Abstract: A system and method for establishing a running clearance position for an electromechanical actuator (28), wherein the running clearance is based on an actuator ram (34) position attained during a force application to a brake stack (30). In particular, a running clearance calibrator (66) determines a position value corresponding to a position of the force applicator when retraction from an application of force on the brake stack commences. The running clearance calibrator also generates a running clearance position as a function of the position value.

Abstract: A system and method for limiting peak power demand of a controller (26) for an electromechanical actuator A motor current command is limited to at least one of a positive current limit or a negative current limit, the positive and negative current limits being a function of motor velocity. A motor drive signal is output to the motor in accordance with the limited motor current command.

Abstract: A system and method for establishing a running clearance position for an electromechanical actuator (28), wherein the running clearance is based on an actuator ram (34) position attained during a force application to a brake stack (30). In particular, a running clearance calibrator (66) determines a position value corresponding to a position of the force applicator when retraction from an application of force on the brake stack commences. The running clearance calibrator also generates a running clearance position as a function of the position value.

Abstract: An electromechanical braking system for an aircraft, including a first power conversion module (PCM) and a second power conversion module (PCM), each configured to receive power from a respective independent power source on the aircraft. The system further includes at least one brake system control unit (BSCU) for converting an input brake command signal into a brake clamp force command signal. At least a first brake control module (BCM) and a second brake control module (BCM) are provided, each configured to receive the brake clamp force command signal from the at least one BSCU and to output a primary brake clamp force command signal and an alternate brake clamp force command signal based on the received brake clamp force command signal. A first electromechanical actuator controller (EMAC) and a second electromechanical actuator controller (EMAC) are provided, each configured to convert a brake clamp force command signal to at least one electromechanical actuator drive control signal.

Abstract: An electrically actuated aircraft brake system and method which provides for brake wear measurement, brake running clearance adjustment, ram position-based control and improved construction and operation. Brake wear and running clearance measurement are obtained by analyzing the output of position sensing circuitry. The position sensing circuitry, preferably including a LVDT position sensor, is also used to determine braking load, a brake controller including circuitry for effecting displacement of one or more reciprocating rams to load a brake disk stack by a predetermined amount based on a present displacement value of the position signal obtained from the position sensor. The position sensor preferably includes a LVDT transducer connected between the reciprocating ram and a brake housing, and the motive device preferably includes a servo motor.

Abstract: An electrically actuated aircraft brake system and method which provides for brake wear measurement, brake running clearance adjustment, ram position-based control and improved construction and operation. Brake wear and running clearance measurement are obtained by analyzing the output of position sensing circuitry. The position sensing circuitry, preferably including a LVDT position sensor, is also used to determine braking load, a brake controller including circuitry for effecting displacement of one or more reciprocating rams to load a brake disk stack by a predetermined amount based on a present displacement value of the position signal obtained from the position sensor. The position sensor preferably includes a LVDT transducer connected between the reciprocating ram and a brake housing, and the motive device preferably includes a servo motor.

Abstract: An electromechanical system and system are provided where a controller generates an electrical drive signal for an actuator using power from a power source. A capacitor stores electrical energy and avails the stored energy to the controller when a voltage potential of the store electrical energy is higher than the supply voltage of the power source. The stored electrical energy may originate from the power source and/or regenerative energy produced by the actuator.

Abstract: An electromechanical braking system is provided that includes an electromechanical brake actuator for converting an electrical drive signal into mechanical energy to effect braking on a wheel of a vehicle. The electromechanical brake actuator is operative based at least in part on a DC supply voltage typically provided by a main supply source. The system further includes an electrical energy back-up system which capacitively stores electrical energy and provides the stored electrical energy as the DC supply voltage in an absence of the main supply source.

Abstract: A brake system including an electromechanical brake actuator having an actuator ram for exerting a brake force on a brake stack of a wheel to be braked in response to a control signal. In addition, the brake system includes a force sensor for sensing the brake force exerted on the brake stack by the actuator ram and outputting a force feedback signal based thereon; and a position sensor for sensing a position of the actuator ram and outputting a position feedback signal based thereon. Moreover, the brake system includes a controller for providing the control signal to the electromechanical brake actuator based on the force feedback signal and the position feedback signal.

Abstract: A parking brake monitor and adjustment control system controls parking brake operation of an electromechanically actuated brake system which applies a parking brake force to a wheel. The system includes a monitor circuit for producing an output signal which intermittently causes the brake system to readjust the parking brake force applied to the wheel.

Abstract: A speed reduction system for decreasing the speed of a moving craft has a craft engaging device, a control mechanism, and a hydraulic energy transfer system adapted to transmit energy from the craft engaging device to the control mechanism. The control mechanism is adapted to actively control release of energy from the hydraulic energy transfer system during the decrease of the speed of the craft. A method of controlling the operation of a valve includes adjusting the valve during the operation of the valve after comparing a condition to a desired condition determined by a profile. A hydraulic valve has a valve member defining passages arranged to balance the force of the fluid pressure acting on the valve member and an actuator connected to the valve member. A valve control system includes a controller and a driver arranged with the controller. The position of the valve is adjusted during a predetermined cycle to control the operation of the valve.

Abstract: An electrically actuated aircraft brake system and method which provides for brake wear measurement, brake running clearance adjustment, ram position-based control and improved construction and operation. Brake wear and running clearance measurement are obtained by analyzing the output of position sensing circuitry. The position sensing circuitry, preferably including a LVDT position sensor, is also used to determine braking load, a brake controller including circuitry for effecting displacement of one or more reciprocating rams to load a brake disk stack by a predetermined amount based on a present displacement value of the position signal obtained from the position sensor. The position sensor preferably includes a LVDT transducer connected between the reciprocating ram and a brake housing, and the motive device preferably includes a servo motor.

Abstract: A parking brake monitor and adjustment control system controls parking brake operation of an electromechanically actuated brake system which applies a parking brake force to a wheel. The system includes a monitor circuit for producing an output signal which intermittently causes the brake system to readjust the parking brake force applied to the wheel.

Abstract: An electrically actuated aircraft brake system and method which provides for brake wear measurement, brake running clearance adjustment, ram position-based control and improved construction and operation. Brake wear and running clearance measurement are obtained by analyzing the output of position sensing circuitry. The position sensing circuitry, preferably including a LVDT position sensor, is also used to determine braking load, a brake controller including circuitry for effecting displacement of one or more reciprocating rams to load a brake disk stack by a predetermined amount based on a present displacement value of the position signal obtained from the position sensor. The position sensor preferably includes a LVDT transducer connected between the reciprocating ram and a brake housing, and the motive device preferably includes a servo motor.

Abstract: An aircraft brake assembly, wherein the actuator portion of the brake assembly is no longer provided as part of the brake assembly but instead as part of the aircraft landing gear. Accordingly, the actuator portion or individual actuators assemblies are designated as Line Replacement Units (LRUs), which are replaceable independently of other brake components, e.g., the torque tube and heat sink, which then comprise the brake assembly designated as a separate LRU. This new arrangement is particularly suited to electro-mechanically actuated brakes, where actuator maintenance intervals will typically be more closely related to landing gear maintenance intervals than to brake maintenance (i.e., hydraulic actuator and/or heat sink maintenance). The invention also provides for more effective and desirable mounting of one or more electromechanical actuators wherein reactionary loads are transferred in compression as opposed to in tension through mounting bolts or other removable fasteners.

Abstract: A speed reduction system for decreasing the speed of a moving craft has a craft engaging device, a control mechanism, and a hydraulic energy transfer system adapted to transmit energy from the craft engaging device to the control mechanism. The control mechanism is adapted to actively control release of energy from the hydraulic energy transfer system during the decrease of the speed of the craft. A method of controlling the operation of a valve includes adjusting the valve during the operation of the valve after comparing a condition to a desired condition determined by a profile. A hydraulic valve has a valve member defining passages arranged to balance the force of the fluid pressure acting on the valve member and an actuator connected to the valve member. A valve control system includes a controller and a driver arranged with the controller. The position of the valve is adjusted during a predetermined cycle to control the operation of the valve.

Abstract: An aircraft brake assembly, wherein the actuator portion of the brake assembly is no longer provided as part of the brake assembly but instead as part of the aircraft landing gear. Accordingly, the actuator portion or individual actuators assemblies are designated as Line Replacement Units (LRUs), which are replaceable independently of other brake components, e.g., the torque tube and heat sink, which then comprise the brake assembly designated as a separate LRU. This new arrangement is particularly suited to electro-mechanically actuated brakes, where actuator maintenance intervals will typically be more closely related to landing gear maintenance intervals than to brake maintenance (i.e., hydraulic actuator and/or heat sink maintenance). The invention also provides for more effective and desirable mounting of one or more electro-mechanical actuators wherein reactionary loads are transferred in compression as opposed to in tension through mounting bolts or other removable fasteners.

Abstract: An electrically actuated aircraft brake system and method which provides for brake wear measurement, brake running clearance adjustment, ram position-based control and improved construction and operation. Brake wear and running clearance measurement are obtained by analyzing the output of position sensing circuitry. The position sensing circuitry, preferably including a LVDT position sensor, is also used to determine braking load, a brake controller including circuitry for effecting displacement of one or more reciprocating rams to load a brake disk stack by a predetermined amount based on a present displacement value of the position signal obtained from the position sensor. The position sensor preferably includes a LVDT transducer connected between the reciprocating ram and a brake housing, and the motive device preferably includes a servo motor.

Abstract: A lining wear measurement system which accepts signals from a plurality of movement/displacement sensors coupled to respective auto-adjusters of vehicle brakes and giving information about prevailing brake pad/lining thickness. The system includes a means to hold internally a target wear-out point representing a minimum acceptable brake lining thickness based upon the characteristics of known linings and an internally stored starting point which is set automatically at a suitable point in time after the brake has been equipped with a set of replacement linings so as thereby to take account of the reducing disc or drum thickness as the life of the brake progress. Alternatively, the system can hold an internally stored starting point which is arranged to be manually initiated but actually stored at some suitable point in time thereafter upon each set of replacement linings being installed.

Abstract: An electromechanical braking system utilizes redundancy features to provide safe and reliable braking. The braking system is configured to operate on power provided by multiple power sources. Different modes of braking are available based on whether a failure has occurred in one or more power sources. Additionally, system redundancy allows for failure in one or more primary components without total loss of braking capacity. Proportional braking is provided even in an emergency braking mode.