An aerial vehicle with a plurality of selectively collapsible arms capable of transitioning between an extended state and a contracted state is described. In the extended position, the distance between the main body of the vehicle and the rotor associated with each arm is maximized. In the contracted state, the distance between the main body of the vehicle and the rotor associated with each arm is minimized. In certain embodiments, each of the arms may include one or more tape springs that are biased to selectively move the associated one or more rotors of each arm between the retracted and extended states.

An aerial vehicle with a plurality of selectively collapsible arms capable of transitioning between an extended state and a contracted state is described. In the extended position, the distance between the main body of the vehicle and the rotor associated with each arm is maximized. In the contracted state, the distance between the main body of the vehicle and the rotor associated with each arm is minimized. In certain embodiments, each of the arms may include one or more tape springs that are biased to selectively move the associated one or more rotors of each arm between the retracted and extended states.

A structural member for use in a rotor system which rotates about a rotational axis includes a pin which extends substantially perpendicular to the rotational axis, a filler component positioned adjacent the pin, and a plurality of layers of composite material having fibers oriented lengthwise along a central axis which is perpendicular to the rotational axis. The plurality of fibers in the layers of composite material is wrapped about the pin and the filler component such that the fibers extend along the central axis and the plurality of layers form an opening filled by the filler component and which decreases as a function of distance from the pin along the central axis.

A structural member for use in a rotor system which rotates about a rotational axis includes a pin which extends substantially perpendicular to the rotational axis, a filler component positioned adjacent the pin, and a plurality of layers of composite material having fibers oriented lengthwise along a central axis which is perpendicular to the rotational axis. The plurality of fibers in the layers of composite material is wrapped about the pin and the filler component such that the fibers extend along the central axis and the plurality of layers form an opening filled by the filler component and which decreases as a function of distance from the pin along the central axis.

An aircraft is provide including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. At least one flight control computer configured to independently control the upper rotor assembly and the lower rotor assembly through a fly-by-wire control system. A plurality of sensors to detect sensor data of at least one environmental condition and at least one aircraft state data, wherein the sensors provide the sensor data to the flight control computer.

An aircraft is provide including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. At least one flight control computer configured to independently control the upper rotor assembly and the lower rotor assembly through a fly-by-wire control system. A plurality of sensors to detect sensor data of at least one environmental condition and at least one aircraft state data, wherein the sensors provide the sensor data to the flight control computer.

A hub assembly for a rotary wing aircraft having a rotor shaft which rotates about a rotational axis includes: a hub extender arm coupled to the rotor shaft; a pitch bearing that is disposed within and connected to the hub extender arm; and a rotor blade assembly having an inboard section disposed within the hub extender arm and connected to the pitch bearing; wherein the hub extender arm has an inboard cross-sectional area where coupled to the rotor shaft that is greater than an outboard cross-sectional area where coupled to the pitch bearing.

An aerial vehicle with a plurality of selectively collapsible arms capable of transitioning between an extended state and a contracted state is described. In the extended position, the distance between the main body of the vehicle and the rotor associated with each arm is maximized. In the contracted state, the distance between the main body of the vehicle and the rotor associated with each arm is minimized. In certain embodiments, each of the arms may include one or more tape springs that are biased to selectively move the associated one or more rotors of each arm between the retracted and extended states.

An aerial vehicle with a plurality of selectively collapsible arms capable of transitioning between an extended state and a contracted state is described. In the extended position, the distance between the main body of the vehicle and the rotor associated with each arm is maximized. In the contracted state, the distance between the main body of the vehicle and the rotor associated with each arm is minimized. In certain embodiments, each of the arms may include one or more tape springs that are biased to selectively move the associated one or more rotors of each arm between the retracted and extended states.

A rotor blade retention device for use in an aircraft having a plurality of blades includes an array of cavities, each cavity adapted to receive a portion of a tension-torsion strap therein. Each cavity is oriented such that, when the portion of the tension-torsion strap is received therein, a central plane of the tension-torsion strap is inclined relative to a blade plane of rotation defined by the plurality of blades. The retention device may have a body that defines an aperture adapted to receive a portion of a rotor mast of the aircraft, may comprise a rotor mast of the aircraft, or may comprise first and second plates that cooperate to form the array of cavities and that are adapted to receive a portion of the rotor mast of the aircraft.