Abstract: A retractable rotor system for an aircraft includes a rotor blade with a leading edge, a trailing edge, and an internal collapsible web. The leading edge includes a flexible portion whose lower edge contacts but is not structurally joined to the lower skin. When the leading edge is peeled forward from the lower skin, the blade elastically collapses to the thickness of its constituent layers. The rotor blade extends through a support frame connectable to the aircraft to secure the rotor blade to a spool. Rotating the spool retracts the rotor blade through the support frame while pulling the rotor blade over a fixed actuating member, placing the rotor blade in the collapsed condition and winding the rotor blade onto the spool. Rotating the spool in the opposite direction unwinds the rotor blade from the spool, through the frame, causing the rotor blade to relax into the expanded condition.

Abstract: A retractable rotor system for an aircraft includes a rotor blade with a leading edge, a trailing edge, and an internal collapsible web. The leading edge includes a flexible portion whose lower edge contacts but is not structurally joined to the lower skin. When the leading edge is peeled forward from the lower skin, the blade elastically collapses to the thickness of its constituent layers. The rotor blade extends through a support frame connectable to the aircraft to secure the rotor blade to a spool. Rotating the spool retracts the rotor blade through the support frame while pulling the rotor blade over a fixed actuating member, placing the rotor blade in the collapsed condition and winding the rotor blade onto the spool. Rotating the spool in the opposite direction unwinds the rotor blade from the spool, through the frame, causing the rotor blade to relax into the expanded condition.

Abstract: An aircraft includes a fuselage, a main wing pivotally coupled to an aft portion of the fuselage, and a canard coupled to a forward portion of fuselage, wherein the main wing and the canard are configured to be connected together for supersonic flight and disconnected from each other for subsonic flight.

Abstract: An aircraft includes a fuselage, a main wing pivotally coupled to an aft portion of the fuselage, and a canard coupled to a forward portion of fuselage, wherein the main wing and the canard are configured to be connected together for supersonic flight and disconnected from each other for subsonic flight.

Abstract: A device is provided to install and remove a fifth wheel hitch from a vehicle. This device includes an attachment bar connected to the kingpin of a fifth wheel trailer. The attachment bar is in communication with an extension arm. The extension arm includes a hoist with a cable to be attached to the fifth wheel hitch. Operation of the hoist will lift or lower the fifth wheel hitch to its desired position.

Abstract: A device is provided to install and remove a fifth wheel hitch from a vehicle. This device includes an attachment bar connected to the kingpin of a fifth wheel trailer. The attachment bar is in communication with an extension arm. The extension arm includes a hoist with a cable to be attached to the fifth wheel hitch. Operation of the hoist will lift or lower the fifth wheel hitch to its desired position.