An unmanned flying device including a body; a first blade and at least a second blade; a coupling assembly for coupling the first blade and the at least second blade to the body, wherein the coupling assembly urges the collapsing of the first blade and the at least second blade towards the body; and wherein both the first blade and the at least second blade are rotateable about the body, and wherein the first blade and the at least second blade are deployable away from the body via rotation of the first and the at least second blades about the body.

A projectile-launched aircraft system includes a projectile launcher including a triggering mechanism, a rotary-wing, hover-capable aircraft including a rotor assembly that includes at least one rotor blade, wherein the rotor blade includes a stowed configuration and a deployed configuration that is circumferentially spaced from the stowed configuration about a pivot axis, wherein, upon actuation of the triggering mechanism, the projectile launcher is configured to launch the aircraft along a flightpath.

The present technology is directed to a remotely controlled aircraft that can be transported without the risk of damaging certain components, such as the arms and/or propellers. In one non-limiting example, the remotely controlled aircraft technology described herein provides a housing that allows the arms of the remotely controlled aircraft to extend and/or retract through openings in the housing. When retracted, the arms and propellers are protected within an area of the structure of the housing, and when extended, the arms and propellers are operable to make the remotely controlled aircraft fly.

A payload delivery device configured to deliver an aircraft deployed payload along a flight path to a predetermined landing destination includes a support member configured to be removably attached to the payload, a flight control and navigation system module configured to control orientation of the plurality of control surfaces while the payload is travelling along the flight path to the predetermined landing destination, a control surface assembly module including a plurality of control surfaces, a rotor assembly including a plurality of rotor blades having a central axis of rotation, and a collective control assembly module including at least one collective servomotor configured to control a plurality of control linkages connected to the plurality of rotor blades.

An unmanned flying device including a body; a first blade and at least a second blade; a coupling assembly for coupling the first blade and the at least second blade to the body, wherein the coupling assembly urges the collapsing of the first blade and the at least second blade towards the body; and wherein both the first blade and the at least second blade are rotatable about the body, and wherein the first blade and the at least second blade are deployable away from the body via rotation of the first and the at least second blades about the body.

The present technology is directed to a remotely controlled aircraft that can be transported without the risk of damaging certain components, such as the arms and/or propellers. In one non-limiting example, the remotely controlled aircraft technology described herein provides a housing that allows the arms of the remotely controlled aircraft to extend and/or retract through openings in the housing. When retracted, the arms and propellers are protected within an area of the structure of the housing, and when extended, the arms and propellers are operable to make the remotely controlled aircraft fly.

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.

The rotary wing drone comprises at least one rotor carried by a drone structure, wherein the drone structure comprises a drone body and at least one group of arms comprising a plurality of arms rotatably mounted on the drone body about the same axis of rotation, between a deployed position for flight and a folded position for transport.

Vehicles such as unmanned air vehicles that are capable of movement from an open, flight configuration to an enclosed configuration in which all major flight components can be protected by an outer shell are disclosed. In the enclosed configuration, the vehicles can take on standard geometric shapes such as a rectangular prism, sphere, cylinder, or another shape, so as to not be recognizable as an unmanned air vehicle. Embodiments of vehicles can also include interchangeable and/or wireless motor arms, motor arms which are electrically connected to the remainder of the vehicle only when in an open configuration, remote controllers removably attached to the remainder of the vehicle, and clip or other attachment mechanisms for attachment to objects such as backpacks.

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.