A sensor arrangement has a structure extending along a length, an optical fibre carrier, and an optical fibre sensor carried by the optical fibre carrier. The optical fibre carrier is fixed to the structure proximal to each end of the structure and is formed of a first carrier portion and a second carrier portion that are movable relative to each other and is formed substantially of a material having a first coefficient of thermal expansion. The optical fibre sensor has a single measurement point and is fixed to the optical fibre carrier either side of the single measurement point; and the structure is formed of a material having a second coefficient of thermal expansion which is different to the first coefficient of thermal expansion
G01K 11/3206 - Measuring temperature based on physical or chemical changes not covered by group , , , or using changes in transmittance, scattering or luminescence in optical fibres at discrete locations in the fibre, e.g. using Bragg scattering
B64D 37/00 - Arrangements in connection with fuel supply for power plant
G01K 1/14 - SupportsFastening devicesArrangements for mounting thermometers in particular locations
G01K 3/06 - Thermometers giving results other than momentary value of temperature giving mean valuesThermometers giving results other than momentary value of temperature giving integrated values in respect of space
G01K 13/00 - Thermometers specially adapted for specific purposes
A joint assembly has an eccentric bush for rotatably mounting to the first aircraft component. The eccentric bush has a rotational axis. A projection is mounted on the eccentric bush such that rotation of the eccentric bush about its rotational axis causes movement of the projection in both a first and a second orthogonal direction relative to the first aircraft component. The first and second orthogonal directions are substantially perpendicular to the rotational axis of the eccentric bush. A rail rotatably mounts to the second aircraft component. The rail has a longitudinal axis which extends in a direction substantially parallel to the second orthogonal direction. The projection has an aperture for receiving the rail. The rail has a threaded surface which is configured to engage with a correspondingly threaded surface of the aperture.
A joint assembly for joining a first aircraft structural component to a second aircraft structural component. The joint assembly has a double eccentric bush for mounting to one of the first and second aircraft structural components, and a spigot mounted on the double eccentric bush. Rotating elements of the double eccentric bush enable adjustment of the spigot relative to the respective aircraft structural component in two orthogonal directions normal to a longitudinal axis of the spigot prior to joining the first aircraft structural component to the second aircraft structural component. A spigot receptacle is provided for mounting to, or is integrally formed with, the other of the first and second aircraft structural components. The spigot receptacle is arranged to receive the spigot. At least one fastener joins the first and second aircraft structural components together when the spigot is received in the spigot receptacle.
A vacuum-insulated pipe assembly having an outer pipe and an inner pipe within the outer pipe, the inner pipe distanced from the outer pipe to provide a space, the space evacuated to define a vacuum. The vacuum-insulated pipe assembly has an annular wall extending inwardly from the outer pipe and defining an aperture about a central axis, the annular wall defining a closed end of the space. The vacuum-insulated pipe assembly has a first connector connected to the inner pipe, and a second connector extending through the aperture and connected to the first connector. The first connector and the second connector are each hollow and connected such that the inner pipe is in fluid communication with the second connector through the aperture. Also a system and a method for making a vacuum-insulated pipe assembly.
A latch for locking an aircraft folding wing is disclosed having a lug including an aperture, and a latch pin moveable within the aperture. The latch further includes a seal configured to inhibit fluid transfer between the aperture and the latch pin as the latch pin moves within the aperture.
A vacuum-insulated pipe assembly including an outer pipe and an inner pipe within the outer pipe, the inner and outer pipes concentric along a common central axis, the outer pipe spaced from the inner pipe to define a space, the space evacuated to define a vacuum. The outer pipe includes first and second outer pipe sections, the first outer pipe section includes a first outer connector, and the second outer pipe section includes a second outer connector, the first outer connector removably connected to the second outer connector at an outer connection interface. The inner pipe includes first and second inner pipe sections, the first inner pipe section includes a first inner connector, and the second inner pipe section includes a second inner connector, the first inner connector removably connected to the second inner connector at an inner connection interface.
A vacuum insulated pipe assembly including a first pipe section and a second pipe section. The first pipe section has a first outer wall and a first inner wall within the first outer wall. The first outer and inner walls are concentric along a common central axis, and the first outer wall is spaced from the first inner wall to define a first space. The second pipe section has a second outer wall and a second inner wall within the second outer wall. The second outer and inner walls are concentric along the common central axis, and the second outer wall is spaced from the second inner wall to define a second space. The first inner wall includes a first inner connector and the second inner wall includes a second inner connector connected to the first inner connector.
F16L 59/075 - Arrangements using an air layer or vacuum the air layer or the vacuum being delimited by longitudinal channels distributed around the circumference of a tube
A bush is provided including a sleeve for receiving a pin; a shoulder extending from the sleeve, the shoulder for delimiting insertion of the sleeve into an aperture; and a sensor mount for mounting a sensor such that the sensor may detect the presence of a pin within the sleeve. Installing such a bush within an aperture of a component may negate the requirement for lugs and/or brackets on the component. This may enable reduction of the weight, size and/or complexity of the component.
Disclosed is a wing assembly for an aircraft. The wing assembly comprises a fixed wing, a wing tip device, a wiring harness and a harness guide. The wing tip device is moveably mounted at a joint at an end of the fixed wing. The wing tip device is moveable about the joint between: (i) a flight configuration for use during flight, and (ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved relative to the fixed wing such that the span of the wing is reduced. The wiring harness extends between the fixed wing and the wing tip device. The wiring harness comprises a plurality of conductors and is arranged to transmit electrical power and/or data to the wing tip device. The harness guide is located between the fixed wing and the wing tip device. The harness guide comprises a helical channel configured to receive the wiring harness and guide the wiring harness between the fixed wing and the wing tip device.
A Coriolis flow sensor for sensing a flow of a cryogenic fluid is disclosed having a flow member for the passage of a flow of cryogenic fluid therethrough, a driver for vibrating the flow member, and one or more detectors configured to generate output signals corresponding to Coriolis deflections of the vibrating flow member with flow of cryogenic fluid therethrough. The flow member includes at least 50 wt % indium.
A method of applying an ice-removal fluid (113) to a folding wing aircraft (100) is described, the method comprising applying the ice-removal fluid (113) to the folding wing portion (103) and holding the folding wing portion in an over-folded position (111) once the ice-removal fluid (113) has been applied. A method of operating an aircraft (100) during ground based operations is further described using the method of applying an ice-removal fluid (113).
An aircraft wing having a fixed wing and a moveably mounted wing tip device is disclosed. A first cable harness and a second cable harness which are received in a protective sleeve extend between the fixed wing and the wing tip device. The protective sleeve is in a secured configuration in which at least two opposing parts of the protective sleeve are secured together between the first cable harness and the second cable harness to provide the sleeve with a first channel in which the first cable harness is received a second channel in which the second cable harness is received, and a webbing region extending between the first channel and the second channel such that the first and second cable harnesses are held apart by the webbing region.
A device including a layer of resin-encapsulated carbon is disposed in the vicinity of an outlet of a hydrogen vent. The vent carries gaseous hydrogen from a hydrogen store on an aircraft, to a location external of the aircraft. Upon pressure-relief of the hydrogen store, hydrogen travels through the vent and out the outlet. In the event of ignition of the hydrogen, the heat of the hydrogen flame melts the resin and releases the carbon. The carbon combusts in the hydrogen flame, thus producing a visible flame. The device is easily removeable and replaceable.
An aircraft assembly is disclosed including a wing structure, and a pipe assembly rotatably coupled to the wing structure by a fixture arrangement. The pipe assembly extends along a longitudinal direction, the fixture arrangement configured to restrict movement of at least a portion of the pipe assembly in the longitudinal direction relative to the wing structure and allow rotation of the pipe assembly relative to the wing structure.
Disclosed is an aircraft structure comprising: at least one aircraft structural element defining a volume; a fuel distribution component, arranged within the volume, configured to hold fuel internally and transport held fuel through the volume; and at least one packing element formed of a reticulated foam, arranged within the volume, and at least partially surrounding the fuel distribution component. An aircraft comprising the aircraft structure is also disclosed.
A landing gear attachment member for an aircraft is provided, the landing gear attachment member including a body comprising metal; and a lug comprising a metal matrix composite, wherein the lug is fused to the body via a joint. The lug may be brazed to the body, and the joint may comprise one or more scarf joints.
Disclosed is an aircraft structure comprising at least one aircraft structural element defining a volume; a fuel-handling component arranged within the volume and configured to handle a fuel; a purging system comprising an inlet and an outlet, the purging system configured to provide a flow of purge gas from the inlet, through the volume, to the outlet, to thereby purge leaked fuel from the volume; and a flow guide member formed of a reticulated foam, arranged within the volume and externally to the fuel-handling component, and configured to guide the flow of purge gas within the volume. An aircraft comprising the aircraft structure is also disclosed.
An aircraft assembly is disclosed including a rib of a wing, an aperture in the rib, and a pipe assembly extending through the aperture. The pipe assembly includes a first rigid pipe section, a second rigid pipe section and a flexible pipe section between the first and second rigid pipe sections; and a fixture arrangement that couples one of the pipe sections to the wing rib. The flexible pipe section is located at a plane of the rib and configured to allow relative movement between the first rigid pipe section and the second rigid pipe section.
A fluid assembly comprising: a first conduit extending in an axial direction and configured to carry a fluid, a double walled outer second conduit extending in the axial direction; the second conduit having an inner wall and outer wall and a first interspace between the inner and outer walls, wherein the first conduit is housed inside the second conduit to form a second interspace between the first conduit and the inner wall of the second conduit.
A method of controlling a pressure in a hydrogen fuel tank of an aircraft hydrogen fuel system. The hydrogen fuel tank stores hydrogen fuel. The method comprises receiving leak information indicative of a leak of hydrogen fuel from the hydrogen fuel system. The method also comprises, based on the leak information received, causing control of the pressure in the hydrogen fuel tank.
An aircraft system is disclosed including a hydraulic actuator, an inlet line for supplying hydraulic fluid to the hydraulic actuator, an outlet line for removing hydraulic fluid from the hydraulic actuator, a first one-way valve configured to allow fluid flow along the inlet line in a direction toward the hydraulic actuator, and a second one-way valve configured to allow fluid flow along the outlet line in a direction away from the hydraulic actuator.
A hydraulic actuator for a hydraulic actuation system of an aircraft includes a housing defining a cavity, a piston dividing the cavity into extension and retraction chambers and movable relative to the housing to increase volume of one chamber and decrease volume of another of the chambers. A bypass includes first and second bypass ports and a connecting bypass line, and first and second chamber ports opening into the extension and retraction chambers at all positions of the piston relative to the housing for passage of hydraulic fluid. The first and second bypass ports open into one of the extension chamber and retraction chamber when the piston is at a first position relative to the housing so the first bypass port and the second bypass port open into respective ones of the extension chamber and the retraction chamber when the piston is at a second position relative to the housing.
F15B 11/024 - Systems essentially incorporating special features for controlling the speed or the actuating force or speed of an output member by means of differential connection of the servomotor lines, e.g. regenerative circuits
A method of actuating a wing tip device on an aircraft, from a flight configuration to a ground configuration in which the span is reduced. The method includes receiving data indicative of a condition, such as the location or speed of the aircraft, and determining an actuation profile in dependence on the condition. The actuation profile may include determining a time period, and/or speed profile of the wing tip actuation over that time period. In this manner the actuation of the wing tip device can be tailored to minimize loads and wear on the actuator assembly.
An aircraft structural element configured to be assemblable into an aircraft structure is disclosed having a sensor disposed on or within the aircraft structural element. The sensor is configured to sense a parameter during assembly of the aircraft structural element into the aircraft structure, and to output a signal indicative of the parameter during assembly of the aircraft structural element into the aircraft structure. An aircraft assembly system, and method of assembly based on the same are also disclosed.
An aircraft wing (3) comprising an aerofoil structure (5) is disclosed. The aerofoil structure (5) comprises a load-carrying member (10) having stiffness properties selected such that the load-carrying member (10) twists in a predefined manner in response to bending of the load-carrying member (10). The aerofoil structure (5) further comprises an actuator (15A, 15B) which is fixedly mounted to the load-carrying member (10) and which is operable to bend the load-carrying member (10) to thereby cause the load-carrying member (10) to twist. An aircraft comprising the aircraft wing and a method of adjusting the twist in an aircraft wing are also disclosed.
An aircraft structural element configured to be assemblable into an aircraft structure, the aircraft structural element including an external surface having an integrally formed photogrammetry target. The aircraft structural element, the integrally formed photogrammetry target and the external surface are formed of a common material composition and are a single piece structure. A photogrammetry system, aircraft assembly system and method of assembly of the aircraft structural element into the aircraft structure.
An aircraft control system and method for controlling electrical power distribution in an aircraft are disclosed. The aircraft control system and method obtain state signals from electrical systems in the aircraft, control characteristics of a power source, and control characteristics of the electrical systems. The control characteristics of the electrical systems are dependent on a flight phase status of the aircraft. Output control data is generated, based on the control characteristics and state signals, and used to control electrical power distribution in the aircraft.
An interface for a wing folding mechanism of an aircraft. The interface has a central region comprising an internal surface, the internal surface being suitable for engaging a driven gear of a rotary actuator, and an attachment pad extending away from the central region in a first direction for attaching a surface to the interface. The interface can be used as part of the casing of a Geared Rotary Actuator. Also described are related wing assemblies, and aircraft and related methods.
A computer-implemented method of estimating characteristics of a hydraulic accumulator of an aircraft. The computer-implemented method includes obtaining pressure information representative of a pressure of hydraulic fluid in the hydraulic accumulator at a plurality of times during a mission of the aircraft, and estimating the characteristics based on the pressure information and a model including relationships between pressure and time for respective variants of the characteristics.
A tire monitoring system including a tire monitoring device and a remote device. The tire monitoring device includes a first processor, and a first wireless communication interface. The remote device includes a second processor, a display device, and a second wireless communication interface. The first processor monitors the tire monitoring device to determine an altered operational mode of the tire monitoring device and causes transmission of a signal encoding an indication of the altered operational mode of the tire monitoring device to the remote device via the first and second wireless communication interfaces. The second processor determines, based on the signal encoding the indication of the altered operational mode of the tire monitoring device, a maintenance message corresponding to the altered operational mode of the tire monitoring device and causes the maintenance message to be displayed on the display device.
G07C 5/00 - Registering or indicating the working of vehicles
B64F 5/60 - Testing or inspecting aircraft components or systems
G01K 3/00 - Thermometers giving results other than momentary value of temperature
G01L 17/00 - Devices or apparatus for measuring tyre pressure or the pressure in other inflated bodies
G01L 19/00 - Details of, or accessories for, apparatus for measuring steady or quasi-steady pressure of a fluent medium insofar as such details or accessories are not special to particular types of pressure gauges
A tire monitoring system that includes a tire monitoring device and a remote device. The tire monitoring device includes a processor, a memory, and a first wireless communication interface. The remote device includes a second wireless communication interface. The processor monitors the tire monitoring device to determine unauthorized interactions with the tire monitoring device, stores a log of determined unauthorized interactions in the memory, and transmits a signal encoding the log to the remote device via the first and second wireless communication interfaces.
A fuel line terminating in a refuel connector is used to fuel or defuel an aircraft, for example with liquid hydrogen. A supply of nitrogen housed on an aircraft, for example a Nitrogen Generating System, is used in conjunction with a gas line to supply nitrogen into the fuel line, to flush out potentially combustible materials before liquid hydrogen is supplied through the fuel line. The aircraft supply of nitrogen is also used to supply inert gas, via a gas line, to the Ground Support Equipment refuelling or defuelling the aircraft. This can provide redundancy for the Ground Support Equipment's systems, and may allow the aircraft to operate at less well-equipped airports.
A pipe support assembly (114), suitable for supporting pipework handling cryogenic fluids, where the pipework passes through a fuel tank support. The pipe support assembly includes first and second pipe supports (116) each having male (119) and female (152) portions that interlock with male (119) and female (152) portions of the other pipe support (116). The pipe supports (116) have an internal surface (121) that contacts a section of the pipe outer surface (112). Each pipe support (116) has a split (140) which allows for a change in dimension of the internal surface (121) of the pipe support (116) contacting the pipe (110). This allows the pipe support assembly (114) to provide a consistent clamping force to the pipe (110) during thermal contraction or expansion. Longitudinal movement of the pipe (110) is permitted if the pipe (110) overcomes the frictional force between itself and the pipe support assembly (114).
A joint assembly in an aircraft, for example between a wing skin and rib foot. The joint assembly includes fasteners mechanically holding the wing skin and rib foot together. The rib foot includes circular faying surfaces and a layer of material is sandwiched between the faying surfaces and the wing skin. The layer of material has adhesive properties such that the joint is a hybrid joint. The layer of material also has structural properties to function as a solid shim, for example once it has cured after application.
A machining system includes an automated manipulator configurable between a measuring configuration, in which a position probe is operable, and a machining configuration, in which a tool is operable, a fixture for holding a template or a workpiece, and a controller. The controller is configured cause the automated manipulator, in the measuring configuration, to move the position probe to at least one reference feature of the template held in the fixture, to determine coordinate data associated with the at least one reference feature. Then, the controller provides the determined coordinate data to a machine learning agent which is trained to provide an estimate of machining coordinate deviation based on the determined coordinate data. If the estimated machining coordinate deviation is below a threshold coordinate deviation, the automated manipulator is allowed to proceed to machine a workpiece.
An aircraft with a folding wing tip arrangement having a wing tip device mounted at a joint at the end of a fixed wing. It is desirable to transfer power and/or data into a folding wing tip, which presents challenges such as repeated exposure to potentially harsh environmental conditions, with movement, and/or with changes in tensional loads. A wiring harness includes a plurality of conductors and is arranged to transmit electrical power and/or data to the wing tip device. A length of the harness is received in a protective sleeve, and the sleeve extends over a length of the wiring harness spanning the joint, the sleeve being removable from the wiring harness.
An aircraft with a folding wing tip arrangement and a wiring harness extending between a fixed wing and a wing tip device is disclosed. It is desirable to transfer power and/or data into a folding wing tip, which presents challenges such as repeated exposure to potentially harsh environmental conditions, with movement, and/or with changes in tensional loads. The wiring harness includes a plurality of conductors and is arranged to transmit electrical power and/or data to the wing tip device. The harness is received in a protective sleeve. The sleeve includes a fluorosilicone polymer.
An aircraft enclosure inerting system has an inerting apparatus which receives air from an inlet, separates that air into nitrogen enriched air to be delivered to one or more enclosures of the aircraft, and oxygen enriched air. The inerting apparatus comprises at least first and second air separators. The first and second air separators are configured differently to one another. In some embodiments one of the air separators is a vortex tube and the other is a membrane-based air separation module. In some embodiments the inerting apparatus has at least two vortex tubes which are configured differently to one another.
An aircraft with a folding wing tip arrangement and first and second wiring harnesses extending between a fixed wing and a wing tip device is disclosed. It is desirable to transfer power and/or data into a folding wing tip, which presents challenges such as repeated exposure to potentially harsh environmental conditions, with movement, and/or with changes in tensional loads. The wiring harnesses include a plurality of conductors and are arranged to transmit electrical power and/or data to the wing tip device. The sleeve includes two channels to receive the harnesses, the position of the channels being fixed, relative to one another, such that the harnesses are held apart.
A method of inspecting an aircraft fuel tank fastener assembly. The assembly includes a fuel tank with a fuel chamber; a fastener comprising a head and a tail at opposite ends of the fastener; and a cap inside the fuel chamber, wherein the cap surrounds the tail of the fastener. The method includes: heating the tail of the fastener; obtaining a thermal image of the tail of the fastener; and inspecting the thermal image of the tail of the fastener.
A robot arrangement is disclosed including one or more robots for moving a component into an assembly position adjacent a fixed structure. The robots are configured to operate collectively to move the component from an initial position located in a coarse adjustment zone into a fine rotational adjustment zone within a set distance of the fixed structure. The coarse adjustment zone is at least the set distance from the fixed structure; and in the fine rotational adjustment zone, robots are configured to collectively perform a rotational alignment cycle to rotationally align the component with the assembly position of the component ready for joining the component to the fixed structure and, upon completion of the rotational alignment cycle, collectively perform a translational movement to move the component into the assembly position.
B23P 21/00 - Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control
A robot arrangement for interacting with an object is disclosed including a plurality of robots adjacent an object; the plurality of robots configured to interact with the object sequentially such that: a first robot of the plurality of robots is configured to perform a first portion of a first task on the object and then, whilst the first robot is not interacting with the object, a second robot of the plurality of robots is configured to perform a second portion of the first task on the object, and the plurality of robots are configured to simultaneously interact with the object, before or after completion of the first task, so as to collectively perform a second task on the object.
A method of joining a wing skin to a structural element of an aircraft wing. A locating through hole is formed in the structural element, extending along a path between a first side of the structural element and a second side of the structural element. A spark containment cap is attached to the first side of the structural element to covering an opening of the locating through hole. A portion of the wing skin is positioned on the second side of the structural element. A fastening through hole having a larger diameter than the locating through hole is formed through both the wing skin and the structural element and along the path of the locating through hole. A fastener is inserted into the fastening through hole and the structural element secured to the wing skin, an end of the fastener being covered by the spark containment cap.
A method comprising moving a vehicle between a plurality of parked aircraft; at each aircraft, receiving aircraft-to-ground data from the aircraft at the vehicle by free-space-optical communication and storing the aircraft-to-ground data at the vehicle; and transferring the stored aircraft-to-ground data from the vehicle, wherein stored aircraft-to-ground data from two or more of the aircraft accumulates at the vehicle before it is transferred from the vehicle. Also a vehicle used in such a method.
H04B 10/112 - Line-of-sight transmission over an extended range
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
An aircraft comprising an aircraft transceiver to transfer data to and from the aircraft by free-space-optical communication when parked. The aircraft transceiver comprises a transmitter to generate outgoing light carrying aircraft-to-ground data; a lens to collimate the outgoing light to generate a collimated beam; a beam steering device to transform the collimated beam to generate a steered beam; a control system to operate the beam steering device to adjust an angle of the steered beam; and a receiver to sense incoming light carrying ground-to-aircraft data. The receiver receives the incoming light via the beam steering device and the lens. Also a vehicle with a similar transceiver to transfer data to and from a parked aircraft by free-space-optical communication.
METHOD FOR DETERMINING AT LEAST ONE CHARACTERISTIC OF A MOVEMENT OF A MOBILE STRUCTURE OF AN AIRCRAFT AND AIRCRAFT COMPRISING A DEVICE FOR ITS IMPLEMENTATION
A method for determining, at a given moment in time, at least one characteristic of a movement of a mobile structure of an aircraft. The method includes determining a pair of coordinates in a reference plane corresponding to a projection of a reference feature forming part of the mobile structure in the reference plane, determining the characteristic of the movement of the mobile structure by comparing the pair of coordinates previously determined with reference coordinate pairs, at least one characteristic of the movement of the mobile structure being associated with each pair of reference coordinates. Also an aircraft having a device for implementing the method.
A method of securing a first structure to a second structure is disclosed including providing a jig assembly having spark containment caps carried by a jig; mounting the jig assembly on a structure so that the spark containment caps and the jig contact the first structure; securing the spark containment caps to the first structure by injecting adhesive material into contact with the first structure and the spark containment caps and then curing the adhesive material; removing the jig after the adhesive material has cured; and securing the first structure to the second structure with fasteners, each fastener having a tail which is inserted through the first and second structures and into a respective one of the spark containment caps.
Disclosed is a method of exchanging cryptographic parameters in a network of tire monitoring devices, the method including broadcasting, from each tire monitoring device to a plurality of other tire monitoring devices, a message comprising a cryptographic parameter generated by that respective tire monitoring device.
Disclosed is a brake component (151) comprising a composite material (200), the composite material comprising a matrix (202) and reinforcements (201) embedded in and supported by the matrix, wherein the matrix is a glass-ceramic matrix. Also disclosed is a braking system, an aircraft braking system, an aircraft and a method of operating an aircraft.
F16D 65/18 - Actuating mechanisms for brakesMeans for initiating operation at a predetermined position arranged in or on the brake adapted for drawing members together
An aircraft including a wing with a fixed wing portion and a wing tip device rotatably hingedly attached at a fixed wing portion outboard end. The wing includes a wing fold mechanism configured to actuate the wing tip device to rotate relative to the fixed wing portion to at least three commanded and predetermined wing fold angles and to restrain rotational movement of the wing tip device at each commanded position. A first position corresponds to high-speed flying, a second position to ground-based operations and a third position to low-speed flying. The flying positions rotate the wing tip to a position where upper and lower wing tip surfaces are continuations of the upper and lower surfaces of the fixed wing, with a low-speed incidence angle being less than a high-speed incidence angle. The ground-based position reduces the wing span to the greatest degree of the three positions.
A fuel line, terminating in a refuel connector, is used to fuel/defuel an aircraft, for example with liquid hydrogen. A barrier is disposed around the area where the refuel connector connects to an aircraft fuel port, and is sealed against the aircraft wing with a seal. A gas line runs generally parallel to the aircraft fuel line, and supplies inert gas, for example nitrogen, into the volume defined by the barrier. The inert gas flushes out air present around the refuel connector such that the oxygen concentration in that area is significantly lowered. This prevents ignition of fuel in the event of a fuel leak from the fuel line structure.
The disclosure is directed to a fuel line terminating in a refuel connector is used to fuel (or defuel) an aircraft, for example with liquid hydrogen. A barrier is deployed around the area where the refuel connector connects to an aircraft fuel port. A gas line supplies inert gas from a supply of gas, for example nitrogen, into the area defined by the barrier. The inert gas flushes out air present around the refuel connector such that the oxygen concentration in that volume is significantly lowered. This prevents ignition of fuel in the event of a fuel leak from the refuel connector. The barrier, the gas supply, and/or the outlets for the inert gas to be supplied through are provided by a part of the aircraft.
A hydraulic actuator for an aircraft. The hydraulic actuator comprises: a housing to accommodate hydraulic fluid; an extension chamber and a retraction chamber each defined by the housing; and a bypass line in fluid communication with the extension chamber and the retraction chamber, wherein the bypass line comprises a flow restrictor and a bypass valve, wherein the flow restrictor restricts a rate of fluid flow through the bypass line, wherein the bypass valve has material defining a port that is openable to allow the hydraulic fluid to flow through the bypass line, and wherein the material is configured to change shape, as a temperature of the material reduces to below a predetermined temperature, to thereby open the port. Also disclosed is a hydraulic actuation system, in the form of a landing gear system, comprising the hydraulic actuator, and an aircraft comprising the hydraulic actuation system.
F15B 15/14 - Fluid-actuated devices for displacing a member from one position to anotherGearing associated therewith characterised by the construction of the motor unit of the straight-cylinder type
A hydraulic actuation system for an aircraft. The system comprises: a hydraulic actuator comprising: a housing to accommodate hydraulic fluid; an extension chamber and a retraction chamber each defined by the housing; and a bypass line in fluid communication with the extension chamber and the retraction chamber, the bypass line comprising a flow restrictor and a bypass valve, the flow restrictor configured to restrict a rate of fluid flow through the bypass line; and a controller configured to receive a signal indicative that the aircraft is in a take-off or a landing procedure, to determine that the aircraft is performing the take-off or the landing procedure based on the signal, and to perform an operation to cause the bypass valve to open to allow the hydraulic fluid to flow through the bypass line only when the controller determines that the aircraft is performing the take-off or the landing procedure.
F15B 15/14 - Fluid-actuated devices for displacing a member from one position to anotherGearing associated therewith characterised by the construction of the motor unit of the straight-cylinder type
An aircraft landing gear has a suspension mechanism which has a four-bar linkage that comprises four links rigidly extending between a corresponding four pivots. A lower link of the four-bar linkage supports front and rear wheels, and is movable relative to an upper link between lengthened and shortened positions. A shock absorber urges the four-bar linkage towards the lengthened position. A length of the upper link of the four-bar linkage is adjustable.
A computer-implemented method of determining a maintenance schedule or maintenance plan for a fuel tank of an aircraft. In a training phase, a predictive model is trained with training data. The training data is associated with fuel tanks of plural aircraft. The training data comprises environmental data indicative of an environmental parameter at locations of the plural aircraft, and test data which is indicative of a level of microbial contamination of fuel in fuel tanks of the plural aircraft. In a prediction phase, input data is received and the predictive model is operated, along with an optimisation algorithm, to determine a maintenance schedule or maintenance plan. One or more microbial contamination maintenance tasks are performed on the fuel tank based on the maintenance schedule or maintenance plan.
An elongate aircraft structural component for an aircraft, the structural component comprising a web and a flange, wherein the flange extends from the web, comprises layers of composite material, and has a length in a direction of a length of the elongate aircraft structural component, a width perpendicular to the length of the flange and a thickness smaller than, and perpendicular to, both the width and the length of the flange, wherein the width of the flange varies along the length of the flange, whereby the flange comprises a wide flange region and a narrow flange region, the narrow flange region having a smaller width than the wide flange region, and wherein the wide flange region comprises stitching interconnecting the layers of composite material, the stitching extending along a path in a direction with at least a component parallel to the width of the flange.
A method of controlling the supply of multiple fuels to an engine of an aircraft is disclosed. The aircraft includes a first fuel having a first composition and a second fuel having a second composition. The second composition comprises a greater proportion of sustainable aviation fuel, SAF, than the first composition. The engine is supplied with the first fuel during a first phase of flight of the aircraft. During a second phase of the flight of the aircraft, subsequent the first phase, supply to the engine is switched from the first fuel to the second fuel.
An aircraft panel is disclosed having a ply of composite material, the ply of composite material curved around an axis such that a free end of the ply extends more than 180 degrees around the axis and defines a wall of a channel for receiving a hinge member of an aircraft component.
The disclosure relates to a rotary tool guide having a top side, an underside and a set of rigid guide members, a set of guide holes each of which extends through one of the guide members. The guide holes are arranged to guide a rotary tool such as a drill or countersink therethrough. The guide members are spaced apart by flexible portions which can deform so as to allow the underside to change shape to conform to a surface of a workpiece.
A landing gear controller that: determines whether a predetermined criterion is met; and causes a power supply system of an aircraft to supply power to an actuation system of the aircraft to cause a component of a landing gear system of the aircraft to move from a first position to a second position selectively according to: a first predetermined supplied-power profile, when the landing gear controller determines that the predetermined criterion is not met, and a second predetermined supplied-power profile, according to which a maximum power supplied by the power supply system to the actuation system is greater than a maximum power supplied by the power supply system to the actuation system according to the first predetermined supplied-power profile, to move the component from the first position to the second position more quickly, when the landing gear controller determines that the predetermined criterion is met.
A tool and method for positioning a sealing member in an aircraft wing assembly by using first and second holes in a first component of the aircraft wing assembly and first and second holes in a second component of the aircraft wing assembly as positioning reference points, wherein a positional relationship of the first and second holes in the first component matches a positional relationship of the first and second holes in the second component.
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B23P 19/04 - Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformationTools or devices therefor so far as not provided for in other classes for assembling or disassembling parts
A connector configured to attach to a boss, the connector including: a connector body having an attachment arrangement configured to attach the connector body to the boss; and a temperature sensing element inserted through a through-hole of the connector body. A first end of the temperature sensing element is configured to attach to a data line and a second end of the temperature sensing element configured to be inserted into an orifice of the boss to sense a temperature of the boss. The temperature sensing element is configured to move relative to the connector body.
A composite structure comprising a body, such as an aircraft wing skin; and an opening in the body, such as a manhole. The body has steered fiber elements and terminated fiber elements. Each steered fiber element has a curved portion with a plurality of steered fibers which follow curved paths around the opening. The terminated fiber elements alternate with the steered fiber elements, and each terminated fiber element comprises a plurality of terminated fibers which terminate next to the curved portion of a respective steered fiber element.
B32B 3/26 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids
B32B 1/00 - Layered products having a non-planar shape
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 37/16 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with all layers existing as coherent layers before laminating
B32B 38/00 - Ancillary operations in connection with laminating processes
B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
A wing assembly has a flexible cover which is movable between an extended position and a retracted position. In the extended position the flexible cover covers the leading edge of the wing assembly, thereby protecting the front of the wing assembly from impact by dirt or debris and preserving the smoothness of its surface. In the retracted position the flexible cover does not cover the leading edge of the wing assembly.
A modular wing portion for installation into a wing assembly as a pre-assembled unit, the modular wing portion comprising at least one rib and at least one internal fuel tank system component, and a cartridge jig for the assembly of the modular wing portion away from an aircraft wing, the cartridge jig comprising a plurality of secondary support members, each secondary support member configured to receive and support a rib such that a fuel system component can be installed to the rib. Also an aircraft and wings, transport frames and methods of assembly.
An assembly comprising a fuel stringer duct, a bulkhead, and a bulkhead retainer. The bulkhead is positioned in the fuel stringer duct to block the flow of fluid along the fuel stringer duct. The bulkhead retainer comprises a retainer portion that extends through an opening in a wall of the fuel stringer duct and which is configured to abut with the bulkhead to prevent movement of the bulkhead along the fuel stringer duct. Also a method of installing a bulkhead in a fuel stringer duct.
A connector for connecting a fluid flow duct to a fuel stringer duct. The connector comprises a body having an internal channel for fluid passage between a first opening and a second opening of the body. A flange surrounds the first opening, the flange configured for insertion into a hole formed in a wall of the fuel stringer duct. An outer surface of the flange is provided with a first sealing member that surrounds the flange, the first sealing member configured to form a seal between the outer surface of the flange and an internal surface of the hole formed in the wall of the fuel stringer duct.
F16L 41/12 - Joining pipes to walls or pipes, the joined pipe axis being perpendicular to the plane of a wall or to the axis of another pipe using attaching means embracing the pipe
F16L 41/08 - Joining pipes to walls or pipes, the joined pipe axis being perpendicular to the plane of a wall or to the axis of another pipe
The volume of a liquid such as cryogenically stored liquid hydrogen in a container such as a fuel tank on an aircraft is measured using acoustic sensors. The container includes multiple chambers each arranged to accommodate a volume of liquid. A computer processor processes signals from acoustic sensors that detect sound and/or vibration from each chamber and provides an indication of the volume of liquid in the container. Such sounds and/or vibrations may arise inherently from the liquid contained therein.
An aircraft assembly includes an aircraft structure, a flexible panel having a supported end fixedly attached to the aircraft structure, wherein the flexible panel is configured to bend about the supported end relative to the aircraft structure, a rigid stopper extending from and fixedly attached to the aircraft structure, wherein the rigid stopper is configured to restrict bending of the flexible panel about the supported end in a first direction and permit bending of the flexible panel in a second direction opposing the first direction.
An aircraft wing has a leading edge, a fixed wing portion and a leading-edge spoiler device. The spoiler device is hingedly mounted relative to the fixed wing portion adjacent the leading edge, moveable between retracted and deployed positions. In the retracted position a spoiler surface forms a continuous surface with a fixed wing portion upper aerodynamic surface, and in the deployed position the spoiler surface is rotated relative to the upper aerodynamic surface. In the retracted position the spoiler surface has a first portion forward of the hinge and a second portion aft of the hinge. A center of pressure of the local wing section acts on the spoiler surface providing a moment about the hinge in a first direction to bias the spoiler device to the retracted position and providing a moment about the hinge in a second, opposite direction, rotating the spoiler device to the deployed position.
An aircraft structural component having an upwardly- or downwardly-extending portion, such as a wing tip or tail fin, comprising one or more outlets for the delivery of anti-icing fluid to a first surface of the aircraft structural component. Anti-icing fluid is delivered through an outlet located at or near the tip of the upwardly-extending portion, or the base of the downwardly-extending portion. The anti-icing fluid thus delivered may, under the influence of gravity, run down the surface of the component, thereby providing the surface of the component with anti-icing fluid.
A computer-implemented method comprising determining, based on a first signal indicative of a pressure in a tire of a wheel of an aircraft and a second signal indicative of a deformation of the tire, a determined load on the wheel, and causing an action to be performed based on the determined load on the wheel. Also a system for an aircraft, the system comprising a monitoring system configured to detect pressure and deformation of a tire of a wheel of the aircraft, and a controller configured to determine, on the basis of the pressure and deformation detected by the monitoring system, load on the wheel.
A computer-implemented method that includes receiving information indicative of an aircraft steering angle of an aircraft, comparing the received information against a threshold above which degradation of a tire of a landing gear of the aircraft is expected to occur and causing an action to be performed based on a result of the comparison. Also an aircraft system.
A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection, wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees.
A pump system is disclosed including a first pump having a first inlet and a first outlet, and a second pump having a second inlet and a second outlet. The second pump is arranged in parallel with the first pump, and the first inlet and the second inlet are for fluidically coupling to one or more fluid reservoirs. A control system is coupled to the first pump and the second pump for controlling the operation of the first pump and the second pump simultaneously. The control system is configured to measure a value of a first pressure head at the first outlet, measure a value of a second pressure head at the second outlet, control the first pump to achieve a required output and control the second pump by providing a demand for the second pump to achieve a measured value of the second pressure head which equals the measured value of the first pressure head.
A computer-implemented method comprising determining, on the basis of a change in pressure in a tire of a wheel of an aircraft, whether a transition between Weight on Wheels and Weight off Wheels has occurred at the wheel. Also disclosed is a system for an aircraft, the system comprising a tire pressure monitoring system configured to detect pressure in a tire of a wheel of the aircraft and output a signal indicative of the pressure detected, and a controller configured to receive the signal and determine, on the basis of the signal, whether a transition between Weight on Wheels and Weight off Wheels has occurred at the wheel.
A seat mounting system having a seat rail and a seat fitting, wherein the seat rail has an upper flange with a plurality of heads thereon. The seat fitting comprises a main body having a void configured to receive the upper flange and at least some of the plurality of heads.
A storage tank arrangement, optionally suitable for a vehicle, includes a storage tank for storage of volatile liquids including a tank inner wall and a tank outer wall separated by an insulating inter-wall region, inner and outer feedthrough arrangements, each configured to form a seal with a respective surface of the storage tank arrangement and to permit passage therethrough, and/or permit connection of, of one or more sensors, and a container external of the storage tank outer wall, configured to inhibit egress of the contents of the storage tank in the event of a failure of at least one of the inner and outer feedthrough arrangements. A vehicle including such a storage tank arrangement is also disclosed.
A wing is manufactured from a sub-assembly made up of a structural component such as a wing rib, and a nut. The structural component has a first seating surface for supporting a lower skin of the wing and a second seating surface for supporting an upper skin of the wing. An aperture extends along an aperture axis, through one of the seating surfaces. A nut retention structure of the structural component holds the nut aligned with the aperture, but allows the nut to move laterally relative to the aperture axis so as to accommodate slight misalignment between the aperture and a hole in one of the skins.
A ground detection system for an aircraft based on capacitive sensing. The system comprises an electrode mounted to an aircraft landing gear. As the aircraft landing gear approaches the ground, the electrode and the ground together form a variable capacitor having a capacitance that depends on a distance of the electrode from the ground. Signal processing electronics are used to measure the capacitance and, on the basis of the measured capacitance, determine a distance of the aircraft from the ground.
A method for reducing aerodynamic loads on an aircraft located on the ground includes moving a wing tip relative to a fixed wing to an on-ground configuration in which the span of the wing is reduced. The wing tip includes an airflow channel, which is in an open configuration in which airflow through the channel between upper and lower surfaces of the wing tip is enabled, when the wing tip is in the on-ground configuration. This has been found to reduce aerodynamic loads on the wing tip and/or parts of the aircraft connected thereto during this phase of the aircraft's use.
A vent system includes a vent stack for venting a tank fluid from a fuel tank that is external to the vent stack, during fuelling of the fuel tank. The vent stack includes a conduit including a conduit inlet and a conduit outlet, the conduit outlet opening to atmosphere external to the conduit. The vent stack also includes an opening into the conduit between the conduit inlet and the conduit outlet. The opening is fluidically connected, or connectable, to the fuel tank so the tank fluid from the fuel tank flows through the opening to the conduit outlet, in use. The vent stack also includes a fluid mover operable to cause a mixer fluid receivable in the conduit inlet to flow through the conduit towards the conduit outlet, thereby to mix the mixer fluid with the tank fluid in the conduit, upstream of the conduit outlet.
An applicator for applying an adhesive film to a surface of an aircraft component includes an adhesive inlet for receiving adhesive from a source of adhesive, adhesive outlets for dispensing of adhesive therethrough, one or more reservoirs for receiving adhesive from a respective adhesive outlet, channels wherein at least two of the channels are configured to facilitate delivery of adhesive from the adhesive inlet to a respective, mutually-different outlet, and one or more adhesive-contacting surfaces for contacting adhesive dispensed from the adhesive outlets into the reservoir and for forming an adhesive film therefrom, the one or more adhesive-contacting surfaces being configured to be maintained in spaced relationship with a surface onto which an adhesive film is to be formed.
B05C 5/02 - Apparatus in which liquid or other fluent material is projected, poured or allowed to flow on to the surface of the work from an outlet device in contact, or almost in contact, with the work
B05C 11/02 - Apparatus for spreading or distributing liquids or other fluent materials already applied to a surfaceControl of the thickness of a coating
A method for assembling a component to an aircraft body portion comprises using a funnel device to guide a portion of the component relative to the body portion for movement into a desired position for assembly. Also a funnel device which is configured to be supported by a body portion in a predetermined position and orientation relative to an orifice of the body portion during an assembly process. Also, a pintle mounting portion of an aircraft landing gear assembly is funneled into a predetermined position relative to a pintle mount portion of an aircraft body.
A support apparatus to support a component such as an aircraft landing gear assembly in an installation location for assembly to a body. The apparatus is adapted to assist movement of the supported component in a direction of a vertical axis to reduce an external force necessary to reposition the component from an approximate alignment position into a desired final alignment position. A method of assembly comprising resiliently supporting a component on a platform to assist vertical movement of a mounting portion of the component to align with a mount portion of the body. A pin having a tapered end portion is inserted through an orifice of a pintle mounting and an orifice of a pintle mount to align an aircraft landing gear assembly with a body.
A double-wall pipe for an aircraft fuel system includes an inner wall defining a first open end, a second open end, and an inner region connecting the first open end to the second open end and via which a fuel is flowable through the double-wall pipe, in use. The double-wall pipe includes an outer wall at least in part around the inner wall to define an interspace, between the inner wall and the outer wall, that is fluidically isolated from the inner region. The double-wall pipe includes at least one barrier that is openable to create a passage that fluidically connects the interspace to the inner region. The at least one barrier is configured to open when a pressure in the interspace is higher than a pressure in the inner region.
An aircraft morphable aerodynamic surface structure including an elastomeric material having a glass transition temperature, a temperature management system for heating or cooling the elastomeric material, and a controller to control the temperature management system, the controller configured to control the temperature management system on the basis of a command received at the controller.
A fiber-optic sensor including an optical fiber comprising a first Fiber Bragg Grating (FBG) arranged along a first part of the optical fiber; and a first element disposed on an outer surface of the optical fiber, the first element having a first coefficient of thermal expansion (CTE) different to a CTE of the optical fiber, and being configured to induce a change in strain across the FBG in response to a change in temperature of the fiber-optic sensor in the region of the first FBG, the first element bonded to the optical fiber at two first locations that are separated, along the optical fiber from one another by the first part and unbonded to the optical fiber along the first part.
G01K 11/3206 - Measuring temperature based on physical or chemical changes not covered by group , , , or using changes in transmittance, scattering or luminescence in optical fibres at discrete locations in the fibre, e.g. using Bragg scattering
An avionics unit for an aircraft including a communications interface arranged to interface with one or more other avionics units. The communication interface is arranged to transmit a signal having a first state indicating a fault condition of the avionics unit to the one or more other avionics units if the first state persists for a predetermined time. A processor is arranged to modulate an output at the communication interface to provide a modulated signal to indicate a characteristic of a present state of the avionics unit with respect to the fault condition. The modulated signal includes the first state and a second state, different from the first state, wherein, in the modulated signal, the first state has a duration less than the predetermined time.
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
B60T 7/04 - Brake-action initiating means for personal initiation foot-actuated
H04L 67/12 - Protocols specially adapted for proprietary or special-purpose networking environments, e.g. medical networks, sensor networks, networks in vehicles or remote metering networks
A fuel system includes a chamber for storing a fuel, an optical differential pressure sensor, and one or more processors in communication with the optical differential pressure sensor. The optical differential pressure sensor is fluidically connected to the chamber and is configured to, when the fuel is stored in the chamber, output a signal indicative of a pressure difference in the optical differential pressure sensor to the one or more processors.
A method for assisting with operations to be effected during a phase of movement over the ground in an airport. The method comprises: obtaining, for at least one phase of movement over the ground performed in an airport, by an aircraft of a fleet, data each representative of one event of a list of events, and a geolocation point of the event and a condition of the phase of movement over the ground; determining, for at least one route, an occurrence rate of each event realized on the route, and per geolocation point, solely on the basis of the data for which the condition of the phase of movement over the ground meets a predefined criterion. A datum representative of a determined occurrence rate and of an associated geolocation point are provided. Also a system.
An aircraft has a landing gear that can be extended and retracted and a landing gear control system that is configured so that it can cause extension/retraction of the landing gear of the aircraft in response to pilot operation of a landing gear lever. The control system is also configured such that in the scenario of pilot incapacitation, it can cause extension/retraction of the landing gear of the aircraft in response to an automated command for landing gear extension/retraction. A kit of parts including a relaying unit can be used for converting an existing aircraft to one that has this functionality. There is also a method of automatically extending/retracting landing gear, for example in the event of pilot incapacitation when performing single-pilot operation of the aircraft.
An aircraft wing is provided having a fixed wing with a gulled wing tip rotatably mounted at the tip thereof, the gulled wing tip extending below a wing plane defined by the end of the fixed wing such that the centre of gravity of the gulled wing tip is located below the wing plane. Lowering the centre of gravity of the gulled wing tip has been found to reduce the onset of flutter. The gulled wing tip may be gulled about a hinge axis where it meets the fixed wing, or may be otherwise folded or curved to lower the centre of gravity of the gulled wing tip.
A wing defines a chord which runs from a leading edge to a trailing edge. The wing has a main portion and a flap which is movable relative to the main portion to change the aerodynamics of the wing, for instance to maximize lift, or to reduce drag at the expense of some loss of lift. The wing has a guide mechanism which guides movement of the flap. The guide mechanism uses a pair of runners which run along respective tracks. The tracks are positioned at different locations along the direction of the chord, but overlap one another in the direction of the chord.
In an aircraft wing structure where space and weight considerations are a principal concern, there may be significant challenges in providing a moveable slat and/or a spoiler, particularly in combination with one another. A control device for an aircraft includes upper and lower flaps pivotably mountable adjacent to a slot in a wing behind a leading edge, wherein the control device is operable in a lift configuration to move the upper and lower flaps towards each other to abut opposing surfaces of the slot, to permit airflow along the slot.
A pipe spacer (50) for separating inner and outer pipes of a double- walled pipe assembly, the pipe spacer comprising: an annular body (60) for positioning in an interspace between inner and outer pipes of a double-walled pipe assembly, wherein the annular body (60) defines an axis of the pipe spacer; a plurality of springs (70) extending radially from the annular body (60), wherein each spring (70) is configured to deform inwardly towards the annular body (60) on contact with one of the inner and outer pipes; and a plurality of projecting stops (80) extending from the annular body (60) which are configured to limit the inward deformation of the springs (70).
F16L 39/00 - Joints or fittings for double-walled or multi-channel pipes or pipe assemblies
F16L 7/00 - Supporting pipes or cables inside other pipes or sleeves, e.g. for enabling pipes or cables to be inserted or withdrawn from under roads or railways without interruption of traffic
A pipe spacer 50 for separating inner and outer pipes of a double-walled pipe assembly, the pipe spacer 50 comprising: an annular body 60 for positioning in an interspace between inner and outer pipes of a double-walled pipe assembly, the annular body 60 formed of a composite material; a plurality of outer arms 70a extending radially outwardly from the annular body 60 for contacting the outer pipe and/or a plurality of inner arms 70b extending radially inwardly from the annular body 60 for contacting the inner pipe; and wherein each of the inner and/or outer arms are springs 71 that extend radially from the annular body 60 and are configured to deform inwardly towards the annular body 70 on contact with the respective outer or inner pipe, the arms formed of a composite material.
F16L 7/00 - Supporting pipes or cables inside other pipes or sleeves, e.g. for enabling pipes or cables to be inserted or withdrawn from under roads or railways without interruption of traffic
F16L 39/00 - Joints or fittings for double-walled or multi-channel pipes or pipe assemblies
F16L 3/01 - Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets for supporting or guiding the pipes, cables or protective tubing, between relatively movable points, e.g. movable channels
An aircraft wing is disclosed having a fixed wing with a tip, and a wing tip device rotatably mounted on a hinge at the tip of the fixed wing, such that the wing tip device is rotatable about the hinge, and an actuation system for rotating the wing tip device about the hinge. The actuation system includes a motor, at least one geared rotary actuator, a reduction gearbox, a clutch for selectively decoupling rotation of the motor from rotation of the geared rotary actuator, the geared rotary actuator is driveable by the motor and arranged to convert rotary motion into a different rotary motion and is arranged to rotate the wing tip device relative to the tip of the fixed wing. The reduction gearbox is positioned between the clutch and the geared rotary actuator along a drive train between the motor and the geared rotary actuator.
An aircraft wing is disclosed having a fixed wing with a tip, and a wing tip device rotatably mounted on a hinge at the tip of the fixed wing, such that the wing tip device is rotatable about the hinge, and an actuation system for rotating the wing tip device about the hinge. The actuation system includes a motor, at least one geared rotary actuator, a reduction gearbox, a clutch for selectively decoupling rotation of the motor from rotation of the geared rotary actuator, the geared rotary actuator is driveable by the motor and arranged to convert rotary motion into a different rotary motion and is arranged to rotate the wing tip device relative to the tip of the fixed wing. The clutch is coupled to the geared rotary actuator by a shaft and the shaft is fixed in rotation to a mass disposed radially outwardly from the shaft.
patents
