Abstract: An improved drone with 4 flat wings reciprocating up and down, complete with motor and electronics. Appendages on each wing's surface allow air to pass across it during the up-motion, and block it in the down-motion; this creates lift and permits flight and manoeuvres. The drone resembles either a flying bird or an insect, depending on wing motion and on passive attachments appropriate for the respective resemblance, making for inconspicuousness. The drone can execute complex work, either as solitary or in a team, either in flight or at rest in various places, after approaching and adhering expertly.

Abstract: A flapping wing driving apparatus includes at least one crank gear capstan rotatably coupled to a crank gear, the at least one crank gear capstan disposed radially offset from a center of rotation of the crank gear; a first wing capstan coupled to a first wing, the first wing capstan having a first variable-radius drive pulley portion; and a first drive linking member configured to drive the first wing capstan, the first drive linking member windably coupled between the first variable-radius drive pulley portion and one of the at least one crank gear capstan; wherein the first wing capstan is configured to non-constantly, angularly rotate responsive to a constant angular rotation of the crank gear.

Abstract: Aircraft with an emission-free drive and method for emission-free driving of an aircraft. The aircraft includes a drive device, having a flapping wing device, structured and arranged to generate thrust, a lift device structured and arranged to generate lift, and a heat engine, having at least one flat-plate Stirling engine drivable by solar thermal radiation, structured and arranged to convert thermal energy into kinetic energy to drive the drive device. The flapping wing device includes at least one flapping wing, which is pivotable transverse to a flight direction.

Abstract: A flapping flying robot including a body with a longitudinal side extending in a front to back direction, a left wing and a right wing respectively including a left front frame and a right front frame, base ends of the left and right front frames rotatably attached to a front side of the body, and a flapping structure mounted on an upper side of the body, the flapping structure powered by a rotary drive source, the flapping structure rotating the left and right front frames and thereby flapping the left and right wings and a duration of an upstroke of the left and right wings flapped by the flapping structure is shorter than a duration of a downstroke of the left and right wings to generate a lift force.

Abstract: A method of controlling wing position and velocity for a flapping wing air vehicle provides six-degrees-of-freedom movement for the aircraft through a split-cycle constant-period frequency modulation with wing bias method that generates time-varying upstroke and downstroke wing position commands for wing planforms to produce nonharmonic wing flapping trajectories that generate non-zero, cycle averaged wing drag and alter the location of the cycle-averaged center of pressure of the wings relative to the center of gravity of the aircraft to cause horizontal translation forces, rolling moments and pitching moments of the aircraft.

Abstract: Disclosed is a flying toy capable of moving by flapping of wings. The flying toy comprises a support structure; an actuation mechanism, for the wings, arranged on the support structure and comprising a crank drive rotated by a means providing the driving force; and two flexible wings arranged symmetrically with respect to the vertical plane of symmetry of the toy and connected, at the wing bases, to the actuation mechanism, the aforementioned wing bases being mounted oscillating about axes arranged on both sides of the vertical plane of symmetry of the toy. A controller receives a control signal indicating a left turn, increases the tension on the right wing and reduces it on the left wing and, for a right turn, the opposite action is performed.

Abstract: The present invention provides a remote-controlled ornithopter capable of flying forward in the upright position, which includes X-shaped main wings? having opposite phases to offset moments applied to a fuselage of the ornithopter. The ornithopter includes the fuselage (100), the X-shaped main wings (200), which are provided on the front end of the fuselage, tail wings (300), which are provided on the medial portion or the rear end of the fuselage, and a tail rotor (400), which controls a direction in which the fuselage flies. The ornithopter further includes a drive unit (500), which operates the main wings, and a flight control unit (600), which has a receiver to receive a signal for controlling the drive unit and the tail rotor. The ornithopter further includes a remote controller (700), which transmits the signal for controlling the drive unit and the tail rotor to the receiver.

Abstract: The invention relates to a flapping-wing flying vehicle, the vehicle including a frame having two pivots mounted thereon to pivot about two parallel hinge axes (X), each pivot carrying a respective wing, the vehicle including a first oscillation generator for causing the pivots to oscillate in order to cause the wings to flap, said first oscillation generator comprising: two arms (6), each secured to a respective pivot (2); two cranks (9), each hinged to the end of a respective one of the arms about respective axes (X1) parallel to the hinge axes (X) of the pivots; a connecting rod (10) hinged to the ends of the two cranks about axes (X2) parallel to the hinge axes (X) of the pivots; synchronization means (4) for synchronizing the rotation of the two pivots such that the rotations of the pivots are equal and opposite; two electric motors (7), each placed to cause one of the cranks to rotate relative to the associated arm; and control means (50) for controlling and synchronizing the speeds of rotation of the m

Abstract: Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension.

Abstract: Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension.

Abstract: A wing-drive mechanism is described that permits, with proper control, movement of a wing about multiple wing trajectories. The wing-drive is capable of independent movement about three rotational degrees of movement; movement about a flap axis is independent of movement about a yaw axis, and both are independent of changes in the pitch of the wing. Methods of controlling the wing-drive mechanism to affect a desired wing trajectory include the use of a non-linear automated controller that generates input signals to the wing-drive mechanism by comparing actual and desired wing trajectories in real time. Specification of wing trajectories is preferably also accomplished in real time using an automated trajectory specification system, which can include a fuzzy logic processor or a neural network.

Abstract: The present invention provides a wing-flapping flying apparatus, which can fly by moving its wings similar to a bird hovering or flying in the air by flapping its wings. The wing-flapping flying apparatus comprises: a body; a rotating shaft rotatably joined to the body; driving means for rotating the rotating shaft; and wings reciprocated between two points and connected to the rotating shaft so as to be rotated together with the rotating shaft and to be relatively torsionally rotated with respect to the rotating shaft. The wing-flapping flying apparatus generates lift throughout an entire wing-flapping movement without generating lift only throughout the half of a wing-flapping movement or offsetting the generated lift by the other half of the wing-flapping movement. Therefore, the wing-flapping flying apparatus can provide not only a stable flight but also a softly hovering or ascending and descending flight.

Abstract: The claimed invention is an ornithopter with three improvements over previous designs. First, it has a more efficient wing. Instead of using a heavy bracing rod to regulate the flexibility of the wing, it uses a lightweight cable tension system. Second, it has a steering mechanism that separates the servos from the tail itself, reducing the likelihood of damage in the event of a crash. Third, the ornithopter has a modular design, which allows more control over the external appearance of the model. Various bodies can be used with the same drive mechanism, and it permits the individual hobbyist or the kit manufacturer to produce additional body designs without having to take on the complex task of designing a new flapping mechanism.

Abstract: A method of transitioning from a complex response flight state to a ground operation control state. Pilot intent is determined through collective position information to control the transition. An independent cockpit switch activates an emergency surface contact transition function for use with a fly-by-wire (FBW) flight control system. Once the surface contact transition function is active, FBW control laws transition from a fully augmented flight state, through an augmentation deactivation state and into the surface contact state.

Abstract: One embodiment of the present invention is a method for automatically reducing the effect of a component of an external force that is laterally incident on a rotorcraft. A signal of the rotorcraft indicative of and proportional to the component is monitored. An absolute value of the signal and a preset high limit are compared. If the absolute value is greater than the preset high limit, manual heading control of the rotorcraft is disabled and the heading of the rotorcraft is adjusted with respect to the external force so as to decrease the lateral component of the external force experienced by the rotorcraft.

Abstract: An ornithopter having segmented, flapping wings and capable of bird-like flight. A main drive system provides flapping motion to the wings. Servo systems are provided for independently moving each wing forward and backward along a major axis of the aircraft fuselage, thereby providing a balance subsystem. A single servomechanism controls upward and downward direction of the wings thereby providing a center angle control subsystem. Two additional servo systems are provided to control a tail assembly that provides steering and other ancillary control functions. Each subsystem is controlled by a dedicated, onboard microcontroller. One embodiment of the aircraft is remotely controlled by a wireless data communication link. The aircraft may be constructed to resemble a natural bird, in both static appearance and flight characteristics. The aircraft may be scaled from model size to a full-size, passenger carrying aircraft.

Abstract: A man-powered ornithopter-sailplane, which has one or two pair of flapping wings and a hang-glider wing wherein substantially novel femoral and humeral muscular propulsion engines with the aid of which the body members connected thereto form integrated moving-flying and controlling-guiding mechanisms. Femoral arms are fixed to the torso base from which the movements for the wings flapping with respect to axles inclined to a horizontal direction are transmitted through the intermediate links of a kinematic chain. The wings comprise a row of rotational rods arranged therein and provided with elastic feather-like panels which produced during flapping, in a closed or turned position thereof, aerodynamic profiles and corresponding lifting and propulsion aerodynamic forces. The controlling-guiding movements are transmitted from the humeral arms to the flapping wings using movable ball joints. The diversity of movements of the femoral arms, humeral arms, hang-glider wing make it possible to control the flight.

Abstract: A MEMS-based micro-unmanned vehicle includes at least a pair of wings having leading wing beams and trailing wing beams, at least two actuators, a leading actuator beam coupled to the leading wing beams, a trailing actuator beam coupled to the trailing wing beams, a vehicle body having a plurality of fulcrums pivotally securing the leading wing beams, the trailing wing beams, the leading actuator beam and the trailing actuator beam and having at least one anisotropically etched recess to accommodate a lever-fulcrum motion of the coupled beams, and a power source.

Abstract: An efficient flying device having flapping wings, an ornithopter, which uses many of the principles seen in bird flight, is presented herein. The wings are highly flexible, translationally stable and oscillate as a natural pendulum. Described as a springboard, the wings have a singular natural frequency, and a pumping means drives the wings at that frequency. Feedback means are described by which to accomplish this, whereby deflection of the wing affects an escapement mechanism which controls the timing and direction of the pumping means. Wing design is described whereby camber, flexure, torsion and directionality of wing components affect efficient propulsion, lift and differential reactivity with air during downstrokes and upstrokes. A crook element in the wing spar at a location proximal to the body of the device redirects vertical oscillation to horizontal.

Abstract: A flapping apparatus includes a first disk rotated by a driving source, and a second disk that rotates in contact with a main surface of the first disk. The second disk is provided with first and second stoppers that limit its angle of rotation. When the stopper is in contact with the first disk, rotation of a wing shaft is caused only by the rotation of the first disk, and when the stoppers are not in contact with the first disk, rotation of the wing shaft is caused only by the rotation of the second disk.

Abstract: A drive assembly for a wing of a micromechanical flying insect. The drive assembly comprises a honey comb structure. A method for flying a micromechanical flying insect comprising moving a wing with a drive assembly having a stiffness to weight ratio greater than about 16×1010 N/mKg.

Abstract: A vehicle for flying and having a forward portion and a rearward portion opposite the forward. The vehicle includes a first pair of wings arranged at the forward portion of the vehicle, a second pair of wings arranged at the rearward portion of the vehicle, and a support structure. The support structure is connected to the forward pair of wings and connected to the rearward pair of wings, the support structure being arranged to drive the forward pair of wings alternately toward each other and apart and drives the second pair of wings alternately toward each other and apart.

Abstract: A rotor blade assembly system includes a trim tab assembly which utilizes relatively thick resilient members bonded between a trim tab and the two trim tab doublers. Spanwise segmenting of the tab and the use of thick resilient member isolates the trim tab from normal strain. Because the trim tab is made of aluminum, the tab can be readily adjusted the field using a conventional tool.

Abstract: A biomimetic pitching and flapping mechanism including a support member, at least two blade joints for holding blades and operatively connected to the support member. An outer shaft member is concentric with the support member, and an inner shaft member is concentric with the outer shaft member. The mechanism allows the blades of a small-scale rotor to be actuated in the flap and pitch degrees of freedom. The pitching and the flapping are completely independent from and uncoupled to each other. As such, the rotor can independently flap, or independently pitch, or flap and pitch simultaneously with different amplitudes and/or frequencies. The mechanism can also be used in a non-rotary wing configuration, such as an ornithopter, in which case the rotational degree of freedom would be suppressed.

Abstract: A flapping apparatus includes a first disk rotated by a driving source, and a second disk that rotates in contact with a main surface of the first disk. The second disk is provided with first and second stoppers that limit its angle of rotation. When the stopper is in contact with the first disk, rotation of a wing shaft is caused only by the rotation of the first disk, and when the stoppers are not in contact with the first disk, rotation of the wing shaft is caused only by the rotation of the second disk.

Abstract: A resonant wingbeat tuning circuit automatically tunes the frequency of an actuating input to the resonant frequency of a flexible wing structure. Through the use of feedback control, the circuit produces the maximum flapping amplitude of a mechanical ornithoptic system, tracking the resonant frequency of the vibratory flapping apparatus as it varies in response to change in flight condition, ambient pressure, or incurred wing damage.

Abstract: An ornithopter has a power assembly which provides flapping of the wings by a reciprocating shaft and bell cranks. The wings are mounted on a hub which rotates in response to the flapping of the wings. The sinusoidal movement of the wings provides lift for flight.

Abstract: An ornithopter has the capability of slow speed flight as a result of vertical movement of its wings. Two sets of wings are provided with vertical movement of each set of wings 180 degrees out of phase for counterbalancing vertical forces on the fuselage. The direction of the flight path is changed by deflecting the fuselage.

Abstract: A thrust reverser having an engine cowl, a nacelle, a blocker door, a nacelle door and a cascade vane. The engine cowl has a hollow body that shrouds a jet engine and which includes a cowl opening. The nacelle surrounds the engine cowl and includes a nacelle opening that is positioned outwardly of the cowl opening. The blocker door is associated with the engine cowl and movable between a first position, wherein the blocker door closes the cowl opening, and a second position, wherein the blocker door is disposed in the propulsive air flow and substantially clears the cowl opening. The nacelle door is associated with the nacelle and movable between a forward position, which substantially closes the nacelle opening, and a rearward position, which substantially clears the nacelle opening. The cascade vane is disposed between the engine cowl and the nacelle and positioned between the cowl and nacelle openings.

Abstract: A wing-drive mechanism is described that permits, with proper control, movement of a wing about multiple wing trajectories. The wing-drive is capable of independent movement about three rotational degrees of movement; movement about a flap axis is independent of movement about a yaw axis, and both are independent of changes in the pitch of the wing. Methods of controlling the wing-drive mechanism to affect a desired wing trajectory include the use of a non-linear automated controller that generates input signals to the wing-drive mechanism by comparing actual and desired wing trajectories in real time. Specification of wing trajectories is preferably also accomplished in real time using an automated trajectory specification system, which can include a fuzzy logic processor or a neural network.

Abstract: An ornithopter with an airframe structure that is lightweight, simple and stable and can generate sufficient lift and thrust. The ornithopter comprises a body, a main wing attached to an upper portion of a front section of the body, and a tail wing attached to a rear section of the body. The ornithopter further comprises a power source and a power transmission mechanism installed within a housing of the body. The main wing includes a wing frame composed of a plurality of frame rods and a skin attached to the wing frame for forming an outline of the main wing. The wing frame of the main wing is supported by a support means exposed to the outside at the upper portion of the front section of the body. The power transmission mechanism includes a gear train for adjusting the rotational motion of the power source at a proper speed and transferring it to the main wing, and connecting rods for converting the rotational motion into a swing motion of the main wing.

Abstract: A power generator comprising: a lifting body for suspension in a moving fluid; a control station; and at least two tethers for tethering the lifting body to the control station. The control station is arranged to transform oscillating tension in the tethers produced by an oscillating movement of the lifting body into mechanical motion.

Abstract: A biomimetic pitching and flapping mechanism including a support member, at least two blade joints for holding blades and operatively connected to the support member. An outer shaft member is concentric with the support member, and an inner shaft member is concentric with the outer shaft member. The mechanism allows the blades of a small-scale rotor to be actuated in the flap and pitch degrees of freedom. The pitching and the flapping are completely independent from and uncoupled to each other. As such, the rotor can independently flap, or independently pitch, or flap and pitch simultaneously with different amplitudes and/or frequencies. The mechanism can also be used in a non-rotary wing configuration, such as an ornithopter, in which case the rotational degree of freedom would be suppressed.

Abstract: An ornithopter has a power assembly which provides flapping of the wings by a reciprocating shaft and bell cranks. The wings are mounted on a hub which rotates in response to the flapping of the wings. The sinusoidal movement of the wings provides lift for flight.

Abstract: A compressed air engine and a flying object using the engine are disclosed. The flying object includes the following elements. That is, the compressed air engine includes: a top member 11 provided with an air inlet 16; an upper cylinder 12; a lower cylinder 13; a bottom member 14; an air pipe, for passing of a compressed air; a shuttle 20 for performing up/down movements within a cylinder formed by the upper and lower cylinders; and a pair of pistons 21a and 21b over and under the shuttle respectively. The pair of the wings are symmetrically and pivotally assembled to the shuttle and the lower cylinder through securing shafts so as to perform up/down movements in accordance with the up/down movements of the shuttle. A compressed air container 2 is assembled to the bottom of the bottom member, for storing the compressed air.

Abstract: A compressed air engine and a flying object using the engine are disclosed. The flying object includes the following elements. That is, the compressed air engine includes: a top member 11 provided with an air inlet 16; an upper cylinder 12; a lower cylinder 13; a bottom member 14; an air pipe, for passing of a compressed air; a shuttle 20 for performing up/down movements within a cylinder formed by the upper and lower cylinders; and a pair of pistons 21a and 21b over and under the shuttle respectively. The pair of the wings are symmetrically and pivotally assembled to the shuttle and the lower cylinder through securing shafts so as to perform up/down movements in accordance with the up/down movements of the shuttle. A compressed air container 2 is assembled to the bottom of the bottom member, for storing the compressed air.

Abstract: A power-driven ornithopter piloted by a remote controller wherein a takeoff and landing motion, a climbing and descending motion, and a turning motion of the ornithopter can be controlled using the remote controller. The ornithopter comprises a body, a main wing attached to an upper portion of a front section of the body, and tail wings attached to a rear section of the body. An electric motor, a power transmission mechanism, a battery, first and second servo motors and a controller are installed within a housing of the body. A crank arm is connected to a rotating shaft of the first servo motor and a connecting rod attached to a free end of the crank arm is then pivotally connected to a lower edge of the horizontal tail support. The second servo motor is mounted into a recess formed at an upper side of a rectangular parallelepiped of the horizontal tail support and a rotating shaft of the second servo motor is disposed on a central axis of the horizontal tail.

Abstract: The present invention to a flying object by flapping motion of two pair of wings, which comprises a compressed air engine, a flying body (or compressed air container) assembled with the compressed air engine and in which compressed air is contained, two pair of wings symmetrically assembled with the compressed air engine and functioning flapping motion up and dawn in the range of 70° while the individual wing being able to get twisted in the range of 15°, a head cover for covering the front and upper part of the compressed air engine, and a tail wing with a horizontal wing and a vertical wing.

Abstract: A compressed air engine and a flying object using the engine are disclosed. The flying object includes the following elements. That is, the compressed air engine includes: a top member 11 provided with an air inlet 16; an upper cylinder 12; a lower cylinder 13; a bottom member 14; an air pipe, for passing of a compressed air; a shuttle 20 for performing up/down movements within a cylinder formed by the upper and lower cylinders; and a pair of pistons 21a and 21b over and under the shuttle respectively. The pair of the wings are symmetrically and pivotally assembled to the shuttle and the lower cylinder through securing shafts so as to perform up/down movements in accordance with the up/down movements of the shuttle. A compressed air container 2 is assembled to the bottom of the bottom member, for storing the compressed air.

Abstract: A flapping wing flying device comprises wings that pivot about a pivot axis extending generally perpendicularly to an elongate body of the flying device, and wings that move relative to said elongate body of the flying device, so that the entire leading edge of each of the wings is moved away from and toward to the body of the flying device during flight.

Abstract: The present invention relates to a flying object by flapping motion of two pair of wings, which comprises a compressed air engine, a flying body (or compressed air container) assembled with the compressed air engine and in which compressed air is contained, two pair of wings symmetrically assembled with the compressed air engine and functioning flapping motion up and dawn in the range of 70° while the individual wing being able to get twisted in the range of 15°, a head cover for covering the front and upper part of the compressed air engine, and a tail wing with a horizontal wing and a vertical wing.

Abstract: An aircraft having a reduced-load wing structure is provided with a controllable canard stabilizer (5G, 5D) at the front end of the aircraft and a controller that controls the canard stabilizer. The controller generates a turn command corresponding to an increase in the lift of the canard stabilizer when, simultaneously, the turn command applied by the pilot to the elevational control surfaces (6G, 6D) exceeds a threshold and the measurement of the vertical acceleration of the aircraft exceeds a threshold.

Abstract: A process for managing air speed of an aircraft in flight. The method includes a first step of determining a point on the flight path at which it is theoretically possible to comply with a required time constraint by following a pre-established speed profile. In a second step, a speed is computed and a fresh speed profile is determined. This is obtained by determining speed corrections segment-by-segment from the point up to the last modifiable segment. The speed change in each segment is restricted to a maximum value. The new speed is computed on the basis of the curve showing the flight time t as a function of the speed V. This curve is approximated by a curve satisfying an equation with three coefficients (C.sub.1, C.sub.2, C.sub.3):V=c.sub.1 /t+c.sub.2 /t.sup.2 +c.sub.3 /t.sup.3Compliance with time constraints are ensured by this method while meeting the requirements of the pilot and air traffic controllers.

Abstract: A new method for boundary layer energization and boundary layer propulsion or use on vehicles moving through fluids, which comprises mounting small airfoils parallel or perpendicular to the vehicle's surface, said airfoils being embedded within the said vehicle's boundary layer and juxtaposed the surface of said vehicle, said airfoils being approximately the height of the boundary layer thickness and exciting said airfoils into flapping oscillation parallel to the chord plane of said airfoils, said oscillation at a frequency up to 100 cycles per second at an amplitude up to 20 percent of the chord length of said airfoil, whereby flow separation is delayed or suppressed which enables the redesign of said vehicle.

Abstract: The disclosed flight control system includes a rotor blade speed monitor for monitoring the rotor blade speed of the jet powered tri-mode aircraft and for outputting a rotor blade speed command. The flight control system also includes an aircraft attitude controller for controlling the aircraft attitude of the jet powered tri-mode aircraft. Weighted rotor blade attitude stabilization commands and weighted aero surface attitude stabilization commands are output from the aircraft attitude controller to distribute power, control, and lift between the rotor blade and the aero surfaces. Relative weights of the weighted rotor blade attitude stabilization commands decrease with increasing aircraft travelling velocities, and relative weights of the weighted aero surface attitude stabilization commands increase with increasing velocities.

Abstract: In a novel hovering aircraft, an airfoil blade structure rotatable about a vertical axis comprises a set of upper blades and a set of lower blades, all having variable lift, the upper blades converging toward the lower blades from root to tip. Struts, located inboard of the blade tips, keep the tips of the upper and lower blades separate from each other to reduce interference effects, and also support motors and propellers.

Abstract: An ornithopter aircraft which flys by flapping a wing. The wing is flapped by a constructively sympathetically forced dampened harmonic oscillation induced in a leading edge strut which preferable is a single flexible steel rod extending the length of the wing. The wing releases the air on its upward recovery stroke by means of flexible flaps which uncover holes in a structural flexible web forming the wing. On the downward power stroke of the wing, the flaps sealingly abut and occlude the holes of the web, forming a wing surface relatively impermeable to the passage of air. An inner section of the wing, on both sides of the aircraft, where relatively little flapping motion displacement occurs, has a flexible layer which permanently covers and seals the holes of the web. This area of the wing generates lift during both upward and downward motion of the wing, due to the forward motion of the ornithopter and due to the capture of pressurized air from the downstroke of the wing.

Abstract: A human powered hang glider has a right main wing and a left main wing, both of which are swingably attached to a post by a universal joint. A rope is stretched in a loop shape between a pedal provided at a lower part of the post and the main wing, and is fixed to the pedal and the main wing. By operation of the pedals, the main wings are flapped like a bird flaps its wing. By this flapping action of the main wings, the hand glider can take wing, whether or not an upcurrent is present.

Abstract: Process and apparatus providing the automatic locking of the wings of a wing-operated flying toy, wherein a locking device associated with the operating mechanism is applied, under the effect of elastic pressure, against a notch or slot of the circular disk of the draw crank of the operating mechanism, so that when an elastic band attains its normal power under the effect of torsional moment, the locking device is unable to engage or hold its position in the notch or slot; whereas when the power has almost attained its lowest value at the moment when the elastic band is almost completely untwisted, the locking device is able to engage and maintain itself in the slit causing the wing operating mechanism to lock and prevent movement of the wings.

Abstract: A machine designed to move a pair of light weight graphite fiber composite covered wings in such a way that their tips will describe a horizontal figure eight through the air. Thereby sustaining an attack angle and creating lift throughout as much as 80% of their travel path. The mechanism retains 100% control over the wing movement and with a locking device in place the preferred embodiment should be capable of a good glide ratio.