Abstract: A landing support assembly to at least partially support an aerial vehicle on a surface may include a strut extendable to a deployed state and retractable to a stowed state during flight. The strut may be configured to pivot with respect to a bracket coupled to the aerial vehicle between the deployed state and the stowed state. The landing support assembly further may include a strut actuator coupled to the strut via a linkage to cause the strut to pivot relative to the bracket. The landing support assembly also may include a foot coupled to an end of the strut remote from the bracket. The foot may be configured to change between a retracted state during flight having a first cross-sectional area and an at least partially splayed state for at least partially supporting the aerial vehicle and having a second cross-sectional area greater than the first cross-sectional area.

Abstract: A powertrain for an aerial vehicle may include a mechanical power source and a propulsion member coupled to the mechanical power source and configured to be coupled to the chassis and convert at least a portion of the mechanical power supplied by the mechanical power source into at least one of a thrust force or cooling. The powertrain also may include an electric power generation device configured to convert at least a portion of the mechanical power into electrical power. The powertrain further may include a powertrain control system associated with the powertrain and configured to at least partially control at least one of an output speed of the mechanical power source or a pitch angle associated with the propulsion member, based on at least one of an operation, a status factor, or at least one component characteristic associated with the aerial vehicle.

Abstract: Powertrains and related methods for an aerial vehicle may include a torque control system associated with the powertrain and configured to receive torque signals indicative of engine torque supplied by a mechanical power source or generator torque generated by an electric power generation device resisting the engine torque. The torque control system may be configured to generate, based in part on torque signals, a torque control signal configured to change the engine torque or change the generator torque. When torque signals indicate a relative reduction in the engine torque supplied by the mechanical power source, torque control signals may be configured to cause a relative reduction in the generator torque resisting the engine torque. When torque signals indicate a relative increase in the engine torque supplied by the mechanical power source, torque control signals may be configured to cause a relative increase in the generator torque resisting the engine torque.

Abstract: An aerial vehicle that can comprise a housing comprising an outer wall at least partially defining an interior space, a mechanical power source at least partially located in the interior space of the housing, an exhaust header in communication with the mechanical power source for communicating exhaust fluid from the mechanical power source, and an exhaust system comprising at least an exhaust chamber extending at least partially in the interior space of the housing. The exhaust chamber can be in communication with the exhaust header, and the exhaust system can comprise an exhaust outlet for communicating the exhaust fluid from the exhaust system outside the aerial vehicle.

Abstract: An aerial vehicle including a frame, a housing at least partially enclosing the frame, and a flap assembly mounted to at least one of the frame and the housing. The flap assembly can include a flap and an actuator. The aerial vehicle further can include a communication device coupled to the flap. The actuator can be operable to move the flap relative to the housing to at least partially maintain an orientation of the communication device relative to a remote system.

Abstract: A landing support assembly to at least partially support an aerial vehicle on a surface may include a strut extendable to a deployed state and retractable to a stowed state during flight. The strut may be configured to pivot with respect to a bracket coupled to the aerial vehicle between the deployed state and the stowed state. The landing support assembly further may include a strut actuator coupled to the strut via a linkage to cause the strut to pivot relative to the bracket. The landing support assembly also may include a foot coupled to an end of the strut remote from the bracket. The foot may be configured to change between a retracted state during flight having a first cross-sectional area and an at least partially splayed state for at least partially supporting the aerial vehicle and having a second cross-sectional area greater than the first cross-sectional area.

Abstract: A powertrain for an aerial vehicle may include a mechanical power source and an electric power generation device mechanically coupled to the mechanical power source. The powertrain further may include an electric motor electrically coupled to the electric power generation device. A first propulsion member may be mechanically coupled to the mechanical power source and configured to provide a first thrust force. The powertrain also may include a second propulsion member mechanically coupled to the electric motor and configured to provide a second thrust force. A vehicle controller may be provided and configured to at least partially control aerial maneuvering of the aerial vehicle, and cause supply of a first portion of the mechanical power to the first propulsion member and a second portion of the mechanical power to the electric power generation device based at least in part on at least one characteristic associated with maneuvering of the aerial vehicle.

Abstract: A rotating suction wand for a cooler box screen including a hollow body for attaching to a suction hose. A first slot and at least a second slot are formed in the hollow body in fluid communication with an interior of the hollow body for facingly engaging a screen. The construction and arrangement of the slots redistributes suction force along the length of the wand in such a way as to compensate for differences in angular rotational speed of the wand at varying radial distances from the center of the wand as well as to overcome suction force reduction which normally occurs from the center to the ends of the wand. Consequently, debris is more effectively removed from the screen from the central regions of the wand to radially distal regions thereof.