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An unmanned air vehicle includes a singular rear landing gear wheel on the aft end of the fuselage. Port and starboard wings with rear facing propellers are retractable to the aft of the fuselage. Upon retraction, the propellers may freewheel and a reversible motor-generator is provided to convert t

An unmanned air vehicle includes a singular rear landing gear wheel on the aft end of the fuselage. Port and starboard wings with rear facing propellers are retractable to the aft of the fuselage. Upon retraction, the propellers may freewheel and a reversible motor-generator is provided to convert the freewheeling propeller energy into electric power. Photovoltaic cells also provide electric power to the unmanned air vehicle. Port and starboard nose fairings are control surfaces for the vehicle. The port and starboard nose fairings also include landing gear wheels. A method of flying an unmanned air vehicle includes retracting port and starboard wings to achieve a ballistic dive.

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1. An unmanned aerial vehicle comprising: a fuselage defining a forward portion, an aft portion, a port side and a starboard side; a port and a starboard nose fairings being pivotably attached to the forward portion of the fuselage; a port retractable wing interconnected to the port side of

1. An unmanned aerial vehicle comprising: a fuselage defining a forward portion, an aft portion, a port side and a starboard side; a port and a starboard nose fairings being pivotably attached to the forward portion of the fuselage; a port retractable wing interconnected to the port side of the fuselage and retractable along the port side and aft portion of the fuselage; a starboard retractable wing interconnected to the starboard side of the fuselage and retractable along the starboard side and aft portion of the fuselage; at least one propeller motor and propeller interconnected to the fuselage; a movable mass interconnected to the fuselage and positionable between the forward portion and aft portion of the fuselage; and an actuator interconnecting the fuselage and the movable mass, and capable of positioning the movable mass between the forward portion and the aft portion of the fuselage. 2. The unmanned aerial vehicle according to claim 1, further comprising a port nose fairing actuator and a starboard nose fairing actuator, each actuator interconnected to its respective nose fairing and capable of pivoting the port and starboard nose fairings with respect to the fuselage.3. The unmanned aerial vehicle according to claim 2, further comprising a port wheel and a starboard wheel, the port wheel interconnected to an outward portion of the port nose fairing, a starboard wheel interconnected to an outward portion of the starboard nose fairing, port and starboard wheels interconnected to the nose fairing to permit rotation of the wheels in a direction of flight over ground during a landing.4. The unmanned aerial vehicle according to claim 3, wherein the port and starboard wheels have a tapered ground contact area to permit the wheel to rotate at an angle to the ground during the landing.5. An unmanned aerial vehicle comprising: a fuselage defining a forward portion, an aft portion, a port side and a starboard side; a port retractable wing interconnected to the port side of the fuselage and retractable along the port side and aft portion of the fuselage; a starboard retractable wing interconnected to the starboard side of the fuselage and retractable along the starboard side and aft portion of the fuselage; a movable mass interconnected to the fuselage and positionable between the forward portion and aft portion of the fuselage; an actuator interconnecting the fuselage and the movable mass, and capable of positioning the movable mass between the forward portion and the aft portion of the fuselage; a port propeller motor and propeller interconnected to an aft section of the port retractable wing, a starboard propeller motor and propeller interconnected to an aft section of the starboard retractable wing; and a wheel interconnected to the aft portion of the fuselage to permit rotation of the wheel in a direction of flight over ground during landing and disposed to permit laminar flow of air between the wheel and propellers when retracted. 6. The unmanned aerial vehicle according to claim 5, wherein the wheel further comprises a wheel assembly comprising: a wheel retainer interconnected to an aft end of the fuselage; a wheel rim rotatably disposed about the retainer; a plurality of wheel bearings disposed between the wheel rim and wheel retainer to permit rotation of the wheel rim about the wheel retainer; and a tire circumferentially disposed about the rim. 7. The unmanned aerial vehicle according to claim 6, wherein the wheel assembly further comprises a wheel support frame interconnecting the aft end of the fuselage to the wheel retainer.8. The unmanned aerial vehicle according to claim 7, wherein the wheel support frame comprises port and starboard wheel fairings, each wheel fairing being hingedly connected to the wheel retainer.9. The unmanned aerial vehicle according to claim 1, wherein the at least one propeller motor comprises a reversible motor-generator and the at lea st one propeller is capable of freewheeling by passage of air such that the freewheeling permits generation of an electric current by the motor generator.10. The unmanned aerial vehicle according to claim 1, further comprising a battery electrically interconnected to and capable of supplying current to the at least one propeller motor.11. The unmanned aerial vehicle according to claim 10, further comprising at least one photovoltaic cell capable of providing an electric current to the battery.12. The unmanned aerial vehicle according to claim 11, further comprising the photovoltaic cell being disposed on a wing surface.13. The unmanned aerial vehicle according to claim 11, further comprising the photovoltaic cell being disposed on the fuselage.14. The unmanned aerial vehicle according to claim 1, further comprising a directed energy weapon disposed on the fuselage.15. The unmanned aerial vehicle according to claim 14, wherein the directed energy weapon comprises at least one chemical oxygen iodine laser.16. The unmanned aerial vehicle according to claim 1, wherein the actuator comprises a motorized worm screw.17. An unmanned aerial vehicle comprising: a fuselage defining a forward portion, an aft portion, a port side and a starboard side; a port retractable wing interconnected to the port side of the fuselage and retractable along the port side and aft portion of the fuselage; a starboard retractable wing interconnected to the starboard side of the fuselage and retractable along the starboard side and aft portion of the fuselage; a port propeller motor and propeller interconnected to an aft section of the port retractable wing; a starboard propeller motor and propeller interconnected to an aft section of the starboard retractable wing; and a wheel interconnected to the aft portion of the fuselage to permit rotation of the wheel in a direction of flight over ground during landing, and disposed to permit laminar flow of air between the wheel and propellers when retracted. 18. The unmanned aerial vehicle according to claim 17, wherein the wheel further comprises a wheel assembly comprising: a wheel retainer interconnected to an aft end of the fuselage; a wheel rim rotatably disposed about the retainer; a plurality of wheel bearings disposed between the wheel rim and wheel retainer to permit rotation of the wheel rim about the wheel retainer; and a tire circumferentially disposed about the rim. 19. The unmanned aerial vehicle according to claim 18, wherein the wheel assembly further comprises a wheel support frame interconnecting the aft end of the fuselage to the wheel retainer.20. The unmanned aerial vehicle according to claim 19, wherein the wheel support frame comprises port and starboard wheel fairings, each wheel fairing being hingedly connected to the wheel retainer.21. The unmanned aerial vehicle according to claim 17, further comprising a nose fairing disposed along the forward portion of the fuselage.22. The unmanned aerial vehicle according to claim 21, wherein the nose fairing further comprises a port nose fairing and a starboard nose fairing pivotably attached to the forward portion of the fuselage.23. The unmanned aerial vehicle according to claim 22, further comprising a port nose fairing actuator and a starboard nose fairing actuator, each actuator interconnected to its respective nose fairing and capable of pivoting the port and starboard nose fairings with respect to the fuselage.24. The unmanned aerial vehicle according to claim 17, further comprising a movable mass interconnected to the fuselage and positionable between the forward portion and aft portion of the fuselage; and an actuator interconnecting the fuselage and the movable mass, and capable of positioning the movable mass between the forward portion and the aft portion of the fuselage. 25. The unmanned aerial vehicle according to claim 24, wherein the actuator comprises a motorized worm screw.26. The unmanned aerial ve hicle according to claim 17, wherein the at least one propeller motor comprises a reversible motor-generator and the at least one propeller being capable of freewheeling by passage of air such that the freewheeling permits generation of an electric current by the motor generator.27. The unmanned aerial vehicle according to claim 17, further comprising a battery electrically interconnected to and capable of supplying current to the at least one propeller motor.28. The unmanned aerial vehicle according to claim 27, further comprising at least one photovoltaic cell capable of providing an electric current to the battery.29. The unmanned aerial vehicle according to claim 28, further comprising the photovoltaic cell being disposed on a wing surface.30. The unmanned aerial vehicle according to claim 28, further comprising the photovoltaic cell being disposed on the fuselage.31. The unmanned aerial vehicle according to claim 17, further comprising a directed energy weapon disposed on the fuselage.32. The unmanned aerial vehicle according to claim 31, wherein the directed energy weapon comprises at least one chemical oxygen iodine laser.33. An unmanned aerial vehicle comprising: a fuselage having a forward portion and an aft portion; a wing surface interconnected to the fuselage; at least one propeller motor and propeller interconnected to the fuselage; a port nose fairing pivotably attached to the forward portion of the fuselage and extending outwardly from the fuselage to a port side of the fuselage; a port nose fairing actuator interconnected to the port nose fairing to permit the actuator to pivot the port nose fairing; a port nose wheel interconnected to an outward portion of the port nose fairing to permit rotation of the port nose wheel in a direction of flight over ground during landing; a starboard nose fairing pivotably attached to the forward portion of the fuselage and extending outwardly from the fuselage to a starboard side of the fuselage; a starboard nose fairing actuator interconnected to the starboard nose fairing to permit the actuator to pivot the starboard nose fairing; and a starboard nose wheel interconnected to an outward portion of the starboard nose fairing to permit rotation of the starboard nose wheel in a direction of flight over ground during landing. 34. The unmanned aerial vehicle according to claim 33, wherein the wheels have a tapered ground contact area to permit the wheel to rotate at an angle to the ground during the landing.35. The unmanned aerial vehicle according to claim 33, wherein the at least one propeller motor and propeller comprises: a port propeller motor and propeller interconnected to an aft section of the port retractable wing; a starboard propeller motor and propeller interconnected to an aft section of the starboard retractable wing; and a wheel interconnected to the aft portion of the fuselage to permit rotation of the wheel in a direction of flight over ground during landing, and disposed to permit laminar flow of air between the wheel and propellers when retracted. 36. The unmanned aerial vehicle according to claim 35, wherein the wheel further comprises a wheel assembly comprising: a wheel retainer interconnected to an aft end of the fuselage; a wheel rim rotatably disposed about the retainer; a plurality of wheel bearings disposed between the wheel rim and wheel retainer to permit rotation of the wheel rim about the wheel retainer; and a tire circumferentially disposed about the rim. 37. The unmanned aerial vehicle according to claim 36, wherein the wheel assembly further comprises a wheel support frame interconnecting the aft end of the fuselage to the wheel retainer.38. The unmanned aerial vehicle according to claim 37, wherein the wheel support frame comprises port and starboard wheel fairings, each wheel fairing being hingedly connected to the wheel retainer.39. The unmanned aerial vehicle according to claim 33, wherein the at l east one propeller motor comprises a reversible motor-generator and the at least one propeller being capable of freewheeling by passage of air such that the freewheeling permits generation of an electric current by the motor generator.40. The unmanned aerial vehicle according to claim 33, further comprising a battery electrically interconnected to and capable of supplying current to the at least one propeller motor.41. The unmanned aerial vehicle according to claim 40, further comprising at least one photovoltaic cell capable of providing an electric current to the battery.42. The unmanned aerial vehicle according to claim 41, further comprising the photovoltaic cell being disposed on a wing surface.43. The unmanned aerial vehicle according to claim 41, further comprising the photovoltaic cell being disposed on the fuselage.44. The unmanned aerial vehicle according to claim 33, further comprising a directed energy weapon disposed on the fuselage.45. The unmanned aerial vehicle according to claim 44, wherein the directed energy weapon comprises at least one chemical oxygen iodine laser.46. An unmanned aerial vehicle comprising: a fuselage having a forward portion and an aft portion; a wing surface interconnected to the fuselage; a port retractable wing interconnected to the port side of the fuselage and retractable along the port side and aft portion of the fuselage; a starboard retractable wing interconnected to the starboard side of the fuselage and retractable along the starboard side and aft portion of the fuselage; at least one propeller reversible motor-generator interconnected to the fuselage permitting motor operation and freewheeling electric generator operation; and a propeller interconnected to the at least one propeller motor-generator capable of freewheeling by air passage through the propeller; a port propeller motor and propeller interconnected to an aft section of the port retractable wing; a starboard propeller motor and propeller interconnected to an aft section of the starboard retractable wing; and a wheel interconnected to the aft portion of the fuselage to permit rotation of the wheel in a direction of flight over ground during landing, and disposed to permit laminar flow of air between the wheel and propellers when retracted. 47. The unmanned aerial vehicle according to claim 46, further comprising: a movable mass interconnected to the fuselage and positionable between the forward portion and aft portion of the fuselage; and an actuator interconnecting the fuselage and the movable mass, and capable of positioning the movable mass between the forward portion and the aft portion of the fuselage. 48. The unmanned aerial vehicle according to claim 47, wherein the actuator comprises a motorized worm screw.49. The unmanned aerial vehicle according to claim 46, further comprising a nose fairing disposed along the forward portion of the fuselage.50. The unmanned aerial vehicle according to claim 49, wherein the nose fairing further comprises a port nose fairing and a starboard nose fairing pivotably attached to the forward portion of the fuselage.51. The unmanned aerial vehicle according to claim 50, further comprising a port nose fairing actuator and a starboard nose fairing actuator, each actuator interconnected to its respective nose fairing and capable of pivoting the port and starboard nose fairings with respect to the fuselage.52. The unmanned aerial vehicle according to claim 51, further comprising a port wheel and a starboard wheel, the port wheel interconnected to an outward portion of the port nose fairing, a starboard wheel interconnected to an outward portion of the starboard nose fairing, port and starboard wheels interconnected to the nose fairing to permit rotation of the wheels in a direction of flight over ground during a landing.53. The unmanned aerial vehicle according to claim 52, wherein the port and starboard wheels have a tapered ground contact area to permit the wheel to rotate at an angle to the ground during the landing.54. The unmanned aerial vehicle according to claim 46, wherein the wheel further comprises a wheel assembly comprising: a wheel retainer interconnected to an aft end of the fuselage; a wheel rim rotatably disposed about the retainer; a plurality of wheel bearings disposed between the wheel rim and wheel retainer to permit rotation of the wheel rim about the wheel retainer; and a tire circumferentially disposed about the rim. 55. The unmanned aerial vehicle according to claim 54, wherein the wheel assembly further comprises a wheel support frame interconnecting the aft end of the fuselage to the wheel retainer.56. The unmanned aerial vehicle according to claim 55, wherein the wheel support frame comprises port and starboard wheel fairings, each wheel fairing being hingedly connected to the wheel retainer.57. The unmanned aerial vehicle according to claim 46, further comprising a battery electrically interconnected to and capable of supplying current to the at least one propeller motor.58. The unmanned aerial vehicle according to claim 57, further comprising at least one photovoltaic cell capable of providing an electric current to the battery.59. The unmanned aerial vehicle according to claim 58, further comprising the photovoltaic cell being disposed on a wing surface.60. The unmanned aerial vehicle according to claim 58, further comprising the photovoltaic cell being disposed on the fuselage.61. The unmanned aerial vehicle according to claim 46, further comprising a directed energy weapon disposed on the fuselage.62. The unmanned aerial vehicle according to claim 61, wherein the directed energy weapon comprises at least one chemical oxygen iodine laser.63. A method of flying an unmanned aerial vehicle having pivotable port and starboard nose fairings, port and starboard nose fairings each having a wheel, the method comprising: individually pivoting the port and starboard nose fairings to control direction of flight of the vehicle; pivoting the port and starboard nose fairings downwardly; and landing the vehicle on the wheels while the port and starboard nose fairings are pivoted downwardly. 64. The method according to claim 63, further comprising locking the port and starboard nose fairings after the step of pivoting the port and starboard nose fairings downwardly.65. The method according to claim 63, wherein the step of individually pivoting the port and starboard nose fairings to control the direction of flight includes pivoting the fairings to control lift.66. The method according to claim 63, wherein the step of individually pivoting the port and starboard nose fairings to control the direction of flight includes pivoting the fairings to control yaw.67. A method of flying an unmanned aerial vehicle having port and starboard retractable wings and a nose fairing comprising: retracting the port and starboard wings on the unmanned air vehicle from a normal flying position; positioning a nose fairing to achieve a downward angle permitting a ballistic glide path toward earth; positioning a mass from fore to aft with respect to the unmanned air vehicle; and positioning the nose fairing to achieve an ascent position of the unmanned air vehicle with respect to the ground. 68. The method according to claim 67, wherein the step of retracting the port and starboard wings comprises unlocking the port and starboard wings and permitting air flow against the wings to cause the wings to retract.69. The method according to claim 67, further comprising locking the port and starboard wings in a stowed position along an aft portion of the vehicle.70. The method according to claim 67, further comprising discharging a directed energy weapon from the vehicle in a direction aft of the vehicle after the step of positioning the nose fairing to achieve an ascent position.71. The method according to claim 70, wherein the step of discharging a directed en ergy weapon further comprises discharging the weapon in an aft direction creating ascent thrust.72. The method according to claim 67, further comprising discharging a thrust mechanism in a direction aft of the vehicle.73. The method according to claim 67, further comprising individually pivoting the port and starboard nose fairings to control direction of flight of the vehicle.74. The method according to claim 67, further comprising repositioning the port and starboard wings to a normal flying position; and positioning the mass from aft to fore with respect to the vehicle. 75. A method of flying an unmanned aerial vehicle having port and starboard propeller motor-generators interconnected to retractable port and starboard wings respectively, the method comprising: retracting the port and starboard wings from a normal flying position; freewheeling the propeller while the wings are retracted; and generating an electrical current at an output of the motor generator from the freewheeling propeller. 76. The method according to claim 75, further comprising: repositioning the port and starboard wings to a normal flying position; and operating the port and starboard motor generators under motor power to provide thrust for the vehicle. 77. A nose assembly for an unmanned air vehicle comprising: a support structure capable of being interconnected to the unmanned air vehicle; a port nose fairing pivotably attached to the support structure extending outwardly from the support structure to a port side of the fuselage; a port nose fairing actuator interconnected to the port nose fairing to permit the actuator to pivot the port nose fairing; a port nose wheel interconnected to an outward portion of the port nose fairing to permit rotation of the port nose wheel in a direction of flight over ground during a landing of the unmanned air vehicle; a starboard nose fairing pivotably attached to the support structure extending outwardly from the support structure to a starboard side of the fuselage; a starboard nose fairing actuator interconnected to the starboard nose fairing to permit the actuator to pivot the starboard nose fairing; and a starboard nose wheel interconnected to an outward portion of the starboard nose fairing to permit rotation of the starboard nose wheel in a direction of flight over ground during a landing of the unmanned air vehicle. 78. The nose assembly according to claim 77, wherein the port and starboard nose fairings each further comprise an airfoil capable of independently controlling yaw of the unmanned air vehicle.79. The nose assembly according to claim 77, wherein the port and starboard wheels each further comprise a tapered ground contact area to permit the wheel to rotate at an angle to the ground during the landing.80. The nose assembly according to claim 77, wherein port and starboard actuators each further comprise: a pivotable shaft fixedly connected to the nose fairing at a pivot axis; and a rotating machine interconnected to the pivotable shaft for rotating the shaft to pivot the nose fairing. 81. The nose assembly according to claim 80, wherein the rotating machine comprises an electromechanical servo-motor.82. The nose assembly according to claim 80, wherein the actuator further comprises a gear for interconnecting the rotating to the shaft.83. The nose assembly according to claim 82, further comprising: at least one locking ring fixedly disposed about the shaft; and a locking device for preventing movement of the locking ring in a predetermined position. 84. The nose assembly according to claim 83, wherein the locking ring further comprises at least one locking hole, and the locking device further comprises a locking pin disposed in an opposed relationship to the locking hole and capable of being inserted into the locking hole.85. The nose assembly according to claim 84, wherein the locking ring further comprises at least one ratchet groove for resisting mo vement of the locking ring at a predetermined position.86. The nose assembly according to claim 85, wherein the locking pin further comprises: a cylinder having a partially enclosed end proximate the locking ring, the partially enclosed end being capable of being inserted into the locking hole; a roller ball restrained by the partially enclosed end of the cylinder and capable of being inserted into the ratchet groove; and a spring disposed within the cylinder to urge the roller ball toward the partially enclosed end. 87. The nose assembly according to claim 84, wherein the locking pin further comprises an electrically controllable solenoid for urging the locking pin in a direction with respect to the locking ring.