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.

Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a plurality of outer tracks, wherein each outer track of the plurality of outer tracks includes: an inner outer roller channel; and an outer inner roller channel positioned above the inner outer roller channel; an aerodynamic surface connected to a carrier, wherein the carrier includes rollers configured to move within inboard inner roller channels of the plurality of outer tracks; and a plurality of fixed rollers mounted to one or more longitudinal structural elements in an aerodynamic structure, wherein the plurality of fixed rollers are disposed within the outer roller channels of the plurality of outer tracks.

Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a plurality of outer tracks, wherein each outer track of the plurality of outer tracks includes: an inner outer roller channel; and an outer inner roller channel positioned above the inner outer roller channel; an aerodynamic surface connected to a carrier, wherein the carrier includes rollers configured to move within inboard inner roller channels of the plurality of outer tracks; and a plurality of fixed rollers mounted to one or more longitudinal structural elements in an aerodynamic structure, wherein the plurality of fixed rollers are disposed within the outer roller channels of the plurality of outer tracks.

A wing (5) for an aircraft (1) including a main wing (11) and a high lift assembly (13) having a high lift body (15), and a connection assembly (17) movably connecting the high lift body (15) to the main wing (11), wherein the connection assembly (17) includes a first connection element (19) and a second connection element (21) movably mounted to the main wing (11) and mounted to the high lift body (15), wherein the connection assembly (17) includes a first drive unit (27) drivingly coupled to the first connection element (19), a second drive unit (29) drivingly coupled to the second connection element (21) and a third connection element (57) movably mounted to the main wing (11) and mounted to the high lift body (15), the third connection element (57) is arranged between the first connection element (19) and the second connection element (21).

A rotary mechanical transmission, includes: a containment structure, a first rotary element, connected to a drive unit to define a mechanical power input unit and rotatable about an axis. The transmission also includes a fixed guide and a second rotary element, rotatable about said axis and defining a power output unit. A connecting element extends along the axis and couples to the first rotary element by a first threaded connection. The connecting element is also coupled with one of either the fixed guide and the second rotary element by a second threaded connection, and with the other of the fixed guide and the second rotary element by a linear guide parallel to the axis. The first threaded connection and second threaded connection have different pitches in such a way as to vary the angular speed between the connecting element and the first rotary element.

A rotary mechanical transmission, includes: a containment structure, a first rotary element, connected to a drive unit to define a mechanical power input unit and rotatable about an axis. The transmission also includes a fixed guide and a second rotary element, rotatable about said axis and defining a power output unit. A connecting element extends along the axis and couples to the first rotary element by a first threaded connection. The connecting element is also coupled with one of either the fixed guide and the second rotary element by a second threaded connection, and with the other of the fixed guide and the second rotary element by a linear guide parallel to the axis. The first threaded connection and second threaded connection have different pitches in such a way as to vary the angular speed between the connecting element and the first rotary element.

A hybrid aerial vehicle (HAV) comprising: a fuselage of the HAV; a first mechanism within the fuselage for accepting a plurality of wings of the HAV, the first mechanism allowing coordinated contraction of the plurality of wings essentially into the fuselage such that tips of the wings are position in proximity of the fuselage and coordinated extension of the wings such that tips of each wing are positioned away from the fuselage; a first wing extending from the port side of the fuselage and connected to the first mechanism; a second wing extending from the starboard side of the fuselage and connected to the first mechanism; a second mechanism placed within the fuselage in proximity to its front end, the second mechanism allowing motion of propellers of the HAV affixed there to between a first plain and a second plain; a first set of propellers affixed at the port side of the fuselage to the second mechanism; a second set of propellers affixed at the starboard side of the fuselage to the second mechanism; a third mechanism placed within the fuselage in proximity to its rear end, the third mechanism allowing motion of propellers of the HAV affixed there to between a first plain and a second plain, and further placing the propellers affixed thereto to be at a vertical displacement with respect to the propellers affixed to the second mechanism; a third set of propellers affixed at the port side of the fuselage to the third mechanism; and a fourth set of propellers affixed at the starboard side of the fuselage to the third mechanism.

A hybrid aerial vehicle (HAV) comprising: a fuselage of the HAV; a first mechanism within the fuselage for accepting a plurality of wings of the HAV, the first mechanism allowing coordinated contraction of the plurality of wings essentially into the fuselage such that tips of the wings are position in proximity of the fuselage and coordinated extension of the wings such that tips of each wing are positioned away from the fuselage; a first wing extending from the port side of the fuselage and connected to the first mechanism; a second wing extending from the starboard side of the fuselage and connected to the first mechanism; a second mechanism placed within the fuselage in proximity to its front end, the second mechanism allowing motion of propellers of the HAV affixed there to between a first plain and a second plain; a first set of propellers affixed at the port side of the fuselage to the second mechanism; a second set of propellers affixed at the starboard side of the fuselage to the second mechanism; a third mechanism placed within the fuselage in proximity to its rear end, the third mechanism allowing motion of propellers of the HAV affixed there to between a first plain and a second plain, and further placing the propellers affixed thereto to be at a vertical displacement with respect to the propellers affixed to the second mechanism; a third set of propellers affixed at the port side of the fuselage to the third mechanism; and a fourth set of propellers affixed at the starboard side of the fuselage to the third mechanism.

A system for an aircraft wing including a power drive unit (101), a first actuator (104C) for actuating a first aerodynamic device (103), a second actuator (104A) for actuating a second aerodynamic device (102), a first drive path (109B) configured to operate between the power drive unit (101) and the first actuator (104C), a second drive path (109A) operably connecting the power drive unit (101) and the second actuator (104A), the first drive path (109B) including a lost motion device (108A), the lost motion device (108A) being configured to selectively operably connect the power drive unit (101) to the first actuator (104C) and selectively operably disconnect the power drive unit (101) from the first actuator (104C).

Various flight control components can be operated through gearbox driven rotary actuators. In the event of a jam occurring the gearbox, the gearbox can be decoupled from a surrounding support housing to enable free-trailing or limited motion relative to the support housing. The motion may or may not be damped. Decoupling the gearbox enables the flight control component to move to a neutral or non-interfering position even when user control over the component has been lost.