Abstract:
A brake for a rotating member is disclosed. The brake is used with a liquid coolant, and includes a housing for containing the liquid, a stationary element disposed in the housing, a wear plate disposed on the stationary element, a friction element coupled to the rotating member for contacting the wear plate, and a removable heat transfer insert disposed adjacent the wear plate and in fluid communication with the coolant, the heat transfer insert consisting of a non-galvanic material.
Abstract:
A braking actuator for a brake of an aircraft, the actuator comprising: an electric motor; a pusher actuated by the motor; and a position sensor for sensing the position of the movable portion of the motor and provided with transmitter and receiver members. The motor has first and second exciters adapted to move the movable portion of the motor and adapted to be powered independently from each other. The transmitter member of the position sensor comprises first and second transmitters adapted to be powered independently, and the receiver member generates the signal representative of position on being excited by at least one of the transmitters.
Abstract:
Systems and methods are disclosed for dissimilar aircraft brake systems for use in, for example, an aircraft. In this regard, a system is provided comprising a carbon/carbon (“C/C”) rotor disk adjacent to a ceramic matrix composite (“CMC”) stator disk. In various embodiments, a system is provided comprising a CMC rotor disk adjacent to a C/C stator disk.
Abstract:
A multi-disc brake, in particular for a road vehicle, is provided with parallel discs which are arranged at a distance from each other and which are rotationally stable and between which a rotatable disc brake is positioned. The radially extending discs and the brake discs can be pressed against one another during braking, by way of a brake application device, while overcoming a clearance and once the brake is released, the discs are separated from each other thus forming a clearance. For transferring the feed motion during braking, a transmission gearing is connected in a movement-dependent manner to a pivotable brake lever of the brake application device and also actively connected to the brake discs.
Abstract:
A backspin reducing device for reducing an amount or a rate of backspin of a rod string when lifting the rotor apart from the stator of an oil or gas downhole progressive cavity pump. The backspin reducing device includes a substantially cylindrical housing having one or more threaded pin receptacles holding respective threaded pins in threaded engagement around a polished rod portion of the rod string of the progressive cavity pump. Turning threaded pins in their respective threaded pin receptacles causes the interior ends of the threaded pins to move towards or away from the polished rod in the center of the housing. Attached to the interior end of each threaded pin is a friction roller.
Abstract:
The invention relates to a connecting device for connection between a brake disc and a hub. The brake disc is fitted on the hub via splined connection with recesses on the brake disc and protrusions on the hub. The connecting device is made of non-rusting material and intended to be fitted between a side surface of a recess and an adjacent side surface of a protrusion. According to the invention, the connecting device has two mutually abutting layers. These are connected to one another and separable from one another by only an axial relative movement between the layers. The invention also relates to a method for fitting a brake disc on a hub.
Abstract:
The invention provides an electromechanical actuator for a vehicle brake, the actuator comprising: a motor; a screw-and-nut system having a first element, the screw or the nut, rotated by the motor; and an antirotation member preventing rotation of the second element of the screw-and-nut system, the nut or the screw, so that the second element moves linearly in response rotation of the motor so as to exert compression selectively on friction elements of the brake. According to the invention, the actuator is subdivided into a first portion comprising the screw-and-nut system, and a second portion comprising the motor, the portions being designed to be separable while the actuator is mounted on a brake.
Abstract:
The method and system for increasing accuracy of clamping force of electric aircraft carbon brakes, once braking has been commenced, provides a first pair of electric brake actuators with a range of low brake clamping force responsive to low brake clamping force commands, and a second pair of electric brake actuators with a range of high brake clamping force responsive to high brake clamping force commands. The first pair of electric brake actuators is actuated to apply a minimum residual braking force once wheel braking is commenced, and the second pair of electric brake actuators is actuated only when the commanded braking force is in the high range of brake clamping force.
Abstract:
A brake (10) for applying a braking force to a shaft includes a housing (11) which defines a chamber (17). The housing (11) includes a plurality of depressions (19) circumferentially spaced around an axis (22). A rotatable actuator (40) is received in the chamber (17) and includes a plurality of depressions (43) circumferentially spaced around the axis (22). The housing depressions (19) face the rotatable actuator depressions (43) and each matching pair of depressions receive a ball (23) therebetween. A spring (50) under compression is positioned centrally about the axis (22). A bearing (56) is interposed between the rotatable actuator (40) and disc assembly (70) which minimizes frictional effects and rotational feedback during brake actuation. When the rotatable actuator (40) is rotated, the balls (23) roll along the depressions (19, 43) to gradually shallower portions thereof. This moves the rotatable actuator (40) axially away from the housing (11), thereby applying a braking force to the shaft. The spring (50) compressively opposes the axial movement of the rotatable actuator (40) away from the housing (11).
Abstract:
An aircraft wheel assembly includes a wheel (12) and a beam key (40) mounted on the wheel (12). The beam key (40) includes a body (46) having first and second longitudinally spaced ends (42, 44), an upper side (48), and a lower side (52) having a first surface (53), and a bore (60) having a first end opening (66) in the first surface and a second end opening (64). The wheel (12) includes a centerline (20), an opening (18) for receiving the body first end (42), a second surface (26) angled with respect to the centerline (20), and a wheel bore (30) coaxially aligned with the beam key bore (60) when the body first end (42) is received in the opening (18), the wheel bore (30) having a first end opening in the second surface (28). A spacer (70) must be included between the beam key (40) and the wheel (12).