Methods and apparatus for transforming unmanned aerial vehicle
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.
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; wherein
the 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.
2. An aircraft according to claim 1 , wherein the first lifting surface and the second lifting surface form a delta wing when the first and second leading edges are positioned toward the forward end of the fuselage.
3. An aircraft according to claim 1 , wherein the first lifting surface and the second lifting surface rotate in opposite directions relative to each other.
4. An aircraft according to claim 1 , wherein the first leading edge and the second leading edge face substantially opposite directions during at least one of takeoff and landing.
5. An aircraft according to claim 1 , wherein the launch system is mounted on a mobile entity.
6. An aircraft according to claim 1 , further comprising a propulsion system, wherein the propulsion system comprises at least one propulsive element connected to each of the first lifting and second lifting surfaces.
7. An unmanned aircraft, comprising:
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.
8. An unmanned aircraft according to claim 7 , wherein the at least two wings are configured to rotate prior to landing such that each of the leading edges forms an angle of between thirty and one hundred fifty degrees relative to the longitudinal axis of the fuselage.
9. An unmanned aircraft according to claim 7 , wherein the at least two wings form a delta wing aircraft when the two leading edges are positioned forward the forward end of the fuselage.
10. An unmanned aircraft according to claim 6 , wherein the at least two wings are configured to rotate in opposite directions relative to each other.
11. An unmanned aircraft according to claim 7 , wherein the two leading edges face substantially opposite directions from each other during at least one of takeoff and landing.
12. An unmanned aircraft according to claim 7 , wherein the launch system is mounted on a mobile entity.
13. An unmanned aircraft according to claim 8 , further comprising a propulsion system, wherein the propulsion system comprises at least one propulsive element connected to each of the first lifting and second lifting surfaces.