| AIRBUS OPERATIONS LIMITED Patent applications |
| Patent application number | Title | Published |
|---|
| 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 |
| 20110115214 | CONNECTOR FOR AN AIRCRAFT FUEL PIPE - A connector for connecting a pipe, such as a fuel pipe, to another fuel pipe or pipe terminal. | 05-19-2011 |
| 20110115115 | RAMPED STIFFENER AND APPARATUS AND METHOD FOR FORMING THE SAME - A stiffener has an elongate web element and an elongate foot element connected by a curved elbow that has a radius greater over a first portion than over a second portion of the stiffener. The stiffener is formed by feeding an elongate member through a roll forming die having first and second rollers, the first roller having a shaped section arranged to be located within a correspondingly shaped recess in the second roller, the first and second rollers defining a gap there between corresponding to the desired shape to be imparted on the elongate member, the desired shape including a curved elbow between a web and a foot portion, wherein the shapes of the recess and the shaped section vary such that the radius of curvature of the gap between the rollers corresponding to the curved elbow varies between a minimum and a maximum value. | 05-19-2011 |
| 20110100128 | INSPECTION DEVICE - An ultrasound scanner ( | 05-05-2011 |
| 20110099829 | Measuring device for determining the shortest distance between features in a structure - A measuring device for determining the shortest distance between features in a structure. | 05-05-2011 |
| 20110095133 | COVER TRAILING EDGE PROFILE - An aircraft wing assembly, comprising a front spar, a rear spar, and upper and lower wing covers extending between the front and rear spars, wherein the upper and/or lower wing cover overhangs the rear spar and has a non-linear trailing edge profile forming an array of tabs and cut-outs. Also, a method of assembling the aircraft wing. | 04-28-2011 |
| 20110089292 | AIRCRAFT JOINT - A method of joining a wing to an aircraft fuselage by forming a series of pinned lug joints between a fuselage side and a wing side of a wing box structure. The joint forming process includes providing a single row of lugs on one side of the joint to be formed, and providing a respective double row of lugs on the other side of the joint to be formed. A gap between opposing lugs of the double row varies along the row. The wing side and the fuselage side of the wing box structure are brought together such that the lugs of the single row are located within the respective gaps between opposing lugs of the double row, and the lugs are pinned to form the series of pinned lug joints. Also, a joint formed by the method. | 04-21-2011 |
| 20110089289 | AIRCRAFT LANDING GEAR ARRANGEMENT AND A NOSE LANDING GEAR ASSEMBLY - An aircraft landing gear arrangement comprises a nose landing gear assembly and at least one main landing gear assembly. The nose landing gear assembly has a nose landing gear wheel with a high energy brake apparatus therein. The main landing gear assembly has a main landing gear wheel with a high energy brake apparatus therein and a main landing gear wheel with a motor therein. The motor is used for driving the main landing wheel during taxiing of the aircraft. | 04-21-2011 |
| 20110084171 | AIRCRAFT FUEL SYSTEM - An aircraft fuel system including a fuel line for carrying liquid fuel, and a microwave energy transmitter for energizing water carried in the fuel line. Also, a method of suppressing ice formation in an aircraft fuel system, the fuel system including a fuel line carrying liquid fuel, and a microwave energy transmitter, the method comprising transmitting microwaves along the fuel line to energize water carried with the fuel in the fuel line. | 04-14-2011 |
| 20110061539 | DESICCANT REGENERATION - An aircraft fuel tank ventilation system, comprising a desiccative dehumidifying device including a desiccant medium disposed in flow communication between a vent open to the atmosphere and a fuel tank, and a microwave energy transmitter for energizing liquid water in the desiccant medium to facilitate regeneration of the medium. Also, a method of regenerating a desiccant medium of a dehumidifying device of an aircraft fuel tank ventilation system, the method comprising directing air through the desiccant medium, and transmitting microwave energy into the desiccant medium for energizing liquid water in the desiccant medium to facilitate regeneration of the medium.) | 03-17-2011 |
| 20110056974 | 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 flamer barrier means, when refuelling. | 03-10-2011 |
| 20110056973 | VENT PIPE FOR AN AIRCRAFT FUEL SYSTEM VENT TANK - A vent pipe is disclosed for use in the vent tank of an aircraft fuel system. The vent pipe is arranged with guide vanes or corner cascades for assisting the flow of fluid around the corners. | 03-10-2011 |
| 20110056972 | AIRCRAFT FUEL TANK SYSTEM - An aircraft fuel tank system is disclosed in which a vent tank is provided with an ullage vent for use in combination with an eternal flamer barrier means during a refuelling process. | 03-10-2011 |
| 20110056971 | 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. | 03-10-2011 |
| 20110056970 | AIRCRAFT FUEL TANK SYSTEM - An aircraft fuel tank system is disclosed in which a vent tank is provided with an ullage vent for use in combination with an eternal flamer barrier means during a refuelling process. | 03-10-2011 |
| 20110049304 | AEROFOIL SLOT BLOWING - An aerofoil defining geometric upper and lower surfaces which together form a leading edge region and a trailing edge region, and comprising a blowing device having a slot in the lower geometric surface in the leading edge region for injecting fluid into the airflow over the aerofoil, wherein the slot is located forward of the leading edge stagnation point at the critical angle of incidence of the aerofoil, and wherein the blowing device is adapted to inject the fluid forwardly of the slot and substantially parallel to the lower surface. Also, a method of improving the performance of the aerofoil by injecting fluid into the airflow over the aerofoil from the slot. The upper surface of the aerofoil can be kept clean, giving the potential for laminar flow during cruise without significantly compromising the high lift performance of a blown leading edge at high incidence. | 03-03-2011 |
| 20110049173 | AIRCRAFT FUEL TANK SYSTEM - An aircraft fuel tank system is disclosed in which a vent tank is provided with a compact vent pipe comprising one or more built-in flame barrier elements providing high liquid fuel outflow rate. | 03-03-2011 |
| 20110042511 | 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. | 02-24-2011 |
| 20110031433 | THERMOSETTING EPOXY RESIN, A COMPOSITE MATERIAL, A METHOD OF FORMING A COMPOSITE MATERIAL ARTICLE, A MOULD AND A METHOD OF MAKING A MOULD - A thermosetting epoxy resin includes particles of magnetite and conductive carbon to act as microwave susceptors. A composite material comprises a thermosetting epoxy resin matrix phase with particles of magnetite and a carbon fibre reinforcement phase. A mould for a composite article comprises a mould body made from a material that is substantially transparent to microwaves with a surface or rear surface layer including microwave radiation absorbing material. | 02-10-2011 |
| 20110031351 | Support assembly - A support assembly for guiding a flap on an aircraft wing during deployment of the flap is disclosed. The assembly comprises an arcuate guide track mountable to an aircraft wing and defining a two-dimensional path, a carriage mounted on the guide track so as to slide along the track during flap deployment, a part-spherical bearing, and a shaft having one end attachable to a flap and the opposite end coupled to the carriage via said part-spherical bearing. The shaft is free to pivot relative to the carriage about a centre of the part-spherical bearing in all directions, as the carriage slides along the track. | 02-10-2011 |
| 20110031349 | Pinned lug joint - A pinned lug joint comprising: a first part comprising two first lugs projecting from a bridge which extends between them; a second part pivotally coupled to the first part, the second part comprising a second lug positioned between the first lugs; and a sealing member, the sealing member being mounted to the first lugs and extending between them to seal an air gap between the second lug and the bridge at least when the second part is in a first position. The pinned lug joint may be used to attach a panel assembly to part of an aircraft. | 02-10-2011 |
| 20110031347 | SPOILER DEPLOYMENT MECHANISM - An aircraft wing assembly comprising: a wing; a spoiler pivotally attached to the wing; and a spoiler deployment mechanism. The deployment mechanism comprises a scissor linkage mechanism comprising an upper link pivotally attached to the spoiler at an upper pivot, and a lower link pivotally attached to the wing at a lower pivot and to the upper link at a central pivot. An actuator is pivotally attached to the wing at a proximal pivot and to the scissor linkage mechanism at a distal pivot. The actuator is adjustable between expanded and contracted configurations so as to vary the distance between the proximal and distal pivots. This opens up the angle between the upper and lower links of the scissor linkage mechanism and pushes the spoiler up into the air-stream above the wing. | 02-10-2011 |
| 20110030477 | ULTRASOUND INSPECTION METHOD AND APPARATUS - A method of inspecting a component, the component comprising a hole with an entrance. The method comprises: directing ultrasound into the component via a liquid coupling medium; receiving ultrasound from the component via the liquid coupling medium; and processing the received ultrasound to determine a property of the component. The entrance of the hole is sealed with tape to prevent the liquid coupling medium from flowing into the entrance of the hole. | 02-10-2011 |
| 20110028061 | Adjustable shim - An adjustable shim comprises a stack of plies comprising plastics material reinforced with a three-dimensional fibre layer, the plastics material being flowable under compressive force prior to cure for adjusting the thickness of the shim. The shim may be used to fill a void between two structural components joined together. Also, a method of filling a void between two structural components using the shim. The shim is easy to handle, can easily be laid up to a variety of thicknesses, and is quick to cure (depending on the plastics material used). The three-dimensional fibre layers make the shim highly compressible prior to cure, and provide significant reinforcement to the plastics material of the plies to support compressive stresses in the shim post cure. | 02-03-2011 |
| 20110024566 | ELECTRICAL POWER TRANSFER ASSMEBLY - 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. | 02-03-2011 |
| 20110005666 | METHOD OF TAPE LAYING OF THERMOPLASTIC COMPOSITE MATERIALS - A method of laying up a thermoplastic composite in a mould tool, the method comprising: providing a mould tool having a mould surface, at least a portion of the mould tool comprising a porous material; applying a negative pressure to the porous material so as to create a negative pressure at the mould surface; laying an initial layer of thermoplastic composite material onto the mould surface, whereby the thermoplastic composite material is held against the mould surface by virtue of the negative pressure at the mould surface; and consolidating the thermoplastic composite material. | 01-13-2011 |
| 20110004376 | METHOD AND DEVICE FOR THE LATERAL CONTROL OF A TAXIING AIRCRAFT - The invention relates to a device ( | 01-06-2011 |
| 20100330893 | Contaminant extraction apparatus - A composite material manufacturing apparatus has an extractor ( | 12-30-2010 |
| 20100327121 | CROSS-BLEED DAM - A panel assembly for an aircraft including a panel having an upper aerodynamic surface and a leading edge, and a hinge fitting connected to an underside of the panel, defining a hinge line for the direction of rotation of the panel. The upper surface of the leading edge has an arcuate portion centered about the hinge line, and has an upturned portion forward of the arcuate portion. The panel assembly is pivotally connected to its hinge fitting to the trailing edge of the fixed wing portion and rotatable between a first position wherein the upper surfaces of the fixed wing portion and the panel are substantially flush, and a second position wherein the panel is rotated downwardly from the first position. A seal member attached to the trailing edge of the fixed wing portion, has a lower surface which seals against the upper surface of the panel during its movement. | 12-30-2010 |
| 20100327118 | Aircraft walkway - An aircraft | 12-30-2010 |
| 20100327114 | 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. | 12-30-2010 |
| 20100327111 | Electrical power transmitting telescopic strut - A telescopic strut comprises a plurality of hollow members arranged to slide one within another between a retracted and an extended position. Adjacent hollow members are arranged to be electrically connected by one or more electrical connector assemblies as the hollow members move between the retracted and extended positions. Each electrical connector assembly includes an electrically conductive pad on one of the hollow members which is in sliding contact with an electrically conductive strip on the other of the hollow members. The telescopic strut may be used to electrically connect a moveable control surface to a fixed aerofoil structure in an aircraft. | 12-30-2010 |
| 20100308169 | AIRCRAFT WIRE FAIRING - A fairing has a moulded body and an electrical wire embedded therein. The body may be constructed from a moulded plastics material or a composite material. | 12-09-2010 |
| 20100307235 | AIRCRAFT FUEL TANK WEIGHT MEASUREMENT APPARATUS AND METHOD - An aircraft fuel tank weight measurement apparatus comprising a first solid element defining a load path for an aircraft fuel tank, an EMW emitter and an EMW detector arranged such that a first EM wave from the EMW emitter to the EMW detector passes through the first solid element, the detector arranged to detect a phase shift in the first wave resulting from a change in length of the first wave path caused by deformation of the first solid element. | 12-09-2010 |
| 20100295293 | Connector for a pipe - A connector for connecting a pipe, such as a fuel pipe, to another fuel pipe or pipe terminal. | 11-25-2010 |
| 20100288888 | BLADE SEAL - A blade seal comprises a flexible member having a relatively thick edge opposite a relatively thin edge, and an actuator at least partially embedded in the flexible member for actively deflecting the thin edge with respect to the thick edge upon activation of the actuator. The blade seal may be fixed to an aerodynamic trailing edge of either a fixed aerofoil portion or a flight control surface of an aerofoil for sealing between the fixed aerofoil portion and the flight control surface. Also, a method of sealing an aerofoil using the blade seal. | 11-18-2010 |
| 20100264274 | EDGE SEAL FOR FIBRE-REINFORCED COMPOSITE STRUCTURE - A fibre-reinforced composite structure includes a cut edge; an elastomeric cap covering the cut edge; and an adhesive sealant bonding the elastomeric cap to the cut edge. The fibre-reinforced composite structure is joined to a component and the elastomeric cap includes a generally Z or L-shaped cap with a web bonded to the cut edge of the fibre-reinforced structure and a flange bonded to the component and extending away from the fibre-reinforced structure. | 10-21-2010 |
| 20100258686 | CABLE RACEWAY - A cable raceway comprising: a base; a pair of side walls extending from the base to define the edges of a cable channel; three or more legs extending from the base; and a flange at a distal end of each leg for attaching the leg to a support structure. The base, side walls, legs and flanges are formed from an elastomeric material. The base contains reinforcement which extends along the length of the raceway and is embedded within the elastomeric material. | 10-14-2010 |
| 20100258674 | TRACK CONTAINER - An aircraft wing assembly comprising: a spar; a fuel tank; a track container which is attached to the spar and extends into the fuel tank; a track which extends through the spar and into the track container; and a high-lift device, such as a slat or flap, carried by the track. The track container comprises a stiffening element encased in an elastomeric sheath. The track container is manufactured by placing a stiffening element and elastomeric material together in a mould; and compressing and heating them to cure and shape the elastomeric material. | 10-14-2010 |
| 20100247934 | 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. | 09-30-2010 |
| 20100247869 | 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. | 09-30-2010 |
| 20100242996 | AIRCRAFT COMPONENT WITH AERODYNAMIC SURFACE COATING - An aircraft component with an aerodynamic surface coating comprising a resilient foam with an array of open cells infused with a cleaning material such as a gel, paste or liquid. This prevents contaminants such as insects from adhering to the aircraft component. The resilient foam stores at least part of the impact energy of the contaminant, the cleaning material is released from the deformed foam so that the cleaning material at least partially coats the contaminant, and the foam springs back to eject the coated contaminant from the aircraft component. | 09-30-2010 |
| 20100226063 | AIRCRAFT JOINT AND BONDING LEAD - A joint on an aircraft, the joint comprising: a first component; a second component joined to the first component; and a bonding lead which forms an electrical connection between the components with a resistance between 100 kΩ and 10 MΩ. Surprisingly, it has been found that a bonding lead with a relatively high resistance can be used without seriously compromising the static discharge performance of the bonding lead, and that the resulting comparatively low flow of current reduces the risk of sparking in the event of an lightning strike. Bonding leads may be provided as a kit of parts in which at least two of the bonding leads have different lengths and the longer lead is formed from a material having a higher bulk conductivity than the shorter lead. Thus the bonding leads can be made with approximately similar resistances regardless of their lengths. | 09-09-2010 |
| 20100226062 | AIRCRAFT JOINT AND BONDING LEAD - A joint on an aircraft, the joint comprising: a first component; a second component; and a bonding lead which provides an electrical pathway between the first and second components. The bonding lead comprises a conductive core and a sheath which covers a substantial length of the core and has a lower electrical conductivity than the core. The path of least electrical resistance between the first component and the core of the bonding lead comprises the sheath, typically with an electrical resistance between 50 kΩ and 50 MΩ. By making the electrical resistance of the core much smaller than that of the sheath, the total resistance of the bonding lead remains substantially the same regardless of its length. | 09-09-2010 |
| 20100226061 | BONDING LEAD - A joint on an aircraft, a bonding lead for use in such a joint, and a method of manufacturing such a joint. The bonding lead comprises an elongate conductive core with a pair of end faces at the extremities of its length. The conductive core is encapsulated along at least a majority of its length and at both end faces in a barrier layer typically formed from an elastomer. The lead is encapsulated along its length in the barrier layer apart from at a first contact region towards a first end of the bonding lead and a second contact region towards a second end of the bonding lead. A first electrical connector passes through a first hole in the barrier layer to engage the first contact region of the conductive core and provide an electrical connection between the conductive core and the first component; and a second electrical connector passes through a second hole in the barrier layer to engage the second contact region of the conductive core and provide an electrical connection between the conductive core and the second component. | 09-09-2010 |
| 20100200700 | TANKS FOR CONTANING A FLUID WITHIN A CHAMBER - A tank for containing a fluid, such as fuel, oil or gas within a chamber. The walls of the chamber are partially defined by a rigid structure having an opening; and partially defined by an elastomeric diaphragm which is attached around its periphery to the rigid structure and covers the opening in the rigid structure. An attachment frame engages the diaphragm and the rigid structure, and extends around the periphery of the diaphragm. The attachment frame has a first portion which engages the diaphragm, and a second portion which is positioned outside an outer edge of the diaphragm and attached to the rigid structure. | 08-12-2010 |
| 20100181422 | NOSE LANDING GEAR ARRANGEMENT FOR AN AIRCRAFT AND AN AIRCRAFT HAVING SUCH AN ARRANGEMENT - A nose landing gear arrangement comprises a leg assembly with a pivot axis A at one end thereof and a landing gear wheel mounting at the other end thereof. Two stays are provided, each stay being mounted at one end thereof to the leg assembly and mountable at the other end thereof to an aircraft. Each stay comprises an upper stay part and a lower stay part which are hinged together by means of a simple hinge. The upper stay part has a cardan joint at its end spaced from the hinge to enable hinged mounting to an aircraft. The lower stay part has a cardan joint at its lower end spaced from the hinge, the cardan joint of the lower stay part hingedly mounting the lower stay part to the leg assembly. The leg assembly and the stays are arranged so that the stays extend from the leg assembly on opposite sides thereof and the stays fold into a stowed position so that they lie substantially alongside the leg assembly when the leg assembly is retracted. | 07-22-2010 |
| 20100127120 | Aircraft Structure - An aircraft control surface mounting structure comprising a cantilever rib ( | 05-27-2010 |
| 20100122737 | 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. | 05-20-2010 |
| 20100121625 | Method of designing a composite laminate - A method of designing a composite laminate, the laminate comprising a plurality of zones, each zone comprising a plurality of plies of composite material, each ply in each zone having a respective ply orientation angle. A global stacking sequence is determined for the laminate, the global stacking sequence comprising a sequence of stacking sequence elements. A local laminate thickness is determined for each zone. A local stacking sequence is then determined for each zone by extracting a subsequence of stacking sequence elements from the global stacking sequence. The global stacking sequence and the local laminate thicknesses are determined together in an optimisation process in which multiple sub-ply selection variables are assigned to each stacking sequence element, each sub-ply selection variable representing the density or sub-ply thickness for a respective candidate ply orientation angle. Optimal values are determined for the sub-ply selection variables and the local laminate thicknesses. A single one of the sub-ply selection variables is assigned to each stacking sequence element thereby forcing a discrete choice of global ply orientation angle for each stacking sequence element. | 05-13-2010 |
| 20100096497 | BI-DIRECTIONAL FLIGHT CONTROL SURFACE MECHANISM - A bi-directional flight control surface mechanism comprises a fixed part V of a vertical stabiliser having leading and trailing edges and a rudder having leading and trailing edges. The rudder is mounted relative to the fixed part of the vertical stabiliser so that the trailing edge of the fixed structure is adjacent the leading edge of the rudder. The rudder is movable from a neutral position in which the rudder lies in line with the fixed part of the vertical stabiliser to define a notional centreline to first and second angled positions in which the rudder is angled relative to the fixed part of the vertical stabiliser at a non-zero angle on one or other side of the notional centreline. An actuator is provided to drive the rudder relative to the fixed part of the vertical stabiliser so as to vary the distance between said part of the trailing edge of the fixed part of the vertical stabiliser and the leading edge of the rudder. | 04-22-2010 |
| 20100068464 | PREPARATION OF A COMPONENT FOR USE IN A JOINT - A method of preparing a component ( | 03-18-2010 |
| 20100045031 | CONNECTOR FOR A PIPE AND BONDING MEANS FOR USE THEREIN - Bonding means for use in a pipe connector, the pipe connector comprising two connector elements each arranged for interconnection and connection to a respective pipe, a retaining means for maintaining interconnection of the connector elements and a ring member arranged for capture by a retaining means and biased into contact with both connector elements of the pipe connector, the ring member being formed as a single piece of electrically conductive material so as to provide electrical bonding directly between the two connector elements of the pipe connector. | 02-25-2010 |
| 20100044511 | Aircraft structure - An aircraft wing ( | 02-25-2010 |
