Abstract: An electromechanical blade pitch control system includes a propeller hub, a blade having an adjustable pitch angle, and a blade bearing hub operably coupled to the blade. The system includes a linear actuator operably coupled to the blade bearing hub and a rotary actuator operably coupled to the linear actuator via a planetary gear system. The system is configured such that the blade bearing hub, linear actuator, and rotary actuator are housed within the propeller hub, and further configured such that actuation of the linear actuator results in a change in a pitch angle of the blade.

Abstract: A sensor lift mechanism for deploying a sensor from a tail cone of an aircraft includes a frame mounted onto a side wall of the tail cone via a mounting assembly. The frame includes a first roller track and a second roller track aligned with the first roller track. A roller carriage assembly includes a plurality of rollers configured for rolling along the first and second roller tracks. A sensor platform is mechanically coupled to the carriage assembly and configured for mounting the sensor thereto. A drive unit is operatively coupled to the frame. The drive unit translates the roller carriage assembly vertically between the first and second roller tracks to move the sensor platform between a stowed position and a deployed position. A floor of the tail cone includes a track door configured to open for deploying the sensor beneath the tail cone.

Abstract: An electromechanical pitch control system for modifying a collective blade pitch of a multi-blade propeller includes a pitch control rod mechanically coupled via a distal end to a plurality of blades of a propeller, a bearing assembly operatively connected to a proximal end of the pitch control rod, and an electric actuator operatively connected to the bearing assembly. The bearing assembly allows the electric actuator to remain stationary while the pitch control rod rotates with the propeller. The electric actuator is configured to translate the pitch control rod in a longitudinal direction for adjusting an incidence angle of the blades.

Abstract: A track door system for an aircraft includes a door having a first side and a second side opposite the first side. A first roller track and a second roller track are aligned adjacent one another on the first side of the door. A third roller track and a fourth roller track are aligned adjacent one another on the second side of the door. A first motion driver is configured to move the door along the first roller track and the second roller track. A second motion driver is configured to move the door along the third roller track and the fourth roller track. A drive unit is operatively coupled to the first motion driver and the second motion driver to provide electromechanical power for cooperatively moving the door forward to an open position or aft to a closed position.

Abstract: An electromechanical blade pitch control system includes a propeller hub, a blade having an adjustable pitch angle, and a blade bearing hub operably coupled to the blade. The system includes a linear actuator operably coupled to the blade bearing hub and a rotary actuator operably coupled to the linear actuator via a planetary gear system. The system is configured such that the blade bearing hub, linear actuator, and rotary actuator are housed within the propeller hub, and further configured such that actuation of the linear actuator results in a change in a pitch angle of the blade.

Abstract: A landing gear system for an aerial device includes a mounting structure and a main landing gear. The mounting structure is configured to be attached relative to a fuselage of the aerial device. The main landing gear includes a pair of aft swept struts and wheels mounted on each of the aft swept struts. The pair of aft swept struts is attached relative to the mounting structure and extends downwardly and rearwardly relative thereto.

Abstract: An electromechanical pitch control system for modifying a collective blade pitch of a multi-blade propeller includes a pitch control rod mechanically coupled via a distal end to a plurality of blades of a propeller, a bearing assembly operatively connected to a proximal end of the pitch control rod, and an electric actuator operatively connected to the bearing assembly. The bearing assembly allows the electric actuator to remain stationary while the pitch control rod rotates with the propeller. The electric actuator is configured to translate the pitch control rod in a longitudinal direction for adjusting an incidence angle of the blades.

Abstract: A track door system for an aircraft includes a door having a first side and a second side opposite the first side. A first roller track and a second roller track are aligned adjacent one another on the first side of the door. A third roller track and a fourth roller track are aligned adjacent one another on the second side of the door. A first motion driver is configured to move the door along the first roller track and the second roller track. A second motion driver is configured to move the door along the third roller track and the fourth roller track. A drive unit is operatively coupled to the first motion driver and the second motion driver to provide electromechanical power for cooperatively moving the door forward to an open position or aft to a closed position.

Abstract: A sensor lift mechanism for deploying a sensor from a tail cone of an aircraft includes a frame mounted onto a side wall of the tail cone via a mounting assembly. The frame includes a first roller track and a second roller track aligned with the first roller track. A roller carriage assembly includes a plurality of rollers configured for rolling along the first and second roller tracks. A sensor platform is mechanically coupled to the carriage assembly and configured for mounting the sensor thereto. A drive unit is operatively coupled to the frame. The drive unit translates the roller carriage assembly vertically between the first and second roller tracks to move the sensor platform between a stowed position and a deployed position. A floor of the tail cone includes a track door configured to open for deploying the sensor beneath the tail cone.