Abstract: A rotor blade having a detachable fairing is disclosed. The rotor blade includes leading and trailing edge fairings secured to the blade spar and one or more control lines extending between of the fairings and the blade spar. A detachable fairing extends from one or both of the leading and trailing edge fairings toward one of the distal and proximal ends of the blade spar. The detachable fairing and blade spar form an airfoil contour. The detachable fairing may secure to a tip jet attachment fitting at a distal end of the blade spar. A mounting structure including upper and lower plates may secure near a proximal end of the blade spar and the detachable fairing may secure to both the upper and lower plates to form all or part of an airfoil contour. The mounting structure may include a spherical seat engaging a spherical surface of a hub shroud.

Abstract: An aircraft is disclosed having an engine and a propeller mounted to a fuselage. An empennage mounts to the aircraft and includes first and second horizontal stabilizers separated by a distance greater than the diameter of a stream tube of the propeller at the horizontal stabilizers. A rudder extends between the horizontal stabilizers and is positioned within the stream tube of the propeller. The rudder may mount to a first vertical stabilizer extending between the horizontal stabilizers. The horizontal stabilizers may be secured to second and third vertical stabilizers to form a duct having the rudder positioned within the duct. Additional rudders may mount to the second and third vertical stabilizers.

Abstract: A rotorcraft is disclosed. The rotorcraft may include a rotor having at least one tip nozzle, a compressor having an outlet for compressed air, and a network of conduits connecting the outlet of the compressor with the tip nozzle. In operation, the compressor may deliver a flow of compressed air to the tip nozzle. As the flow of compressed air exits the at least one tip nozzle, it may cause rotation of the rotor. This rotation may prerotate the rotor and shorten the take off distance required by the rotorcraft. Take off of the rotorcraft may be accomplished without ever adding fuel to the flow of compressed air to the tip nozzle.

Abstract: Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use.

Abstract: Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use.

Abstract: Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use.

Abstract: Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use.

Abstract: A dual-seat control system for an aircraft provides an upright mounted at one end to pivot by actuation of a user near the other end. Cross beams extend from the upper end of the upright to positions in front of each user. The cross beams each carry a handle at an outboard end by which an operator can move the upright as a control stick in either a pitch-control direction, or a roll-control direction. The cross beams are free to move in one degree of freedom with respect to the upright, and are fixed in the other degree of freedom. Typically, the handle is attached in a manner to move in rigid body motion with respect to the upright in a pitch-control direction, while being free to move in a plane defined by the cross beam and upright at will, according to the desires of an operator. In certain embodiments, the handle may be required to be parallel to the upright in all positions, from a lower stowed position to an upper deployed position.