A trim actuator (102) for a horizontal stabilizer (210) comprises a power screw (106), a rotary actuator (104), configured to rotate the power screw (106), and a nut (108), configured to translate along the power screw (106) when the power screw (106) is rotated. Trim actuator (102) also comprises an anti-back-drive mechanism (114), configured to prevent the power screw (106) from rotating in a first rotational direction when a first force is applied to the nut (108) in a first axial direction and to prevent the power screw (106) from rotating in a second rotational direction, opposite the first rotational direction, when a second force is applied to the nut (108) in a second axial direction. Trim actuator (102) further comprises a sensor (120), configured to measure internal loading of the anti-back-drive mechanism (114) when the first force is applied to the nut (108) in the first axial direction or when the second force is applied to the nut (108) in the second axial direction.

A trim actuator (102) for a horizontal stabilizer (210) comprises a power screw (106), a rotary actuator (104), configured to rotate the power screw (106), and a nut (108), configured to translate along the power screw (106) when the power screw (106) is rotated. Trim actuator (102) also comprises an anti-back-drive mechanism (114), configured to prevent the power screw (106) from rotating in a first rotational direction when a first force is applied to the nut (108) in a first axial direction and to prevent the power screw (106) from rotating in a second rotational direction, opposite the first rotational direction, when a second force is applied to the nut (108) in a second axial direction. Trim actuator (102) further comprises a sensor (120), configured to measure internal loading of the anti-back-drive mechanism (114) when the first force is applied to the nut (108) in the first axial direction or when the second force is applied to the nut (108) in the second axial direction.

A gear drive, such as for an actuator, is a right-angle drive where toothed outer ridge of a face gear is coupled to teeth of a motor output shaft, and a set of planetary gears are engaged with a central sun gear of the face gear. The sun gear and planetary gears are aligned with the motor output shaft. For instance the motor output shaft may be substantially in the same plane with the sun gear and the planetary gears. From another standpoint the axis of the motor output shaft may intersect the sun gear, as well as intersecting a volume that the planetary gears sweep through as the planetary gears engage the sun gear.

An aircraft having an empennage rotatable about a longitudinal axis via an electric motor drive is disclosed herein. A pair of horizontal stabilizers extend from opposing sides of the rotatable empennage and are independently rotatable via electric motor drives. The rotatable empennage is operable for controlling yaw, pitch and rolling moments without a traditional vertical stabilizer and rudder system which can reduce weight as well as the radar cross section of the aircraft. This technology can also be applied to a weapon control system such missile such as a missile.

An aircraft having an empennage rotatable about a longitudinal axis via an electric motor drive is disclosed herein. A pair of horizontal stabilizers extend from opposing sides of the rotatable empennage and are independently rotatable via electric motor drives. The rotatable empennage is operable for controlling yaw, pitch and rolling moments without a traditional vertical stabilizer and rudder system which can reduce weight as well as the radar cross section of the aircraft. This technology can also be applied to a weapon control system such missile such as a missile.

A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

In order to improve linear drives on aircraft with regards to backlash, gear reduction, self-lock capability, load transfer and wear, a linear drive device is provided that has a first member with engaging teeth, such as a tooth rack and a second member which functions as a drive unit. The second member includes a plurality of movable teeth that are actuated by a cam shaft. The cam shaft has a control cam portion that is shaped such that the movable teeth perform a wave-like motion that forces the first member along its longitudinal direction relative to the second member.

In order to improve linear drives on aircraft with regards to backlash, gear reduction, self-lock capability, load transfer and wear, a linear drive device is provided that has a first member with engaging teeth, such as a tooth rack and a second member which functions as a drive unit. The second member includes a plurality of movable teeth that are actuated by a cam shaft. The cam shaft has a control cam portion that is shaped such that the movable teeth perform a wave-like motion that forces the first member along its longitudinal direction relative to the second member.

An aircraft wing with a wing structure and a spoiler movable between a stowed configuration and a deployed configuration are disclosed. The spoiler includes an actuator configurable between an engaged mode and a disengaged mode. When the actuator is in the engaged mode, the actuator can restrict movement of the spoiler and move the spoiler between the stowed configuration and deployed configuration. In the disengaged mode, the actuator allows free movement of the spoiler, such that the spoiler may pop up due to reduced air pressure on the aircraft wing.