An apparatus for selectively increasing a wing area of an aircraft having a fuselage with an interior space includes an inflatable wing moveable between a stowed condition located in the interior space and a deployed condition located outside the interior space. The wing includes at least one inflatable spar. The inflatable spar is operatively coupled to a source of pressurized inflation fluid for selective inflation as the wing moves into the deployed condition. A plurality of reels is secured to the aircraft. A plurality of cables connects the wing to the reels. At least one reel is operable to unwind a selected cable to allow the wing to partially inflate to the deployed condition by ram air generated by movement of the aircraft as the inflatable spar is being inflated by the pressurized inflation fluid. A method for selectively increasing a wing area of an aircraft is also provided.

An apparatus for selectively increasing a wing area of an aircraft having a fuselage with an interior space includes an inflatable wing moveable between a stowed condition located in the interior space and a deployed condition located outside the interior space. The wing includes at least one inflatable spar. The inflatable spar is operatively coupled to a source of pressurized inflation fluid for selective inflation as the wing moves into the deployed condition. A plurality of reels is secured to the aircraft. A plurality of cables connects the wing to the reels. At least one reel is operable to unwind a selected cable to allow the wing to partially inflate to the deployed condition by ram air generated by movement of the aircraft as the inflatable spar is being inflated by the pressurized inflation fluid. A method for selectively increasing a wing area of an aircraft is also provided.

An aircraft wing having a fixed root part hingedly connected to a moveable tip part is disclosed. The tip part is configured to pivot relative to the root part about a substantially horizontal axis, between a load-alleviating configuration in which the tip part is oriented relative to the root part such that at least one of the upper and lower surface of the tip part is positioned away from the respective surface of the root part and a flight configuration in which the upper and lower surfaces of the tip part are continuations of the upper and lower surfaces of the root part. The shape of the tip part is controllably switchable between a cruise shape in which the tip part has positive camber and a recovery shape in which the tip part has negative camber.

A manned/unmanned aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. A tailless airplane which uses a control system that takes inputs for a traditional tailed airplane and translates those inputs to provide control utilizing non-traditional control methods.

A manned/unmanned aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. A tailless airplane which uses a control system that takes inputs for a traditional tailed airplane and translates those inputs to provide control utilizing non-traditional control methods.

A skin for an aircraft is configured to be disposed on a first rigid member and on a second rigid member. The second rigid member is movable with respect to the first rigid member and a distance is defined between the first rigid member and the second rigid member. A morphing member of the skin extends between the first rigid member and the second rigid member. The morphing member comprises first segments forming a first portion attached to the first rigid member and second segments forming a second portion attached to the second rigid member. The first and second portions are separated along a substantially linear seam in the absence of change in the distance and an orientation between the first rigid member and the second rigid member.

An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The system may include a sweeping gearbox designed to deploy at least one wing from a compact to a deployed arrangement. A controller may be configured to detect launch conditions, monitor for conditions, and trigger the gearbox upon condition fulfillment. Activation of the sweeping gearbox may result in wing deployment, adapted to the detected conditions. The method may involve deploying wings using the sweeping gearbox, launching detection, monitoring for conditions, and activating the gearbox for wing deployment upon condition detection.

An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The system may include a sweeping gearbox designed to deploy at least one wing from a compact to a deployed arrangement. A controller may be configured to detect launch conditions, monitor for conditions, and trigger the gearbox upon condition fulfillment. Activation of the sweeping gearbox may result in wing deployment, adapted to the detected conditions. The method may involve deploying wings using the sweeping gearbox, launching detection, monitoring for conditions, and activating the gearbox for wing deployment upon condition detection.

An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.