A quick release propeller for model airplanes is disclosed including two or more blades mounted to a hub. For each blade, the hub includes a slot and a shoulder. Each blade includes a base portion having pins which slide into the slot in the hub. The slots are curved which prevents the blades from being removed unless they are rotated at predefined threshold angle with respect to the hub.

Disclosed is a system and method for reducing the total latency for transferring a frame from the low latency camera system mounted on an aerial vehicle to the display of the remote controller. The method includes reducing the latency through each of the modules of the system, i.e. through a camera module, an encoder module, a wireless interface transmission, wireless interface receiver module, a decoder module and a display module. To reduce the latency across the modules, methods such as overclocking the image processor, pipelining the frame, squashing the processed frame, using a fast hardware encoder that can perform slice based encoding, tuning the wireless medium using queue sizing, queue flushing, bitrate feedback, physical medium rate feedback, dynamic encoder parameter tuning and wireless radio parameter adjustment, using a fast hardware decoder that can perform slice based decoding and overclocking the display module are used.

A folding propeller-hub assembly for VTOL aircraft provides two modes of operation, a vertical mode with unfolded propeller blades and a horizontal mode with propeller blades positionable in both an aerodynamic folded position and an active unfolded position. The propeller-hub assembly includes a plurality of propeller blades, a bedplate operably associated with a propeller-hub to fold or respectively unfold the propeller blades, the motor arranged between the propeller-hub and a rotating plate, a push rod positioned in the axis of the propeller rotation along the propeller-hub assembly. The bedplate is operably associated with a device which connects with the spinner bottom of the spinner to rotate the propeller blades. A restraint plate by virtue of the push rod is operably associated with the propeller blades to rotate each propeller blade about a propeller blade pin axis.

A rotor blade rotation system includes two or more rotor blades, each rotor blade in mechanical communication with a hub and pivotable about an axis of rotation, a bearing plate comprising a rotating portion and a non-rotating portion, a fold linkage coupled to the rotating portion of the bearing plate and in mechanical communication with the rotor blade, and an actuator coupled to the non-rotating portion of the bearing plate and operable to reposition the bearing plate from a first position to a second position such that the folding links pivot the rotor blades from a deployed position to a forward folded position.

Embodiments of the present invention disclose an arm and an unmanned aerial vehicle (UAV). The arm is mounted on a movable object and is in contact with an outline of the movable object after being folded. The UAV includes a vehicle body, the arm connected to the vehicle body and a power device disposed on the arm. The arm is in contact with an outline of the vehicle body after being folded. According to the technical solutions, the arm provided in the embodiments of the present invention can be in contact with the outline of the movable object after being folded, so that the structure of the movable object to which the arm is applied is more compact.

An exemplary high-speed hybrid propulsion system for a tiltrotor aircraft includes two pivotal nacelles, each nacelle comprising an electric motor coupled to a proprotor; an electric aircraft system; an electric generator; an electrical bus electrically connected to the electric generator, the electric motors, and the electric aircraft system; and a convertible turbofan engine coupled to an electric generator through a drive shaft.

An aircraft capable of vertical take-off and landing comprises a fuselage, at least one processor carried by the fuselage and a pair of aerodynamic, lift-generating wings extending from the fuselage. A plurality of vectoring rotors are rotatably carried by the fuselage so as to be rotatable between a substantially vertical configuration relative to the fuselage for vertical take-off and landing and a substantially horizontal configuration relative to the fuselage for horizontal flight. The vectoring rotors are unsupported by the first pair of wings. The wings may be modular and removably connected to the fuselage and configured to be interchangeable with an alternate pair of wings. A cargo container may be secured to the underside of the fuselage, and the cargo container may be modular and interchangeable with an alternate cargo container.

A manned or unmanned aircraft has a main body with a circular shape and a circular outer periphery. One or more rotor blades extend substantially horizontally outward from the main body at or about the circular outer periphery. In addition, one or more counter-rotation blades extend substantially horizontally outward from said main body at or about the circular outer periphery, but vertically offset from the main rotor blades. The rotor blades and counter-rotation blades can be folded upward into a storage position. In addition, the unmanned aircraft can have solar panels positioned about the top housing and fuselage of the aircraft.

A multi-rotor unmanned aerial vehicle (UAV) includes a central body, a plurality of branch members connected to the central body, each branch member configured to support a corresponding actuator assembly, a communication module disposed within the central body and configured to establish a communication channel between the UAV and a remote device, and an indicator light disposed on one of the plurality of branch members. The indicator light is configured to indicate whether the communication channel is established.

An unmanned aerial vehicle (UAV) includes a central body and a plurality of arms extending from the central body. Each of the plurality of arms supports one or more propulsion units. At least one arm of the plurality of arms is configured to transform between (1) a flight configuration that provides lift while the UAV is in flight and (2) a landing configuration in which the at least one arm is configured to function as a landing support that bears weight of the UAV while the UAV is not in flight. The at least one arm is configured to transform between the flight configuration and the landing configuration in response to operation of the one or more propulsion units supported by the at least one arm.