93 results about "Arresting gear" patented technology

The invention concerns a Brake carrier (10) for disc brake arrangement (11), the disc brake arrangement (11) having brake pads (24) that are displaceable relative to a brake disc (100), wherein the brake carrier (10) is configured to support the brake pads (24) during their displacement; wherein the brake carrier (10) comprises at least a first portion (14) that is arrangeable on a first side (13) of the brake disc (100), a second portion (16) that that is arrangeable on a second side (15) of the brake disc (100) and two connecting portions (18, 20) each connecting the first and second portions (14, 16); wherein at least one of the connecting portions (18, 20) comprises an air channel (12) having a first end (34) that is arranged so as to face towards the brake disc (100). Also disclosed is a disc brake arrangement (11) comprising such a brake carrier (10).

A wing (3) for an aircraft (1) including a fixed wing (5), a foldable wing tip portion (9) mounted to the fixed wing (5) via a hinge (11) in a manner rotatable about a hinge axis (13) between an extended position and a folded position, an actuation device (24) for actuating the foldable wing tip portion (9) for movement between the extended position and the folded position, and an arresting device (37) for arresting the foldable wing tip portion (9) in the extended position and / or in the folded position. The arresting device (37) includes a clutch device (39) configured for selectively holding the foldable wing tip portion (9) in a fixed position relative to the fixed wing (7) and releasing the foldable wing tip portion (9) for movement relative to the fixed wing (7) about the hinge axis (13).

A brake apparatus may include a rotary member, a friction member configured to apply a frictional force to the rotary member, an electric actuator configured to move the friction member, a clamping force detection member configured to detect a clamping force in accordance with contact between the rotary member and the friction member, and a controller configured to control an operation of the electric actuator, in which the controller determines a reference position on the basis of a position of the friction member at a time point at which the rotary member and the friction member are separated, determines a clearance between the rotary member and the friction member on the basis of the detected clamping force on the basis of the reference position, and control the movement of the friction member on the basis of the clearance.

The invention relates to a magnetic braking device for a vehicle wheel, the device comprising: at least one stator element (2) arranged to be rotatably connected to a vehicle supporting a portion of the wheel; a rotor element (3) arranged to be rotatably connected to the wheel; a magnet for generating a magnetic flux between the elements, the magnetic flux being capable of generating an eddy current in one of the elements when the wheel rotates; and a brake control unit (11) that receives the brake command as an input to apply a braking force in accordance with the brake command. The magnet comprises at least one electromagnet (9), and the device comprises at least one anti-lock control unit (16) which receives as input a vehicle speed signal and a wheel rotation speed signal and provides as output a signal controlling the electromagnet as a function of a comparison of the speeds from the signals received as input. The invention also relates to an aircraft wheel and a landing gear comprising such a device.

The invention relates to a magnetic braking device comprising at least one stator (2) and at least one rotor (3), and electromagnets (5) rigidly connected to the rotor and / or the stator so as to produce therebetween, when the rotor rotates, at least one magnetic field capable of generating eddy currents braking the rotor. According to the invention, the device comprises at least one control unit (7) capable of controlling an AC power supply of at least some of the electromagnets such that the magnetic field is a rotating magnetic field, the control unit being configured to adapt a rotational speed of the magnetic field as a function of at least one data item characteristic of the rotational speed of the rotor (1) by determining at least one of the power supply parameters of at least one of the electromagnets.

Provided is an electric actuator which has fewer movable portions of a motion conversion mechanism so that slapping sound less liable to occur at the time of operation of an electric drive unit, and hence has quietness. An electric actuator includes: an electric driving source configured to generate a rotational motion as a driving force; and a motion conversion mechanism configured to convert the rotational motion to a rectilinear motion. The motion conversion mechanism includes: a first member configured to be blocked to execute a rotational motion and a rectilinear motion; and a second member configured to engage with this first member to relatively rotate with respect to this first member, to thereby generate a rectilinear motion. This second member is configured to be rotationally driven by the driving force of the electric driving source.

Aircraft wheel (10a) mounted for rotation on an axle (5), comprising: an annular rim (11) connected by a disc (12) to a hub (13) received for pivoting on the axle, the rim delimiting with the hub an annular space partially closed by the disc which includes through holes (12.1) forming air passages (P); a braking device (20) comprising brake discs (21) extending in the annular space opposite an inner face of the disc; a wheel rotation drive device (40), comprising an electric actuator extending axially opposite an outer face of the disc; and a cooling device (50) for the brake discs and the electric actuator, comprising a fan (51) extending axially opposite the electric actuator such that said electric actuator extends axially between the rim and the fan, and a ferrule (52) extending around the drive device and the fan.FIGURE DE L’ABREGE: Fig. 3A.

A braking device for an aircraft wheel (101), comprising at least one stack (8) of at least one rotor disc (8.1) and one stator disc (8.2), an actuator housing (2), at least one actuator (13) mounted in the actuator housing (2) to exert a pressing force on the stack of discs (8), the actuator housing (2) comprising a connecting portion (2.1) to the landing gear and a receiving portion (2.2) for the actuator. The device includes a braking force sensor comprising: a body (1.1) having a first end (1.1.1) mechanically fixed to the connecting portion (2.1) and a second end (1.1.2) mechanically fixed to the receiving portion (2.2), the body being arranged to have a state representative of a distance between its two ends, and a sensing component near the body (1.1) for measuring a change in the state of the body (1.1). FIGURE FROM THE ABRIDGED: Fig. 1

A braking device for a wheel pivotally mounted on a shaft, comprising a rotor assembly having at least one element for rotationally connecting to the wheel, a stator assembly, and a torque tube engaged in the stator assembly and arranged to be fixedly mounted around the shaft, with at least one tenon projecting outward from the torque tube to rotationally connect the torque tube and the stator assembly and allow torque transmission between the torque tube and the stator assembly, the tenon being separate from the torque tube and arranged to be removable relative to the torque tube. (Figure from the abbreviation: Fig. 3)

The invention relates to a device for preventing rotation of a wheel (1) rotatably mounted on an axle (2) for rotation about an axis of rotation (X), comprising: a receiving member (4) rigidly attached to the wheel and provided with an inner face having regularly distributed axial cavities (4e); a rotationally stationary cage (6) extending around the axle and facing the receiving member, the cage comprising an axial recess (6a) accommodating a section (7), the section (7) being movable within the cage in a respective radial direction between an engaged position, in which the section engages in the receptacle of the receiving member, and a released position, in which the section (7) does not engage in the receptacle of the receiving member; the section is disengaged from the receiving portion of the receiving member; a pushing member (5) made of a material capable of guiding magnetic flux, extending around the axle so as to cooperate with the section via the inclined bearing surface and mounted for axial movement between a locked position, in which the pushing member forces the section into the engaged position, and an unlocked position, in which the pushing member does not engage with the section. The urging member urges the section into the release position; a resetting member (12) for resetting the pushing member to its locking position and maintaining it there; a permanent magnet (14) exerting an electromagnetic force on the urging member, intended to hold the urging member in the unlocked position against the force of the resetting member; an electromagnet (15) selectively energizable to counteract the force of the permanent magnet to allow the push member to move from the unlocked position to the locked position under the action of the reset member, or to enhance the force of the permanent magnet to move the push member from the locked position to the unlocked position against the force of the reset member. The invention also relates to a wheel and an aircraft equipped with such a device.

An electrohydraulic system for controlling a landing gear of an aircraft, said landing gear comprising a plurality of retractable landing gear units each provided with at least one wheel. Said system comprises two braking devices for braking said wheel of two landing gear units, one movement device per landing gear unit for moving a landing gear unit relative to a housing of said aircraft, and two hydraulic units, hydraulically connected to said movement devices and to at least one of said braking devices. Each hydraulic unit comprises a reservoir containing a fluid, a pump driven by an electric pump motor and a distributor configured to distribute said fluid to said at least one braking device and to said movement devices, by means of braking, extension, retraction and discharge valves.

The invention relates to an aircraft wheel (10a) rotatably mounted on an axle (5), comprising: - an annular rim (11) connected by a web (12) to a hub (13) pivotably received on the axle, the rim delimiting with the hub an annular space partially closed by the web which comprises through-holes (12.1) forming air passages (P); - a braking device (20) comprising brake discs (21) extending in the annular space facing an inner face of the web; - a device (40) for driving the rotation of the wheel, comprising an electric actuator extending axially facing an outer face of the web; and - a system (50, 50', 50'') for cooling the brake discs and the electric actuator, comprising a fan (51, 51', 51'') extending axially facing the electric actuator, and a shroud (52) extending around the drive device and the fan.

The invention relates to a brake device (100), said brake device (100) having: a separately actuatable brake (102), which has at least one brake lining (102-2) and an actuator (102-4), which is designed to move the at least one brake lining (102-2); a sensor device (106) assigned to the brake (102), the sensor device being designed to detect a variable characterizing a state of the brake (102); and a diagnostic device (108), which is in a signal exchange connection with the sensor device (106) and is designed to perform a diagnosis on the brake (102) on the basis of the sensor signal received by the sensor device (106).

The invention relates to the technical field of railway vehicle brake systems, aims to solve the problems that an existing integrated brake device is insufficient in piping connection integration degree, poor in sealing performance, high in piping strength, large in number of parts and large in weight, and provides an integrated brake device without an internal piping system and free of air cylinder maintenance, which comprises a middle body and a maintenance-free air cylinder. A cavity and a gas path are arranged in the middle body, and the maintenance-free air cylinder is communicated with the corresponding gas path; the maintenance-free air cylinder is directly connected in a sealed mode and fixedly connected to the middle body, or the maintenance-free air cylinder and the middle body are of an integrated casting forming structure; the intermediate is provided with an external test maintenance interface; according to the integrated brake device, a piping-system-free and maintenance-free air cylinder integrated design is adopted, a piping system between an existing air cylinder and a middle body is omitted, and a direct sealing and fixed connection or integrated casting forming structure is adopted, so that the sealing performance of the integrated brake device is improved, meanwhile, piping system suffocation is eradicated, the number of parts and the overall weight of the device are reduced, and the integration degree of the device is improved.

A brake control device (1) controls a mechanical brake device (30) comprising a force-multiplying mechanism, a pressing mechanism (31), and a transmission mechanism (38). The force-multiplying mechanism generates braking force by pressing a friction material against a rotating body in response to received pressing force. The pressing mechanism (31) presses the force-multiplying mechanism. The transmission mechanism (38) is in contact with the pressing mechanism (31) and the force-multiplying mechanism, and presses the force-multiplying mechanism with force exerted by the pressing mechanism (31). The brake control device (1) comprises a target brake force determination unit (11), a target mechanical brake force determination unit (12), a brake control unit (13), and a transmission control unit (18). The transmission control unit (18) allows or inhibits the pressing of the force-multiplying mechanism by the transmission mechanism (38).

The invention relates to the technical field of wind power generation, and provides a braking device, a position adjusting system and a wind generating set, and the braking device comprises a gear braking part, a braking pressing block and an adjusting assembly. The gear brake part is in meshed connection with a to-be-braked structure; the brake pressing block is provided with a first pressure-bearing face and a second pressure-bearing face which are oppositely arranged, and the first pressure-bearing face abuts against or is separated from the gear brake part. The adjusting assembly is connected with the second pressure bearing face and used for adjusting the distance between the adjusting assembly and the gear braking piece. In this way, braking force can be provided for the to-be-braked structure through the gear braking part, then the to-be-braked structure can be prevented from moving relative to the braking device, and therefore the braking force provided for the to-be-braked structure can be increased. Therefore, the braking effect of the braking device on the to-be-braked structure can be improved, and the reliability of the braking device can be improved.

The invention discloses a brake device of a rotary platform, a hydraulic control system and a control method thereof in the field of brake systems, and the brake device comprises a rotary motor which is in transmission connection with the rotary platform; the output end of the tail end brake is meshed with the slewing bearing; the speed reducer is used for reducing the speed of the rotary motor; a middle end brake is arranged in the speed reducer; the tail end brake and the middle end brake are both connected to a hydraulic control system, and the hydraulic control system is used for controlling synchronous opening and closing of the tail end brake and the middle end brake. According to the braking device of the rotary platform, the tail end brake is installed on the rotary bearing and directly brakes the rotary bearing, so that braking of the rotary platform is achieved, a braking conduction path is reduced, shaking during braking is reduced, and in addition, the service life of the rotary platform is prolonged. And the tail end brake on the slewing bearing and the middle end brake in the speed reducer are both controlled by the hydraulic control system, so that synchronous braking is realized, and the stability during braking is further ensured.

To provide a replacing method of an elevator hoist braking device and a braking device capable of realizing miniaturization without deteriorating performance and capable of safely being detached / attached from / to a hoist with the aid of a lifting device.SOLUTION: A replacing method of a braking device places a fixing part placed through any bolt among multiple bolts and a bracket with a locking part extending from the fixing part on the braking device, locks them at the locking part of the bracket with a hook of a lifting device or with a rope, and removes the braking device from the hoist or installs the same to the hoist while any bolt to fix at least the bracket is held in the braking device.SELECTED DRAWING: Figure 4

The invention relates to a braking device comprising an armature, coils (7) received in slots (5) of the armature, and wedges (1) engaged in the slots (5) to at least partially close off the slots (5), each of the wedges (1) being composed of at least one material with permanent magnetization in a polarization direction. The invention also relates to an aircraft wheel (103) comprising such a braking device.

The invention relates to a system, housed in a pit in an aircraft runway, comprising at least one immobilizing member (1) which comprises a framework (2) that is fixed relative to the walls of the pit, a receiving mat (3) intended to receive landing gear of the aircraft, drive means (4) for driving this mat relative to the framework, braking means (5) for braking this mat, and control means (8) able to activate the drive means in response to a first signal, then deactivate the drive means while activating the braking means in response to a second signal. The system according to the invention provides for the immobilization of an aircraft in difficulty without significant stresses being exerted on this aircraft, which remains in perfect flying condition. The invention makes it possible to do away with any subsequent operation for checking the integrity of the aircraft structure. Moreover, the invention makes it possible to avoid any technical unavailability of the runway. Lastly, the invention is applicable to the immobilization of aircraft during both the landing phase and the take-off phase thereof.

The present disclosure provides an aircraft with an emergency braking system comprising an emergency braking device designed, upon activation, to significantly increase the friction between the aircraft and the runway. The emergency braking device causes the controlled destruction of at least one sacrificial component, thereby improving the deceleration of the aircraft on the runway. The sacrificial component may include collapsible wheels, a destructive braking device (306b), or an underside braking surface. The emergency braking system can be activated automatically or manually in response to emergency situations during takeoff or landing, thus providing improved safety and braking capability for the aircraft.

A brake for a means of transport, in particular a brake for a means of single track transport with at least two wheels, which comprises a standing part (3), with a standing board (17), and at least one front wheel (4) and at least one rear wheel (5), which are mounted on the standing part (3), by means of a supporting frame part (14), in such a way that the standing board (17) is arranged in the space between the front wheel (4) and the rear wheel (5), which comprises a control pedal (1), which is arranged in the front part of the standing part (3), and at least one braking means (2) is arranged on at least one rear wheel (5), with a tread wedge (10) being arranged between the standing board (17) and the control pedal (1).

The application provides a multistage anti-collision fender, which comprises a vertically arranged base, a fixed frame fixedly connected with the base, a buffer head movably connected with the fixed frame through a connecting block, a first spring, a first movable plate, a rack, a first hinge base, a first connecting rod, a second hinge base, a second movable plate and a reset device arranged in the fixed frame in sequence from the direction away from the base to the direction close to the base; the rack is further engaged with a gear set, the gear set is sleeved on the upper end of a second connecting rod, a first rope winding disc is sleeved on the lower end of the second connecting rod, the second connecting rod is arranged at one end of a motor, a brake device is fixedly connected to the other end of the motor, and a second rope winding disc is arranged on the brake device; and elastic ropes are sleeved on the first rope winding disc and the second rope winding disc. The multistage gear in the fender designed by the application can control the change speed of the fender reaction force, can effectively protect the ship body from deformation, and can realize the design requirements of low fender reaction force and high energy absorption.

The invention relates to a braked aircraft wheel (103) comprising: - a rim (104) having an inner periphery delimiting a space for receiving brake rotor discs (107b); - at least one bar (10) attached to the rim by means of a screw (31) for rotatably connecting the brake rotor discs to the rim, the screw extending in a radial direction (Y) with respect to the rim in a first bore (104.2) provided in the rim and in a second bore (12) provided in the bar; and - a wedge (20, 20', 20'') interposed between the rim and the bar and traversed by the screw, characterized in that a portion of the wedge is received with a fit in a first counterbore (104.3) provided at an inlet of the first bore (104.2) of the rim and / or in a second counterbore provided at an outlet of the second bore of the bar.

A pad for a brake device can include a body portion in contact with a torque member, a pair of insertion portions connected to the body portion such that a portion of the torque member is inserted into the insertion portions, a pair of guide portions respectively connected to the pair of insertion portions and configured to guide a brake pad, a pair of support portions respectively connected to the pair of guide portions and configured to support the brake pad, and a pair of return portions respectively connected to the pair of insertion portions, located on opposite sides of the insertion portions, and configured to provide a return force to the same point of the brake pad when the brake pad moves. In a pad for a brake device according to the present disclosure, the return portions can press the same position of the brake pad while recovering to an initial state by an elastic force, thereby generating a uniform return force in the brake pad.

A vehicle braked wheel (103) comprising at least one hub portion (104.1) and a rim portion (105.1) coaxial with the hub portion (104.1) and connected to the hub portion (104) by a disc portion (106.1), the wheel having an eddy current magnetic braking device comprising a rotor (3) rotationally linked to the wheel and a stator (2) that is rotationally free relative to the rim portion (105.1) and the rotor (3) and that carries a plurality of magnets (11) capable of emitting a magnetic flux generating eddy currents in the rotor (3), made of an electrically conductive material, when the stator (2) and the rotor (3) are facing each other and in relative motion. The rotor (3) is integral with the rim portion (105.1). Landing gear and aircraft comprising such a wheel. FIGURE FROM THE ABRIDGED: Fig. 3

A wheel including a rim that rotates on a shaft defining a primary rotational axis and a magnetic braking device. The magnetic braking device includes an actuator which includes a first transmission assembly and one second transmission assembly each includes a pinion mounted on the support to pivot about a secondary rotational axis parallel to the primary axis, an operating bar extending about the secondary axis, a first mechanical connecting member connecting the operating bar to the pinion of the transmission assembly and a second mechanical connecting member connecting the operating bar to one of the stators, and the mechanical connecting members are arranged. The rotation of the pinions causes a movement of the stators parallel to the secondary axis in opposite directions, for varying the air gap, one or more of the mechanical connecting members of each transmission assembly being arranged to ensure a screw-nut helical connection.

A wheel device includes: a plurality of wing members configured to rotate around a central axis, wherein each wing member of the plurality of wing members may include an outer circumferential surface and each wing member of the plurality of wing members is configured to be movable to a first position in which the respective outer circumferential surfaces combine to form a circle, and to a second position in which an end of each outer circumferential surface is rotated away from the central axis of the wheel device; a deforming device configured to move each wing member of the plurality of wing members to the first position or the second position; a plurality of rollers provided on the respective outer circumferential surfaces of the plurality of wing members, wherein each roller of the plurality of rollers has a rotation axis that is not parallel to the central axis; and a braking device including a brake pad configured to contact one or more rollers of the plurality of rollers when the plurality of wing members are in the second position and to separate from the plurality of rollers when the plurality of wing members are in the first position.