Abstract: A reconfigurable air vehicle wing may be selectively reconfigured to increase its chord. The wing has a leading edge portion and a trailing edge portion that are moved relative to one another to change the chord of the wing. The wing may be reconfigured from a compact configuration with a smaller chord, to and expanded configuration with a larger chord. The wing may include a foam material that forms part of the outer surface of the wing when the wing is in the expanded configuration. The foam may be a shape memory foam. Alternatively the leading edge section and the trailing edge section may be composed substantially fully of rigid materials. In either case the trailing edge section may be hingedly coupled to the leading edge section.

Abstract: A computer implemented method, apparatus, and computer usable program product for symmetric and anti-symmetric control of aircraft flight control surfaces to reduce wing-body loads. Commands are sent to symmetrically deploy outboard control surfaces to shift wing air-loads inboard based on airplane state and speed brake deployment. Surface rate retraction on a wing with peak loads is limited to reduce maximum loads due to wheel checkback accompanied by utilization of opposite wing control surfaces to retain roll characteristics. Airloads are shifted inboard on a swept wing to move the center of pressure forward, thereby reducing the tail load required to perform a positive gravity maneuver. In a negative gravity maneuver, speed brakes are retracted, thereby reducing the positive tail load and reducing the aft body design loads. High gain feedback commands are filtered from wing structural modes above one hertz by a set of linear and non-linear filters.

Abstract: An aircraft wing folding system folds an outboard wing section relative to an inboard wing section between a deployed position and a stored position in two discrete motions where each motion has an independent load path separate of the loading of the wing experienced by in-flight aerodynamic forces. The wing-fold mechanism of the present invention includes a fold assembly comprising a twist component and a fold component operable to fold the outboard wing section from the deployed position to the stored position that remains substantially unloaded with respect to in-flight aerodynamic forces when the wing is in the deployed or flight configuration.

Abstract: An aircraft with wings that may be fixed for flight and which swing and fold for storage and for maneuvering and otherwise operating the aircraft while not in flight is disclosed. An embodiment includes wings which swing backwards and through the body of the aircraft and then fold by drooping elevons which span the trailing edges of the wings along the sides of the body. Another embodiment includes wings which swing forward and control surfaces which fold upwards at the sides of the aircraft. The invention provides for a narrow width for the aircraft when not in flight using a simple mechanism.

Abstract: A low-wing, low-span canard aircraft with a protected pusher-style propeller is designed to transition simply between use in the air and use on the ground, without any mechanical effort on the part of the pilot. The vehicle may include deformable aerodynamic bumpers, embedded road-safety vehicle lighting and license plates, a protected propeller, and an integrated RFID airport access system. The vehicle may be designed for potential certification by the Federal Aviation Administration as a Light Sport Aircraft.

Abstract: A roadable aircraft may be registered and driven as a motorcycle on the roadways, does not require that any parts be “left behind” at the airport when configuring to roadable use and does not require removing portions of the aircraft and towing them behind. A foldable and collapsible wing comprises a number of wing ribs, which are hinged to a main forward spar. To fold for road usage, the wing ribs fold about a hinge fitting to collapse against the wing spar. To maintain tension on the wing skin (to prevent flutter) tensioning bladder(s) may be used to keep the fabric taut. Once retracted and folded, the wings align with tail booms to form a compact and aerodynamic package. The ductless fan may be provided with a center-mounted extraction fan ducted to inlets along the fuselage to draw low energy air in toward the fuselage and thus prevent boundary layer separation.

Abstract: System and method for a flyable and roadable vehicle. According to an embodiment, the present invention provides a vehicle capable of air and road travel. The vehicle is adaptable to a flying configuration and a road configuration. The vehicle includes a fuselage having a front end, a rear end, a top side, a bottom side. The vehicle also includes a wing component having a plurality of planes. The plurality of planes includes a first plane and a second plane. The vehicle additionally includes a connecting component for coupling the planes of the wing and the fuselage. The connecting component is able to accommodate a substantial relative rotation between the first plane and the fuselage. The vehicle further includes a plurality of wheels coupled to the bottom side of the fuselage.

Abstract: An aircraft structure is provide, an aircraft structure for an aircraft. Including front wings And rear wings of the Swan-Wings, vertical winglets and the first level floor body. The Fuselage has a cross-section of substantially flat fuselage shape being is wide enough to Provide lifting force. The front wings of the Swan-Wings are disposed horizontally in Front portion of the fuselage. The rear wings of the Swan-Wings are disposed Horizontally in rear portion of the fuselage. The vertical winglets are disposed at the top of the rear fuselage. The first level disposed fuel tank storages, a plurality of landing gear bays, cockpits with Control panels, various avionics and cabin doors. The top of the rear fuselage disposed jet power plants, the fuselage provide lifting force And the wings provides steering force and lifting force the whole structure of an aircraft Comprises carbon fiber honey comb composite molded structure which lighter weight And shear strong structure. The cockpit and cabins disposed.

Abstract: An unmanned aerial vehicle mounts a payload section to an air delivery vehicle. The air delivery vehicle includes deployable wings and tail fins for gliding or powered flight. A set of propeller blades are provided for powered flight. The propeller blades are mounted for movement from a stowed position to deployed position extending radially from the fuselage for powered flight.

Abstract: Disclosed are a wing deployment apparatus and an apparatus for launching a flying object having the same, the wing deployment apparatus including wings configured to be in a folded state and a deployed state, a driving unit connected to the wings, and configured to drive the wings to be switched from the folded state to the deployed state or vice versa, and a damper cooperative with the operation of the driving unit, and configured to damp a driving force of the driving unit from the start of the wings being moved to the completion of the movement of the wings.

Abstract: A foldable deployable panel device (12) attached to a body (16) of an object is disclosed. The device includes a panel pivotally attached to the body by a first pivot element (40/42) at a first pivot position and a second pivot element (29) at a second pivot position. The first pivot element (40/42) is disengageable from the first pivot position, when the panel (12) is aligned in a predetermined orientation. The second pivot element (29) is fixed at the second pivot position, when the first pivot element (40/42) is engaged at the first pivot position. The panel (12) is urged by an energy storing element (28), when the first pivot element (40/42) is disengaged from the first pivot position, to move into a deployed position.

Abstract: Embodiments of the present invention relate a wing arrangement for an aerial vehicle configured to adjust the vehicles aspect ratio in response to flight mission parameters. The wing arrangement may include a pair of wing assemblies capable of deploying to a first winged position defining a first aspect ratio. Each wing assembly may have a forward inboard wing pivotally connected to the fuselage and an aft inboard wing pivotally connected to the carriage. The forward inboard wing and aft inboard wing of each assembly may be connected, forming a bi-plane configuration. Additionally, the each assembly may include a set of outboard wings configured to telescope from the inboard wings to an extended winged position defining a second aspect ratio greater than the first aspect ratio.

Abstract: Disclosed are a wing assembly including a wing movably accommodated in a launch tube, and a buffer unit detachably mounted to the wing to come in contact with the launch tube and configured to be separated from the wing after the wing comes out of an inner space of the launch tube, and an apparatus for launching a flying object having the same.

Abstract: Embodiments of the present invention relate a wing arrangement for an aerial vehicle configured to adjust the vehicles aspect ratio in response to flight mission parameters. The wing arrangement may include a pair of wing assemblies capable of deploying to a first winged position defining a first aspect ratio. Each wing assembly may have a forward inboard wing pivotally connected to the fuselage and an aft inboard wing pivotally connected to the carriage. The forward inboard wing and aft inboard wing of each assembly may be connected, forming a bi-plane configuration. Additionally, the each assembly may include a set of outboard wings configured to telescope from the inboard wings to an extended winged position defining a second aspect ratio greater than the first aspect ratio.

Abstract: An aerial surveillance device is provided, comprising an image capturing device capable of being supported by an airframe structure above the ground. The airframe structure includes a body portion defining a longitudinal axis and configured to support the image-capturing device. A tail portion having control surfaces is operably engaged with the body portion along the axis. Transversely-extending wing portions are directly engaged with the body portion. Each wing portion is defined by longitudinally-opposed spars extending from a spaced-apart disposition at the body portion to a common connection distally from the body portion. The spars have a fabric extending therebetween to provide a wing surface. A support member extends along an aerodynamic center, transversely to the body portion, of each wing portion, to tension and rigidify the wing portions so as to provide a positive camber for the wing portions and to form an airfoil.

Abstract: A wing pivot mechanism that is configured to pivot two wings about a single pivot axis of a vehicle, such as an aircraft. The wing pivot mechanism includes a hub, a set of gears positioned at least partially within an interior region of the hub, and two wings that are rotatably connected to the hub. Each wings includes a gear surface extending therefrom. Each gear of the hub assembly engages a gear of a respective wing such that rotation of the gears of the hub assembly causes rotation of the gears of the wings and pivoting of the wings about the single pivot axis in opposite rotational directions between a stowed position and a deployed position. A releasable locking mechanism is provided for locking the wings in a fixed rotational position in both the deployed position and the stowed position.

Abstract: A stowable wing structure incorporates a wing having a span equal to a fuselage length and movable from a stowed position longitudinally aligned with the fuselage to a deployed position perpendicular to the fuselage. A pivot offset laterally from a centerline of the fuselage and aft from a symmetry point on the centerline with a corresponding offset forward toward the leading edge from a chord centerpoint on the wing allows rotation of the wing from the stowed position to the deployed position with the rotation resulting in an aft position of the chord center point relative to the fuselage symmetry point.

Abstract: A low-wing, low-span canard aircraft with a protected pusher-style propeller is designed to transition simply between use in the air and use on the ground, without any mechanical effort on the part of the pilot. The vehicle may include deformable aerodynamic bumpers, embedded road-safety vehicle lighting and license plates, a protected propeller, and an integrated RFID airport access system. The vehicle may be designed for potential certification by the Federal Aviation Administration as a Light Sport Aircraft.

Abstract: A ducted fan air vehicle and method of operation is disclosed for obtaining aerodynamic lift and efficiency in forward flight operation without significantly impacting hover stability. One or more retractable wings are included on the ducted fan air vehicle and are deployed during forward flight to provide aerodynamic lift. The wing or wings are retracted when the vehicle hovers to reduce the impact the wings have on stability in a wind. Each wing may conform to the curvature or profile of the vehicle when retracted, and may be constructed in one or more wing sections. The wing or wings may be deployed and retracted automatically or at the command of an operator. Each wing and related components may be integrated into the vehicle or may be detachable.

Abstract: A surveillance vehicle (10) comprising a vessel (11) and a parasail (12). The vehicle (10) is loaded, in a pre-launch condition, into a mortar tube for projection therefrom towards an area of interest. In this pre-launch condition, the vessel (11) resembles a conventional mortar round and the parasail (12) is stowed within the vessel (11). Upon arrival at the area of interest, the parasail (12) is deployed from the vessel (11) and instrumentation collects survey data.

Abstract: Improved mechanisms for folding and locking an aircraft wing and controlling the wing's aileron through a wing fold have been motivated by development of a roadable aircraft. Applicable to a broader class of aircraft, these mechanisms allow for a safer, lighter-weight solution to the wing-folding challenge than currently available. The cable control system allows an outer wing section to be moved in concert with an actuated inner wing section. The locking mechanism allows for automated operation and visual inspection. The aileron control mechanism provides centering and locking in addition to flight control through the hinge axis.

Abstract: An unmanned air vehicle for military, land security and the like operations includes a fuselage provided with foldable wings having leading edge flaps and trailing edge ailerons which are operable during ascent from launch to control the flight pattern with the wings folded, the wings being deployed into an open unfolded position when appropriate. The vehicle is contained within a pod from which it is launched and a landing deck is provided to decelerate and arrest the vehicle upon its return to land.

Abstract: A structural mechanism for an aircraft includes a support, a hinged surface, and a hinge assembly joining the hinged surface to the support. An actuation system includes an actuator shaft engaged to the hinges and lying coincident with a hinged-surface hinge axis and extending through the aligned center passageways of the hinges of the hinge assembly. A lock is selectively operable to lock the hinged surface to the support when the actuator shaft engages the lock. An actuator structure is controllably operable to move the actuator shaft longitudinally along the hinge-surface hinge axis between a first shaft axial position wherein the actuator shaft engages the lock and the hinges, and a second shaft axial position wherein the actuator shaft does not engage the lock but does engage the hinges, and is controllably operable to rotate the actuator shaft about the hinged-surface hinge axis.

Abstract: A stowable wing structure incorporates a wing having a span equal to a fuselage length and movable from a stowed position longitudinally aligned with the fuselage to a deployed position perpendicular to the fuselage. A pivot offset laterally from a centerline of the fuselage and aft from a symmetry point on the centerline with a corresponding offset forward toward the leading edge from a chord centerpoint on the wing allows rotation of the wing from the stowed position to the deployed position with the rotation resulting in an aft position of the chord center point relative to the fuselage symmetry point.

Abstract: Improvements to the hinge of a folding aircraft wing including a load bearing hinge mechanism with multiple locking mechanisms. The mechanism includes rigid panels that cover the hinge area when the wing is deployed, and the wing itself covers the hinge area when the wing is retracted. A control lever is used to actuate the wing and incorporates safety features to prevent unwanted actuation.

Abstract: An unmanned aerial vehicle mounts a payload section to an air delivery vehicle. The air delivery vehicle includes deployable wings and tail fins for gliding or powered flight. A set of propeller blades are provided for powered flight. The propeller blades are mounted for movement from a stowed position to deployed position extending radially from the fuselage for powered flight.

Abstract: A system for deploying a deployable structure in an aircraft, comprising a drogue parachute, at least one deployable structure, a riser line attached to the drogue parachute and the at least one deployable structure, wherein when the drogue parachute is deployed, a tension is applied to the riser line, and a parachute deployment system, wherein the parachute deployment system is configured to utilize the applied tension to deploy the at least one deployable structure.

Abstract: An aircraft with wings that may be fixed for flight and which swing and fold for storage and for maneuvering and otherwise operating the aircraft while not in flight is disclosed. An embodiment includes wings which swing backwards and through the body of the aircraft and then fold by drooping elevons which span the trailing edges of the wings along the sides of the body. Another embodiment includes wings which swing forward and control surfaces which fold upwards at the sides of the aircraft. The invention provides for a narrow width for the aircraft when not in flight using a simple mechanism.

Abstract: A portable unmanned air vehicle and launcher system that includes a foldable unmanned air vehicle having a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.

Abstract: A foldable wing for use with a very high altitude aircraft capable of operating at an altitude at or above 85,000 feet is disclosed. The foldable wing may employ a spiral fold deployment, wherein a hinge between each segment of the foldable wing is slightly offset from the perpendicular. Successively positioned wing segments fold over one another. Alternatively, the hinges are substantially perpendicular so that each respective wing segment folds linearly against the next wing segment. An inflatable rib, with inflatable arms, can be inflated to provide a force against two adjacent arms, thereby deploying the wing segments through a full 180° of rotation.

Abstract: A flight machinery with high stability in the air having a pendulum structure and an active posture control principle which can be designed for universal purposes at a low cost is provided. The flight machinery includes a structure in which a main body and a lightweight wing having an unvalued weight compared with the main body are connected by use of a power joint on a line joining the center of a lift force and the center of gravity of the wing in the manner that the main body is positioned under the wing. Accordingly, it is possible to exhibit a function of the flight machinery by adjusting the power joint connecting the upper part and the lower part or the wing to the main body even if the wing and the main body have different characteristics. Additionally, it is possible to stabilize a posture by positioning the total center of gravity at the main body at the lower part. At the same time, it is possible to stabilize the posture just by controlling the position of the servomotor of the power joint.

Abstract: In a preferred embodiment, an apparatus, including: an aircraft having rotatable blades; and the rotatable blades are movable between horizontal and vertical positions.

Abstract: A structural mechanism for an aircraft includes a support, a hinged surface, and a hinge assembly joining the hinged surface to the support. An actuation system includes an actuator shaft engaged to the hinges and lying coincident with a hinged-surface hinge axis and extending through the aligned center passagways of the hinges of the hinge assembly. A lock is selectively operable to lock the hinged surface to the support when the actuator shaft engages the lock. An actuator structure is controllably operable to move the actuator shaft longitudinally along the hinge-surface hinge axis between a first shaft axial position wherein the actuator shaft engages the lock and the hinges, and a second shaft axial position wherein the actuator shaft does not engage the lock but does engage the hinges, and is controllably operable to rotate the actuator shaft about the hinged-surface hinge axis.

Abstract: An inflatable endurance unmanned vehicle includes an inflatable hull with at least one inflatable wing extending therefrom. The inflatable wing has at least one spar movable between an extended position and a retracted position. Photovoltaic arrays are used to power the vehicle during daytime operation and power an electrolyzer. A fuel cell powers the vehicle during nighttime operation.

Abstract: A vehicle adapted for airborne flight and waterborne sailing has a fuselage (20) with left and right wings (52, 54) that pivot independently about a respective longitudinal axis from a generally horizontal orientation for flight to a generally vertical orientation to provide wind-driven propulsion for sailing. Further, the wings (52, 54) pivot about a respective second axis (66) that is generally perpendicular to the longitudinal axis to trim the wings (52, 54) for sailing with a given relative wind direction. The wings (52, 54) are mounted by a respective first pivotal joint (56, 58) to the distal ends of respective stub wing/decks (48, 50). The stub wing/decks form a fixed central wing section (46). Water hulls (28) are mounted below the distal ends of the stub wing/decks (48, 50) on vertical pylons (30) to provide stable flotation. Vertical and horizontal stabilizers (40, 60) are mounted on the back ends of the water hulls (28).

Abstract: An aerodynamic vehicle is comprised of a pair of forward wing sections and a pair of rearward wing sections that are connected together by four pivot assemblies as a four-bar linkage. The four-bar linkage surrounds an opening provided between the forward wing sections and rearward wing sections. Movement of the wing sections varies the cumulative area of the wing sections, and adjusts the shape of the opening between the forward wing sections and rearward wing sections. Movement of the wing sections improves the aerodynamic performance of the vehicle and allows the wing sections to assume optimum configurations for operation of the vehicle at high speed and low speed.

Abstract: A hypersonic vehicle having in one or more embodiments a control surface that is movable to a deployed position. The control surface is movable in a pivotal manner that establishes a gap between the leading edge of the control surface and the outer surface of the vehicle to provide a flow path. The gap allows a boundary layer along the outer surface of the vehicle to pass through the flow path with out separation from the outer surface, to further improve the effectiveness of the control surface.

Abstract: Methods and apparatuses for launching, capturing, and storing unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be assembled from a container with little or no manual engagement by an operator. The container can include a guide structure to control motion of the aircraft components. The aircraft can be launched from an apparatus that includes an extendable boom. The boom can be extended to deploy a recovery line to capture the aircraft in flight. The aircraft can then be returned to its launch platform, disassembled, and stored in the container, again with little or no direct manual contact between the operator and the aircraft.

Abstract: The invention is a helicopter that includes a fuselage with a longitudinal axis, a main rotor and tail rotor; and right and left wings mounted to said fuselage. The right and left wings having at least a portion of which are rotatable from a horizontal position wherein they produce lift in forward flight, to an at least partially downward position wherein they act as landing struts.

Abstract: Methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be launched from an apparatus that operates with a wedge action. A launch carriage carrying an unmanned aircraft is positioned on first and second launch members. At least one of the launch members moves relative to the other from a first position to a second position, causing the launch carriage to move from a first launch carriage position to a second launch carriage position. As the launch carriage moves, it accelerates the aircraft and releases the aircraft for takeoff.

Abstract: Apparatus for stowing and deploying a plurality of control surfaces of a guided air vehicle comprises: a housing including: a plurality of slotted openings along an outside surface thereof; and a corresponding plurality of cavities within the housing, each cavity extending to the outside surface of the housing through the slotted opening corresponding thereto and configured to accommodate span wise stowage of a corresponding control surface of the plurality, and each cavity having a section including an angled ledge and side wall support surface to accommodate stowage of the corresponding control surface in a span wise canted position with respect to the corresponding slotted opening.

Abstract: An articulated wing (20) is readily deployable from a stowed configuration that occupies minimal volume to an extended configuration for flight. The wing (20) includes a frame (24) having a pair of beams (30) spaced by one or more ribs (36), and a flexible covering material (26) over the frame (24) that defines the surface of the wing (20). Each beam (30) typically has multiple segments (40), and each segment (40) is pivotally connected to an adjacent segment (40) at a joint (42). A flexible actuation line (52) extends past each joint (42) and is attached to a portion of the beam beyond the joint. The beam (30) also includes portions that act as stops (46). The stops (46) limit the range of angular motion through which the respective segments (40) can rotate relative to one another. Consequently, when tension is applied to the line (52), the segments (40) rotate until respective stops (46) prevent further rotation. Tension in each line (52) keeps the wing (20) in its extended configuration.

Abstract: A method and structure for a full-bore artillery projectile fin deployment device comprising a projectile stabilization fin comprising an aperture and a movable pawl; a rod comprising a head portion and a shaft portion terminating with a beveled tip configured for engaging the pawl; a tailboom configured for housing the fin, wherein the tailboom comprises a hollow bore configured for receiving the rod; a pin slotted through the aperture and attached to the tailboom; and a bias member adjacent to the head portion of the rod. The rod is slotted to simultaneously engage a plurality of fins. The tailboom comprises a forward end and a rearward end and a slot configured for permitting the fin to articulate out of the tailboom, and wherein the tailboom connects to a projectile. Additionally, the power source for the device is the naturally occurring launch accelerations.

Abstract: A wing is presented that unfolds in a chordwise direction upon the launch of its aircraft at some velocity as it is projected into the air or launched from a moving craft at altitude. The wing is made up of two or more stiff, upper segments including the leading edge with foam used to complete the underneath wing shape. The foam is covered with a film of plastic or composite material to makeup the underneath shape of the wing as supported by the foam. The foam can be pressurized to enhance its final shape in support of the underneath film. The upper segments are joined by hinges using twisted, staked pins to provide force for the desired wing unfolding. Aerodynamic forces also enhance the unfolding motion. The wing can be used on a craft to be deployed at higher air speeds than any other type of folding wing of comparable stowing efficiency.

Abstract: An amphibian delta wing jet aircraft, which has a plurality of triangular folding wing panels, two of which are hingedly attached to a lifting shape body, which incorporates a W-shaped hull in it's cross section of a fuselage so that the craft operates efficiently as an aircraft when flying through the air with the wings in a fully unfolded extended position. The craft also performs well as a watercraft capable of relatively high speeds on the water surface when the wing are folded-up in a non extended position. The W-shape hull transverse cross section also provides excellent characteristics so that the craft can hydroplane over marshlands or waterlogged soil which may be covered with emersed rushes, or snow, cattails and other tall grasses. The craft is also provided with four retractably mounted mechanically extendable wheels, to be utilized when configured as a land vehicle.

Abstract: A deployment device for a fin of a projectile incorporating a hinge fixed to the projectile body which allows said fin to make a pivoting movement along at least one axis, wherein said hinge comprises a support for said fin mounted able to tilt over with respect to an axis substantially perpendicular to the projectile axis, said fin being linked to said support by a rod whose axis is substantially parallel to said projectile axis when said fin is in the folded position and substantially perpendicular to said projectile axis when said fin is in the deployed position, said rod itself being able to pivot with respect to said fin support when such said support tilts over, this pivoting of said rod being controlled by driving means.

Abstract: A missile to be fired from a barrel contains a tail, a tail sleeve attached to the tail, a stop element fixed to the tail sleeve, and a movable structural part disposed at the tail. Fin assembly wings are provided and are to be released from a subcaliber launch position to an overcaliber functional position by the movable structural part moving toward the stop element through a given distance. A pressure area is disposed between the tail end surface and the movable structural part. A propellant gas enters the pressure area during the firing of the missile, for moving the movable structural part away from the tail end surface against the stop element after firing. Bearing shafts are supported by the tail sleeve, the fin assembly wings are configured as a wrap around tail fin assembly held about the bearing shafts.

Abstract: A foldable tail assembly for an aircraft includes a stabilizer and a pair of right and left fins mounted with respect to the stabilizer so that the fins may lay flat over the stabilizer during periods when the aircraft is not flight-ready, and so that the fins may be erected above the stabilizer to form a triangular configuration when the aircraft is ready to fly.

Abstract: The present invention concerns a method for designing a deployment mechanism for a flight surface on an airborne body, including the steps of determining a stowed position of the flight surface, determining a deployed position of the flight surface, identifying a first rotation axis and respective rotation angle and a second rotation axis and respective rotation angle about and through which the flight surface is rotatable in sequence to move the flight surface from the stowed position to the deployed position, or vice versa, and using the identified first and second rotation axes and rotation angles to determine a single equivalent rotation axis and angle, about and through which the flight surface can be rotated from the stowed position to the deployed position, or vice versa.

Abstract: An STOL aircraft structure has a variable-attitude, variable-area wing in addition to a traditional airfoil. The variable wing has an angle of attack that varies from 0° to a predetermined angle far in excess of the stall angle. The variable wing area can be adjusted from 0% to 100% by a roller furling arrangement. The aircraft structure operates during takeoff by deploying the variable wing with an attitude exceeding the stall angle, applying thrust to the aircraft so that the variable wing generates reaction lift and the aircraft attains a predetermined altitude, and stowing the variable wing so that the traditional airfoil is the primary lifting surface. Those steps are reversed for landing.