Abstract: A method, apparatus, and computer program product are present for controlling a control surface. A load is identified on the control surface to form an identified load. A direction of movement of the control surface is identified from the identified load to form an identified movement. A brake associated with the control surface is engaged if the identified movement is away from a desired position for the control surface.

Abstract: A method, apparatus, and computer program product are present for controlling a control surface. A load is identified on the control surface to form an identified load. A direction of movement of the control surface is identified from the identified load to form an identified movement. A brake associated with the control surface is engaged if the identified movement is away from a desired position for the control surface.

Abstract: A system and method of command signal conditioning in high response systems is disclosed. The system includes a central digital controller having a digital controller frame rate, a motor, a motor controller in communication with the digital controller and the motor, the motor controller having a motor controller frame rate higher than the digital controller frame rate, and a signal conditioner adapted to condition the command signal to produce a modified command signal at the motor controller frame rate. The signal conditioner is preferably implemented in software. In one embodiment, the signal conditioner is adapted to calculate a moving average at the frame rate of the motor controller. In another embodiment, the signal conditioner comprises a first order hold and a filter in communication therewith. A method of command signal conditioning in accordance with the foregoing is also disclosed.

Abstract: A flight control system for an aircraft directs a primary surface that is pivotable with respect to the aircraft with a moveable tab located at the end of the primary surface. A primary surface actuator maintains a position of the primary surface. A tab actuator moves the tab with respect to the primary flight control surface. A controller configured to coordinate the movement of the primary flight control surface with the movement of the tab by deflecting the tab with respect to the primary flight control surface, thereby allowing aerodynamic forces acting upon the deflected tab to position the primary flight control surface at a desired position. The primary flight control surface can then be maintained at the desired position by the primary surface actuator.

Abstract: Systems and techniques are described for actuating a control surface about a pivot point using variable moments. A bracket having a moment arm is coupled to the pivot point such that the bracket is rotatable about the pivot point to actuate the surface. A power actuator has a shaft coupled to the bracket at a coupling point on the moment arm such that actuation force applied to the shaft results in a moment produced about the pivot point. A linear actuator is configured to adjust the location of the coupling point with respect to the pivot point to thereby changing the moment arm and the moment produced about the pivot point as the bracket rotates. By adjusting the distance between the pivot point and the coupling point, the moments produced about the pivot point can be increased while conserving actuator power.

Abstract: A system and method for monitoring a reliability status of an actuator include determining a virtual actuator load value (VALV) based on various load factor parameters of a structural system component controlled by the actuator, absent sensed load values from the actuator. A virtual output force value (VOFV) is determined based on various actuator operational control values that occur in response to a position command from a main control and monitoring system of the structural system. A virtual torque efficiency (VTE) of the actuator is calculated based on the VALV and the VOFV. The VTE of the actuator is periodically calculated as the measured load factor parameters and the measured actuator operational control values change during operation of the structural system. The VTE data is collected, stored and analyzed to monitor the reliability status of the actuator during the life of the actuator.

Abstract: A system and method for monitoring freeplay within an actuator is provided. In accordance with various embodiments, the method includes collecting a plurality of actuator parameter data sets during a predetermined period. During the predetermined time period the actuator drive motor is commanded to extend and retract an actuator output ram operably connected to a movable component of a structural system such as a mobile platform. The method additionally includes selectively isolating various sets of the plurality of actuator parameter data sets that meet specific predetermined criterion. Furthermore, the method includes computing an amount of freeplay value within the actuator based on the isolated actuator parameter data sets.