Abstract: An air vehicle wing includes foldable ribs coupled to a leading-edge spar. The ribs each have multiple rib segments which are foldable (hinged) relative to each other. Extension linkages, each with multiple extension linkage segments, pass through openings in the rib segments, and may be coupled to the rib segments with pin couplings, able to change relative angle between the individual rib segments and the extension linkage segments to which they are coupled. A skin may cover the ribs, to provide an outer surface of the wing that may be unfolded as the wing is expanded from a stowed, small-chord condition, to a deployed, large-chord condition.

Abstract: A system and method to control flight of an aircraft. The aircraft having an engine with a rotatably nozzle assembly configured to create forward propulsion and yaw control of the aircraft. The engine exhaust passing through the nozzle is redirected with a valve disposed within the nozzle. Lift is created with a lift system carried by the wing of the aircraft. Additional lift is created during flight with a retractable wing extension disposed within the wing of the aircraft.

Abstract: The invention relates to a method for managing the flight of an aircraft flying along a trajectory and being subject to an absolute time constraint (on a downstream point) or relative time constraint (spacing with respect to a downstream aircraft), the said aircraft comprising a flight management system calculating a temporal discrepancy to the said time constraint, wherein the said method includes the following steps: the calculation of a distance on the basis of the temporal discrepancy, the modification of the trajectory: if the temporal discrepancy to the time constraint corresponds to an advance, the lengthening of the trajectory by the distance; if the temporal discrepancy to the time constraint corresponds to a delay, the shortening of the trajectory by the distance.

Abstract: An aircraft includes a fuselage, a first wing, and a second wing. The first wing and the second wing each have at least two wing panels, where the at least two wing panels of each wing are telescopically related to one another for movement between an extended position and a retracted position. The first wing and the second wing are both connected to the fuselage and are positioned with respect to the fuselage such that the first wing is offset with respect to the second wing.

Abstract: An aircraft hull attachment device may be configured for attachment to a fuselage of an aircraft. The aircraft hull attachment device can include one or more floats to enable the aircraft to operate on water. The aircraft hull attachment device can also include a structure such as, for example, a saddle-shaped structure, for mounting the device against a bottom region of a fuselage of the aircraft. Upon being operatively coupled to the aircraft, the aircraft hull attachment device can convert an aircraft previously configured to operate only on ground landing strips into an aircraft configured to operate on water landing strips. Additionally or alternatively, the device can include a water tank and a water-tank door to enable the aircraft to which the device is mounted to perform in-flight water drops (e.g., during fire fighting aerial operations).

Abstract: A method and apparatus for controlling the shape of a control surface. A structure is rotated about an axis. The structure is located between a flexible skin and a skin located substantially opposite of the flexible skin. An assembly is moved to change the shape of the control surface in response to a rotation of the structure. The assembly is movably connected to the structure and is configured to move such that the flexible skin forms a plurality of curvatures.

Abstract: A shape-changing structural member has a shape-changing material, such as a suitable foam material, for example a polymer foam capable of withstanding at least 300% strain or a metal alloy foam capable of withstanding at least 5% strain. Springs, such as one or more coil springs, provide structural support for the shape-changing material. The springs may also be used to provide forces to expand and contract the shape change material. The springs may include pairs of concentric springs, one inside of another. The concentric springs may surround an underlying skeleton structure that supports the shape-changing material and/or aids in changing the shape of the material. The concentric springs may or may not be wrapped around the underlying skeleton structure. Multiple springs or pairs of springs may be coupled together using a sheet metal connector.

Abstract: Apparatus and methods provide for the use of retractable aircraft wing tips to increase the wingspan of an aircraft to decrease drag and increase fuel efficiency. According to various embodiments, a flexible lifting envelope is attached to an outboard end of an aircraft wing. Upon receiving pressurized air, the flexible lifting envelope extends outward to a lift-producing configuration that extends the span of the aircraft wing to which it is attached. When deflated, the flexible lifting envelope retracts into a stowed configuration to decrease the wingspan of the aircraft to allow for parking at airport gates or to alleviate flight loads. Various implementations provide for a telescoping wing tip and for a rolled wing tip.

Abstract: A composite flexible and aerodynamic load bearing wing structure suitable for compact unmanned vehicles, is described. Flexible printed circuitry and micro fuel cells can be incorporated as, or part of, the flexible aerodynamic structure. Accordingly, the overall system configuration can be optimized with respect to weight, space and size requirements. The flexible aerodynamic structure for the unmanned vehicle may be configured with a flexible dielectric substrate having an electrical contact on at least one surface of the substrate, and a flexible printed circuit disposed upon the substrate. The printed circuit can flex with the substrate and the substrate, with the printed circuit, to form a load lifting aerodynamic wing configuration when unfolded from a folded position.

Abstract: One embodiment is directed to a method for testing an aircraft prior to flight. The method includes receiving a user signal from a pre-flight test input source, the user signal indicating that a pilot of the aircraft has directed engine control circuitry, which is arranged to electronically control operation of a set of piston engines of the aircraft during flight, to begin testing the aircraft in an automated manner. The method includes, in response to the user signal, conducting a pre-flight test of the aircraft from the engine control circuitry. The method includes, upon completion of the pre-flight test, outputting a result of the pre-flight test from the engine control circuitry.

Abstract: A reinforced inflatable wing improves the tolerance of the OML and reinforces the wing in at least the high load areas. This approach provides fitment constrained air vehicles with wings having increased surface area to improve flight endurance or aerodynamic control. A wing box forms a first portion of the wing. A skin having a plurality of rigid plates affixed thereto is inflated to form a second portion of the wing to either increase the chord length or lengthen the wing span. The skin is suitably inflated with foam to form a solid wing.

Abstract: A system includes a fabric wing, such as a Rogallo wing or parafoil, a roller connected to the fabric wing, cables connected to the fabric wing, a motor connected to the roller. Upon activation, the motor causes the roller to roll-up or unroll at least a portion of the fabric wing. The system may include a rigid or collapsible roller support structure connected to the roller. The roller may be located along a central axis of the fabric wing. A control unit may be connected to the cables, the control unit including a logic controller, power source, communications system, GPS and inertial navigation sensor system, motor controller, and one or more sensors including an air speed sensor, altitude sensor, obstacle detection sensor, and/or a ground proximity sensor. The system may include a second roller with an attached motor, with each roller located at an end of the fabric wing.

Abstract: The invention relates to an improved ram air inflating lifting body (1) such as a para-foil. The lifting body (1) being configured so as to be controllable by changing the effective chord length (5) of at least one of the surfaces (2, 3) of the lifting body and thus the aerodynamic properties of the lifting body (1).

Abstract: A shape-changing structural member has a shape-changing material, such as a suitable foam material, for example a polymer foam capable of withstanding at least 300% strain or a metal alloy foam capable of withstanding at least 5% strain. Springs, such as one or more coil springs, provide structural support for the shape-changing material. The springs may also be used to provide forces to expand and contract the shape change material. The springs may include pairs of concentric springs, one inside of another. The concentric springs may surround an underlying skeleton structure that supports the shape-changing material and/or aids in changing the shape of the material. The concentric springs may or may not be wrapped around the underlying skeleton structure. Multiple springs or pairs of springs may be coupled together using a sheet metal connector.

Abstract: A trimmable horizontal stabilizer is provided adjacent to the fuselage of an aircraft and has a predetermined aerodynamic profile. A movable elevator is arranged adjacent to the horizontal stabilizer. The horizontal stabilizer has a load-bearing structure which extends in the span direction and is firmly connected to the fuselage of the aircraft, and movable areas which are connected to the load-bearing structure such that they can move and can be moved independently of the elevator in order to trim the horizontal stabilizer by varying the aerodynamic profile.

Abstract: An aircraft includes a fuselage and takeoff and landing wings that are extended at takeoff and landing and serve as the main aerodynamic elements producing the lift. The takeoff and landing wings are in a retracted position in cruising flight to attain a minimum possible drag coefficient of the aircraft and, as a result, reduce fuel requirements in the cruising configuration significantly. When retracted, the takeoff and landing wings are integrated compactly into the fuselage surface. The retracted takeoff and landing wings are fixed in position by retracted position locks of the fuselage. A takeoff and landing wing has a turbine blade profile in cross-section. A takeoff and landing wing has longitudinal rows of slots simulating the operation of a slat and a two-slot flap. The slots are closed with shutters on the outer side of the wing.

Abstract: An assembly for controlling a vehicle, including a fluid contact surface constructed and arranged to act against a fluid passing over the fluid contact surface; and a support structure coupled to the fluid contact surface. The support structure is constructed and arranged to expand or contract between a first position and a second position, such that a first dimension of the support structure changes during movement of the support structure between the first position and the second position, while a second dimension of the support structure remains substantially constant during the movement of the support structure between the first position and the second position.

Abstract: This invention relates generally to a collapsible, nesting wing structure with or without wing warp flight control. The invention also incorporates means to maintain wing extension during flight, methods of wing construction for nesting collapsible wings, and control surfaces for collapsible wings.

Abstract: An aircraft wing includes a stationary root section and a telescoping end section slideable in the span wise direction, where the loads for the root and extendable end sections are carried predominately by the airfoil composite skins, rather than a framework of spars and ribs as in conventional aircraft wings. In a single-telescoping configuration the telescoping end section slides within the root section as it extends and retracts during flight, and in another, the telescoping end section slides over the root section as it extends and retracts during flight. The aircraft wing can also include a second telescoping distal end section, and can sweep back during flight, while the end sections or distal end sections are extended or retracted.

Abstract: Disclosed is a telescoping wing locking system for use in aircraft having wings that collapse and expand in a telescoping fashion, such as aircraft designed for use on roadways. Companion wing segments are locked in place when gas is supplied to inflate a bladder located between overlapping sections of the wing segments. Wing segments are unlocked when gas is removed from the bladder so that it deflates and allows the wing segments to be moved relative to each other. The wing segments may be locked in any position relative to each other in which a section of one segment overlaps a section of the neighboring segment with the bladder between.

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: A method of controlling an aircraft in a turn without the use of a rudder by producing induced yaw. Induced yaw being produced by creating a net induced drag differential between an inboard wing to the turn and an outboard wing to the turn, whereby the net induced drag differential overcomes adverse yaw produced by the outboard wing.

Abstract: A telescopic aircraft wing having an articulated structural spar. The telescopic wing includes a root portion and a tip portion that is telescopically related to the root portion. A spar assembly connects the root portion to the tip portion for providing structural support to the tip portion, and the spar assembly has a plurality of links that are pivotally connected to one another. The spar assembly moves the tip portion with respect to the root portion between an extended position and a retracted position.

Abstract: In a blade vortex interaction (BVI) noise reduction system for a helicopter a rotor blade, a tab is movable via an actuator from a first position, wherein the tab is within the blade, to a second position, wherein the tab extends outwardly from a trailing edge of the rotor blade. The actuator is operated so that the tab advances and retreats in response to rotating timing of the rotor blade, to reduce the BVI noise of the rotor blade.

Abstract: A telescoping structure includes an alignment mechanism to keep aligned an inner structure member and outer structure member, as the members translate relative to one another to extend or retract the telescoping structure. The alignment mechanism includes multiple parts that are mechanically coupled to respective of the structure members. For example, the alignment mechanism may include sprockets or pinions (rotating, toothed elements) on one of the structure members that engage racks or chains (linear, tooth-receiving elements having recesses therein) on the other of the structure members. By keeping the telescoping structure members in alignment with other during telescoping translation, jamming is prevented or at least made less likely. The parts of the alignment mechanism may also be used to provide force for extending or retracting the telescoping structure, for example using a motor move the tooth elements and/or the tooth-receiving elements to cause relative translation of the structure members.

Abstract: Systems and methods for providing differential motion to wing high lift devices are disclosed. A system in accordance with one embodiment of the invention includes a wing having a leading edge, a trailing edge, a first deployable lift device with a first spanwise location, and a second deployable lift device with a second spanwise location different than the first. The wing system can further include a drive system having a drive link operatively coupleable to both the first and second deployable lift devices, and a control system operatively coupled to the drive system. The control system can have a first configuration for which the drive link is operatively coupled to the first and second deployable lift devices, and activation of at least a portion of the drive link moves the first and second deployable lift devices together.

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 deformable aerodynamic profiled member has a front profile area and a rear profile area in the outflow area. It is bounded by shells on the pressure side and/or on the suction side, converging in a rear profile edge (6). D33 piezo actuators are provided in at least some locations for deformation of the profiled member. The piezo actuators are aligned such that their length changes essentially in the direction of the planes of the shells when acted upon by electricity.

Abstract: Apparatus and methods provide for the use of retractable aircraft wing tips to increase the wingspan of an aircraft to decrease drag and increase fuel efficiency. According to various embodiments, a flexible lifting envelope is attached to an outboard end of an aircraft wing. Upon receiving pressurized air, the flexible lifting envelope extends outward to a lift-producing configuration that extends the span of the aircraft wing to which it is attached. When deflated, the flexible lifting envelope retracts into a stowed configuration to decrease the wingspan of the aircraft to allow for parking at airport gates or to alleviate flight loads. Various implementations provide for a telescoping wing tip and for a rolled wing tip.

Abstract: A shape-changing structural member has a shape-changing material, such as a suitable foam material, for example a polymer foam capable of withstanding at least 300% strain or a metal alloy foam capable of withstanding at least 5% strain. Springs, such as one or more coil springs, provide structural support for the shape-changing material. The springs may also be used to provide forces to expand and contract the shape change material. The springs may include pairs of concentric springs, one inside of another. The concentric springs may surround an underlying skeleton structure that supports the shape-changing material and/or aids in changing the shape of the material. The concentric springs may or may not be wrapped around the underlying skeleton structure. Multiple springs or pairs of springs may be coupled together using a sheet metal connector.

Abstract: An apparatus for increasing an aerodynamic surface area of an aircraft, e.g., a wing thereof, includes coaxially disposed first and second elongated airfoils and an inflatable device arranged to move the first airfoil coaxially relative to the second airfoil. The second airfoil has a root end fixed to the vehicle and an opposite outboard end, and the first airfoil is arranged to move axially between a retracted position generally inboard of the outboard end of the second airfoil and a deployed position generally outboard thereof. When the movable airfoil is deployed, a latching mechanism locks it in position. The inflatable device can include a collapsible duct that is sealed at one end and coupled at a second end to an inflating source, such as a reservoir of a compressed gas or a pyrotechnic gas generator.

Abstract: This invention relates generally to a collapsible, nesting wing structure with or without wing warp flight control. The invention also incorporates means to maintain wing extension during flight, methods of wing construction for nesting collapsible wings, and control surfaces for collapsible wings.

Abstract: Methods and apparatus for systems having deployable elements according to various aspects of the present invention comprise a system including a deployable surface and an adaptive actuator including a polymer foam. In one embodiment, the system comprises a vehicle including a deployable wing comprising an exterior surface. The exterior surface may be adjusted by adjusting the shape, size, position, and/or orientation of the adaptive actuator.

Abstract: A method of controlling an aircraft in a turn without the use of a rudder by producing induced yaw. Induced yaw being produced by creating a net induced drag differential between an inboard wing to the turn and an outboard wing to the turn, whereby the net induced drag differential overcomes adverse yaw produced by the outboard wing.

Abstract: A morphing aircraft includes a lifting body and a telescopic lifting or control surface, such as a wing, coupled to the lifting body. The lifting surface is deployable between extended and retracted positions relative to the lifting body and configured such that, when disposed in the extended position, the flight characteristics of the aircraft correspond to those of a low-speed, high-lift aircraft, and when disposed in the retracted position, the flight characteristics of the air-craft correspond to those of a high-speed, low-lift aircraft, the lifting surface is disposed entirely within the lifting body, and an outboard end surface of the lifting surface blends continuously into an outer mold line surface of the lifting body.

Abstract: A wireless-controlled airplane includes a flying unit and an on-ground controller which is connected to the flying unit through a communication section and flies the flying unit. The flying unit includes a body, a drive section installed on the body, a propulsion apparatus which generates a propulsive force when driven by the drive section, a main wing including a plurality of wing elements which are installed so as to be able to move with respect to each other, an opening and closing mechanism which changes the relative positions of the wing elements to change the effective area of the main wing, and a dropping apparatus which selectively holds and drops a load. By changing the effective area of the main wing, the flight speed can be changed, so the capacity and size of the drive section for rotating the propulsion apparatus can be decreased.

Abstract: The invention provides a wing structure for an aircraft, including a top skin and a bottom skin defining a primary wing surface, the surface having a width, a length, a leading edge and a trailing edge; a flap having a width smaller than the width of the wing surface and a length extending over a major portion of the wing length, the flap being hingedly joined adjacent to the trailing edge of the wing, wherein the flap is capable of assuming two limit dispositions, a first disposition in which the flap extends substantially parallel to the bottom skin, and a second disposition extending towards the trailing edge of the wing, at an obtuse angle. A method for slowing down the speed of flight of an aircraft is also provided.

Abstract: A Fluidynamic Lift Combined Array, Technology for flying, and/or land, and/or other motor vehicles comprises: a. an aerodynamic structure of chord-telescopic smooth-united multisegment lifting wings; and/or b. a set of hydrodynamic circuits including closed loop waved tunnels each with placed inside pump impelling operative liquid and having curved elbows with lifting winglets; and c. a method of generating high lift forces in combined fluidynamic, self-boosting, accumulative, and energy integrating and conservative technology. This proposal can provide: Short, safe, convenient for people, and appropriate for planes takeoffs and landings at speeds about 20 miles per hour. Sure overcoming any difficulties connected with heavy load for land and other vehicles. High general efficiency and profound reliability in upkeeping and thrifty technology with substantial energy conservation by additional lift generated in any tense situations.

Abstract: Method and spoiler system for ensuring the aerodynamic continuity of the upper surface of an aircraft wing. According to the invention, the spoiler 7 has a chord (C) of adjustable length and means (16, 19, 20) are provided for acting on the length of said chord when said spoiler (7) is in the retracted position.

Abstract: A deployment system for deploying a moveable wing surface (22) from a main wing section (8). The deployment system includes a plurality of swing arm assemblies (24,26) connecting the moveable wing surface (22) to the main wing section (8) and a drive means for deploying and retracting the moveable wing surface (22), wherein at least one of the swing arm assemblies (24,26) includes a swing arm (28) pivotably connected to the main wing (8) and a connector mechanism (34) for connecting the movable wing surface (22) to the swing arm (28).

Abstract: Wing parts (20, 21) which influence the lift of aircraft wings (1), especially wings (1) with a cross section and an angle of attack which is suitable for high-speed flight, which parts can be moved out of an aerodynamically inactive servicing position within the aircraft fuselage (30) or out of chambers (40) mounted on the wings (1) into an aerodynamically efficient active position and from the active position back into the servicing position, are assigned to the wings (1). These wing parts (20, 21) in their active position are located on the top (3) and optionally also on the bottom (4) of the wings (1) and are shaped for example such that the wing parts (21) located in their active position on the bottom (4) of the wings (1) jointly with the wing parts (20) located in their active position on the top (3) of the wings (1) increase the lift and optionally at the same time change the angle of attack of the wing.

Abstract: An airfoil member (14) is provided including a geometric morphing device (18). The geometric morphing device (18) has an inflatable member (30). The inflatable member (30) has an exterior wall (32) and multiple inflated states. A fiber mesh (34) is coupled to at least a portion of the exterior wall (32) and changes in shape according to fiber angle. Shape and size of the geometric morphing device (18) are adjustable by changing inflated state of the inflatable member (30). An airfoil member altering system (12) and a method of performing the same are also provided as well as a method of forming the geometric morphing device (18).

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.

Abstract: The present invention is a wing having telescoping segments deployed via an actuator composed of a heat activated material. The actuator is a coiled tube of shape memory alloy (SMA) with large force-displacement characteristics activated thermally by either a fluid or an electrical charge. Actuator motion extends an inner wing segment from an outer wing segment when the coiled tube is compressed. Compression is achieved by heating the coiled tube so as to cause a phase transformation from Martensite to Austenite. The inner wing segment may be retracted by a mechanical device or second SMA coil when the coiled tube is cooled and returned to its Martensite phase.

Abstract: An airfoil member (14) is provided including a geometric morphing device (18). The geometric morphing device (18) has an inflatable member (30). The inflatable member (30) has an exterior wall (32) and multiple inflated states. Multiple layers are coupled to at least a portion of the exterior wall (32) and control size, shape, and expansion ability of the geometric morphing device (18). The geometric morphing device (18) is adjustable in size and shape by changing inflated state of the inflatable member (30). An airfoil member altering system (12) and a method of performing the same are also provided as well as a method of forming the geometric morphing device (18).

Abstract: An airfoil member (14) is provided including a geometric morphing device (18). The geometric morphing device (18) has an inflatable member (30). The inflatable member (30) has an exterior wall (32) and multiple inflated states. A fiber mesh (34) is coupled to at least a portion of the exterior wall (32) and changes in shape according to fiber angle. Shape and size of the geometric morphing device (18) are adjustable by changing inflated state oft he inflatable member (30). An airfoil member altering system (12) and a method of performing the same are also provided as well as a method of forming the geometric morphing device (18).

Abstract: Personal Aircraft capable of vertical take-off and landing (“VTOL”) which comprises:

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.

Abstract: A geometric morphing wing 12 is provided, including a rigid internal core 20 surrounded by an expandable spar 22 and covered by a wing surface overlay 24. The expandable spar 22 includes an elastomeric bladder 30 movable between a non-inflated state 26 and an inflated state 28 such that the airfoil shape 29 of the geometric morphing wing 12 is adjusted.

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.