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 structural mechanism for an aircraft includes a support, a hinged surface, and a hinge assembly joining the hinged surface to the support. An actuation system includes an actuator shaft engaged to the hinges and lying coincident with a hinged-surface hinge axis and extending through the aligned center passagways of the hinges of the hinge assembly. A lock is selectively operable to lock the hinged surface to the support when the actuator shaft engages the lock. An actuator structure is controllably operable to move the actuator shaft longitudinally along the hinge-surface hinge axis between a first shaft axial position wherein the actuator shaft engages the lock and the hinges, and a second shaft axial position wherein the actuator shaft does not engage the lock but does engage the hinges, and is controllably operable to rotate the actuator shaft about the hinged-surface hinge axis.

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.