the toothed ring and for maintaining the driving engagement as the landing gear deflects during a ground taxiing operation. Also, a method of operating the aircraft landing gear. | 06-21-2012 |
20120134679 | DATA TRANSMISSION NETWORK - A data transmission network comprising: a base comprising: a base light source and a base light detector; a plurality of nodes, each node comprising a node light source and a node light detector; and a plurality of optical fibres arranged to form a optical fibre network. Each optical fibre is arranged to receive light from the base light source, transmit the light received from the base light source to one or more of the node light detectors via an air gap, receive light from one or more of the node light sources via an air gap, and transmit the light received from the node light source(s) towards the base light detector. | 05-31-2012 |
20120126061 | GAS EXHAUST DIVERTER - An aircraft comprises an outer aerodynamic surface and an exhaust duct having an opening in the outer aerodynamic surface. The duct has a duct wall curved at the opening so as to blend with the aerodynamic surface downstream of the duct. At least one fixed flow diverter is provided for diverting high temperature exhaust gas exiting the duct away from the aerodynamic surface immediately downstream of the duct opening. The curved duct wall provides low aerodynamic drag in cruise. The flow diverter(s) give aircraft designers freedom in terms of where the duct opening can be positioned without compromising the structural integrity of the aircraft through excessive heating of the aerodynamic surface immediately downstream of the duct opening. | 05-24-2012 |
20120125870 | SPACER PLATE AND SUPPORT STRUCTURE - A spacer plate ( | 05-24-2012 |
20120112016 | CONDUIT HARNESS - A conduit harness has an inner part and an outer part which are snap-fitted together to provide redundancy in the event of failure of either part. | 05-10-2012 |
20120112005 | Wing tip device attachment apparatus and method - A winglet ( | 05-10-2012 |
20120104180 | KRUEGER - A Krueger, or leading edge flap, deployable from a lower aerodynamic surface of an aircraft main wing element so as to form a slot between the Krueger and the main wing element when deployed, the deployed Krueger having a leading edge, a trailing edge and upper and lower aerodynamic surfaces extending between the leading edge and the trailing edge, and a flow deflector which provides an effectively divergent flap profile thickness in the downstream direction at or adjacent the Krueger trailing edge so as to direct airflow away from the lower aerodynamic surface of the deployed Krueger towards an upper aerodynamic surface of the main wing element. Also, aircraft wing assembly including a main wing element and the Krueger. | 05-03-2012 |
20120103685 | AIRCRAFT CABLE ROUTING HARNESS - A harness is provided comprising a body having a series of electrical conductors embedded therein and substantially running along the length thereof. The body may be part of a structural component such as stringer. | 05-03-2012 |
20120103192 | AIRCRAFT FUEL TANK VENTILATION - An aircraft fuel tank ventilation system includes a dehumidifying device disposed in flow communication between a vent open to the atmosphere and a fuel tank. A method of dehumidifying air introduced into an aircraft fuel tank via a ventilation system includes directing atmospheric air through a dehumidifying device disposed in flow communication between a vent of the ventilation system and the fuel tank, which removes water vapour from the air flowing from the vent towards the fuel tank. A method of regenerating a desiccant medium used to dehumidify air introduced into an aircraft fuel tank via a ventilation system includes directing air through the desiccant medium so as to dry the desiccant medium. | 05-03-2012 |
20120099923 | HYBRID COMPONENT - A method of forming a hybrid component comprising at least two metallic parts, the method comprising preparing a first metallic part by forming at least one macroscopic interfacing feature on an interfacing surface of the part; positioning the first part in a mould tool; introducing a metallic powder into the mould tool and around the interfacing feature(s); and consolidating the metallic powder by a Hot-Isostatic Pressing (HIP) process to form a second metallic part which encapsulates the interfacing feature(s) to provide a mechanical connection between the first and second parts of the component. Also, a hybrid component so formed. The metallic parts may have substantially different material properties. | 04-26-2012 |
20120096879 | AIRCRAFT FUEL TANK VENTILATION - An aircraft fuel tank ventilation system, comprising a refrigerative dehumidifying device having a refrigerating element in contact with air flowing between a vent open to the atmosphere and a fuel tank. Also, a method of dehumidifying air introduced into an aircraft fuel tank via the ventilation system, the method comprising directing atmospheric air from the vent into contact with the refrigerating element, and cooling the refrigerating element so as to remove water vapour from the air flowing from the vent towards the fuel tank by condensation. An aircraft fuel tank ventilation system, comprising a refrigerative dehumidifying device having a refrigerating element in contact with air flowing between a vent open to the atmosphere and a fuel tank. Also, a method of dehumidifying air introduced into an aircraft fuel tank via the ventilation system, the method comprising directing atmospheric air from the vent into contact with the refrigerating element, and cooling the refrigerating element so as to remove water vapour from the air flowing from the vent towards the fuel tank by condensation. | 04-26-2012 |
20120073137 | AIRCRAFT RIB-SPAR JOINT - A method of forming a rib-spar joint during assembly of an aircraft wing, the method comprising: providing a spar with a fixedly attached rib post, the rib post having a first coordination feature; providing a rib having a web with a first tooling feature; providing a tooling component having a second tooling feature for cooperating with the first tooling feature, a second coordination feature for cooperating with the first coordination feature, and a plurality of drill bushings; fixedly attaching the tooling component to the rib web by aligning the first and second tooling features; aligning the rib with the spar by aligning the first and second coordination features; drilling fastener holes in the rib and the rib post off the drill bushings of the tooling component; removing the tooling component from the rib web; and fastening the rib to the rib post using the fastener holes to form a rib-spar joint. The method may be applied to form front and/or rear rib-spar joints. | 03-29-2012 |
20120065904 | AIRCRAFT FUEL LEVEL MEASURMENT APPARATUS AND METHOD - A fuel level probe has a series of stacked, annular capacitors, the capacitance of which changes with the dielectric constant of the fluid in which they are immersed. A multiplexer provides sequential measurement of each capacitor to determine a step change in capacitance and hence fluid levels based on the time at which the capacitance changes. | 03-15-2012 |
20120057840 | Apparatus for providing support for an optical fibre - A support for an optical fibre partially submerged in a substrate is discloses in which the support is arranged with fibre fixing means for fixing a portion of the fibre to the support so that strain on the portion of the fibre external to the substrate and support member is at least partially diverted from the portion of the fibre internal to the support member. | 03-08-2012 |
20120057267 | PIPE CONNECTOR - A pipe connector is disclosed, comprising two connector elements, arranged for interconnection of two pipes, wherein one or both of the connector elements is formed from electrically resistive material so as to provide electrical resistance between the connected pipes. | 03-08-2012 |
20120045613 | COMPOSITE STRUCTURE - A structure comprising a cured composite part formed from a series of plies of fibre-reinforced composite material; a doubler plate attached to the composite part by an array of pointed prongs which partially penetrate the composite part; and a hole passing through the doubler plate and the composite part. An interface plate carries the array of prongs on a first side and is attached to the doubler plate on a second side. | 02-23-2012 |
20120043419 | AIRCRAFT LANDING GEAR ASSEMBLY - An aircraft landing gear assembly comprising an impact protection boot mounted to a landing gear component, the impact protection boot comprising: a resilient inner impact energy absorption layer which engages the component; and an outer protective layer which substantially covers the impact energy absorption layer, wherein the inner layer is more compressible than the outer layer. The boot has first and second ends which are tied to each other by a connector which exerts oppositely directed forces on the first and second ends respectively, the forces being directed around the circumference of the boot so as to tighten the boot against the landing gear component. | 02-23-2012 |
20120037755 | WING STRUCTURE - A wing structure is provided, wherein the wing structure comprises; an upper covering, a lower covering, and a spar, the spar comprising; a spar web, an upper spar cap attached to the upper covering, and a lower spar cap attached to the lower covering, the wing structure also comprising a face spaced apart from the spar web extending between the upper and lower spar caps. The wing structure is arranged to contain fuel in a fuel containment area between the upper and lower coverings on one side of the spar web. The upper and lower spar caps extend from the spar web only on the other side of the spar web to the fuel containment area. | 02-16-2012 |
20120035406 | DEHYDRATION OF LIQUID FUEL - A method for dehydrating liquid fuel, the method comprising injecting a supply of dry gas into a liquid fuel via an outlet submerged in the liquid fuel. Also, a system for dehydrating liquid fuel, the system comprising a container for storing a liquid fuel, a line for delivering a supply of dry gas, and an outlet disposed near the bottom of the container and connected to the gas line for injecting dry gas into the liquid fuel. | 02-09-2012 |
20120034026 | Single-sided fitting - A single-sided fitting comprising a shaft with two or more axially extending legs. Each leg has a catch which extends radially outwardly from the leg. A clamping plate has two or more holes each receiving a respective one of the legs. A projection is carried by the clamping plate and extends axially between the legs towards the catches. The clamping plate and projection are axially movable along the shaft to a locking position where the projection is positioned between the catches thus preventing the catches from moving radially inwardly. Means are provided for preventing the clamping plate and projection from withdrawing back along the shaft away from the catches after they have been moved to the locking position. For instance an internally threaded nut may be carried by the shaft, the clamping plate being positioned between the nut and the catches, wherein the nut can be spun along the shaft to engage the clamping plate in its locking position. | 02-09-2012 |
20120030922 | FIBRE PLACEMENT TOOL - A fibre placement tool comprising a plurality of tool segments, each tool segment having an outer surface defining a predetermined profile, each tool segment being removably mounted on at least one elongate shaft. | 02-09-2012 |
20120027507 | ORIENTATION OF INTERFACING PROJECTIONS - A method of joining a first component to a second component, the method comprising preparing the first component by forming an array of elongate projections on a bond surface of the component, each projection having a centreline, a tip, and a base. The centreline at the tip of each projection is oriented at an angle with respect to the normal to the bond surface at its base, and the angular orientation of the tip centrelines varies across the array of projections. Next, the first component and a flexible layer are brought together so as to embed the projections in the flexible layer before hardening the flexible layer to form the second component. Also, a joint so formed. | 02-02-2012 |
20120025026 | Venting gas from a tank - The present invention provides a tank vent device for venting gas from a tank | 02-02-2012 |
20120025025 | Aircraft refuel system piping - The invention provides a pipe | 02-02-2012 |
20120024418 | Refuel valve assembly and method for refuelling an aircraft - The invention provides a refuel valve assembly | 02-02-2012 |
20120006942 | COUPLING ASSEMBLY - A coupling assembly for joining a first component to a second component, the assembly comprising a shaft for connecting to a first component, and a bracket including a mounting plate for connecting to a second component. The bracket has a bracket arm extending from the mounting plate, and a head having a through-bore on the bracket arm. The shaft is received in the through-bore. A setting device acts between the head and the shaft for setting of the position of the shaft with respect to the head in the axial direction of the shaft. The assembly further includes one or more spherical bearing surfaces, which permit self-alignment of the setting device to accommodate tilting of the shaft with respect to the head about a central point in two orthogonal directions. Also, a joint comprising a first component joined to a second component by one or more of the coupling assemblies. Also, a method of forming a joint using one or more of the coupling assemblies. | 01-12-2012 |
20120000864 | CYCLONIC SEPARATOR - A fuel system comprising a liquid fuel tank, an engine, and a cyclonic separator having an inlet fluidically connected to the fuel tank, a first outlet fluidically connected to an engine fuel feed system, and a second outlet. The cyclonic separator is adapted to discharge relatively denser material from the first outlet and relatively less dense material from the second outlet. The fuel system may be used to remove water or ice from the fuel tank by separating the liquid fuel in the tank into water rich fuel and purified fuel using the cyclonic separator. The water rich fuel is discharged to the engine where the water is burnt off with the fuel. The cyclonic separator may be retrofit in an existing fuel system. The fuel system may be in an aircraft. | 01-05-2012 |
20110303799 | AIRCRAFT CONDUIT HARNESS RETENTION SYSTEM - A conduit harness retention system has a base, a first spacer, a second spacer and a cap which snap-fit together to retain P-clip harnesses in position spaced from an aircraft fuselage. | 12-15-2011 |
20110303792 | TELESCOPIC STRUT - A telescopic strut for electrically connecting a fixed structure of an aircraft to a movable structure mounted to the fixed structure, wherein the strut is adapted to be mechanically connected to the fixed structure by its one end and to be mechanically connected to the movable structure by its opposite end, the strut comprising a plurality of telescopic elements and containing a helically coiled electrical cable, wherein the cable is adapted to move between retracted and extended positions with the telescoping of the strut. Also, a method of operating an aircraft having a movable structure mounted to a fixed structure, and one or more of the telescopic struts mechanically and electrically connected between the fixed and movable structures. | 12-15-2011 |
20110303456 | MODULAR CONDUIT RETENTION SYSTEM - A conduit retention system comprises a base and a plurality of polygonal elements which can snap-fit together. | 12-15-2011 |
20110301741 | AIRCRAFT COMPONENT MANUFACTURING METHOD AND APPARATUS - A method of manufacturing in which a robot arm is used to pick up a workpiece which is subsequently scanned by a scanner and positioned relative to a manufacturing system for manufacturing in order to eliminate the use of a bespoke jig. | 12-08-2011 |
20110299918 | Device for locating a first aerospace component relative to a second aerospace component - A device for locating a first aerospace component relative to a second aerospace component, comprising a bladder with a flexible membrane which defines a fluid receiving space such that, when a hardenable hydraulic fluid is injected into the bladder, said membrane is urged to deform into abutment with said first and second aerospace components to locate said components relative to each other when the hydraulic fluid hardens. | 12-08-2011 |
20110293362 | PACKER ASSEMBLY - An assembly comprising first and second structural components and a packer disposed between the first and second components, wherein the first component and the packer have mating part-spherical surfaces, and the first and second components are fixed relative to one another. Also, a method of aligning first and second structural components relative to one another to form an assembly, the method comprising bringing together first and second structural components with a packer disposed between the components, wherein the first component and the packer have mating part-spherical surfaces, sliding adjustment of the first component relative to the packer until the first and second components are aligned in a desired relationship, and then fixing the first and second components relative to one another. | 12-01-2011 |
20110290946 | AIRCRAFT SLAT ASSEMBLY - An aircraft slat assembly comprises a slat, two tracks and two joints, each joint connecting a respective track to the slat. Each track is moveable on a wing structure between a fully extended position and a stowed position. Each joint is arranged to allow relative rotation between the slat and the respective track such that the slat is able to adopt a skewed position in which one track is in the fully extended position and the other track is in the stowed position. | 12-01-2011 |
20110290945 | AIRCRAFT SLAT ASSEMBLY COMPRISING A PLURALITY OF SLATS - An aircraft slat assembly comprises a first slat and a second slat positioned adjacent thereto. The first and second slats are moveable between extended and retracted positions. The slats are connected by a joint, the joint being arranged to transfer a shear load from one slat to the other slat when the slats are urged into a configurations in which there would be differential extension/retraction of the slats, such as a skewed position. | 12-01-2011 |
20110290943 | METHOD AND APPARATUS FOR COOLING FUEL IN AN AIRCRAFT FUEL TANK - Fuel in an aircraft fuselage fuel tank is cooled by means of cold air flowing from the exterior of the aircraft to a cooling region inside the aircraft. The cooling region may be (a) located to the exterior of the fuel tank, (b) in thermal communication with the fuel tank and (c) in fluid communication with a region downstream of, and remote from, said cooling region, for example, an exhaust port on the outside of the aircraft. The flow of air may be caused by air entering a ram air intake, into which air passes as a result of the motion of the airborne aircraft relative to the surrounding air. | 12-01-2011 |
20110284687 | Structural assembly for an aircraft - A structural assembly for an aircraft comprising a cover with outer and inner faces, an inner support element and urging means on the inner support element, wherein opposing edges of the cover are fixedly mounted relative to the inner support element, and the urging means acts on the inner face of the cover to urge the cover to distend outwardly and locate in a predetermined position. Another aspect of the invention relates to a method of forming a structural assembly for an aircraft comprising an cover with outer and inner faces, an inner support element and urging means on the inner support element, the method comprising the steps of fixedly mounting opposing edges of the cover relative to the inner support element and operating the urging means to act on the inner face of the cover so that the cover is urged to distend outwardly into a predetermined position. | 11-24-2011 |
20110283508 | Apparatus for fixedly locating a first aerospace component relative to a second aerospace component - An apparatus for fixedly locating a first aerospace component relative to a second aerospace component comprising a housing mountable on a first component with a cylinder formed in said housing, and a piston slidably received in said cylinder, wherein a first end of the piston is extendible from the housing such that, when a hardenable hydraulic fluid is injected into the cylinder to act on a second end of said piston, said first end of the piston is urged to slide away from the housing and into abutment with a second component to locate said second component, and said second component is fixedly located in a desired position relative to said first component when the hydraulic fluid hardens. | 11-24-2011 |
20110272530 | WING TIP DEVICE - An aircraft includes a wing having a positive dihedral, the wing having a tip and a wing tip device mounted in the region of the tip. The wing tip device is generally downwardly extending and has a region inclined at a cant of more than 180 degrees. The region is arranged to generate lift during flight. The region inclined at a cant of more than 180 degrees may be located at the distal end of the wing tip device. The wing tip may be swept and may aeroelastically deform during flight. | 11-10-2011 |
20110271509 | JOINT - A joint comprising first and second abutting components, and an adjustable strap assembly bridging the abutting components, the strap assembly including a first strap part attached to one of the components, and a second strap part attached to the other component, the first and second strap parts having mating inclined faces for adjustment of the second strap part with respect to the first strap part such that the position of the second strap part is adjustable with respect to the first strap part in the direction of the incline. Also, a method of forming the joint, comprising attaching the first strap part to the first component, providing the second strap part such that the inclined faces of the first and second strap parts are in mating engagement, adjusting the second strap part with respect to the first strap part in the direction of the incline to position the second strap part in a desired relationship with respect to the first strap part, and attaching the second strap part to the second component. | 11-10-2011 |
20110253841 | METHOD AND SYSTEM FOR CHECKING THE FORMATION OF ICE ON AN AIRCRAFT IN FLIGHT - The invention relates to a method for checking the formation of ice on an aircraft in flight, characterized in that the method comprises:
| 10-20-2011 |
20110253832 | Slat support assembly - A support assembly for deployment and retraction of an aero surface from an aircraft is disclosed. The assembly comprises a guide track, a primary support arm having one end coupled to a carriage mounted on the track such that the primary support arm is rotatable relative to the carriage about multiple axes, and a control arm having one end coupled to the primary support arm and a second end pivotably attachable to a fixed support forming part of the structure of the aircraft. The assembly being configured such that, when the carriage is driven along the guide track, the control arm causes the primary support arm to pivot about said multiple axes to deploy and/or retract an aero surface pivotally attached to an opposite end of the primary support member along an arcuate path. | 10-20-2011 |
20110240200 | Method of forming a joint - A method of forming a joint between a first component and a second component, the first component comprising a plurality of layers of fibres impregnated with a thermosetting matrix. A welding interface element is provided with an array of pointed prongs. One or more of the layers of fibres are penetrated with the prongs, either before or after the fibres have been impregnated with the thermosetting matrix. The first component is cured by heating the thermosetting matrix after the prongs have been embedded. A thermoplastic weld is formed between the second component and the welding interface element. | 10-06-2011 |
20110233338 | JOINT - A joint between an aircraft wing box cover and a leading/trailing edge structure, the cover and the structure having flush aerodynamic outer surfaces, wherein the structure has an integrally formed land that extends over an inner surface of the cover, and the land of the structure is fastened to the cover. Also a method of forming the joint. | 09-29-2011 |
20110219878 | METHOD AND APPARATUS FOR MEASURING THE STRUCTURAL INTEGRITY OF A SAFE-LIFE AIRCRAFT COMPONENT - The structural integrity of a safe-life aircraft component on an aircraft is measured and assessed by a processing unit. The component includes a load-bearing metal element that is free from cracks. In the method, acoustic emissions generated in the metal element are converted into electronic signals. The acoustic emissions converted include relevant acoustic emissions resulting from changes in the structure of the element that make the element more susceptible to the formation of cracks. The electronic signals are set to a processing unit. The processing unit processes over time the signals in conjunction with stored reference data that allows a measure of the structural integrity to be made. Information providing a measure of the structural integrity of the aircraft component is outputted. Thus, deterioration of the structure of the component can be detected and monitored before a crack occurs. | 09-15-2011 |
20110215196 | ENGINE DEBRIS GUARD - An engine debris guard for preventing tyre propelled debris striking an aircraft engine, the debris guard comprising a guard bar pivotably connected to an aircraft main landing gear having at least one wheel and tyre assembly, the guard bar being arranged to be movable between a first position and a second position wherein in the first position the guard bar extends laterally across the wheel and tyre assembly to intersect the possible trajectories between the wheel and tyre assembly and an engine of the aircraft of any tyre propelled debris. | 09-08-2011 |
20110215077 | WATER DRAIN TOOL - A water drain tool for opening a water drain valve of an aircraft fuel tank, the tool comprising a probe and a heat source, wherein the probe is adapted to engage the valve in order to open it and the heat source is adapted to direct heat towards the valve when the valve is being opened. The valve is heated with the probe in order to melt ice formed within the valve which may otherwise impede its normal operation. | 09-08-2011 |
20110204185 | AIRCRAFT FAIRING - A shock control fairing for mounting a junction between adjoining aircraft surfaces. The fairing has a cross-sectional profile which varies along the length of the fairing. The cross-sectional profile of the fairing has a maximum area at a location which, when mounted to an aircraft, is substantially proximal to a location on the surface of the aircraft at which a shock would be expected to develop without the fairing. | 08-25-2011 |
20110204184 | ELECTRICAL CONNECTOR - An aircraft pressure bulkhead electrical connector comprising a first connection terminal proximate at least one side of the electrical connector and a pressure seal arranged to maintain an applied air pressure differential across the electrical connector in use. | 08-25-2011 |
20110198465 | AIRCRAFT RACEWAY MOUNTING AND CLAMPING APPARATUS - An aircraft raceway mounting apparatus comprising an attachment formation for attachment of the apparatus to an aircraft structure, a raceway receiving formation for receiving a raceway, the raceway receiving formation comprising a snap fit formation for retention of a raceway. An aircraft raceway clamping apparatus comprising a concave raceway receiving formation having a raceway support region and a mouth, a bridge member configured to at least partially span the mouth, a clamping member movably mounted to the bridge member to advance into the mouth. | 08-18-2011 |
20110186690 | BRIDGING SEAL - A bridging seal comprising a stack of two or more layers of elastomer, the bridging seal having a first edge and a second edge opposite the first edge, adjacent layers being attached to each other at the first and second edges, wherein adjacent layers of the bridging seal have opposing surfaces and a substantial portion of the opposing surfaces is unbonded. The bridging seal may be used to seal a gap between two aerodynamic surfaces on an aircraft. | 08-04-2011 |
20110186680 | Aircraft landing gear - An aircraft landing gear for an aircraft having an engine, an outer surface, a cavity formed in the outer surface, a cover arranged to close the cavity, the landing gear being arranged to be movable between a stowed configuration, in which it is stowed in the cavity, and a deployed configuration, the landing gear comprising an engine debris guard panel arranged to inhibit tyre propelled debris striking the engine whilst the landing gear is in the deployed configuration, wherein the guard panel is arranged to form at least a part of the cover when the landing gear is in the stowed configuration. | 08-04-2011 |
20110183106 | RAMPED STIFFENER AND APPARATUS AND METHOD FOR FORMING THE SAME - A die tool for forming a C-section component having radiused shoulders has first and second outer dies, each outer die having a truncated conical portion connected to a flange portion by a radiused portion and being symmetrically disposed to one another along a common axis such that each flange portion is outermost, and a cylindrical outer support die located between the first and second outer dies. | 07-28-2011 |
20110180684 | METHOD AND APPARATUS FOR CONTROLLING AN ELASTOMERIC DAMPER - A method of controlling an elastomeric damper. The damper is heated by passing an electric current through the damper or through a heating element in contact with the damper said heating causing a decrease in stiffness of the damper. The elastomeric damper may comprise an elastomeric material filled with electrically conductive particles, and the damper may be heated by passing an electric current through the elastomeric material. Alternatively the damper may be heated using a discrete resistive heating element, such as a coil embedded within the elastomeric damper or wound around it. | 07-28-2011 |
20110180659 | AIRCRAFT TAXIING ACTUATOR - An aircraft wheel assembly comprising a wheel and an aircraft taxiing actuator comprising, a first shaft for connection to a drive source, the first shaft defining a first axis and a second shaft for connection to the wheel to rotate the wheel, the second shaft defining a second axis substantially perpendicular to the first axis, in which the first shaft and second shaft are connected in driving engagement by a ball-worm gear. | 07-28-2011 |
20110180658 | AIRCRAFT STEERING ACTUATOR - An aircraft steering actuator has a driving shaft for connection to a drive source, the driving shaft defining a first axis, and a driven shaft for substantially perpendicular connection to a landing gear axle of an aircraft, the driven shaft defining a driven axis substantially perpendicular to the first axis, in which the driving shaft and driven shaft are connected in driving engagement by a ball-worm gear. | 07-28-2011 |
20110180356 | AIRCRAFT BRAKING ACTUATOR - An aircraft wheel brake assembly has a housing for attachment to the landing gear of an aircraft, a friction plate in non-rotational sliding engagement with the housing, an actuated plate for non-rotational sliding engagement with an aircraft wheel, an aircraft brake actuator comprising, a first shaft for connection to a drive source, the first shaft defining a first axis, and, a second shaft for connection to, and actuation of, the brake assembly, the second shaft defining a second axis substantially perpendicular to the first axis, in which the first shaft and second shaft are connected in driving engagement by a ball-worm gear. | 07-28-2011 |
20110180320 | Bracket for attaching an electrical cable to a vehicle - The invention provides a bracket 1 for attaching an electrical cable 6 to a vehicle, the bracket comprising a vehicle attachment portion 11, 31 for attaching the bracket to a vehicle attachment surface of the vehicle, and a cable securing portion 13, 33 for securing the cable to the bracket 1, the cable securing portion 13, 33 comprising a cable abutment portion 4, 8 against the front surface of which the cable 6 can be secured by a cable-tie 7 forming a closed loop around the cable 6 and cable abutment portion 4, 8, and a non-planar rear surface which at least partially defines the path of the closed loop of the cable-tie 7 behind the cable abutment portion 4, 8, the path passing a first region on one side of the non-planar rear surface and a second region on the opposite side of the non-planar rear surface, wherein, in use, the non-planar rear surface directly supports the cable-tie 7 at a third region along the path of the closed loop, the third region being positioned, along the path, between the first and second regions. The invention also provides an aircraft fuel tank comprising a plurality of such brackets 1 and an electrical cable 6, secured to each of the brackets with a cable-tie 7. | 07-28-2011 |
20110179893 | LINEAR ACTUATOR - A linear actuator has a housing, a piston slideable within the housing along a slide axis, a first shaft rotatable about a first axis substantially perpendicular to the slide axis, a second shaft rotatable about a second axis parallel to the slide axis, in which the second shaft and the piston are engaged to convert rotational motion of the second shaft into linear motion of the piston, and in which the first shaft and the second shaft are engaged by a ball-worm gear. | 07-28-2011 |
20110174933 | SLOT SEAL - A panel assembly for an aircraft comprises a panel rotatably connected to a support structure and moveable between a first position and a second position. The panel has an aerodynamic surface with a slot at one edge thereof which receives a portion of the support structure when the panel is in the first position. The assembly further comprises a resilient seal member which occupies the slot when the panel is in the second position. The panel may be an aircraft flight control surface, or an aircraft landing gear bay door. | 07-21-2011 |
20110168845 | AIRCRAFT SKIN PANEL WITH ULTRASONIC GAUGE - An aircraft panel which is a wall of a fluid tank when in use, the panel comprising a skin layer with an outer surface which is an aerodynamic surface of an aircraft when in use; a hole in the skin layer; an ultrasonic gauge which is mounted to an inner surface of the skin layer adjacent to the hole in the skin layer; and an access panel which covers the hole and can be removed to gain access to the gauge. | 07-14-2011 |
20110147523 | PIPE COUPLING DEVICE FOR AIRCRAFT WING - An aircraft wing comprising first and second fuel pipe segments which are coupled together with a pipe coupling device comprising a corrugated tube formed from an elastomer filled with conductive material. The pipe coupling device is particularly useful for connecting together fuel pipe segments in an aircraft wing as it removes the need to attach bonding leads between fuel pipe segments to dissipate lightning currents and static. | 06-23-2011 |
20110143100 | ASSEMBLING AND SHAPING LAMINATE PANEL - A method of assembling and shaping a laminate panel. An intermediate member is mounted on a lay-up table and a lay-up is assembling by laying a series of plies onto the intermediate member on the lay-up table. The intermediate member and the lay-up are then removed from the lay-up table and placed them on a shaped surface. The lay-up is then forced against the shaped surface, via the intermediate member, in a manner that modifies the shape of the lay-up to form a shaped laminate panel. Finally the shaped laminate panel is removed from the intermediate member. The lay-up table can thus support the flexible intermediate member during assembly, and can be relatively flat to enable the lay-up to assembled by an automated process. | 06-16-2011 |
20110135886 | RAMPED STIFFENER AND APPARATUS ANDMETHOD FOR FORMING THE SAME - A die tool for forming a C-section component having radiused shoulders, the includes a cylindrical inner die and an outer die having a cylindrical central portion connected to opposing end flanges by respective radiused concave portions. A portion of the inner die is arranged to be disposed between the end flanges of the outer die and spaced apart therefrom to define a cavity corresponding to the desired cross-section of the C-section component to be formed. The radiused convex and concave portions have a radius of curvature that varies about the circumference of the respective inner and outer dies. The inner and outer dies are rotatable such that the radius of curvature of the radiused convex and concave portions where the inner and outer dies are adjacent to one another varies as the inner and outer dies are rotated. | 06-09-2011 |
20110127387 | TRAILING EDGE FLAP - A trailing edge flap arrangement for an aircraft wing, comprising an array of flap elements each discretely moveable between a retracted and an extended position by a respective actuator, wherein the flap elements are arranged to be deployed so as to open up a through slot between an adjacent pair of the flap elements only when the aerodynamic leading element of the pair has reached its extended position. Also, a method of operating the trailing edge flap arrangement. | 06-02-2011 |
20110127386 | TRAILING EDGE FLAP - A single slotted trailing edge flap arrangement for an aircraft wing, comprising a main flap element and an auxiliary flap element sealed to and supported by the main flap element for movement between a retracted and an extended position relative to the main flap element so as to vary the planform area of the flap. The auxiliary flap element remains sealed to the main flap element when in its extended position, and movement of the auxiliary flap element relative to the main flap element is solely translational. The auxiliary flap element may be translationally deployed from the main flap element by sliding the auxiliary flap element out from the underside of the main flap element. Also, a method of operating the flap arrangement. | 06-02-2011 |
20110127385 | TRAILING EDGE FLAP - A trailing edge flap arrangement for an aircraft wing, comprising an array of flap elements moveable collectively between a retracted and an extended position, wherein at least the leading flap element is rotatable about its axis independently of the collective array movement. Also, a method of operating the trailing edge flap arrangement, comprising collectively moving the array of flap elements between a retracted and an extended position, and rotating at least the leading flap element about its axis independently of the collective array movement. The flap arrangement can be deployed as a single slotted flap which can be vented to further improve lift performance. The flap arrangement can also be operated to provide variable camber across the performance envelope. | 06-02-2011 |
20110121487 | METHOD OF MANUFACTURING A COMPOSITE ELEMENT - A method of manufacturing a composite element. A stack of plies is assembled on a lay-up table, each ply comprising a plurality of reinforcement elements such as dry-fibres. A first part of the stack of plies is bound to form a partially bound stack of plies, a second part of the stack of plies remaining unbound. The partially bound stack of plies is press-formed in a mould cavity between a pair of mould tools to form a shaped pre-form, plies in the second part of the stack sliding against each other during the press-forming. A liquid matrix material is injected into the shaped pre-form in the mould cavity and subsequently cured. | 05-26-2011 |
20110116528 | Thermal test apparatus and method - Thermal test apparatus comprising a specimen supported by a fixture, a thermal shroud comprising a flexible insulating fabric forming an enclosure around at least a portion of the specimen, and a temperature controlled air supply connected to an opening formed in the enclosure for delivering a supply of temperature controlled air into the enclosure. Also, a method of conducting a thermal test. | 05-19-2011 |