US 6,206,324 B1Grant

Wing-drive mechanism, vehicle employing same, and method for controlling the wing-drive mechanism and vehicle employing same

Issue Date:2001-03-27

•20 Claims

•6 Drawing Sheets

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. A vehicle that derives controlled motion as a whole from the wing-drive mechanism is also disclosed.

Metadata

Inventor

Michael J. C. Smith

Application Information

Application Number:US 09/385,326

Filing Date:1999-08-30

Priority Date:1999-08-30

Art Unit:7

Classifications

IPC:

B64C 3302

Field of Search:

244 11244 22244 72446 39446313490 32490 21490 13416 74416 75416 83

Patent Drawings (6 sheets)

Description

Statement Regarding Federally Sponsored Research or Development

[0002] The research and development leading to the subject matter disclosed herein was not federally sponsored.

Background of the Invention

[0003] This invention relates to vehicles that derive motion from one or more flapping wings.

[0004] Since the advent of controlled heavier-than-air flight in the early 1900's, development of aircraft has focussed primarily on fixed-wing and rotary wing technologies. Fixed-wing technologies are typified by commercial, military and pleasure airplanes, in which thrust is generated by a propeller or jet engine and the forward movement of an airfoil through the atmosphere creates lift. Rotary-wing technologies are employed in helicopters, in which lift is generated by pushing air downward with rotating rotor blades. Each of these technologies has its advantages and limitations.

[0005] Fixed-wing technologies, for example, permit very high forward velocities and maneuverability. However, both lift and maneuverability depend on the forward motion of the aircraft. Vertical short take-offs or landings (VSTOL), hovering and other maneuvers cannot be accomplished using fixed-wing technology alone. Similarly, turns cannot be executed without rolling the fuselage, and very sharp angle turns cannot be accomplished. Rotary-wing technologies offer improved VSTOL and hovering ability, but their forward and sideways velocities usually are limited, as is their ability to turn. In addition, rotary-wing aircraft often respond poorly to wind gusts.

[0006] Hybridized vehicles incorporate fixed-wing and rotary wing technologies to create a combined lift-thrust force. These vehicles have shown limited improvements in maneuverability and versatility compared to fixed-wing and rotary wing vehicles.

[0007] A third approach to heavier-than-air flight employs flapping wings to generate a combined lift-thrust force. In principle, flapping wing technology offers the possibility of creating versatile flight vehicles that can combine and in some cases exceed the performance advantages of fixed-wing and rotary-wing technologies. In particular, flapping wing technology offers the possibility of providing improved maneuverability compared to even rotary-wing technologies. Vehicles employing flapping wing technologies are referred to as “ornithopters”.

[0008] Unfortunately, very few ornithopters have succeeded in flying. In 1929, Lippisch developed a human-powered ornithopter that achieved non-sustained flight. In 1986, MacCready et al. developed an ornithopter modeled on a pterosaur, an extinct flying reptile. That ornithopter was winch launched and could not sustain flight for an extended duration. More recently, Harris and DeLaurier developed an ornithopter that was capable of sustained flight. In addition, various toys have been developed that employ flapping wing technology to fly, including that described in U.S. Pat. No. 4,729,728 to Van Ruymbeke.

[0009] Unfortunately, even those previous ornithopters that were capable of flight were very limited in their maneuverability. These ornithopters operated by flapping wings only in a single trajectory, i.e., in an up and down motion. Thus, the aerodynamic force developed by the flapping wings over the course of a series of “beats” was fixed in a fixed (relative to the vehicle), substantially vertical plane. To develop lift, these ornithopters mimicked conventional fixed wing aircraft in that in all cases lift was achieved by creating airflow past an airfoil due to the forward motion of the vehicle as a whole. Thus, these ornithopters suffered from the same maneuverability limitations as conventional fixed-wing aircraft.

[0010] In an analogous way, conventional and submersible watercraft, spacecraft and satellites also are limited in their maneuverability due to the design of their propulsion systems.

[0011] It would be desirable to provide a wing-drive mechanism, that can affect more than one wing trajectory, thereby generating a force vector over the course of a “beat” or series of “beats” which has an arbitrary but predetermined and changeable magnitude and/or direction. It would also be desirable to provide a method of controlling a wing-drive mechanism that can affect more than one wing trajectories. It would further be desirable to provide a vehicle having at least one flapping drive wing that can affect multiple wing trajectory. It would further be desirable to provide a method for improved control of the motion of an ornithopter or other vehicle as a whole.

Brief Description of the Drawings

[0012] FIG. 1 is an overhead view of an embodiment of the wing-drive mechanism of this invention.

[0013] FIG. 2 is a graphical representation of an example of how torques can be applied by the first, second and third axis drive mechanisms of the wing-drive mechanism of the invention over the course of a beat cycle.

[0014] FIG. 3 is a graphical representation of an example of how a drive wing can move through a beat cycle.

[0015] FIG. 4 is a schematic diagram of an automated control system for the wing-drive mechanism of this invention.

[0016] FIG. 5 is an overhead view of a second embodiment of the wing-drive mechanism of this invention.

[0017] FIG. 6 is an isometric view, partially in section, of a flying vehicle having four wing-drive mechanisms of this invention.

[0018] FIG. 7 illustrates a third embodiment of the wing-drive mechanism of this invention.

[0019] FIG. 8 illustrates a fourth embodiment of the wing-drive mechanism of this invention.

Summary of the Invention

[0020] In one aspect, this invention is a wing-drive mechanism for a vehicle having a fuselage, comprising

[0021] a) a drive wing having an adjustable pitch relative to said fuselage and being moveable relative to said fuselage about yaw and flap axes;

[0022] b) a first axis drive mechanism for moving said drive wing about said flap axis in response to a first movement input signal,

[0023] c) a second axis drive mechanism for moving said drive wing about said yaw axis in response to a second movement input signal, wherein said second axis drive mechanism operates independently of said first axis drive mechanism and

[0024] d) a third axis drive mechanism for adjusting the pitch of said drive wing in response to a third movement input signal, wherein said third axis drive mechanism operates independently of said first and second axis drive mechanisms.

[0025] Because the wing-drive mechanism of this invention is capable of independent movement in three degrees of rotation, it can with proper control be operated to move over multiple trajectories. Multiple, arbitrary wing trajectories can be produced by varying the relative operation of the three axis drive mechanisms, thereby permitting the drive-wing to generate, over the course of a “beat” or series of beats, a net force vector that can have varying magnitudes and directions relative to the orientation of the fuselage in space.

[0026] The wing-drive mechanism of this invention also allows for the development of vehicles having two or more independently operated drive wings; i.e. the trajectory of one drive wing can be specified arbitrarily with respect to the trajectory of another drive wing. By operating independently in this fashion, the forces generated by each drive wing can be combined in various ways to maneuver the vehicle. As discussed below, the wing-drive mechanism of this invention most preferably operates independently of the orientation of the fuselage in inertial space, i.e. the ability of the wing-drive mechanism to affect a certain trajectory relative to an inertial frame of reference is not conditioned on the vehicle occupying a unique orientation in space. This can provide yet further refinements in maneuverability and control.

[0027] Unless the context requires a narrow meaning, the terms “wing” or “drive wing” are used herein broadly to mean any wing, aileron, stabilizer, rudder, paddle or other propulsion and/or steering device that is moved through a trajectory by the wing-drive mechanism of the invention. “Fuselage” is used herein as shorthand for any host body to which the wing-drive mechanism is affixed.

[0028] In a second aspect, this invention is a vehicle that derives motion from at least one wing-drive mechanism attached to a fuselage, said wing-drive mechanism comprising

[0029] a) a drive wing having an adjustable pitch relative to said fuselage and being moveable relative to said fuselage about yaw and flap axes;

[0030] b) a first axis drive mechanism for moving said drive wing about said flap axis in response to a first movement input signal,

[0031] c) a second axis drive mechanism for moving said drive wing about said yaw axis in response to a second movement input signal, wherein said second axis drive mechanism operates independently of said first axis drive mechanism and

[0032] d) a third axis drive mechanism for adjusting the pitch of said drive wing in response to a third movement input signal, wherein said third axis drive mechanism operates independently of said first and second axis drive mechanisms.

[0033] In a third aspect, this invention is a method of controlling a wing-drive mechanism of the first aspect, comprising

[0034] a) inputting a desired drive wing trajectory into a controller including a computer that is programmed to calculate first, second and third movement input signals in real time using a non-linear controlling function that relates said desired drive wing trajectory to torques to be applied by each of said first, second and third axis drive mechanisms,

[0035] b) using said controller, generating said first, second and third movement signals in real time, and

[0036] c) transmitting said first, second and third movement signals to said first, second and third axis drive mechanisms, respectively, whereby said first, second and third axis drive mechanisms affect movement of the drive wing in the desired trajectory in response to said first, second and third input signals.

[0037] In a fourth aspect, this invention is another method of controlling the wing-drive mechanism of the first aspect, comprising

[0038] a) developing two or more sets of coordinated movement input signals, each such set including a first, second and third movement input signal, each such set corresponding to a specific drive wing trajectory;

[0039] b) recording each set of first, second and third movement input signals,

[0040] c) inputting a desired drive wing trajectory into a controller that is adapted to access said recorded sets of drive wing trajectories and generate a set of first, second and third movement input signals that correspond to the desired drive wing trajectory and

[0041] d) using said controller, generating and transmitting a set of first, second and third movement input signals corresponding to said desired drive wing trajectory to said first, second and third axis drive mechanisms, respectively.

Detailed Description of the Invention

[0042] In this invention, a vehicle has one or more movable drive wings that are attached directly or indirectly to a fuselage. The vehicle can be, for example, a flying vehicle such as an ornithopter, a watercraft such as a submersible or a boat, a spacecraft or a satellite. As used herein, the term “fuselage” refers to a structure to which the drive wings are attached, and in relation to which the drive wings move during a beat cycle. The “fuselage” can have any arbitrary shape, size and orientation, and may optionally include one or more platforms or enclosed spaces for carrying operational systems, cargo and/or passengers.

[0043] The drive wing(s) move(s) relative to the fuselage in a periodic manner to produce a force over the course of a beat cycle or series of beat cycles. A “beat cycle” describes the periodic movement of a drive wing from an initial starting orientation relative to the fuselage, through a trajectory relative to the fuselage and returning to the initial starting orientation, whereupon a new beat cycle begins. The “trajectory” of a drive wing is the entire course of movement that is undertaken by the drive wing during the course of a beat cycle. The “trajectory” includes the movement of the drive wing in at least three rotational degrees of freedom, i.e. about flap and yaw axes, and through changes of pitch. A drive wing trajectory can be described in relation to the fuselage or an inertial frame of reference.

[0044] FIG. 3 illustrates how a wing trajectory can be expressed in terms of motion about a flap axis (curve 301) and a yaw axis (curve 302) and changes in pitch (curve 303) over the course of a single beat. The wing trajectory illustrated in FIG. 3 simulates naturally occurring wing movement related to an analysis of a sphingid moth. All angles are expressed in terms of Euler angles, which relate wing motions to a preselected coordinate system based on orientation of the moth as a whole. Methods for relating Euler angles to wing motions are described in “Simulating Flapping Insect Wings Using an Aerodynamic Panel Method: Towards the Development of Flapping-Wing Technology”, Ph.D. Thesis of M. J. C. Smith, Purdue University (1995), incorporated herein by reference. However, any convenient method for representing the orientation angles can be used, such as those methods described in Wakeling and Ellington, “Dragonfly Flight I. Gliding Flights and Steady-State Aerodynamic Forces”, J. Experimental Biology, V. 200, pp. 543-556 (1997); Wakeling and Ellington, “Dragonfly Flight II. Velocities, Accelerations and Kinematics of Flapping Flight”, J. Experimental Biology, V. 200, pp. 557-582 (1997); Wakeling and Ellington, “Dragonfly Flight III. Quasi-steady Lift and Power Requirements”, J. Experimental Biology, V. 200, pp. 583-600 (1997). Vertical line 304 intersects lines 301, 302 and 303 at points 305, 306 and 307, respectively, and indicates the values of the Euler angles at sampling time t_s. Points 305, 306 and 307 together designate a desired wing position at time t_s. The first and second derivatives of lines 301, 302 and 303 at time t_srepresent angular velocities and accelerations of the wing in terms of Euler angles. Together these derivatives designate the desired angular wing velocity and acceleration at time t_s.

[0045] The shape and dimensions of the drive wing will of course be a matter of design choice, and the particular shape and dimension are not critical to the invention. All that is necessary is that the drive wing be shaped in a way that it can be moved over a trajectory, over the course of a beat cycle or a series of beat cycles, such that it generates a net force in a predetermined direction. This is most easily achieved by designing the drive wing with an average width significantly greater than its average thickness, so that the force exerted by the moving drive wing at a given point in its trajectory can be increased or decreased by varying the pitch of the drive wing. For flying vehicles, it is not necessary that the drive wing be shaped so as to function as an airfoil, although it is optionally shaped in such a manner.

[0046] In practice, the particular size, shape, construction and weight of the drive wing(s) will be selected in conjunction with many other design considerations, including, notably, the size, shape, orientation and weight of the vehicle as a whole, the design of other drive wings, the position of the drive wing relative to the fuselage and other drive wings and structural features, power requirements and availability, and desired performance characteristics of the vehicle as a whole. The development of suitable drive wing designs is advantageously done together with the development of accompanying drive wing trajectories.

[0047] For purposes of evaluating suitable drive wing designs for a particular flying vehicle in connection with suitable drive wing trajectories, the net aerodynamic force that is performed by a beating drive wing over a beat cycle or series of beat cycles can be ascertained empirically or estimated using one or more modeling techniques as are known in the art. Among the mathematical models that are useful for estimating the magnitude and direction of the aerodynamic force created by a wing over a beat cycle are those described in the Ph.D. Thesis of Smith, cited above; Smith, “Simulating Moth Wing Aerodynamics: Towards the Development of Flapping-Wing Technology”, AIAA Journal 34:7, pp. 1348-1355 (1996); Smith et al., “The Advantages of an Unsteady Panel Method in Modeling the Aerodynamic Forces on Rigid Flapping Wings”, J. Experimental Biology 199, 1073-1083 (1996); Smith, Leading-Edge Effects on Moth Wing Aerodynamics: Towards the Development of Flapping-Wing Technology, 14^thAIAA Applied Aerodynamics Conference (1996); Liu et al., “A computational fluid dynamic study of hawkmoth hovering”, J. Experimental Biology, Vol. 201, pp. 461-477 (1968); Vest and Katz, “Unsteady Aerodynamic Model of Flapping Wings”, AIAA Journal, 34:7, pp. 1435-1440 (1996); Tuncer and Platzer, “Thrust Generation due to Airfoil Flapping”, AIAA Journal, 34:2, pp. 324-331 (1996); and Tuncer et al., “Computational Analysis of Flapping Airfoil Aerodynamics”, Advances in Computations Methods in Fluid Dynamics, American Society of Mechanical Engineers, New York, FED-Vol. 196, pp. 9-18 (1994), all incorporated herein by reference.

[0048] Empirical methods for measuring the aerodynamic force created by a single flapping wing or a plurality of flapping wings in combination are described, for example, by Reavis and Luttges, “Aerodynamic Forces Produced by a Dragonfly”, AIAA 888-0330 (1988); Saharon and Luttges, “Dragonfly Unsteady Aerodynamics-the Role of the Wing Phase Relations in Controlling the Produced Flows”, AIAA 89-0832 (1989); and the Wakeling and Ellington articles mentioned above.

[0049] For any particular drive wing design for a flying vehicle, relationships between specific drive wing trajectories and resultant aerodynamic and inertial forces can be established empirically or through modeling techniques, or combinations of both. These relationships advantageously are used to develop programming algorithms for automated specification of drive wing trajectories, as discussed below. Wing designs and trajectories for watercraft can be developed in an analogous way.

[0050] The wing-drive mechanism of the invention is characterized in that the drive wing can move simultaneously and independently in three rotational degrees of freedom relative to the fuselage, as described more fully hereinafter. For each drive wing, there are independent axis drive mechanisms for moving the drive wing about a flap axis and a yaw axis. There is another independent axis drive mechanism for changing the pitch of the drive wing. In this context, the axis drive mechanisms are said to operate “independently” if the motion imparted to the drive wing by each individual axis drive mechanism can be specified arbitrarily with respect to the motions imparted to the drive wing by the other axis drive mechanisms.

[0051] The flap and yaw axes are advantageously fixed with respect to the orientation of the fuselage. Provided that the yaw and flap axes are not coincident or parallel, they can have any relative orientation that allows for the drive wing to move up-and-down relative to an inertial frame of reference, backward-and-forward (or side-by-side) relative to fuselage 100, and in any combination of up-and-down and backward-and-forward (or side to side). Note that the descriptors “flap” and “yaw” are arbitrary, as are the orientation of the “yaw” and “flap” axes relative to fuselage 100. For design purposes, however, the “flap” axis is preferably substantially horizontal (for example +/− up to about 45° from horizontal) and the “yaw” axis is preferably substantially vertical (for example +/− up to about 45° from vertical) when the fuselage is in a nominally “ordinary” orientation during flight. It is not necessary that the flap and yaw axes be perpendicular to each other, although an angle of from about 45-90° is preferred, an angle of about 60-90° is more preferred and an angle of about 90° is most preferred. In the embodiment shown in FIG. 1, the flap axis is substantially horizontal and parallel with the nominal front-to-rear orientation of fuselage 100 (shown in outline), and the yaw axis is substantially vertical and perpendicular to the front-to-rear orientation of fuselage 100.

[0052] FIG. 1 illustrates an embodiment of a wing-drive mechanism according to the invention. Drive wing 101 is affixed to spar 102 that is connected to third axis drive mechanism 103 that includes joint 104. Drive wing 101 has an average width W and an average thickness T. Third axis drive mechanism 103 is affixed, directly or indirectly, to fuselage 100 (shown in section, with the direction of its “front” being arbitrarily designated by arrow 150 and “up” relative to an inertial frame of reference being designated by arrow 151). Pitch axis 105 is fixed in space in relation to fuselage 100 by virtue of third axis drive mechanism 103 being affixed to fuselage 100. Third axis drive mechanism 103 affects rotation about pitch axis 105 in a direction of rotation indicated by the double-headed arrow a-a′. In FIG. 1, the direction of rotation about the pitch axis is arbitrarily designated as “positive” in the clockwise direction (facing outward along spar 102) and “negative” in the counterclockwise direction, but any suitable convention for expressing the rotation about the pitch axis may be used. Rotation about pitch axis 105 results in rotation of spar 102 and, correspondingly, a variation of the pitch of drive wing 101.

[0053] Joint 104 forms part of third axis drive mechanism 103 and is designed to transfer torque applied by third axis drive mechanism 103 about pitch axis 105 to spar 102 and thus affect changes of the pitch of drive wing 101 while simultaneously allowing drive wing 101 to move independently about yaw axis 123 and flap axis 113. A universal joint is suitable for this purpose. A coil spring can also be used to couple spar 102 to third axis drive mechanism 103, provided that the spring provides sufficient torsional strength (i.e. provides for efficient transfer of torque from third axis drive mechanism 103 to drive wing 101) but is flexible enough to permit spar 102 to be rotated about the yaw and flap axes. Similarly, a “concertina” type mechanism that is torsionally rigid but flexes freely about the yaw and flap axes over the desired range of motion is suitable.

[0054] A flap motion is imparted to drive wing 101 via first axis drive mechanism 111. First axis drive mechanism 111 provides torque to spar 102 about flap axis 113. In the embodiment shown, torque is transferred to spar 102 via guide rail 110, which forms part of first axis drive mechanism 111. As shown, guide rail 110 is in the form of a slotted arc, and spar 102 is inserted through slot 112 of guide rail 110. First axis drive mechanism is adapted to apply torque to guide rail 110, thereby rotating guide rail 110 and spar 102 about flap axis 113 to impart an oscillating flap motion to spar 102 and drive wing 101. The orientation of flap axis 113 is fixed in space with respect to fuselage 100 by virtue of first axis drive mechanism 111 being affixed directly or indirectly to fuselage 100. The direction of rotation imparted by first axis drive mechanism 111 to guide rail 110 is shown by double-headed arrow b-b′. A clockwise rotation (as seen facing the “rear” of the fuselage) is arbitrarily designated as “positive”, and the opposite rotation is arbitrarily designated as “negative”. The direction of flap motion imparted to drive wing 101 is shown by double-headed arrow B-B′.

[0055] A yaw motion is imparted to drive wing 101 via second axis drive mechanism 121. Second axis drive mechanism 121 provides torque to spar 102 about yaw axis 123. In the embodiment shown, torque is transferred to spar 102 via guide rail 120, which forms part of second axis drive mechanism 121. As shown, guide rail 120 is in the form of a slotted arc, and spar 102 is inserted through slot 122 of guide rail 120. In this embodiment the radius of curvature of guide rail 120 is larger than that of guide rail 110, so that the two guide rails can move freely and independently with respect to each other. The direction of rotation imparted by second axis drive mechanism 121 to guide rail 120 is shown by double-headed arrow c-c′. A clockwise rotation (as seen facing “upward” through the fuselage) is arbitrarily designated as “positive”, and the opposite rotation is arbitrarily designated as “negative”. The direction of yaw motion imparted to drive wing 101 is shown by double-headed arrow C-C′.

[0056] Axis drive mechanisms 103, 111 and 121 affect movement of drive wing 101 by providing torque to spar 102 about the pitch, flap and yaw axes. In response to a movement input signal, each of axis drive mechanisms 103, 111 and 121 (1) transfer torque to drive wing 101 (2) independently of the operation of the other axis drive mechanisms. As such, axis drive mechanisms 103, 111 and 121 each include means for receiving a movement input signal and applying torque in response thereto, as well as coupling apparatus for transferring the torque to spar 102. Axis drive mechanisms 103, 111 and 121 also include or are coupled to a source of mechanical power such as a motor. It will be readily appreciated that a great many variations in the designs and configurations of the axis drive mechanisms are possible.

[0057] Two simple but suitable variations of axis drive mechanisms are shown in FIG. 1. A first type is exemplified by third axis drive mechanism 103, which includes motor 161 that provides torque about shaft 160. Shaft 160 is aligned with pitch axis 105. Joint 104 is affixed to shaft 160 so that torque applied to shaft 160 is transferred directly to spar 102. Of course, gearing, clutches or the like can be interposed between shaft 160 and joint 104 if desired. A second variation of axis drive mechanism is exemplified by first and second axis drive mechanisms 111 and 121. Second axis drive mechanism 121 includes motor 181 that provides torque about shaft 180. Shaft 180 is aligned with yaw axis 123. Arced guide rail 120 is affixed to shaft 180 so that torque applied to shaft 180 is transferred to arced guide rail 120, thereby affecting movement of spar 102 in the direction indicated by double arrow C-C′. Similarly, first axis drive mechanism 111 includes motor 171 that provides torque about shaft 170 that is aligned with flap axis 113. The torque is applied to spar 102 by arced guide rail 110 that is affixed to shaft 170. Rotations of arced guide rail 110 affect movement of spar 102 in the direction indicated by the double arrow B-B′. As with third axis drive mechanism 103, many variations of this second variation of drive mechanism are possible, and apparatus such as clutches, gearing and the like may be added as appropriate.

[0058] In the embodiment shown in FIG. 1, mechanical power is supplied to axis drive mechanisms 103, 111 and 121 by motors 161, 171 and 181, respectively. Such motors can be of any type, including but not limited to internal combustion engines, pneumatic motors, steam engines, electrical motors and hybrid electrical motors. Electrical motors are preferred, as the use of an electrical motor for mechanical power greatly facilitates the creation of complex torque sequences over the course of a beat cycle. Electrical motors that operate bidirectionally are especially preferred as such motors tend to be light weight and offer the possibility of controlling the magnitude and direction of the applied torque through variations in the electrical power supply to the motor.

[0059] Although each axis drive mechanism shown in FIG. 1 has its own source of mechanical power, it is possible through appropriate linkages for two or more axis drive mechanisms to share a single mechanical power source.

[0060] Axis drive mechanisms 103, 111 and 121 also contain connections to fuel or power supplies. If an axis drive mechanism does not contain a dedicated source of mechanical power, it is coupled to one. Suitable power supplies include fossil fuels, compressed gasses, steam, batteries, hydrogen fuel cells, solar panels, generators or combinations of these.

[0061] The combined operations of axis drive mechanisms 103, 111 and 121 move drive wing 101 through its trajectory. The trajectory produced through the combined operations of axis drive mechanisms 103, 111 and 121 can be altered through changes in the frequency, sequencing, phasing and magnitude of the flap, yaw and pitch motions, or through combinations of such changes. The ability of the wing-drive mechanism to affect multiple trajectories is an important advantage of this invention, and is a result of employing a wing-drive mechanism that permits the drive wing to move over three independent rotational degrees of freedom. By changing the drive wing trajectory, both the magnitude and the direction of the net force (relative to the fuselage or an inertial frame of reference, or both) created by the drive wing over the course of a beat cycle or series of beat cycles can be varied in a predetermined way.

[0062] Flap, yaw and pitch motions are affected by the application of torque to drive wing 101 by each of axis drive mechanisms 103, 111 and 121. To affect a specific drive wing trajectory, each of axis drive mechanisms 103, 111 and 121 apply torque, over the course of a beat cycle, in a predetermined pattern. Generally, the torque applied by each of axis drive mechanisms 103, 111 and 121 changes in a continuous or piecewise continuous manner over the course of beat cycle. To maintain a specific drive wing trajectory, those torque patterns are simply repeated over multiple beat cycles. Changes in drive wing trajectory are affected by altering the pattern of torque that is applied by at least one and possibly two or three of the axis drive mechanisms 103, 111 or 121.

[0063] FIG. 2 provides a graphical illustration of how torques might be applied over a beat cycles by each of the first, second and third axis drive mechanisms to affect an arbitrary drive wing trajectory. In FIG. 2, the applied torque (in arbitrary units) is plotted against time over 1 beat cycle. Curves 201, 202 and 203 correspond to the torque applied by the first, second and third axis drive mechanisms, respectively. Positive and negative torque values indicate arbitrarily designated directions of rotation about the flap, yaw and pitch axes for curves 201, 202 and 203, respectively. As shown, the patterns of applied torque can be graphically illustrated as a continuous or piecewise continuous function.

[0064] Thus, in order to affect a given drive wing trajectory, it is necessary to create a set of coordinated torque patterns that are to be applied by each of the axis drive mechanisms over a course of a beat cycle. Control over the wing-drive mechanism of this invention is exercised by (1) identifying a desired drive wing trajectory and (2) generating and transmitting movement input signals which actuate the respective axis drive mechanism to supply the appropriate torque sequences to affect the desired drive wing trajectory.

[0065] An alternative design for the wing-drive mechanism of this invention is illustrated in FIG. 5. In FIG. 5, joint 500 connects third axis drive mechanism 503 with spar 501. Spar 501 is affixed to the drive wing (not shown). Third axis drive mechanism 503 is affixed to arced joint member 531 and directly or indirectly to the fuselage. Third axis drive mechanism 503 operates in response to a third movement input signal to rotate shaft 561 about pitch axis 552 in a direction indicated by double headed arrow 504, thereby affecting a like rotation of arced joint member 531 and spar 501. Arced joint member 531 is rotatably affixed to shafts 581. Second axis drive mechanisms 521 are mounted on central cross-member 570, and in response to a second movement input signal affect rotation of cross-member 570 about shafts 581 (and yaw axis 551) in a direction indicated by double-headed arrow 522. This imparts a yaw motion to spar 501 in the direction indicated by double-headed arrow D-D′. First axis drive mechanisms 511 are mounted on central cross member 570, and in response to a first movement input signal rotate shafts 571 about flap axis 550 in a direction imparted by double-headed arrow 512. Shafts 571 are affixed to arced joint member 532 so that arced joint member 532 moves in a flap direction indicated by double-headed arrow E-E′as shafts 571 rotate. Spar 501 is affixed to arced joint member 532.

[0066] FIG. 7 illustrates yet another design variation for a wing-drive mechanism. Third axis drive mechanism 703 includes motor 761 which rotates shaft 760 about pitch axis 705 in the direction indicated by double arrow g-g′. Shaft 760 is affixed to joint 704, and joint 704 transfers torque to spar 702. A drive wing (not shown) is affixed to spar 702. First axis drive mechanism 711 includes motor 771, which rotates shaft 770 about axis 713. Shaft 770 is threaded, and sleeve 775 is rotatably mounted on a worm gear that is, in turn mounted on the threads of shaft 770. As shaft 770 is rotated, sleeve 775 and the underlying worm gear travel back and forth along shaft 770 in the direction indicated by double-headed arrow e-e′. Connector 772 is hingedly mounted to sleeve 775 through ball joint 773 and to connector 791 through ball joint 774. Connector 791 is mounted onto spar 702 in such a way that spar 702 can rotate freely beneath connector 791. As sleeve 775 moves up and down shaft 770, it pulls connector 772 and connector 791 upwardly and downwardly, imparting a flap motion to spar 702 in the direction indicated by double-headed arrow E-E′. Second axis drive mechanism 721 includes motor 781, which rotates shaft 780 about axis 723. Shaft 780 is threaded, and sleeve 785 is rotatably mounted on a worm gear that is, in turn, mounted on the threads of shaft 780. As shaft 780 is rotated, sleeve 785 travels back and forth along shaft 780 in the direction indicated by double-headed arrow f-f′. Connector 782 is hingedly mounted to sleeve 785 through ball joint 783 and to connector 791 through ball joint 784. Connector 791 is mounted onto spar 702 in such a way that spar 702 can rotate freely beneath connector 791. As sleeve 785 moves back and forth along shaft 780, it pulls connector 782 and connector 791 back and forth, imparting a flap motion to spar 702 in the direction indicated by double-headed arrow F-F′.

[0067] FIG. 8 illustrates a wing-drive mechanism suitable for use with a source of mechanical power that operates in only one direction. Spar 802 connects a drive wing (not shown) with joint 804. Joint 804 is suitably a universal joint or other connection that transfers rotational movement from third axis drive mechanism 803 to spar 802 while permitting independent motion to be imparted by first axis drive mechanism 811 and second axis drive mechanism 821. Joint 804 is fixed in space in relation to the fuselage (not shown) through connections that are also not shown. Third axis drive mechanism 803 includes wheel 805, which has radial slot 806. Peg 807 extends from member 808 and into slot 806. Wheel 805 is coupled to a source of mechanical power (not shown) which, during operation, causes wheel 805 to rotate in the direction indicated by arrow j-j′. The rotation of wheel 806 causes member 808 to move in a up-and-down motion. Member 808 is toothed where it contacts worm gear leg 884, which is affixed to joint 804, in such a way that as member 808 moves up-and-down, it rotates worm gear leg 884. This rotation of worm gear leg 884 rotates joint 804 and causes spar 802 to rotate, thereby effecting changes in the pitch of the drive wing.

[0068] First axis drive mechanism 811 includes wheel 812. Wheel 812 includes radial slot 813. Frame 815 includes wheel peg slot 816. Wheel peg 814 is inserted into or through wheel peg slot 816 and radial slot 813. Frame 815 also includes spar slot 817, through which spar 802 is inserted. Wheel 812 is coupled to a source of mechanical power (not shown) which rotates wheel 812 in the direction indicated by arrow h-h′. The rotation of wheel 812 causes frame 815 to move up-and-down. This movement of frame 815 causes spar slot 817 to move up-and-down, and in turn causes spar 802 to rotate up-and-down about joint 804, as shown by double-headed arrow H-H′.

[0069] Second axis drive mechanism 821 includes wheel 822. Wheel 822 includes radial slot 823. Frame 825 includes wheel peg slot 826. Wheel peg 824 is inserted into or through wheel peg slot 826 and radial slot 823. Frame 825 also includes spar slot 827, through which spar 802 is inserted. Wheel 822 is coupled to a source of mechanical power (not shown) which rotates wheel 822 in the direction indicated by arrow i-i′. The rotation of wheel 822 causes frame 825 to move left-to-right. This movement of frame 825 causes spar slot 827 to move left-to-right, and in turn causes spar 802 to rotate left-and-right about joint 804, as shown by double-headed arrow I-I′.

[0070] The position of pegs 807, 814 and 824 may be varied along the respective lengths of slots 806, 813 and 826 to vary the amplitude of the motion applied to spar 802.

[0071] In the embodiment shown in FIG. 8, each axis drive mechanism may include or be coupled to its own source of mechanical power. Alternatively, a single power source of mechanical power, such as an internal combustion engine, may be used to power two or even three of the axis drive mechanisms. Movement input signals are delivered to the motors directly, or to intermediate clutch and/or gear systems (also not shown) in order to affect the desired movement of each axis drive mechanism.

[0072] A preferred means of controlling the wing-drive mechanism of this invention is through the automated specification of drive wing trajectories and resultant automated generation of the movement input signals. An automated trajectory specification system (ATSS) can be used to specify the drive wing trajectory. The ATSS preferably includes a fuzzy logic processor or neural network, and generation of movement input signals is preferably accomplished through automated application of a non-linear controlling function.

[0073] A schematic diagram of an exemplary fuzzy logic ATSS is shown in FIG. 4. In FIG. 4, a fuzzy logic ATSS 401 contains a fuzzy logic inference engine 404, a set of membership functions 402 coupled to the fuzzy logic inference engine 404, and a rules database 403 that is also coupled to fuzzy logic inference engine 404. As shown, inputs to the fuzzy logic ATSS include current data specifying the position of the vehicle in space and the rate of motion of the vehicle. This data is provided, in this embodiment, in the form of three inertial position vectors x, y and z, which identify the position of the vehicle relating to an external, inertial frame of reference, and three corresponding inertial velocity vectors dx/dt, dy/dt and dz/dt. Inputs specifying the orientation of the vehicle in space (Θ,Φ,Ψ) and the rate of change of the vehicle's orientation (dΘ/dt, dΦ/dt, dΨ/dt) are also provided to the fuzzy logic ATSS in the preferred embodiment illustrated. Acceleration data (i.e. d²x/dt², d²y/dt², d²x/dt², d²Θ/dt²d²Φ/dt²and/or d²Ψ/dt²) can also be inputted. When drive wing trajectories are specified by taking vehicle orientation into account, the further advantage of affecting a drive wing trajectory independent of the vehicle orientation can be achieved.

[0074] The actual positional, orientation, velocity and acceleration inputs are preferably sampled over an appropriately short time period by an appropriate sensing device, smoothed if necessary, and provided to the fuzzy logic ATSS in real time.

[0075] Fuzzy logic engine 404 “fuzzifies” the input values using membership functions 402 to create fuzzy inputs that relate actual position, velocity and/or acceleration and, optionally but preferably, orientation, rate of change in orientation and/or rate of change of rate of change in orientation with the corresponding desired values. Fuzzy logic engine 404 then applies rules database 403 through application of “if-then” rules to generate a fuzzy output that relates the desired vehicle movement to a desired drive wing trajectory, preferably a desired drive wing trajectory for each wing-drive mechanism on the vehicle. The fuzzy output is defuzzified to produce “sharp” outputs, i.e. a specific desired drive wing trajectory for each wing-drive mechanism. The sharp outputs can take any convenient form, but is most preferably a continuous signal or signals to controller 405 that, at any specific point in time, specifies a desired angular position, velocity and/or acceleration of the drive wing. The sharp outputs are delivered to controller 405, which in turn provides movement input signals to each of the three axis drive mechanisms for each drive wing. If there are more than one wing-drive mechanisms, controllers for the additional wing-drive mechanisms are also in communication with fuzzy logic ATSS 401 and receive a corresponding desired trajectory for that drive wing. It is preferred that the fuzzy logic ATSS generates desired drive wing trajectories in real time.

[0076] Accordingly, a suitable output from a fuzzy logic ATSS to the controller is a signal that at any time t_sprovides values corresponding to or convertible into a desired flap, pitch and yaw angle, angular velocity about the flap, yaw and pitch axes, and/or angular accelerations about each of those axes. These signals can be in analog or digital form. Referring to the specific drive wing trajectory illustrated in FIG. 3, a suitable output from a fuzzy logic ATSS at time t_sis a signal or signals corresponding to points 305, 306 and 307 and the values of the first and preferably also the second derivatives of curves 301, 302 and 303 at that time. These signals together designate, for any time t_s, the desired drive wing angular position, velocity and preferably acceleration. As shown in FIG. 3, these values are conveniently expressed in terms of Euler angles, but they can be easily converted to rotational angles about flap, yaw and pitch axes and transmitted to the controller in such form.

[0077] The development of membership functions 402 and the if-then rules database is conveniently based on empirically or modeled relationships between drive wing trajectories and vehicle motion that result from the aerodynamic and inertial forces created as a result of affecting each of such drive-wing trajectories. In this way, an if-then rules database is developed which correlates a desired change in vehicle position and/or motion to a drive wing trajectory and frequency (or in the case where there is more than one wing-drive mechanism, a set of drive wing trajectories and frequencies).

[0078] For purposes of developing automated control of the wing-drive mechanism of this invention, it is noted that in most if not all cases, drive wing trajectories such as represented in FIG. 3 can be approximated by a mathematical function. For example, each of curves 301, 302 and 303 in FIG. 3 can be approximated as periodic trigonometric function, i.e., as the sum of a series of sine and cosine functions. Such a periodic trigonometric function has the form

f (t) = a_{of} + \sum_{n = 1}^{N} [a_{nf} \cos (n ω t) + b_{nf} \sin (n ω t)]

[0079] for a suitable number of terms N. Generally, a better match of the function to an actual curve increases with increasing N. In the foregoing function f(t), the values of a_of, a_nfand b_nfand the frequency ω_fdetermine the graphical shape of the resulting function f(t), and f(t) itself represents φ(t) θ(t), and/or ψ(t) (to use the angular designations shown in FIG. 3). Accordingly, the specification and designation of a particular drive wing trajectory can be achieved by generating values for a_of, a_nf, b_nfand ω_ffor each f(t) (i.e., φ(t) θ(t), and ψ(t)) for each wing drive mechanism. Thus, a suitable way of developing membership functions and an if-then rule database is by relating desired vehicle movements (i.e., one or more of x, y, z, dx/dt, dy/dt, dz/dt, d²x/dt², d²y/dt², d²z/dt², Φ, Θ, Ψ, dΦ/dy, dΘ/dy, dΨ/dt, d²Φ/dt², d²Θ/dt²and d²Ψ/dt²) to specific drive wing trajectories by associating such movements with a set of values for a_of, a_nf, b_nfand ω_f. Once values for a_of, a_nf, b_nfand ω_fare specified for each axis drive mechanism of each wing drive mechanism, the ATSS calculates the values of desired drive wing positions ψ, θ, φ (expressed, for example, as Euler angles), desired drive wing angular velocities ψ′, θ′ and φ′ and optionally desired drive wing angular accelerations ψ″, θ″ and φ″ for each wing drive mechanism. At any time t_s, the ATSS generates signals that correspond to those values and transmits those signals to the controller. Those signals designate desired drive wing angular position, velocity and acceleration at any time t_s.

[0080] Beside Fourier methods, other mathematical methods of generating the wave functions, such as wavelet methods or Bessel methods, can alternatively be used. Note further that if the ATSS employs a neural network or other type of programming to specify desired wing trajectories, those programs may use inputs as discussed above with respect to the fuzzy logic processor, and may generate the same types of outputs.

[0081] In this preferred embodiment, the controller compares this desired drive wing position, velocity and optionally acceleration with actual drive wing position, velocity and optionally acceleration, calculates the torque needed to be applied by each of the first, second and third axis drive mechanisms, and delivers the appropriate movement input signals to each of the axis drive mechanisms. If the desired drive wing position, velocity and/or acceleration are specified in terms of Euler angles, conversion to rotation about each of the flap, yaw and pitch axes can be done by the fuzzy logic ATSS (or neural network or other ATSS) or the controller using pre-established relationships.

[0082] Thus, in the preferred embodiment, controller 405 receives signals from fuzzy logic ATSS 401 that specify desired drive wing angular position, velocity and/or acceleration as well as inputs that specify actual drive angular wing position, velocity and/or acceleration. (Note that in any instance where desired and actual inputs for a variable are provided to the controller or ATSS, these can be supplied in the form of the differences in these values.) Controller 405 then develops movement input signals for the first, second and third axis drive mechanisms in real time by applying a controlling function that calculates needed applied torques for all three axis drive mechanisms by comparing the actual and desired drive wing angular position, velocity and/or acceleration inputs (or the value of the difference between them). Most preferably, the movement input signals are generated continuously. At any point in time t_s, the movement input signals specify the torques to be applied at time t_sby each of the axis drive mechanisms. An example of a non-linear, Lyapunov-based controlling function for calculating a needed applied torque to affect a desired wing trajectory within prescribed error limits by comparing actual with desired angular velocities and accelerations as applied to moth wings is described by Smith and Zenieh, “Trajectory Control of Flapping Wings: Towards The Development of Flapping-Wing Technology”, 6^thAIAA/NASA/USAF Multidisciplinary Analysis and Optimization Symposium (1996).

[0083] Singular perturbation and/or H_∞methods of control can also be used to generate a controlling function for creating movement input signals in real time.

[0084] In the preferred method, movement input signals are generated by a controlling function that receives sampled actual orientations, angular velocities and/or angular accelerations of the drive wing about each of the flap and yaw axes, and the actual pitch, rate of change of pitch and/or acceleration of the pitch, and compares those variables to corresponding desired values. For each wing-drive mechanism, the preferred controller then applies a controlling function to the actual and desired drive wing angular position, velocity and/or acceleration data to calculate the torques that are to be applied. The controller generates corresponding first, second and third movement input signals and transmits them to the first, second and third axis drive mechanisms. Preferably, the controller receives drive wing angular position, velocity and/or inputs continuously (or over very short time intervals) and generates the movement input signals continuously (or over very short time intervals). Most preferably, the preferred controller calculates the needed torques using a Lyapunov-based controlling function. Suitable controlling functions for a particular drive wing design can be developed using methods similar to those described in Smith and Zenieh, cited above.

[0085] A preferred controller that develops the movement input signals therefore includes means for receiving sampled drive wing angular position, velocity and/or acceleration data, a means for calculating the torques to be applied to the drive wing by each of the first, second and third axis drive mechanisms to affect a desired drive wing trajectory, and means for generating and transmitting corresponding movement input signals for each of the axis drive mechanisms. In addition, a preferred controller includes or receives desired drive wing trajectory inputs, advantageously in the form of desired drive wing angular position, velocity and/or acceleration.

[0086] Drive wing angular position, velocity and acceleration data are advantageously obtained using a sensing device that directly monitors the drive wing itself (for example, an optical, laser, ultrasonic or similar system), or preferably by using one or more sensing devices that directly detect rotational movements of each of the axis drive mechanisms about their respective axes of rotation. Optical, laser or mechanical encoders, especially optical or laser shaft encoders, are preferred sensing devices. Referring to FIG. 1, optical and/or laser shaft encoders can be mounted on each of shafts 160 and 180 (as well as the corresponding shaft of axis drive mechanism 111) to monitor the angular rotation, angular velocity and/or angular acceleration of each shaft. The encoder then generates a corresponding signal and communicates the signal to the controller. The sensing device preferably provides drive wing angular position, velocity and/or acceleration data to the controller over a suitably short sampling period, and may smooth the data before providing it to the controller. The wing movement input signals to the controller can be of any suitable form, but are preferably electrical, electromagnetic or ultrasonic signals, most preferably an electrical signal. The signal may be in analog or digital form. Suitable apparatus for transmitting the signals to the controller include physical connections from the sensing device to the controller, such as wiring or fiber optic connections, or transmission apparatus such as light, laser, radio or ultrasonic transmitters, and the like. The controller includes a corresponding means for receiving the signal, such as a suitable receiver for light, laser, radio or ultrasonic signals.

[0087] The preferred controller also contains a computer that calculates needed applied torques for each axis drive mechanism and generates corresponding movement input signals. The computer can be of any type that can perform the needed calculations quickly enough to affect the desired drive wing trajectory and frequency. One or more microprocessors having a topologically embedded program for receiving drive wing motion input signals and calculating the required torque for each axis drive mechanism using the aforementioned controlling functions is suitable. Alternatively, a general-purpose computer programmed in a similar way, or a programmable microprocessor, again similarly programmed, is suitable.

[0088] It is noted that although the ATSS and the controller have been discussed above as separate devices, it is possible and even desirable that both functions be integrated into a single device. For example, a fuzzy logic or neural network processor is suitably programmed onto a general-purpose computer, a programmable microprocessor or topologically embedded on a microprocessor. The controller can be programmed into or embedded on the same processor or computer if desired. However, the functions can reside on separate computers.

[0089] The preferred controller just described creates signals corresponding to the necessary torque sequences for each axis drive mechanism. These signals are transmitted to the first, second and third axis drive mechanisms, respectively, in any convenient form. The signals can be in digital or analog form. However, a preferred signal form is an analog of the desired torque pattern, preferably an analog electrical signal or an analog electromagnetic signal such as a light, laser sonic or radio signal. The controller and the axis drive mechanisms include communication means adapted to the form of the signal. Such means include electrical wiring, fiber optic connections, and/or appropriate light, laser, sonic or radio transmitters and receivers.

[0090] More preferably, the controller is in electrical communication with each drive mechanism, and the movement input signals are or are convertible to analog electrical signals. Most preferably, these analog electrical signals are amplified if necessary and used as the electrical power supply for electric or hybrid motors that supply mechanical power to the axis drive mechanisms, with the pattern of the amplified signal corresponding to the desired pattern of torque to be applied by the corresponding axis drive mechanism over the course of a beat cycle. In this most preferred embodiment, the first, second and third movement input signals double as or are amplified to form the power supplies for the respective axis drive mechanisms.

[0091] Alternatively, the movement input signal can be amplified if necessary and used to affect the operation of clutches or other devices that couple the source of mechanical power to the drive wing to control the applied torque in a corresponding manner. In all cases, the movement input signals can be repeated as often as desired to create continuous beating over a predetermined drive wing trajectory.

[0092] To develop a simplified controller, sets of coordinated movement input signals for each of the first, second and third axis drive mechanisms are developed for a number of specific wing trajectories. The signals are then recorded onto a suitable recording medium or stored in an electronic database. Alternatively, the signals can be expressed as mathematical functions, and the mathematical functions programmed into a computer or programmable processor or topologically embedded onto a microprocessor. To affect drive wing movement in a desired trajectory, the controller is instructed to select a specific set of movement input signals or functions, generate a corresponding set of movement input signals, and transmit the signals to the axis drive mechanisms.

[0093] Thus, in one aspect, the wing-drive mechanism of this invention receives movement input signals from a controller that can generate two or more preselected sets of coordinated movement input signals that each include a first, second and third movement input signal for the first, second and third axis drive mechanisms, respectively. The preselected sets of coordinated movement input signals, or corresponding mathematical functions, can be recorded in any suitable form. For example, they can be recorded in a portable medium such as magnetic recording tape or a compact disk, digitally stored in an electronic memory means or be embedded in a program residing in a memory device or topologically embedded on a microprocessor. The controller therefore advantageously accesses said sets of movement input signals or corresponding mathematical functions, selects among such recorded movement input signals in response to a command, and generates and transmits said movement input signals to the corresponding drive mechanisms. Depending on the form in which the sets of movement input signals are recorded, suitable controllers include, for example, simple apparatus such as an ordinary tape player, an ordinary compact disk player, or a computer (programmed general purpose computer, programmed programmable microprocessor or microprocessor) that is programmed to select among pre-programmed or pre-recorded sets of movement input signals or corresponding mathematical functions when instructed and transmit the corresponding movement input signals to the first, second and third axis drive mechanisms.

[0094] To use a simplified controller as just described, a desired drive wing trajectory is selected, appropriate instruction is provided to the controller, and in response the controller generates a set of first, second and third movement input signals for the corresponding axis drive mechanisms to affect that drive wing trajectory. It is noted that a simplified controller of this type can be used in conjunction with a variety of means for specifying drive wing trajectories. Because the movement input signals are developed beforehand, all that is necessary to specify a particular drive wing trajectory is to provide a signal to the controller instructing it to generate one particular set of movement input signals or another. Thus, the simplified controller of this type is easily adapted to manual control through common devices such as a simple joystick, computer keyboard, radio controller, or the like, which can be configured to send two or more distinct signals to the controller, each of which constitutes an instruction to the controller to create a specific set of movement input signals. The simplified controller can also be used with an ATSS. Such preferred ATSS include a fuzzy logic or neural network ATSS as described above with the difference that the signal generated by the fuzzy logic or neural network ATSS is a simple instruction to generate a specific set of pre-developed movement input signals.

[0095] The controller and ATSS can be situated on the vehicle or be remotely located. Both the controller and ATSS can be remote systems, in which case the movement input signals for each drive mechanism are transmitted to the individual axis drive mechanisms on the vehicle. However, it is preferred that at least the controller be located on the vehicle, in order to simplify the signals that must be transmitted to the vehicle from a remote location.

[0096] Actual vehicle position, velocity, acceleration, orientation, rate of change of orientation and rate of change of rate of change of orientation data can be supplied to an ATSS in several ways. Systems for sampling and supplying this data may be located on the vehicle or remotely. A suitable system for developing orientational inputs (orientation, rate of change in orientation and/or rate of change of rate of change of orientation) is an on-board gravitational stabilization/inertial sensor. Such sensors are commercially available, and can also be used to develop inputs relating to the vehicle position, velocity and/or acceleration. Alternatively, one or more gyroscopes can be used to develop orientational and/or vehicle position, velocity and acceleration inputs, and on-board inertial navigation systems can provide inputs as to vehicle position, velocity and acceleration. Position, velocity and acceleration inputs can also be developed by suitable means for accessing the Global Positioning System or other external positioning system. On-board radar, sonar, visual or other systems can also be used to develop positional and or orientational inputs. Of course, any of these methods for developing the inputs can be external to the vehicle.

[0097] Similarly, desired vehicle position, velocity, acceleration, orientation, rate of change of orientation and rate of change of rate of change of orientation data can be supplied to the ATSS in many ways. These include, for example, radio controllers, joysticks. Keyboards, inputs from position and/or orientation sensing devices, and the like are all suitable. Any of those devices may be in direct connection with the ATSS, such as through an electrical connection or fiber optic cable, or may communicate with the ATSS through any remote device.

[0098] FIG. 6 illustrates a way in which the wing-drive mechanism of this invention can be used to drive a flying vehicle. In the embodiment shown, four wing-drive mechanisms 601, 602, 603 and 604 are used, in opposing pairs of two. A vehicle preferably will have at least two wing-drive mechanisms according to the invention, which are advantageously provided as one or more pairs symmetrically situated on opposing sides of a plane bisecting the fuselage. Embodiments having from one to four or more pairs of wing-drive mechanisms can be made. Of particular interest is a vehicle having at least two pairs of wing drive mechanisms, arranged similarly to the configuration of dragonfly wings, as shown in FIG. 6. By coordinated operation of the pairs of drive wings, unwanted movement of the fuselage 600 in response to movement of the drive wings 610, 611, 612 and 613 or any other disturbance can be minimized. In addition, kinematic studies of pairs of drive wings operating in tandem suggest that improved efficiencies can be achieved in such a manner. See, e.g., Tuncer & Platzer, “Thrust generation due to airfoil flapping”, AIAA Journal, vol. 34, No. 2, pp. 324-331 (1966).

[0099] Alternatively, a vehicle may have only a single wing-drive mechanism. For example, a single wing-drive mechanism might be employed as a rudder, aileron or elevator system on an otherwise conventional fixed-wing or rotary wing aircraft. In such cases, the wing-drive mechanism can function to provide thrust, stability and/or steering. A single wing-drive mechanism would ordinarily be used in conjunction with other flying technologies, such as a fixed wing or rotary wing, in order to develop lift, additional thrust and/or control.

[0100] The movements of multiple wing-drive mechanisms are desirably coordinated in order to impart a desired motion to the vehicle as a whole. Accordingly, when more than one wing-drive mechanism is present, the trajectory of each drive wing is specified in concert with the trajectory of at least one other drive wing in order to achieve a desired overall vehicle motion. Preferably, any ATSS simultaneously specifies trajectories for at least two drive wings, and more preferably for all drive wings on the vehicle. As discussed before, specification of drive wing trajectories and generation of movement input signals can be generated in real time using the preferred ATSS and non-linear-based controlling functions described before. In this case, the ATSS advantageously specifies trajectories for at least two drive wings, preferably all drive wings, simultaneously in real time, and each drive wing preferably has a separate controller that calculates and generates movement input signals in real time. Of course, simplified controllers as discussed before, that generate previously developed movement input signals upon appropriate instruction, can also be used in multiple drive wing vehicles.

[0101] When more than one wing-drive mechanism of the invention is used, the trajectory of each individual drive wing can be related or unrelated to the trajectory of the other drive wing(s). For example, the trajectory of one member of an opposing pair of drive wings may be specified as the mirror image of that of the other member. In such a case, the same sequences of movement input signals may be transmitted to the axis drive mechanisms of each drive wing, and it is even possible that the pair members use shared axis drive mechanisms and/or a shared controller.

[0102] However, it is preferred the trajectory of each drive wing can be specified independently of the trajectory of at least one other drive wing, i.e. the trajectory of each wing can be arbitrarily specified in relation to the trajectory of at least one other drive wing. By proper specification of different trajectories for two or more drive wings, maneuvers such as sideways flight, rotation about a stationary vertical axis or other complex maneuvers can be achieved. Thus, in preferred embodiments, the trajectories of each drive wing are specified independently of each other, and most preferably, each wing-drive mechanism operates in response to a separate controller that provides movement input signals having an arbitrary relationship to movement input signals provided to the axis drive mechanisms of any other wing-drive mechanism.

[0103] In addition to the controller and ATSS, various monitoring and feedback systems can be added to enhance the performance of the wing-drive mechanism. For example, the in put to the axis drive mechanisms can be monitored to determine whether the torques actually delivered by the axis drive mechanisms are as specified. Corresponding signals can then be fed back into the controller or ATSS to effectuate modifications of the movement input signals or to specify an alternative drive wing trajectory. Similarly, the actual versus expected motion of the vehicle can be monitored in various ways to create inputs back into the controller(s) and/or ATSS to effectuate appropriate modifications in drive wing trajectory or movement input signals. Alternatively, these inputs can be fed into a separate trim module that can specify adjustments to the specified drive wing trajectories.

[0104] The wing-drive mechanism of this invention can be used in conjunction with other navigational or flight-control system such as fixed wings, rotary wings, tails, rudders, stabilizers, rotors, jet or propeller engines, airfoils, and the like. Similarly, the wing-drive mechanism may be modified as needed or desired for particular applications. For example, the wing-drive mechanism may be made such that the drive wing can be fixed in a certain position from time to time in order, for example, to permit the vehicle to glide or perform other specialized maneuvers.

[0105] In addition, the drive wing mechanism may be used to operate wings that extend from other wings (which, in turn, may extend from yet other wings). Such extended wings may serve as “elbows” or “wrists”, and can also be used for mass balancing the vehicle.

[0106] It will be appreciated that many modifications can be made to the wing-drive mechanism as described herein without departing from the spirit of the invention, the scope of which is defined by the appended claims. For example, redundant systems may be employed as a hedge against failure of a particular component.

[0107] A flying vehicle according to this invention can be used, for example, as a surveillance vehicle, and inspection vehicle, a search-an-rescue vehicle or as a cargo or passenger vehicle, or even as a toy, depending on the particular size and design. A flying vehicle according to the invention can be made on a very small scale (wingspan of six inches or less, an intermediate scale (wingspan from six inches to 12 feet, or a large scale (wingspan greater than 12 feet). It can be manned or unmanned (i.e., a drone). A watercraft employing the wing-drive mechanism of this invention can, with suitable insulation, by used as a submersible or surface vessel. Similarly, a spacecraft or satellite can be used for exploration, telecommunications, surveillance and the like.

Claims

What is claimed is:

1. A wing-drive mechanism for a vehicle having a fuselage, comprising

a) a drive wing having an adjustable pitch relative to said fuselage and being moveable relative to said fuselage about yaw and flap axes;

b) a first axis drive mechanism for moving said drive wing about said flap axis in response to a first movement input signal,

c) a second axis drive mechanism for moving said drive wing about said yaw axis in response to a second movement input signal, wherein said second axis drive mechanism operates independently of said first axis drive mechanism and

d) a third axis drive mechanism for adjusting the pitch of said drive wing in response to a third movement input signal, wherein said third axis drive mechanism operates independently of said first and second axis drive mechanisms.

2. The wing-drive mechanism of claim 1, wherein said first, second and third movement input signals are electrical, sonic or electromagnetic signals, and said first, second and third axis drive mechanisms each comprise a means for receiving said first, second and third movement input signals, respectively, and applying torque to said drive wing in response to said first, second and third input signals.

3. The wing-drive mechanism of claim 2, wherein each of the first, second and third axis drive mechanisms include or are coupled to an electrical motor that supplies mechanical power to its respective axis drive mechanism, and said first, second and third movement input signals constitute or is amplified to form the electrical power supplies for the electrical motors included in or coupled to the first, second and third axis drive mechanisms, respectively.

4. The wing-drive mechanism of claim 1, wherein said drive wing is affixed to a spar that is coupled to said third axis drive mechanism through a joint such that torque generated by said third axis drive mechanism is transferred to said spar through said joint to affect changes in pitch of said drive wing, said joint being such that said spar is capable of independent movement about yaw and flap axes.

5. The wing-drive mechanism of claim 4, wherein said spar is inserted through a slot of a first slotted arc in said first axis drive mechanism, said first slotted arc being rotatable about said flap axis, such that rotation of said first slotted arc about said flap axis imparts a flap motion to said drive wing.

6. The wing-drive mechanism of claim 5, wherein said spar is inserted through a slot of a second slotted arc in said second axis drive mechanism, said second slotted arc being rotatable about said yaw axis, such that rotation of said second slotted arc about said yaw axis imparts a yaw motion to said drive wing.

7. The wing-drive mechanism of claim 2, wherein said first, second and third movement input signals are generated by a controller that calculates said first, second and third movement input signals in real time using a non-linear controlling function that relates a desired drive wing trajectory to torques to be applied by each of said first, second and third axis drive mechanisms, and said first, second and third axis drive mechanisms are in electrical, sonic or electromagnetic communication with said controller.

8. The wing-drive mechanism of claim 7, wherein said desired drive wing trajectory is generated by an automated trajectory specification system that generates said desired drive wing trajectory by comparing inputted actual and desired data that is selected from the group consisting of vehicle position, velocity, acceleration, orientation, rate of change of orientation, rate of change of rate of change of orientation and combinations of two or more thereof.

9. The wing-drive mechanism of claim 8, wherein said automated trajectory specification system includes a fuzzy logic processor or a neural network.

10. A method of controlling a wing-drive mechanism for a vehicle having a fuselage, the wing drive mechanism including a drive wing having an adjustable pitch relative to said fuselage and which is moveable relative to said fuselage about yaw and flap axes; a first axis drive mechanism for moving said drive wing about said flap axis in response to a first movement input signal; a second axis drive mechanism for moving said drive wing about said yaw axis in response to a second movement input signal, wherein said second axis drive mechanism operates independently of said first axis drive mechanism, and a third axis drive mechanism for adjusting the pitch of said drive wing in response to a third movement input signal, wherein said third axis drive mechanism operates independently of said first and second axis drive mechanisms, said method comprising

a) inputting a desired drive wing trajectory into a controller including a computer that is programmed to calculate said first, second and third movement input signals using a non-linear controlling function that relates desired drive wing trajectory to torques to be applied by each of said first, second and third axis drive mechanisms,

b) using said controller, generating said first, second and third movement signals in real time, and

c) transmitting said first, second and third movement signals to said first, second and third axis drive mechanisms, respectively, whereby said first, second and third axis drive mechanisms affect movement of the drive wing in the desired trajectory in response to said first, second and third input signals.

11. The method of claim 10, wherein said desired drive wing trajectory is specified in real time by an automated trajectory specification system that generates said desired drive wing trajectory by comparing inputted actual and desired date that is selected from the group consisting of vehicle position, velocity, acceleration, orientation, rate of change of orientation, rate of change of rate of change of orientation, and combinations of two or more thereof.

12. The method of claim 11, wherein said automated trajectory specification system includes a fuzzy logic processor.

13. The method of claim 11, wherein said automated trajectory specification system includes a neural network.

14. The method of claim 11, wherein said automated trajectory specification system generates said desired drive wing trajectory by comparing inputted actual and desired data that is selected from the group consisting of vehicle position, velocity, acceleration, orientation, rate of change of orientation, rate of change of rate of change of orientation, and combinations of two or more thereof.

15. The method of claim 11, wherein said vehicle has at least two wing-drive mechanisms, and said automated trajectory specification system simultaneously generates desired drive wing trajectories for at least two drive-wings on said vehicle.

16. A method of controlling the wing-drive mechanism of claim 1, said method comprising

a) developing two or more sets of coordinated movement input signals, each such set corresponding to a specific drive wing trajectory and including first, second and third movement input signals;

b) recording each set of coordinated first, second and third movement input signals;

c) inputting a desired drive wing trajectory into a controller that is adapted to access said recorded coordinated sets of movement input signals and generate a set of first, second and third movement input signals that correspond to the desired drive wing trajectory and

d) using said controller, generating and transmitting a set of first, second and third movement input signals corresponding to said desired drive wing trajectory to said first, second and third axis drive mechanisms, respectively.

17. A vehicle that derives motion from at least one wing-drive mechanism attached to a fuselage, said vehicle comprising

a) a fuselage;

b) a drive wing having an adjustable pitch relative to said fuselage and being moveable relative to said fuselage about yaw and flap axes;

c) a first axis drive mechanism for moving said drive wing about said flap axis in response to a first movement input signal;

d) a second axis drive mechanism for moving said drive wing about said yaw axis in response to a second movement input signal, wherein said second axis drive mechanism operates independently of said first axis drive mechanism; and

e) a third axis drive mechanism for adjusting the pitch of said drive wing in response to a third movement input signal, wherein said third axis drive mechanism operates independently of said first and second axis drive mechanisms.

18. The vehicle of claim 17 that has at least two of said wing-drive mechanisms in opposing positions relating to the fuselage.

19. The vehicle of claim 18, wherein the first, second and third movement input signals for each wing-drive are generated by separate controllers that generate said first, second and third input signals for the respective wing-drive mechanisms in response to an inputted desired drive wing trajectory, and a controller for at least one wing-drive mechanism can generate movement input signals for its corresponding drive wing that have an arbitrary relationship to movement input signals generated by a controller for at least one other drive wing.

20. The vehicle of claim 19 wherein said desired drive wing trajectories for each drive wing are generated by an automated trajectory specification system that generates said desired drive wing trajectories by comparison of inputted actual and desired data that is selected from the group consisting of vehicle position, velocity, acceleration, orientation, rate of change of orientation, rate of change of rate of change of orientation, and combinations of two or more thereof.

Patent Citations (9)

Patent	Date	Inventor	Cited By
US1355111	1920-10-01	Simons	Examiner
US1752100	1930-03-01	Meindersma	Examiner
US4139171	1979-02-01	Harris	Applicant
US4718877	1988-01-01	Girsch et al.	Applicant
US4729748	1988-03-01	Van Ruymbeke	Applicant
US4749149	1988-06-01	Gruich	Applicant
US4793573	1988-12-01	Kelfer	Applicant
US5163861	1992-11-01	Van Ruymbeke	Applicant
US5899408	1999-05-01	Bowers, Jr.	Applicant

Non-Patent Literature (17)

Michael J. C. Smith, “Simulating Flapping Insect Wings . . . ”, Ph.D. Thesis, Purdue University, May 25, 1995.Applicant
Michael J. C. Smith, “Reinstating Inquiry into Mechanized Flapping-Wing Flight . . . ”, AIAA 97-0533, 35th Aerospace Sciences Meeting and Exhibit, Jan. 6-10, 1997.Applicant
Smith et al., “The Advantages of an Unsteady Panel Method in Modelling . . . ”, J. Experimental Biology 199, 1073-1083 (1996).Applicant
Michael J. C. Smith, “Simulating Moth Wing Aerodynamics: Towards the Develoment of Flapping-Wing Technology”, AIAA Journal 34:1348-1355 (1996).Applicant
DeLaurier and Harris, “A Study of Mechanical Flapping-Wing Flight”, Aeronautical Journal, Oct. 1993.Applicant
Hargrave's Flying Machine, The American Engineer, May 1893, pp. 233-234.Applicant
Michael J. C. Smith, “Trajectory Control of Flapping Wings: . . . ”, 6th AIAA/NASA/USAF Multidisciplinary Analysis and Optimization Symposium, Sep. 4-6, 1996.Applicant
“Spencer's Ornithopter”, Model Airplane News, Feb. 1999, pp. 40-43, 45.Applicant
Hollingum, “Military to look to flying insect robots”, Industrial Robot, 25:123-128 (1998).Applicant
Michelson, “Update on Flapping Wing Micro Air Vehicle Research”, 13th Bristol International RPV Conference, Mar. 30 - Apr. 1, 1998.Applicant
“Tiny Drones May Be Soldier's New Tool”, Aviation Week & Space Technology, Jun. 8, 1998, pp. 42-48.Applicant
“Honey, I Shrunk the Plane”, Machine Design, Oct. 8, 1998, pp. 353-348.Applicant
“Several Micro Air Vehicles In Flight Test Programs”, Aviation Week & Space Technology, Jul. 12, 1999, pp. 47-48.Applicant
“Quetzalcoatl”, Model Aviation, Aug. 1986, pp. 84-90, 158.Applicant
“Microplanes”, Popular Science, Jan. 1998, pp. 54-59.Applicant
Michael J. C. Smith, “Leading Edge Effects on Moth Wing Aerodynamics, . . . ”, 14th AIAA Applied Aerodynamics Conference, Jun. 17-20, 1996.Applicant
“Learning From the Birds and Bees”, I. D. Magazine, Nov. 1998, pp.66-69.Applicant

Abstract