A ball screw comprising a screw shaft, a ball nut, and alpha and beta load circuits. The alpha and beta load circuits each include first and second parts. The screw shaft is longitudinally extending with a longitudinal central axis (A) and at least part of the longitudinally extending surface of the screw shaft comprises an external thread, and at least one of the first parts of the alpha and beta load circuits comprise a part of the external thread. The ball nut comprises a body, a bore, the second parts of the alpha and beta load circuits, and an alpha and a beta lubricant channel. The bore is defined by the body, is longitudinally extending with a longitudinal central axis (A), has a first and second end, and has at least one longitudinally extending surface extending between the first and second ends.
A ball screw comprising a screw shaft, a ball nut, and a load circuit. The load circuit includes a first and second part. The screw shaft is longitudinally extending with a longitudinal central axis (A) and at least part of the longitudinally extending surface of the screw shaft comprises an external thread. The first part of the load circuit comprises a part of the external thread. The ball nut includes a body, a bore, and the second part of the load circuit, and a lubricant channel. The bore is defined by the body, is longitudinally extending with a longitudinal central axis, has a first and second end, and has a longitudinally extending surface extending at least partially between the first and second ends. The first and second ends of the bore each comprise a mouth, and each mouth opens through an outside surface of the body.
An eddy-current sensor includes an electrically conductive coil, an electrically conductive casing and a separator formed from non-magnetic material. The eddy-current sensor is arranged to sense a distance between the electrically conductive coil and an outer surface of an electrically conductive target, the electrically conductive target separated from the electrically conductive coil along a target spacing direction. The separator is interposed between the electrically conductive coil and the electrically conductive casing. The electrically conductive casing comprises a first portion, positioned outwards of the electrically conductive coil along the target spacing direction and extending perpendicular to the target spacing direction, and a second portion, extending from the first portion along the target spacing direction past at least part of the electrically conductive coil, so as to focus a magnetic field produced by the electrically conductive coil along the target spacing direction.
G01D 5/20 - Mechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using electric or magnetic means influencing the magnitude of a current or voltage by varying inductance, e.g. by a movable armature
4.
COCKPIT CONTROLLER INCEPTOR WITH YAW CONTROL BY LATERAL DISPLACEMENT
A cockpit control inceptor for an aircraft includes an armrest configured to receive the forearm of a user and to be operated by the forearm of the user in at least one direction. A first end of the armrest is coupled to a handle; wherein the armrest is connected to a fixed part of the cockpit control inceptor, wherein the armrest is configured to move relative to the fixed part of the cockpit control inceptor to provide a first aircraft control command.
A blade spar for a rotor blade for a rotor of an aircraft or vessel, preferably wherein the rotor is a propeller, the blade spar comprising a laminate structure. The laminate structure includes a plurality of plies of fibres in a matrix, wherein the blade spar has generally a longitudinal axis defining a longitudinal direction, the longitudinal axis extending along a radial direction of the rotor. The blade spar includes at least a portion that is curved from the longitudinal axis, wherein the plurality of plies comprises a first ply comprising a plurality of first fibres, wherein an alignment of the first fibres varies along the longitudinal direction to align the first fibres to the curved blade spar.
A propeller propulsion system includes: a prime mover having at least one spool, a propeller arranged to be driven by the spool, a pitch adjustment subsystem comprising an electronic control unit and an electronic protection unit, a prime mover speed sensor arranged to detect a rotation speed of the spool; and an additional speed sensor arranged to detect the rotation speed of the spool or arranged to detect a rotation speed of the propeller. A first of the electronic control unit and the electronic protection unit is arranged to use an output from the prime mover speed sensor to determine the rotation speed of the propeller; and a second of the electronic control unit and the electronic protection unit is arranged to use an output from the additional speed sensor to determine the rotation speed of the propeller.
An electromagnetic sensor system and a method for sensing distance to a conductive target. The sensor system has filtering circuitry, a first sensor having a first electromagnetic sensor coil driven with a first alternating current at a first predetermined frequency, and a second sensor having a second electromagnetic sensor coil driven with a second alternating current at a second predetermined frequency. The second predetermined frequency is offset from the first predetermined frequency by an offset amount. The first sensor outputs a first signal having a component that is that is indicative of a distance from the first electromagnetic sensor coil to the conductive target, and the filtering circuitry applies a low-pass filter to the first signal. The low-pass filter has a cut-off frequency that is below the offset amount such that a component of the first signal caused by inductance between the first and second electromagnetic sensor coils is attenuated.
G01B 7/02 - Measuring arrangements characterised by the use of electric or magnetic techniques for measuring length, width, or thickness
G01D 5/20 - Mechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using electric or magnetic means influencing the magnitude of a current or voltage by varying inductance, e.g. by a movable armature
A flight control system for an aircraft. The flight control system includes a thrust lever configured to control a thrust magnitude for the aircraft during flight. The thrust lever is in the form of a control stick that can be moved along a first direction to control the thrust magnitude. The thrust lever is also configured to control a yaw angle of the aircraft during flight. The control stick, or at least a portion of the control stick, can be twisted to control the yaw angle of the aircraft.
A sensing system and a method of sensing. The sensing system has a sensor apparatus and a target portion for sensing by the sensor apparatus. The target portion is integral with, or configured for coupling to, a component of an assembly so as to translate along an axis, and the target portion has an outer surface which has a profile that changes with distance along the axis. The sensor apparatus is configured for non-translating mounting adjacent the target portion, and has at least one distance sensor. The method comprises sensing a distance between the distance sensor and the outer surface of the target portion, wherein the sensed distance varies as the target portion translates axially, and outputting a signal in dependence on the sensed distance.
G01D 5/20 - Mechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using electric or magnetic means influencing the magnitude of a current or voltage by varying inductance, e.g. by a movable armature
A flight control system for an aircraft. The aircraft has a set of principle axes including a roll axis and a pitch axis. The flight control system includes a control stick that is configured to move forwards and backwards and left and right to control movement of the aircraft about its roll and pitch axes, such movement of the control stick thus providing a first set of inputs to the flight control system. The control stick includes a further input in the form of a moveable element that can be moved between a range of positions and that is configured to provide a graduated input to the flight control system based on the position of the moveable element relative to a default position of the moveable element, the moveable element being positioned on a side or front portion of the control stick.
A pitch control system includes: a coarse pitch pressure circuit configured to receive a pressurised fluid; a pitchlock mechanism configured to pitchlock a propeller blade of a propeller; and a controller configured to detect undesired feathering of a propeller blade. The controller is configured to, in response to detecting undesired feathering of the propeller blade, reduce the pressure of the pressurised fluid received by the coarse pitch pressure circuit so as to stop the propeller blade feathering and simultaneously cause the pitchlock mechanism to pitchlock the propeller blade.
A control system for an aircraft. The control system includes: an inceptor operable by a pilot; an actuator configured to generate a force on the inceptor; a first sensor configured to measure an acceleration of the control system; and a control unit configured to: determine an acceleration force on the inceptor based on the measured acceleration; and modify the force generated by the actuator based on the acceleration force.
G05G 9/047 - Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks
A rotary blade includes one or more structural beams extending generally in a direction from a root end of the blade to a tip of the blade, a shell enclosing the one or more structural beams and defining the outer shape of the blade, wherein the one or more structural beams is made of a thermoplastic material and the shell is formed of a fibrous material. The blade includes a thermoset resin injected into the shell fibrous material to strengthen the shell and to bond the shell to the one or more beams.
A variable pitch aircraft propeller assembly includes: a plurality of propeller blades and at least one counter-weight arrangement mounted on a propeller blade. The counter-weight arrangement comprises: a first counter-weight and a second counter-weight. The counter-weights are arranged such that when the propeller blade is in fine pitch, the counter-weights are in a first position with respect to the plane of rotation of said propeller blade, and when the propeller blade is substantially feathered, the counter-weights are in a second position with respect to the plane of rotation of said propeller blade. The counter-weights are aligned such that a line drawn between the center of mass of the first counter-weight and the center of mass of the second counter-weight is substantially perpendicular to a longitudinal axis of the propeller blade.
A blade pitch control and protection system for a propeller includes: an actuator where displacement of said actuator corresponds to a change in blade pitch of said propeller; an electronic unit, a position control sensor configured to interact with said actuator. The position control sensor detects actuator position and thereby said blade pitch of said propeller, and to send a control feedback signal to said electronic unit via a first channel, based on said blade pitch, and a protection sensor configured to interact with said actuator, configured to detect actuator position and thereby said blade pitch of said propeller, and to send a protection feedback signal to said electronic unit via a second channel, based on said blade pitch. The electronic unit is configured to, based on said control feedback signal, control movement of said actuator to alter said blade pitch through a control command.
An apparatus for adjusting aircraft inceptor trim includes an inceptor centring device mechanically coupled to a control shaft that rotates in response to inceptor inputs. The inceptor centring device includes an inceptor centring spring preloaded with a preload force to provide a first biasing force to bias the control shaft to an inceptor neutral position. The apparatus has a trim mechanism, mechanically coupled to the inceptor centring device, and includes a trim locking device having a locked state and an unlocked state. A resistance force of the trim mechanism with the trim locking device in the unlocked state is less than the preload force, such that when the trim mechanism is in the unlocked state, actuation of the inceptor adjusts the position of the inceptor centring device to alter the degree of trim.
An aircraft flight control apparatus includes a control input device comprising a moveable control input component and a feeling feedback apparatus. A processing apparatus is arranged to use user information to determine a control input profile and generate at least one aircraft control signal and/or control the feeling feedback apparatus to apply force to the control input component. The processing apparatus is arranged to generate the at least one aircraft control signal and/or control the feeling feedback apparatus based at least partially on the control input profile.
A control mechanism for an aircraft includes: a conversion mechanism having a translatable part and a rotatable part, the translatable part being reversibly translatable and being connectable to an inceptor; an inceptor connector connected to the translatable part of the conversion mechanism; a differential device connected to the rotatable part of the conversion mechanism, the conversion mechanism being configured to reversibly convert translational motion of the inceptor connector to rotational motion of the differential device; an adjustment member connected to the differential device; and a control member connected to the differential device; wherein the differential device is configured such that the adjustment member is maintainable in position during an aircraft control process to permit: translation of the inceptor connector from a translational neutral position; and corresponding movement of the control member, to control the aircraft through the differential device.
A method of performing health monitoring for an aircraft having a variable pitch propeller system. The method includes: receiving aircraft flight information; performing a virtual pitch calculation to determine a virtual propeller pitch or virtual blade angle from the aircraft flight information; receiving a measured propeller pitch or blade angle from at least one physical sensor associated with the propeller; and using the virtual propeller pitch or virtual blade angle and the measured propeller pitch or blade angle to perform a health monitoring process to determine a health condition of at least one component of the aircraft, wherein the at least one component is distinct from the blades.
A method of operating a variable pitch propeller system for an aircraft. The method includes: receiving aircraft flight information; performing a virtual pitch calculation to determine a virtual propeller pitch or virtual blade angle from the aircraft flight information; and performing a pitch protection process in response to low virtual propeller pitch or virtual blade angle being determined.
An assembly for maintaining the pitch angle of a flight control surface for an aircraft. The assembly includes a shaft comprising a screw thread and defining a shaft axis, and a nut. The nut includes a housing, a barrel located in the housing and comprising a screw thread for engaging with the screw thread of the shaft, and at least one locking element located in the housing. The housing comprises a radially inner cam surface adjacent to the locking element. The barrel is configured to rotate relative to the housing when the screw thread of the barrel is engaged and rotating with the screw thread of the shaft so as to move the locking element along the cam surface from a disengaged position in which the locking element is spaced from the screw thread of the shaft, to an engaged position.
A method of operating a propeller system for an aircraft. The method includes: receiving propeller speed information, the propeller speed information indicating propeller speed; receiving a target propeller speed; performing a propeller speed threshold adjustment process, the propeller speed threshold adjustment process comprising adjusting a propeller speed threshold as a function of the target propeller speed; comparing the propeller speed to the propeller speed threshold; and in response to propeller speed exceeding the propeller speed threshold, performing an overspeed protection process.
A resistive and locking system for locking rotation of a shaft. The system includes a housing defining an axis AX therethrough. The housing includes a drive shaft mounted in the housing and extending axially from a bottom end of the housing and a first stage comprising a resistive mechanism provided in the housing. The housing also includes a second stage comprising a locking mechanism arranged in the housing above the first stage. The locking mechanism is biased axially to frictionally engage with and lock the first stage mechanism to prevent rotation of the drive shaft, the locking mechanism including a magnetic unlocking mechanism configured to remove the frictional engagement with the first stage on application of power to the locking mechanism.
A multi-layer braided article and a method of making the multi-layer braided article. The multi-layer braided article includes a braid extending along a first axis, wherein the braid is folded over itself to form a first layer and a second layer; and a wrapper laid over the first layer of the braid and extending circumferentially around the first axis, wherein the wrapper defines an edge of the first layer about which the braid is folded. The multi-layer braided article may form part of a blade for an aircraft. A sleeve may be provided around a conical portion of the article to connect the article to something else, such as a propeller hub, where the multi-layer braided article is formed as part of a blade. The sleeve may provide a primary or secondary load path.
A pedal cartridge for an aircraft. The pedal cartridge is connectable to a pedal mechanism and includes: a pedal. The pedal includes a pedal axle receiving portion configured to receive a pedal axle of the pedal mechanism such that the pedal is rotatably connectable to the pedal axle. The mechanism also includes a first rotation sensor component, the first rotation sensor component configured to interact with a second rotation sensor component of the pedal mechanism to permit rotation of the pedal about the pedal axle to be detected.
A pedal mechanism for an aircraft. The pedal mechanism includes: a pedal arm connectable to a pedal at a pedal connection point, the pedal arm rotatable about a pedal arm rotation point on translation of the pedal; and a stature adjustment mechanism, the stature adjustment mechanism actuatable, during a stature adjustment process, to move the pedal arm rotation point.
A propeller blade comprising a composite member. The composite member comprises a stack of plies and a matrix in which the stack of plies is embedded. At least one ply comprises a plurality of first yarns aligned in a first direction defining a plane of the ply and a plurality of second yarns extending transverse to the plane of the ply. Each second yarn does not extend through more than one ply. Also provided is a propelling system comprising the propeller blade, a composite propeller blade prepreg, and a method of forming a propeller blade.
B29C 59/16 - Surface shaping, e.g. embossingApparatus therefor by wave energy or particle radiation
B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
28.
METHOD FOR GENERATING A TOOL PATH FOR ENGRAVING ON VARIOUS SHAPED SURFACES
A computer-implemented method of generating a toolpath for engraving at least one character on a surface of a workpiece. The method includes: receiving, by a post processor, PP, information pertaining to: the shape of the surface to be engraved on the workpiece; an area to be engraved on the surface of the workpiece; and at least one character to be engraved on the surface of the workpiece. Then, the method includes generating, by the PP, a toolpath for engraving the at least one character on the surface of a workpiece by: mapping a pre-stored predefined reference 2D toolpath of each character to be engraved on the surface onto the surface to be engraved according to the received information.
G05B 19/4097 - Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by using design data to control NC machines, e.g. CAD/CAM
G05B 19/414 - Structure of the control system, e.g. common controller or multiprocessor systems, interface to servo, programmable interface controller
A motor system includes a brushless motor with a stator, a rotor having a first number of rotor poles, and a motor shaft connected to the rotor. The motor system also includes control electronics configured to control a brushless motor that has a second, number of rotor poles, different from the first number of rotor poles. The second number of rotor poles is an integer multiple, N, of the first number of rotor poles. A position sensor is communicatively connected to the control electronics. A first gear is mounted on the motor shaft and connected for rotation with the motor shaft, the first gear having a first number of teeth. A second gear is engaged with the first gear, the second gear having a second number of gear teeth. The position sensor is configured to detect an angular position of the second gear and provide it to the control electronics.
A gear assembly for a side stick on an aircraft. The gear assembly includes a first gear, a second gear configured to engage with the first gear, and a viscoelastic material provided in the first gear.
A screw actuator includes a primary ball nut, a secondary nut, and a ball screw. The primary ball nut and secondary nut are both in threaded engagement with the ball screw, in which the inner functional plays of the screw actuator are configured such that in normal operation the threads of the secondary nut are in contact with the ball screw threads.
A throttle control lever suitable for controlling the magnitude and direction of thrust of one or more aircraft engines is described. The throttle control lever comprises a frame, a trigger mechanism, a connection element, a cam engagement mechanism, a biasing means, a cam, and a grip suitable for gripping by a user when the throttle control lever is in use, The cam comprises a slot having first and second slot portions and a stop portion. The stop portion extends between and connects the first and second slot portions. The cam engagement mechanism comprises a cam lever and a slot engagement element, the cam lever is pivotally attached to the frame via a cam lever pivot, and the slot engagement element is attached to the cam lever. The trigger mechanism comprises a trigger lever and a trigger, the trigger lever is pivotally attached to the frame via a trigger pivot.
A piloting device for piloting an aircraft includes a piloting member suitable for being actuated by a pilot, a mechanism for mounting and guiding in rotation the piloting member about at least one rotation axis with respect to a frame, at least one force sensor connected between the piloting member. The mechanism includes at least one sensing element configured to produce a signal upon deformation indicative of a force applied to the piloting member. The force sensor comprises at least one pair of bearing surfaces. The device also includes at least one pair of stops configured to limit the angular amplitude of rotation of the piloting member with respect to the frame on abutment of the at least one pair of bearing surfaces with at least one pair of stops. The stops or at least one of the bearing surfaces comprises a compliant material.
G05G 5/04 - Stops for limiting movement of members, e.g. adjustable stop
G05G 9/047 - Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks
The brake assembly includes a housing, a rotor disc. The rotor disc includes at least one internal cavity. The at least one internal cavity includes a pawl and a thermal fuse. In use, the thermal fuse is configured to maintain the position of the pawl in the at least one internal cavity when a temperature is below a predetermined threshold, and wherein the thermal fuse is configured to melt when a predetermined threshold of temperature is reached during braking to release the pawl out of the at least one internal cavity towards the housing. The housing includes at least one recess configured to receive the pawl.
F16D 9/08 - Couplings with safety member for disconnecting by breaking due to shear stress over a single area encircling the axis of rotation, e.g. shear necks on shafts
F16D 63/00 - Brakes not otherwise provided forBrakes combining more than one of the types of groups
A torque limiter device includes an input shaft having a first contact surface and an output shaft having a second contact surface. The input and output shafts are operable in an engaged position and a disengaged position A biasing mechanism provides a bias force that mechanically biases the input and output shafts in one of the positions and sets a threshold torque. An electromagnet is arranged to selectively provide an electromagnetic force that opposes the bias force when an activation current is supplied. A controller determines a difference in rotations of the shafts and selectively supply the activation current to the electromagnet so as to disengage the input and output shafts when the rotation difference exceeds a threshold. Each of the contact surfaces comprises one or more grooves, wherein at least one rotatable member is disposed in at least one of said grooves.
F16D 27/112 - Magnetically-actuated clutchesControl or electric circuits therefor with an electromagnet not rotating with a clutching member, i.e. without collecting rings with axially movable clutching members with flat friction surfaces, e.g. discs
F16D 27/00 - Magnetically-actuated clutchesControl or electric circuits therefor
A pitch change actuation system for varying a propeller blade pitch includes: an actuator body defining an interior volume; and a chamber separator located within the interior volume of the actuator body and dividing the interior volume into a first chamber and a second chamber, the two chambers being fluidly separated by the chamber separator. The first and second chambers are configured to receive hydraulic fluid. The actuator body is configured to translate relative to the chamber separator in response to a difference in hydraulic pressure between the first chamber and second chamber; and the translation of the actuator body is configured to effect a change in propeller blade pitch.
B64C 11/38 - Blade pitch-changing mechanisms fluid, e.g. hydraulic
B64C 27/64 - Transmitting means, e.g. interrelated with initiating means or means acting on blades using fluid pressure, e.g. having fluid power amplification
A method of calculating and outputting pressure information about the status of an actual pressure of a gas bottle of a door damper at 200 C, performed on a smart device. The method includes receiving, from a non-compensated pressure gauge, a pressure input indicating an actual pressure of said gas bottle of said door damper at ambient temperature, receiving a temperature input indicating an actual temperature of said gas bottle of said door damper, and using said inputs to calculate and convert said actual pressure of said gas bottle of said door damper at ambient temperature to a pressure at a temperature of 200 C, and further comprising outputting pressure information about the status of the gas bottle of said door damper based on said converted pressure at 200 C.
G01L 19/08 - Means for indicating or recording, e.g. for remote indication
G01J 5/10 - Radiation pyrometry, e.g. infrared or optical thermometry using electric radiation detectors
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
The present disclosure provides a coated aircraft propulsion system component, in particular an aircraft blade, comprising a coating applied to at least a part of said aircraft propulsion system component, wherein said coating comprises a polymer matrix material, an inorganic filler, an organic filler, and a lamellar filler, and a method of preparing the same.
A pivot assembly for a control lever. The pivot assembly include a primary pivot bearing arranged about a longitudinal axis (A) and a redundant pivot bearing arranged about the longitudinal axis (A). The redundant pivot bearing is configured to become operative as a bearing in the event that the primary pivot bearing malfunctions, and to produce haptic feedback in the control lever throughout operation of the redundant pivot bearing.
A brake for an aircraft includes a housing, a shaft defining an axis (X) and extending into the housing, a floating brake disk on the shaft, the brake disk fixed for rotation with the shaft and arranged to be axially movable within the housing, a static brake pad arranged on a first side of the floating brake disk, a movable brake pad arranged on a second, opposite, side of the floating brake disk and biasing means for moving the movable brake pad relative to the housing to press the movable brake pad against the floating brake disk. The biasing means press the floating brake disk against the static brake pad to apply braking force to the floating brake disk. The brake also includes a thermal fuse in thermal contact with the static brake pad. The thermal fuse has a fusing temperature, T, above which the thermal fuse fuses.
A control lever assembly for controlling an aircraft system. The lever includes: a housing having an outer side and an aperture defined by a rim; and a control lever extending through the aperture and movable in the aperture; the control lever having an outer cover member arranged to slide over the outer side of the housing and cover the rim throughout the range of movement of the control lever.
G05G 9/047 - Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks
A strain gauge assembly includes: a strain gauge comprising a plurality of resistive elements connected as a Wheatstone bridge or half Wheatstone bridge; an excitation signal generator arranged to provide an excitation signal to two resistive elements of the strain gauge; phase shifting circuitry arranged to determine phase shifts in the excitation signal responsive to changes in resistance of the two resistive elements and an end stage configured to output a measure indicative of the phase shift as an indication of strain on the assembly.
G01L 1/22 - Measuring force or stress, in general by measuring variations in ohmic resistance of solid materials or of electrically-conductive fluidsMeasuring force or stress, in general by making use of electrokinetic cells, i.e. liquid-containing cells wherein an electrical potential is produced or varied upon the application of stress using resistance strain gauges
A pneumatic release system has an inlet arranged to be connected, in use, to a supply of pressurised fluid, and an outlet arranged, to be connected, in use, to an end device. The system defines therethrough, a flow path for fluid from the inlet to the outlet. The system includes a piston mounted in and axially moveable relative to a cylinder, the inlet and outlet defined in the cylinder. The piston has a piston end on which are mounted upper and lower seals and is biased to a first closed position, in which the upper and lower seals define a chamber within the cylinder to retain pressurised fluid from the inlet, the upper seals preventing flow of the fluid from the chamber to the outlet, and wherein an external force applied to the piston moves the upper seals away from sealing engagement with the cylinder.
An asynchronous first device in communication with an asynchronous second device. The time for the first device to complete a processing cycle is a first device major frame and the first device major frame comprises a first device dedicated processing time slot at the end of the first device major frame. The first device is configured to send a rescheduling signal to the second device when it has completed a first device major frame. The first device is configured, during every first device dedicated processing slot, to: monitor for a rescheduling signal sent from the second device to the first device; and if a rescheduling signal from the second device is received: reschedule the current first device major frame to a rescheduled first device major frame; wherein the end of the rescheduled first device major frame coincides with the time the rescheduling signal from the second device was received.
A dust retainer for a brake system comprising a retainer receptacle mounted integrally to one or more components of the brake assembly, wherein the retainer receptacle comprises a drum have first and second open ends, one open end being secured to a component of the brake system and the other open end being closed by a dust retainer cap, the drum defining a space within which a brake disk of the brake system is located, in use, wherein removal of the dust retainer cap allows the brake disk to be removed from the open end of the retainer drum, and a removable drawer integrated in the drum. A fastening means to removably secure brake components to each other is also disclosed.
F16D 55/24 - Brakes with substantially-radial braking surfaces pressed together in axial direction, e.g. disc brakes with a plurality of axially-movable discs, lamellae, or pads, pressed from one side towards an axially-located member
A brake disk defines an annular shape having a radially inner side and a radially outer side. The brake disk includes: a radially outer braking surface, the braking surface having a maximum operating temperature; a fusible material section radially inward from and connected to the braking surface. The fusible material has a maximum operating temperature, the fusible material section suitable for transmitting torque between the braking surface and a shaft. The maximum operating temperature of the braking surface is higher than the maximum operating temperature of the fusible material section. When the temperature of the fusible material section raises above the maximum operating temperature of the fusible material section, the fusible material section is configured to no longer transmit torque between the braking surface and the shaft.
A device for assisting the opening and closing of a door in a structure. The device may comprise: a door shaft configured to rotate about a longitudinal axis thereof in both a first direction and in a second opposite direction, and configured to be mounted to the structure to form a hinge about which the door may rotate in the both the first and second directions relative to the structure; a first actuator linked to the door shaft and configured to control a speed of rotation of the door shaft in the first direction; and a second actuator linked to the door shaft and configured to drive rotation of the door shaft in the second direction. The second actuator is an electromechanical actuator.
A blade pitch control assembly includes a pitch control actuator having a coarse actuator chamber having a coarse chamber area and a fine actuator chamber having a fine chamber area. The coarse chamber area is biased to a feather position. The assembly also includes a primary pitch control valve configured to control the flow of pressurised fluid to the coarse actuator chamber and the fine actuator chamber, respectively via a coarse fluid line and a fine fluid line. The assembly further includes a hydraulic protection system located between the actuator and the primary pitch control valve, configured to bypass the primary pitch actuator in response to a trigger. The hydraulic protection system has a hydraulic protection system valve located between the fluid lines and when activated fluidly connects the fluid lines to balance fluid pressure between the coarse chamber and the fine chamber.
A thrust bearing includes cylindrical rollers arranged circumferentially in a bearing race with their rotational axes pointing radially to the central axis of the thrust bearing and each having a contact surface extending around and lengthwise of the cylindrical roller. The rollers includes at least pairs of radially adjacent first rollers with a radially inner first roller of each pair arranged with its rotational axis in alignment with the rotational axis of a radially outer first roller of the pair. The rollers also includes second rollers with at least one such second roller being arranged between adjacent pairs of first rollers in the circumferential direction, the at least one second roller being offset in the radial direction relative to the radially outer first rollers between which it is circumferentially arranged.
F16C 19/30 - Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for axial load mainly
A propeller blade comprises a root, a tip distal from the root, a trailing edge extending from the root to the tip, a trailing edge, e.g. foam, insert, a shell forming an outer surface of the propeller blade and a plurality of stitches of yam extending through two parts of the shell adjacent the trailing edge, wherein the yarns do not extend through the trailing edge insert.
B23P 15/04 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
A serial communications bus system comprising a plurality of end users arranged to transmit data on a common data bus, each end user provided with a bus arbiter, physically separate from the respective end user, configured to define, for that end user, a cycle of transmission enable intervals whereby the end user may transmit data on the data bus and transmission disable intervals whereby the end user may not transmit data on the data bus.
A flight control actuator for actuating an aircraft flight control system is provided. The flight control actuator comprises a gearbox, an output shaft attached to the gearbox and an output lever provided on the output shaft. The output lever is declutchable from the output shaft. The output lever includes an inner diameter through which the output shaft passes and at least one indentation in said inner diameter. The output shaft includes a hollow cylindrical member with at least one hole provided at the axial position of the at least one indentation of the output lever.
A multi-layer braided article and a method of making the multi-layer braided article. The multi-layer braided article includes a braid extending along a first axis, wherein the braid is folded over itself to form a first layer and a second layer; and a wrapper laid over the first layer of the braid and extending circumferentially around the first axis, wherein the wrapper defines an edge of the first layer about which the braid is folded. The multi-layer braided article may form part of a blade for an aircraft. A sleeve may be provided around a conical portion of the article to connect the article to something else, such as a propeller hub, where the multi-layer braided article is formed as part of a blade. The sleeve may provide a primary or secondary load path.
A system for monitoring propeller health includes a processing unit having a processor which is programmed to apply a plurality of algorithms to inputted aircraft parameter data. The system also includes a plurality of data inputs for inputting aircraft parameter data into the algorithms, wherein the processor is configured to apply the physics based algorithms to the aircraft parameter data to determine at least the fatigue life consumption of one or more critical components of a propeller. In addition, the system includes an output device which is able to output an indication of the determined fatigue life consumption to an observer.
A propeller blade arrangement comprising a propeller blade attached to and rotatable with a hub, via a retention bearing, the blade being rotatable about a center line of the blade, the retention bearing configured to tilt the blade such that its center line is tilted with respect to the hub.
An aircraft inceptor system includes an inceptor member arranged to be operated by a user to cause a corresponding movement of a moveable aircraft surface. The system also includes means for detecting the operation of the inceptor member by the user and for providing a movement signal, associated with the detected operation, to a flight control computer, the flight control computer providing a control signal to an actuator to move the aircraft surface according to the movement signal. The means for detecting the operation of the inceptor member by the user comprises a force sensor configured to sense the force applied by the user to the inceptor member, the movement signal being derived based on the sensed force.
A blade de-icing system for a blade to be de-iced that has a body extending between a leading edge and a trailing edge, said leading edge ending at an apex. The system includes a de-icer component having a recess formed therein and being positioned on said leading edge of said blade so that said de-icer component covers and extends away from said apex and so that said recess is positioned at said apex of said leading edge; and an anti-erosion strip provided in said recess of said de-icer component; wherein said anti-erosion strip and said recess are sized and shaped such that said anti-erosion strip fits within said recess so that outer surface of said anti-erosion strip is flush with the outer surface of said de-icer component. A method of manufacturing the same is also described herein.
A blade pitch actuation mechanism comprising a rotating race member in which is formed a race configured to receive a trunnion pin attached to a blade, whereby the race defines a cam profile such that rotation of the race member causes the trunnion pin received in the race to rotate as it slides over the cam profile.
A torque limiter device includes an input shaft having a first contact surface and an output shaft having a second contact surface. The input and output shafts are operable in an engaged position wherein the contact surfaces are brought into mechanical engagement, and a disengaged position wherein the contact surfaces are separated. A biasing mechanism provides a bias force that mechanically biases the input and output shafts in one of the positions and sets a threshold torque. An electromagnet is arranged to selectively provide an electromagnetic force that opposes the bias force when an activation current is supplied. A rotation sensor arrangement measures a respective rotation of the input shaft and of the output shaft. A controller determines a difference in rotations of the shafts and selectively supply the activation current to the electromagnet so as to disengage the input and output shafts when the rotation difference exceeds a threshold.
F16D 27/112 - Magnetically-actuated clutchesControl or electric circuits therefor with an electromagnet not rotating with a clutching member, i.e. without collecting rings with axially movable clutching members with flat friction surfaces, e.g. discs
F16D 27/00 - Magnetically-actuated clutchesControl or electric circuits therefor
A propeller health monitoring system for an aircraft includes an aircraft having one or more propellers that includes light in or on them. The system includes one or more receptors mounted to a fuselage or a nacelle of the aircraft, each receptor having a sensor surface which is able to detect a position for each light beam crossing over the sensor surface as the propeller rotates, such that the receptor generates a signal that is indicative of the position as a measure of blade tip trajectory for each passing propeller blade The system also includes a processing unit which analyses the signals from the receptor to determine health of the propeller blades of the one or more propellers based on where the beams of light from the propeller blades have crossed over the sensor surface.
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided forHandling, transporting, testing or inspecting aircraft components, not otherwise provided for
G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings
An emergency actuation device for opening a door, the emergency actuation device includes: at least one pressurised gas supply; an actuator including: an actuator chamber, an actuator piston moveable between a retracted position and a fully extended position to open the door, a vent for venting the actuator chamber when the actuator piston is in its extended position. The emergency actuation device further includes a percussion device including a percussion piston moveable on activation of the percussion device between: a storage position in which the pressurised gas supply is isolated from the actuator and an activated position in which the pressurised gas supply is coupled to the actuator. The actuator is coupled to the percussion device; and the actuator is configured such that movement of the actuator piston towards its activated position resets the percussion piston.
A method of applying a braided cover to a core comprises braiding a plurality of tows around the core from a plurality of bobbins. One or more properties of the tow on a respective bobbin vary along the length of the tow.
A screw actuator comprises a nut having an internal helical formation and a screw having an external helical formation and rotatably received within the nut, relative rotational movement of the nut and screw causing axial movement of one of the nut and screw relative to the other of the nut and screw. The actuator further comprises a lubricant reservoir and a lubricant pressuriser for pressurising lubricant within the lubricant reservoir. A lubricant receiving chamber is formed in the nut. The screw extends through the lubricant receiving chamber. A lubricant supply passage fluidly connects the lubricant reservoir and the lubricant receiving chamber. A valve controls the flow of lubricant between the lubricant reservoir and the lubricant receiving chamber. A lubricant supply piston is received in the lubricant receiving chamber and is mounted on the external helical formation of the screw.
A lubrication system comprises a lubricant reservoir, a lubricant supply passage fluidly connecting the lubricant reservoir and a space requiring lubrication, and a lubricant supply pump. The supply pump includes a piston having a first piston head slidably received in a chamber in fluid communication with the lubricant reservoir and a second piston head slidably received in a pumping chamber. The pumping chamber is divided into a first and second cavities by the second piston head. The first cavity is between the first piston head and second piston head. The first and second cavities are placeable in fluid communication with pressure sources externally of the pumping chamber to provide a pressure differential between the first cavity and the second cavity, whereby the piston may move as a result of the pressure differential to cause the first piston head to dispense lubricant from the lubricant reservoir to the space.
F16N 7/38 - Arrangements for supplying oil or unspecified lubricant from a stationary reservoir or the equivalent in or on the machine or member to be lubricated with a separate pumpCentral lubrication systems
F16N 13/16 - Actuation of lubricating-pumps with fluid drive
A rotating assembly such as a counter-rotating propeller system or a turbofan includes a first rotating part rotatable relative to a second part, the first and second parts mounted on a common axis, a combustion engine arranged to rotate the first part, and an electric motor connected to drive the second part. In a first drive mode, the combustion engine rotates the first part in first direction relative to the axis while the electric motor drives the second part in a second, opposite direction relative to the axis and in a second drive mode, the combustion engine rotates the first part in the first direction and the electric motor does not drive the second part in the second, opposite direction.
A system for providing pressure/load control at an end stroke stop is provided. The system includes an actuator housing having an end stroke stop and a first actuator housing side, an actuator piston provided in the actuator housing, wherein the actuator piston is movable along a longitudinal axis (A), the actuator piston having a first piston portion perpendicular to the longitudinal axis (A), and means for regulating the pressure/load control at the end stroke stop provided in the first piston portion, wherein the means for regulating the pressure/load control at the end stroke stop is configured to move from a closed position to an open position when in contact with the first actuator housing side.
F15B 15/22 - Other details for accelerating or decelerating the stroke
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
There is provided a system comprising a brushless DC (“BLDC”) electric motor for a propeller engine and a motor controller. The motor comprises a rotor including one or more permanent magnets and one or more alternator windings, and a stator including one or more stator windings. The controller is configured to apply a first, transient DC voltage to the windings of the stator, wherein the first, transient DC voltage is configured to provide commutation switching for the windings of the stator so as to generate a torque on the rotor. The controller is further configured to apply a second, static DC voltage to the windings of the stator, wherein the second, static DC voltage is configured to induce an electric current in the alternator windings so as to generate an AC voltage in the alternator windings.
A gearbox assembly comprising a plurality of component parts in torque transmission connection via gear, shaft and/or housing components; the assembly further comprising means for providing redundancy at selected locations where failure can lead to loss of torque transmission between component parts of the assembly.
F16H 57/03 - GearboxesMounting gearing therein characterised by means for reinforcing gearboxes, e.g. ribs
F16H 1/22 - Toothed gearings for conveying rotary motion without gears having orbital motion involving more than two intermeshing members with a plurality of driving or driven shaftsToothed gearings for conveying rotary motion without gears having orbital motion involving more than two intermeshing members with arrangements for dividing torque between two or more intermediate shafts
F16H 57/021 - Shaft support structures, e.g. partition walls, bearing eyes, casing walls or covers with bearings
A field programmable gate array (FPGA) having at least first and second processing circuits implemented thereon. Each of the first and second processing circuits comprises a numerical core and associated peripheral components. The numerical core in the first processing circuit is dissimilar to the numerical core in the second processing circuit. The first and second processing circuits are segregated from each other in floorplan view.
A brush assembly for transmitting electrical power to a rotating component includes one or more electrically conductive brushes, a housing configured to receive the one or more brushes and hold the one or more brushes in alignment with an opposing surface, and one or more brush carriers. Each carrier is configured to receive and clip onto a respective brush such that each of the one or more brushes can be removed from its respective carrier by unclipping the carrier from the brush.
There is provided an hydraulic actuation system for an aircraft, the hydraulic actuation system includes an actuator (A), a primary actuation arrangement to provide hydraulic fluid to control the actuator (A), wherein the hydraulic actuation system is configured to detect a fault in the actuator (A). The hydraulic actuation system also includes a secondary actuation arrangement to provide hydraulic fluid to control the actuator (A) in response to a detection of a fault in the actuator (A).
A method and system for simulating pilot controls in a cockpit simulator by controlling one or more arms on which is/are mounted a control grip, pedal or the like, to locate the grip at different positions and allow movement of the grip in a plurality of movement directions and trajectories while allowing varying force feedback.
G06F 3/01 - Input arrangements or combined input and output arrangements for interaction between user and computer
G09B 9/10 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer with simulated flight- or engine-generated force being applied to aircraft occupant
G09B 9/16 - Ambient or aircraft conditions simulated or indicated by instrument or alarm
A rotary position sensor is includes a static portion that comprises a first board and a second board and a rotatable portion that comprises a third board. The second board comprises a first planar coil; and the third board comprises a second planar coil as well as means for generating luminance. The first board comprises means for receiving the generated luminance and the first planar coil of the second board is configured to transmit power to said second planar coil of said third board via inductance. The power received by said second planar coil is configured to supply a current to said means for generating luminance; and said means for generating luminance is configured to emit a luminance signal which has a luminance level.
G01D 5/26 - Mechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using optical means, i.e. using infrared, visible or ultraviolet light
A position sensing system for sensing a position of an input shaft of a variable differential transformer (VDT), comprising said VDT, which comprises first and second AC signal output means that are configured to output a first AC output signal and a second AC output signal respectively. The sensing system further comprises AC/DC converting means configured to convert said first AC output signal to a first DC output signal and an AC/DC converting means configured to convert said second AC output signal to a second DC signal. The first and second DC output signals each indicate an individual position of said input shaft.
G01D 5/22 - Mechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using electric or magnetic means influencing the magnitude of a current or voltage by varying inductance, e.g. by a movable armature differentially influencing two coils
H01F 21/04 - Variable inductances or transformers of the signal type continuously variable, e.g. variometers by relative movement of turns or parts of windings
An actuator assembly may comprise a screw shaft having a shaft axis; a drive arrangement pivotally supported about the screw shaft axis for driving the screw shaft, e.g., about the shaft axis or along the shaft axis, and a rod mounted to the drive arrangement at a location off the shaft axis for providing a primary function of reacting torque about the shaft axis on the drive arrangement. The rod may comprise a rod axis and provide a load path along the rod axis for reacting torque. The rod may also comprise a device for which provides a secondary function for the actuator assembly based on the load experienced along the load path provided by the rod.
B64C 13/28 - Transmitting means without power amplification or where power amplification is irrelevant mechanical
G01L 5/00 - Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
F16H 57/025 - Support of gearboxes, e.g. torque arms, or attachment to other devices
G01L 1/26 - Auxiliary measures taken, or devices used, in connection with the measurement of force, e.g. for preventing influence of transverse components of force, for preventing overload
F16H 57/01 - Monitoring wear or stress of gearing elements, e.g. for triggering maintenance
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
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
A propeller blade comprises a composite blade spar and at least one cover shell section adhesively bonded to the blade spar by a thermoplastic adhesive.
A gas distribution assembly for providing gas to an actuator for opening an aircraft door and to an aircraft evacuation slide, the assembly comprising a single common gas supply and valve means for controlling distribution of gas from the common supply between the slide and the door actuator based on door opening position.
A multiplexer switching device is described herein comprising a first data network comprising a plurality of NO contacts; and a second data network comprising a plurality of NC contacts; wherein said a first data network is connected to said second data network via a common DC voltage link.
G05G 9/047 - Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks
H01H 25/04 - Operating part movable angularly in more than one plane, e.g. joystick
A magnetic position sensor for determining the angular position of a magnet on a rotatable component, comprising: at least one magnetic sensor for determining different vector components of a magnetic field of the magnet; a memory having a look-up table stored therein that is populated with data representative of different angular positions of the magnet, the data representative of each angular position being correlated with data in the look-up table that is representative of the vector components that would be detected by the at least one magnetic sensor at that angular position; wherein the magnetic position sensor is configured to use the vector components determined by the magnetic sensor and logic to determine the angular position of the magnet from the look-up table.
G01B 7/30 - Measuring arrangements characterised by the use of electric or magnetic techniques for measuring angles or tapersMeasuring arrangements characterised by the use of electric or magnetic techniques for testing the alignment of axes
A thrust control assembly includes a balk application arrangement which provides, in response to a received balk command to prohibit command of thrust in a balk direction, a balk force on a rotatable thrust lever acting to oppose an attempt by the pilot to move the lever in a direction so as to command or increase thrust in the balk direction. The balk application arrangement controls an auto-throttle actuator to provide the balk force on the thrust lever.
A method of detecting that ice has been shed from an external surface of a component is provided, the method comprising applying power to a heating means to provide heat to said external surface. The method further comprises sensing the temperature of the component and calculating the rate of change of temperature increase of the external surface over time. Further, the method comprises detecting a change in said rate of change of temperature increase over time, wherein said detected change in rate of change of temperature increase indicates that said ice has been shed from said external surface of said component.
An apparatus for monitoring the pressurisation of a control valve for a hydraulic actuator and a control valve. The apparatus including a spool movable along an axis (X), wherein the spool is configured to control the flow of hydraulic fluid through the control valve based on its position along the axis (X), and wherein in an unpressurised state of the control valve the spool occupies a first axial position, and in a pressurised state of the control valve the spool occupies a second, different axial position. The apparatus also including a position sensor configured to monitor the position of the spool within the control valve and detect whether the spool occupies the first axial position or the second axial position, wherein the first axial position and the second axial position correspond to neutral positions of the spool.
F16K 11/07 - Multiple-way valves, e.g. mixing valvesPipe fittings incorporating such valvesArrangement of valves and flow lines specially adapted for mixing fluid with all movable sealing faces moving as one unit comprising only sliding valves with linearly sliding closure members with cylindrical slides
F15B 15/06 - Mechanical layout characterised by the means for converting the movement of the fluid-actuated element into movement of the finally-operated member for mechanically converting rectilinear movement into non-rectilinear movement
F15B 13/04 - Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with a single servomotor
A brake unit comprises said rotor disc rotatable about a central axis of rotation and a first brake pad mounting element having a first end and a second end and a longitudinal outer, side, surface extending there between, wherein a first brake pad is provided at said first end of said first brake pad mounting element and positioned facing a first face of said rotor disc. The first brake pad mounting element comprises a first locking feature provided on its outer, side, surface. The brake unit further comprises first locking element that pivots about pivot and that is movable about said pivot axis so that a locking feature of said locking element can come into contact with, or be moved away from said outer, side, surface of said first brake pad mounting element.
F16D 55/224 - Brakes with substantially-radial braking surfaces pressed together in axial direction, e.g. disc brakes with axially-movable discs or pads pressed against axially-located rotating members by clamping an axially-located rotating disc between movable braking members, e.g. movable brake discs or brake pads with a common actuating member for the braking members
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
F16D 121/20 - Electric or magnetic using electromagnets
F16D 127/06 - Locking mechanisms, e.g. acting on actuators, on release mechanisms or on force transmission mechanisms
A method of manufacturing a spar for a propeller blade comprises forming a hollow inner core from a composite material, and then braiding carbon fibres around the inner core to form an outer spar structure. The hollow inner core may be formed using an inflatable bladder and a mould defining an outer shape of the spar. This construction avoids the need for a foam core to be provided within the spar.
B29K 63/00 - Use of epoxy resins as moulding material
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
A brake rod for a steering/braking mechanism includes a rod body having a longitudinal axis, a rod end at a first end of the rod body, the rod end having a bore therethrough having a bore axis arranged generally perpendicular to the rod longitudinal axis, and a rod end shield mounted to the rod and extending in a longitudinal direction axially beyond the rod end.
F16H 21/44 - Gearings comprising primarily only links or levers, with or without slides all movement being in, or parallel to, a single plane for conveying or interconverting oscillating or reciprocating motions
B64C 13/30 - Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
A method of mounting a metal blade root to a composite propeller blade body includes inserting a connection portion of the blade body into a bore formed in the blade root, wherein the connection portion comprises at least one depression formed in an outer surface thereof, and applying pressure to the outer surface of the blade root to cause it to deform and engage with the depressions, thereby mechanically coupling the blade root to the propeller blade body.
A tank that may be used in combination with an actuating means such as a pneumatic door actuator includes a first, inner, enclosure positioned and enclosed within a second, outer, enclosure, to provide an enclosed chamber between the inner enclosure and outer enclosure. The pressure in the chamber may be measured with a gauge that does not extend into the inner enclosure. The measured pressure may then be monitored and compared in order to detect a change in pressure and thereby also detect a leak through a wall from the inner enclosure. The tank may also be used to inflate and/or deploy an emergency evacuation slide in an aircraft.
F17C 13/00 - Details of vessels or of the filling or discharging of vessels
G01M 3/32 - Investigating fluid tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors for containers, e.g. radiators
F17C 13/02 - Special adaptations of indicating, measuring, or monitoring equipment
F17C 1/00 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge
A brake component indicator configured to provide a visual indication of the release state of the brake component; the indicator comprising an indicator element connected to the brake component and moveable with the component during a braking operation, whereby the indicator element is provided with means to provide a visual indication of the direction and/or the distance moved by the indicator element during the braking operation. Preferably, the indicator element is in the form of a rod connected to a brake disk or pad that engages a moving part in a braking operation to brake the moving part, the rod provided with indicator means whose position is an indication of the distance the brake disk or pad has traveled to engage the moving part.
A system for monitoring engagement and wear in a brake include: a pin, a first marker positioned on the pin at a first location; a second marker spaced from the first marker long the pin; and a first fixed sensing arrangement. The pin extends in an axial direction parallel to the axis of rotation, and is in contact with and moves with the moveable brake pad in use. The first fixed sensing arrangement is adapted to provide a first signal when adjacent the first or second marker, and a second signal otherwise. The first and second markers and the first fixed sensing arrangement are positioned such that the second signal indicates that the brake is in the engaged position, and a change from the second signal to the first signal indicates that the moveable brake pad and the second brake pad have been worn down by a predetermined amount.
F16D 55/226 - Brakes with substantially-radial braking surfaces pressed together in axial direction, e.g. disc brakes with axially-movable discs or pads pressed against axially-located rotating members by clamping an axially-located rotating disc between movable braking members, e.g. movable brake discs or brake pads with a common actuating member for the braking members the braking members being brake pads in which the common actuating member is moved axially
B60T 17/22 - Devices for monitoring or checking brake systemsSignal devices
B64C 27/82 - RotorcraftRotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
F16D 66/00 - Arrangements for monitoring working conditions of brakes, e.g. wear or temperature
90.
Hydraulic rotor brake with additional fire barrier
New methods and devices are described that are aimed at preventing the outbreak of fire in a hydraulic rotor brake. These methods and devices can be used in the rotor brake of a helicopter and comprise a first and second seal, with a drain groove positioned in between these two seals to drain leaked fluid away from the hot parts of the brake. In the brakes described, the second seal is positioned closer to the heat sink of the brake than the first seal. The drain groove is also connected via a channel or channels to a drain outlet or outlets.
B60T 1/06 - Arrangements of braking elements, i.e. of those parts where braking effect occurs acting by retarding wheels acting otherwise than on tread, e.g. employing rim, drum, disc, or transmission
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
F16D 65/847 - Features relating to cooling for disc brakes with open cooling system, e.g. cooled by air
F16J 15/06 - Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
A dust retainer for a brake system comprising a retainer receptacle mounted integrally to one or more components of the brake assembly, wherein the retainer receptacle comprises a drum have first and second open ends, one open end being secured to a component of the brake system and the other open end being closed by a dust retainer cap, the drum defining a space within which a brake disk of the brake system is located, in use, wherein removal of the dust retainer cap allows the brake disk to be removed from the open end of the retainer drum, and a removable drawer integrated in the drum. A fastening means to removably secure brake components to each other is also disclosed.
F16D 55/24 - Brakes with substantially-radial braking surfaces pressed together in axial direction, e.g. disc brakes with a plurality of axially-movable discs, lamellae, or pads, pressed from one side towards an axially-located member
A control stick pivot (200) comprises a primary pivot bearing (210), a redundant pivot bearing (220), and a detection component for detecting malfunction of the primary pivot bearing. The redundant pivot bearing is provided on one side of the primary pivot bearing. The redundant pivot bearing becomes operative as a bearing in the event that the primary pivot bearing malfunctions. The detection component may comprise one or more features (230) provided on the redundant pivot bearing for applying a torque to the redundant pivot bearing during maintenance or testing and/or a sensor (300; 310; 320) configured to detect relative motion at an interface between the primary pivot bearing and the redundant pivot bearing.
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
F16C 19/16 - Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with a single row of balls
G05G 9/047 - Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks
G05D 1/00 - Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
G05D 1/08 - Control of attitude, i.e. control of roll, pitch, or yaw
There is provided a control stick module (10) comprising: a first shaft (100); a second shaft (110); a joint (140) connecting the first and second shafts; and a gimbal mechanism (120); wherein the joint is nested within the gimbal mechanism. The gimbal mechanism provides axes of rotation (201, 202) for the first shaft (100) and the joint provides axes of rotation (203, 204, 205) for the first shaft (100); and the axes of rotation (201, 202) provided by the gimbal mechanism intersect at a point corresponding to a point of intersection of the axes (203, 204, 205) provided by the joint.
The system of the present disclosure provides two or more sensors located on two parallel transmission or kinematic paths having different ratios with respect to the actuator position. Each sensor provides a different position measurement output and the difference between the sensor outputs provides a reduced indication of the position of the actuator/moved component. Integrating sensors in the reduction path avoids the need for the reduction gear mechanism.
G01D 5/04 - Mechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using mechanical means using leversMechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using mechanical means using camsMechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using mechanical means using gearing
B64C 13/30 - Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
The system of the present disclosure replaces the reduction gearbox of a conventional system with a screw shaft and nut system wherein the position of the nut feeds into a linear sensor that determines the stabilizer position based on the nut position. The screw shaft and nut system in the position sensor train is reflective of the screw shaft and nut system and the stabilizer movement end of the assembly whereby rotation of the shaft causes axial movement of the nut along the shaft.
G01D 5/04 - Mechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using mechanical means using leversMechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using mechanical means using camsMechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using mechanical means using gearing
B64C 13/28 - Transmitting means without power amplification or where power amplification is irrelevant mechanical
A bellows comprises a unitary bellows body extending from a first end to a second end in an axial direction. The stiffness of the bellows body varies in at least an axial direction.
G05G 9/047 - Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks
A propeller blade retention element comprises a body portion formed of a corrosion resistant metal, and at least one bearing race portion attached to the body portion, the race portion being formed of an induction hardenable, corrosion resistant metal.
C21D 1/10 - Surface hardening by direct application of electrical or wave energySurface hardening by particle radiation by electric induction
C21D 9/40 - Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articlesFurnaces therefor for ringsHeat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articlesFurnaces therefor for bearing races
F16C 19/06 - Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for radial load mainly with a single row of balls
An actuator is disclosed comprising: a moveable member; a first hydraulic chamber in contact with a first surface of the moveable member; a second hydraulic chamber in contact with a second, opposing surface of the moveable member; a movable locking mechanism coupled to a moveable wall of the second hydraulic chamber; and a resilient biasing member acting on the moveable wall of the second hydraulic chamber so as to bias the moveable wall and locking mechanism. The actuator is configured to selectively vary the pressure in the second hydraulic chamber so that the resilient biasing member is able to bias the moveable wall to move, thereby moving the locking mechanism to engage the moveable member so as to prevent the movement of the moveable member towards at least one of the first and second hydraulic chambers.
A propeller component, for example a propeller blade airfoil, includes an external surface exposed in use to an oncoming airstream (A), and a protective polymeric film applied over substantially the entire exposed external surface of the component.
An ice breaking seal for a ball screw comprises a first, ice breaking section and a second, sealing section formed integrally with the ice breaking section. The ice breaking section is formed of a polymeric material and has a first hardness. The sealing section is formed of a polymeric material and has a second hardness, which is lower than the first hardness.
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