136 results about "Arresting gear" patented technology

Disclosed is a method for guaranteeing aerodynamic braking satisfies emergency braking safety, comprising: step S1: performing computation by means of fluid simulation software to acquire a wind load borne by an aerodynamic braking apparatus, separately performing static strength simulation, fatigue strength simulation, and impact strength simulation, and, on the basis of simulation results, optimizing the structure of the aerodynamic braking apparatus; and step S2: designing the means of opening and the shape of braking wings of the aerodynamic braking apparatus, and designing the means of arranging the braking wings on a train; by means of the fluid simulation software, performing simulation and analysis on the train on which the aerodynamic braking apparatus is mounted, and, on the basis of a simulation result, performing optimization on the means of opening and the shape of the braking wings and the means of arranging the braking wings on the train. According to the present invention, optimization of the structure of the aerodynamic braking apparatus is achieved, and further, the optimization of the means of opening, the shape, and the means of arranging the braking wings mounted on the train is achieved, so that the safety of aerodynamic braking is improved.

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 present invention belongs to the field of earthquake and impact safety of nuclear power plants, and specifically discloses a new type of nuclear power plant with a potential energy-based self-rotating shock-resistant interlayer seismic isolation, including a nuclear island lower structure, a nuclear island upper structure, an interlayer seismic isolation layer, an excitation device and nuclear equipment, wherein the interlayer seismic isolation layer is connected between the nuclear island lower structure and the nuclear island upper structure, and includes a seismic isolation support, a roller track, a roller shaft, a roller, a spring pull rod, a braking device, an impact sensor, an air hole and a friction plate; the excitation device is distributed in a circular array on the inner wall of the nuclear island upper structure, and multiple layers are arranged at equal intervals above and below, and include a bottom plate, a side plate, a pre-tensioned spring, an impact mass block and a release control system. The present invention changes the traditional structure that adopts a resistance method to prevent aircraft impact damage to an energy conversion method to prevent aircraft impact damage, and at the same time utilizes rotation to deflect the impact direction represented by an aircraft, thereby reducing the transmission of impact energy to the structure.

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.

A braking device according to one embodiment comprises: a rotary element, a linear motion element which is movable in a first direction when the rotary element is rotated in a first direction and is movable in a second direction when the rotary element is rotated in a second direction, a piston which is able to push a brake pad in the first direction by being pushed by the linear motion element in the first direction;and a projection extending from the brake pad, housed in a recess provided in the piston, and having an inclined surface inclined obliquely with respect to an axis of rotation, wherein the piston, rotating in the second direction of rotation, comes into contact with the inclined surface of the brake pad at a first end face of the recess and presses the brake pad in the first direction, and when the projection is viewed in the first direction, a projected area of ​​the inclined surface is greater than half a projected area of ​​the projection.

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.

A device (1) for braking a wheel (2) of an aircraft, wherein the wheel hub (5a, 5b) is mounted for rotation about an axle (6), and comprises a stack of wheel discs (11) screwed onto a torque tube (12) attached to the axle and internally provided with a heat shield (20) extending opposite the outer surface (5.1) of the wheel hub facing the stack of wheel discs to protect the wheel hub from the heat radiation generated by the stack of wheel discs. The heat shield comprises a tubular body (21) coaxial with the torque tube and a plurality of retaining tabs (22) elastically deformable and fixed to the tubular body, each retaining tab and the inner surface (12.1) of the torque tube comprising an additional raised portion intended to engage with each other so as to secure the heat shield axially inside the torque tube. A wheel, landing gear and aircraft are provided with such a braking device.

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 present invention relates to a braking device (100) for braking the movement of at least one movable element (1) relative to a housing (2), preferably relative to the housing of an air discharge opening, wherein the movable element (1) is an element for guiding and / or restricting an air flow and / or an actuating element, wherein the braking device (100) has at least one elastic element (4), and wherein the elastic element (4) has a main extension direction that is at least substantially perpendicular to the movement path of the at least one movable element (1). The present invention also relates to a device having such a braking device, preferably an air discharge opening.

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).

Disclosed is an actuator for a brake device. In accordance with an aspect of the disclosure an actuator for a brake device includes a motor; a first reduction gear unit connected to the motor; and a second reduction gear unit connected to the first reduction gear unit; wherein the first reduction gear unit is provided as a planetary gear assembly, and the second reduction gear unit is provided as a bevel gear assembly.

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

One aspect of the invention relates to a ventilation system (9) for ventilating the braking device of an aircraft wheel and optionally an electric taxiing motor, which comprises a ventilation wheel (12), an electric motor (10) for rotating the ventilation wheel, and an epicyclic reduction gear (13) interposed between the rotating shaft (11) of the electric motor and the ventilation wheel. The epicyclic reduction gear preferably comprises a sun gear (20) integral with the rotating shaft, planet gears with fixed planet carriers, and a rotating ring gear (23) integral with the ventilation wheel.

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 invention discloses a cylinder protection method for a tail clamp brake device, comprising the following steps: after the bar is cut by a multiple-length shear, the bar is completely driven by a brake roller, and the bar movement speed is equal to the brake roller linear speed; the brake roller linear speed is reduced by controlling the motor speed of the tail clamp brake device to reduce the bar movement speed, and the tail movement position of the bar is obtained by calculation and tracking according to the feedback speed of the bar movement speed; when the bar movement speed on the brake roller line is equal to the release speed, and the tail movement position of the bar is in front of the brake roller, the brake roller is opened to realize that the brake roller has been opened to release the bar when the tail of the bar leaves the brake roller, thereby eliminating the secondary closing action of the brake roller. The invention can solve the problem that the cylinder of the tail clamp brake device of the existing high-speed steel system is easily damaged and the service life is reduced.

The invention relates to a braking device (10) for an aircraft wheel (1), comprising:-a torque tube (13, 13 ') extending along a longitudinal axis; -a stacked brake disk (11) comprising a last stator disk; -at least one actuator (18) comprising a piston translationally mounted between a first end position in which the piston is spaced apart from the stacked disks in order to apply pressure to the first stator disk, and a second end position in which the piston is spaced apart from the stacked disks in order to apply pressure to the first stator disk; and-at least one strut (14) arranged between the second end of the torque tube and the last stator disk in order to withstand and transmit pressure to the torque tube. The last stator disk and torque tube are shaped to define a minimum gap therebetween that is less than a distance that separates the piston from its second end position when the piston applies pressure.