Abstract: A propulsor brake lock system includes an aircraft propulsor, a reduction gear assembly, a brake shaft, and a brake assembly. The aircraft propulsor includes a propeller having a propeller input shaft coupled thereto. The reduction gear assembly includes at least an input gear and an output gear. The input gear and output gear are both rotatable with the propeller input shaft. The brake shaft is coupled to, and is rotatable with, the output gear. The brake assembly is coupled to the brake shaft and is moveable between a disengaged position, in which the brake shaft may rotate whenever the output gear rotates, and an engaged position, in which the brake shaft is prevented from rotating, thereby preventing rotation of the output gear, the input gear, and the propeller input shaft.

Abstract: A propulsor brake lock system includes an aircraft propulsor, a reduction gear assembly, a brake shaft, and a brake assembly. The aircraft propulsor includes a propeller having a propeller input shaft coupled thereto. The reduction gear assembly includes at least an input gear and an output gear. The input gear and output gear are both rotatable with the propeller input shaft. The brake shaft is coupled to, and is rotatable with, the output gear. The brake assembly is coupled to the brake shaft and is moveable between a disengaged position, in which the brake shaft may rotate whenever the output gear rotates, and an engaged position, in which the brake shaft is prevented from rotating, thereby preventing rotation of the output gear, the input gear, and the propeller input shaft.

Abstract: An actuator assembly including an actuator housing assembly and a single axis of rotation locking member fixedly attached to a portion of the actuator housing assembly and an external mounting structure. The single axis of rotation locking member restricting rotational movement of the actuator housing assembly about at least one axis. The single axis of rotation locking member is coupled at a first end to the actuator housing assembly about a Y axis and at a 90° angle to an X and Z axis providing rotation of the actuator housing assembly about the Y axis. The single axis of rotation locking member is coupled at a second end to a mounting structure, and more particularly a mounting pin, about an X axis and at a 90° angle to a Y and Z axis providing rotation of the actuator housing assembly about the X axis. The actuator assembly is thereby restricted from rotation about the Z axis.

Abstract: A relatively small, lightweight actuator includes a plurality of motors, an actuation element, a translation member, and a plurality of position sensors. The motors each supply a drive force to the actuation member, causing it to rotate. The translation member is configured, upon rotation of the actuator, to translate to a position. The position sensors sense the translational position of the translation member and the rotational position of each motor. The actuator is relatively small, lightweight, and can withstand the relatively severe environmental conditions and relatively significant levels of vibration and shock associated with many aerospace applications.

Abstract: An actuator assembly including an actuator housing assembly and a single axis of rotation locking member fixedly attached to a portion of the actuator housing assembly and an external mounting structure. The single axis of rotation locking member restricting rotational movement of the actuator housing assembly about at least one axis. The single axis of rotation locking member is coupled at a first end to the actuator housing assembly about a Y axis and at a 90° angle to an X and Z axis providing rotation of the actuator housing assembly about the Y axis. The single axis of rotation locking member is coupled at a second end to a mounting structure, and more particularly a mounting pin, about an X axis and at a 90° angle to a Y and Z axis providing rotation of the actuator housing assembly about the X axis. The actuator assembly is thereby restricted from rotation about the Z axis.

Abstract: An aircraft brake actuation system implements an anti-hysteresis feature that compensates for various hysteresis effects exhibited in an aircraft brake actuation system due to one or more sources of mechanical inefficiency within the system. The anti-hysteresis feature adjusts the command signal up or down, depending on the direction of the command, a predetermined amount based on the amount of hysteresis in the system. By doing so, the actual brake force supplied to the aircraft brake elements more accurately represents the brake force being commanded.

Abstract: A relatively small, lightweight valve actuator assembly that can withstand relatively high levels of vibration and shock includes a motor, a position sensor, and a drive belt mounted on an actuator housing assembly. The position sensor is preferably disposed within a sensor housing that is mounted on a side of the actuator housing assembly. As a result, the overall center-of-gravity (CG) and weight of the actuator assembly is significantly reduced, as is the overall size envelope.

Abstract: An electromechanical inlet guide vane actuation system includes one or more electric motor driven actuators that are used to appropriately position the inlet guide vanes in a gas turbine engine. The actuation system includes a control circuit that supplies guide vane actuation control signals in response to guide vane position command signals it receives. The guide vane actuation control signals are supplied to one or more electric motors, which position actuators, and thus the inlet guide vanes, to the commanded position.

Abstract: An aircraft brake actuation system includes an actuator for selectively moving to a position that corresponds to a commanded brake force. A cap assembly is coupled to the end of the actuator and is configured to engage an aircraft brake element and supply the commanded brake force to one or more aircraft wheels. The cap assembly is constructed of a low thermal conductivity material and has thermal resistance grooves formed therein. The cap assembly is also configured to compensate for certain undesired tangential movements that may occur during an aircraft brake cycle.

Abstract: A valve actuator assembly is provided for selectively opening and closing a valve. The valve actuator assembly includes a primary motor and secondary motor both operatively coupled to an output shaft and adapted to receive valve position commands and operable, in response thereto, to selectively drive the output shaft in a valve open or close direction and a tertiary motor adapted to receive a flow of pressurized air and operable, in response thereto, to drive the output shaft in a valve close direction.