Methods and apparatus for transforming unmanned aerial vehicle
First Claim
1. An aircraft, comprising:
- a fuselage comprising a forward end and an aft end;
a first lifting surface with a first leading edge, wherein the first lifting surface is rotatably connected to the fuselage;
a second lifting surface with a second leading edge, wherein the second lifting surface is rotatably connected to the fuselage;
whereinthe first and second lifting surfaces are configured to;
rotate prior to at least one of takeoff and landing such that each of the first and second leading edges forms an angle of between thirty and one hundred fifty degrees relative to a longitudinal axis of the fuselage when the fuselage is disposed in a substantially vertical position; and
rotate after takeoff such that each of the first and second leading edges is positioned toward the forward end of the fuselage;
wherein the fuselage is configured to engage a launch system adapted to rotate the fuselage about its longitudinal axis prior to launch.
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Accused Products
Abstract
Methods and apparatus for a transforming aerial vehicle according to various aspects of the present invention may operate in conjunction with a launch system configured to rotate the aerial vehicle about its longitudinal axis. A lifting surface pivotally connected to the aerial vehicle may be positioned such that the rotation of the aerial vehicle causes the lifting surface to generate a lifting force on the aerial vehicle. This lift causes the aerial vehicle to rise gyroscopically before the lifting surface is rotated to a second position such that the aerial vehicle transforms from a gyroscopic mode to a fixed-wing aerial vehicle. The lifting surface may then be rotated again to allow the aerial vehicle to land as an auto gyro.
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Citations
13 Claims
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1. An aircraft, comprising:
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a fuselage comprising a forward end and an aft end; a first lifting surface with a first leading edge, wherein the first lifting surface is rotatably connected to the fuselage; a second lifting surface with a second leading edge, wherein the second lifting surface is rotatably connected to the fuselage;
whereinthe first and second lifting surfaces are configured to; rotate prior to at least one of takeoff and landing such that each of the first and second leading edges forms an angle of between thirty and one hundred fifty degrees relative to a longitudinal axis of the fuselage when the fuselage is disposed in a substantially vertical position; and rotate after takeoff such that each of the first and second leading edges is positioned toward the forward end of the fuselage; wherein the fuselage is configured to engage a launch system adapted to rotate the fuselage about its longitudinal axis prior to launch. - View Dependent Claims (2, 3, 4, 5, 6, 10)
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7. An unmanned aircraft, comprising:
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a fuselage comprising a forward end and an aft end; and at least two wings rotatably connected to the fuselage, wherein; each of the at least two wings comprises a leading edge; and each of the at least two wings is configured to; rotate prior to takeoff such that each of the first and second leading edges forms an angle between thirty and one hundred fifty degrees relative to a longitudinal axis of the fuselage when the fuselage is disposed in a substantially vertical position; and rotate after takeoff such that each of the first and second leading edges is positioned toward the forward end of the fuselage; wherein the fuselage is configured to engage a launch system adapted to rotate the fuselage about its longitudinal axis prior to launch. - View Dependent Claims (8, 9, 11, 12, 13)
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Specification