Apparatus and methods for variable sweep body conformal wing with application to projectiles, missiles, and unmanned air vehicles

• US 6,923,404 B1
• Filed: 01/10/2003
• Issued: 08/02/2005
• Est. Priority Date: 01/10/2003
• Status: Expired due to Fees

• Current Assignee: Zona Technology, Inc.
• Original Assignee: Zona Technology, Inc.
• Inventors: Chen, Ping-Chih, Sarhaddi, Darius, Liu, Danny D.
• Primary Examiner(s): Carone, Michael J.
• Assistant Examiner(s): Holzen, Stephen
• Application Number:
  US10/339,908
• Time in Patent Office: 935 Days
• Field of Search: 244/46, 244/7.R, 244/7.A, 244/8, 244/14, 244/16, 244/45.R, 244/123, 244/124, 244/3.1, 244/3.24, 244/3.13, 244/3.26, 124 70- 77, 102/382, 102/384, 102/385, 102/501, 102/503
• US Class Current: 244/46
• CPC Class Codes: B64C 3/40 Varying angle of sweep
• CPC Class Codes: B64C 3/56 Folding or collapsing to reduce overall dimensions of aircraft
• CPC Class Codes: B64C 30/00 Supersonic type aircraft
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64C 39/028 Micro-sized aircraft
• CPC Class Codes: B64C 39/08 having multiple wings
• CPC Class Codes: B64C 5/12 for retraction against or within fuselage or nacelle
• CPC Class Codes: B64F 1/04 for launching aircraft
• CPC Class Codes: B64U 2101/15 for conventional or electronic warfare
• CPC Class Codes: B64U 2101/19 for use as targets or decoys
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2101/35 for science, e.g. meteorology
• CPC Class Codes: B64U 2201/10 autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS]
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/12 Variable or detachable wings, e.g. wings with adjustable sweep
• CPC Class Codes: B64U 30/40 Empennages, e.g. V-tails foldable or collapsible UAVs B64U20/50
• CPC Class Codes: B64U 50/11 using internal combustion piston engines
• CPC Class Codes: B64U 50/12 using turbine engines, e.g. turbojets or turbofans
• CPC Class Codes: B64U 50/13 using external fans or propellers
• CPC Class Codes: B64U 50/15 using combustion exhausts other than turbojets or turbofans, e.g. using rockets, ramjets, scramjets or pulse-reactors
• CPC Class Codes: B64U 50/19 : using electrically powered motors
• CPC Class Codes: B64U 70/50 : Launching from storage containers, e.g. from submarine missile tubes
• CPC Class Codes: B64U 70/70 : Launching or landing using catapults, tracks or rails launching from storage containers B64U70/50
• CPC Class Codes: F42B 10/14 : using fins spread or deployed after launch, e.g. after leaving the barrel
• CPC Class Codes: F42B 10/64 : of fins
• CPC Class Codes: Y02T 50/10 : Drag reduction

Abstract

An unmanned air vehicle (“UAV”) apparatus is configured to have a body and a body-conformal wing. The body-conformal wing is configured to variably sweep from a closed position to a fully deployed position. In the closed position, the body-conformal wing span is aligned with the body axis and in the fully deployed position the body-conformal wing span is perpendicular to the axial direction of the body. Delivery of the UAV comprises the steps of: positioning the span of a body conformal wing in alignment with the axis of the body of the UAV; initiating the flight of the UAV; and adjusting the sweep angle of the body-conformal wing as a function of the current speed, altitude, or attack angle of the UAV, with the adjustment starting at a 0 degree position and varying between a closed position and a fully deployed position. The UAV also has a control mechanism configured to variably adjust the sweep of the body-conformal wing to achieve a high lift over drag ratio through out the flight path of the UAV.

Claims

1. An unmanned air vehicle (“

UAV”

) for delivery of a payload and for extended range operation comprising,

a body,

a body-conformal wing, wherein said body-conformal wing is configured to form the outer surface of said UAV body when it is an an un-deployed position, thereby having a seamless outer-mold-line conformal to the UAV body,

the body conformal wing is of elliptical or quasi-elliptic platform shape and its airfoil designs are to satisfy the low drag and large lift to drag ratio requirement for optimal aerodynamic performance and to satisfy containment requirements under high-G conditions during a gun launch,

further comprising in its un-deployed condition, an outer-mold-line completely compliant with that of an axi-symmetric body or a body of revolution, allowing it to be gun launched, tube launched or aircraft launched,

a control pivot mechanism to actuate the wing to perform variable wing sweep and wing-incidence according to a pre-set schedule in order to achieve optimal flight performance throughout the trajectory,

control surfaces for stability and for flight control,

said control surfaces comprise a set of fins, for pitch-yaw control, said wing for roll control, canards for pitch-yaw control, wherein said fins are necessary for de-spinning and stabilizing,

ascending and descending trajectories throughout a plurality of flight phases, wherein the UAV is in a ballistic trajectory phrase when in its ascending phase and a gliding trajectory phase in its descending phase,

wherein said fins and a boat-tail are deployed in the ballistic phase,

wherein said fins, said wing, a wing extension and canards are deployed during the gliding phase.

2. The unmanned air vehicle as claimed in claim 1, wherein said control mechanism is configured to adjust the wing-sweep angle and the angle-of-attack (incidence) of said body-conformal wing in order for the UAV to achieve optimal aerodynamic performance and maximum lift to drag ratio at all flight conditions throughout the trajectory.

3. The unmanned air vehicle as claimed in claim 2, further comprising a controller capable of a guided munitions, loitering and reconnaisance missions.

4. The unmanned air vehicle as claimed in claim 1, wherein said UAV is configured to be controlled by said wing for roll control and at least one of said fin(s) and canard(s) for pitch and yaw control.

5. The unmanned air vehicle as claimed in claim 1, wherein the control mechanism is configured to variably adjust the wing sweep in conjunction of the wing incidence of the body-conformal wing according to a general sweep and angle of attack schedule, which has been obtained either by computational means or through wind-tunnel measured data, stored in a computer memory, to achieve optimal lift to drag ratios throughout the flight.

6. The unmanned air vehicle as claimed in claim 1, wherein said UAV further comprises a propulsion device in order to enhance the extended range of the UAV, said propulsion device is one of a rocket-motor, turbo-propulsion or propeller propulsion.

7. The unmanned air vehicle as claimed in claim 1, wherein said UAV is capable of being gun-launched or tube-launched from underwater or from in air or from one of a aircraft or rotorcraft from the air.

8. The unmanned air vehicle as claimed in claim 7, wherein said UAV by gun launch has a robust structure and component design, capable of sustaining gravitational accelerations between the range of 7,000-G to 16,000-G.

9. The unmanned air vehicle as claimed in claim 8, wherein said UAV body diameter is between 5 and 16 inches.

10. The unmanned air vehicle as claimed in claim 1, wherein the controlled pivot mechanism will first raise the wing to a higher elevation above the outer mode-line of the body, then actuate to perform the wing-sweep and wing-incidence adjustments according to the sweep-incidence scheduling.

11. The unmanned air vehicle as claimed in claim 10, wherein said controlled pivot mechanism at the attachment point is actuated to be movable in the fore/aft direction in order to trim and maintain stability of the UAV under various flight conditions.

12. The unmanned air vehicle as claimed in claim 1 wherein said UAV further comprises tail fins and wherein said tail fins are deployable and embedded within the body in an un-deployed configuration, wherein they are deployed immediately after launch and wherein said fins are body conformal.

13. The unmanned air vehicle as claimed in claim 1 wherein said body-conformal wing further comprise a telescopically extendable wing portion, said portion increases the wing span thereby reducing the induced drag, enhancing the lift to drag ratio and extending the UAV'"'"'s range.

14. The unmanned air vehicle as claimed in claim 1 wherein the UAV is capable of being used as a reusable launch munition, as well as during loitering and reconnaissance missions, further comprising a propeller during subsonic flight, wherein the second wing planform is identical to the first wing.

15. The unmanned air vehicle as claimed in claim 14, further comprising a second body-conformal wing wherein said first and second body conformal wings are attached to opposite sides of the UAV, and are to be deployed in a biplane configuration for low subsonic cruising, wherein the second wing is to have a different airfoil section from the single wing on top.

16. A method for delivering the UAV of claim 15 comprising

deploying said fins, to de-spin the UAV body and achieve UAV stability,

blowing-out said boat-tail in order to reduce base drag,

swinging out the wing after UAV reaches an apogee,

optionally deploying canards,

gliding said UAV after the UAV reaches its apogee to a pre-set wing seep-wing incidence schedule,

optionally extending the first wing for an extended range operation

wherein said second wing enhances the aerodynamic performance in the cruise phase, and has two release plans,

the first of said release plan releases the second wing after a point of loitering, wherein the second wing swings out while the single wing is already in a fully extended position,

the second of said release plan releases the second wing during the subsonic descending phase, wherein both wings swing out symmetrically to form an X-configuration, which rapidly transitions to a final biplane configuration.

17. The unmanned air vehicle as claimed in claim 1, wherein said second wing enhances the aerodynamic performance in the cruise phase, and has two release plans,

the first of said release plan releases the second wing after a point of loitering, wherein the second wing swings out while the single wing is already in a fully extended position,

the second of said release plan releases the second wing during the subsonic descending phase, wherein both wings swing out symmetrically to form an X-configuration, which rapidly transitions to a final biplane configuration.

18. A method for delivering the UAV of claim 1 comprises,

deploying said fins, to de-spin the UAV body and achieve UAV stability,

blowing-out said boat-tail in order to reduce base drag,

swinging out the wing after UAV reaches an apogee,

optionally deploying canards,

gliding said UAV after the UAV reaches its apogee to a pre-set wing seep-wing incidence schedule,

optionally extending the wing for an extended range operation.

19. The method of claim 18 further comprising the step using at least one control surface for terminal homing.

20. The method of claim 18, wherein the UAV'"'"'s flight is initiated by firing said UAV from a gun.

21. The method of claim 18, further comprising initiating UAV flight by launching said UAV as a rocket.

22. The method of claim 18 further comprising the step of extending the body-conformal wing with a telescope extension.

23. The method of claim 18 further comprising the step of remote piloting the UAV.

24. The method of claim 18 wherein the UAV is controlled as a Guided Munitions Projectile.

25. The method of claim 18, wherein the UAV flight is initiated by an underwater tube launch.

26. The unmanned air vehicle as claimed in claim 1 or in claim 7, wherein a second wing enhances the aerodynamic performance in the single-wing supersonic cruise phase, and has two release plans,

the first of said release plan release the second wing after a point of single-wing cruising, wherein the second wing swings out while the single wing is already in its oblique design position for supersonic cruise,

the second of said release plan releases the second wing during the supersonic cruising phase, wherein both the wings swing out symmetrically to form an X-configuration, whose swing-out angle is confined within the Mach cone in order to achieve minimum save drag and sonic-boom signature.

27. An unmanned air vehicle (UAV) delivery system comprising

a body,

a body conformal wing, wherein said body conformal wing is configured to variably sweep from a closed position to a deployed position, wherein said body-conformal wing has a span which is aligned with the longitudinal axis of said body in said closed position,

wherein the body-conformal wing is configured to pivot about an attachment point on said body and a pivot point on said body-conformal wing,

wherein said attachment point is configured to be moveable in the for and aft directions,

a control mechanism configured to variable adjust the sweep of said body conformal wing,

an UAV acceleration device.

28. The unmanned air vehicle as claimed in claim 27, wherein the UAV delivery system further comprises a control system for remote communications.

29. The unmanned air vehicle as claimed in claim 27, wherein the control systems comprise one of a PZT (piezoelectric controls), MEMS (micro electric mechanical control), synthetic jets, or winglets (Flaperon) for roll control.