Aircraft having omnidirectional ground maneuver capabilities

1. An aircraft having omnidirectional ground maneuver capabilities, the aircraft comprising:

an airframe including first and second wings;

a plurality of propulsion assemblies attached to the airframe including at least two propulsion assemblies attached to the first wing and at least two propulsion assemblies attached to the second wing, each of the propulsion assemblies including a nacelle having a mast axis, a rotor assembly including a ball joint and a rotor hub that is rotatable and tiltable relative to the ball joint such that the rotor hub has a tilting degree of freedom relative to the mast axis and a tail assembly rotatable about the mast axis, the tail assembly including at least one wheel having a rotational axis; and

a flight control system operable to independently control each of the propulsion assemblies including tilting each rotor assembly and rotating each tail assembly;

wherein, for each propulsion assembly, the rotor assembly and the tail assembly have complementary configurations in which a thrust vector generated by the rotor assembly has a horizontal component that is generally perpendicular to the rotational axis of the wheel, thereby enabling omnidirectional ground maneuvers.

2. The aircraft as recited in claim 1 wherein, the tail assemblies have a fore/aft ground maneuver configuration in which the rotational axes of the wheels are generally parallel with the wings.

3. The aircraft as recited in claim 1 wherein, the tail assemblies have a lateral ground maneuver configuration in which the rotational axes of the wheels are generally perpendicular with the wings.

4. The aircraft as recited in claim 1 wherein, the tail assemblies have a plurality of radial ground maneuver configurations in which the rotational axes of the wheels are between generally parallel and generally perpendicular with the wings.

5. The aircraft as recited in claim 1 wherein, the tail assemblies have a turning ground maneuver configuration in which the rotational axes of first and second a first pair of the wheels are generally parallel with the wings and the rotational axes of third and fourth a second pair of the wheels are between generally parallel and generally perpendicular with the wings.

6. The aircraft as recited in claim 1 wherein, the tail assemblies have a turning ground maneuver configuration in which the rotational axes of a first pair of the wheels are generally perpendicular with the wings and the rotational axes of a second pair of the wheels are between generally parallel and generally perpendicular with the wings.

7. The aircraft as recited in claim 1 wherein,

the aircraft has a rotational axis.

8. The aircraft as recited in claim 7 wherein, the tail assemblies have a rotation ground maneuver configuration in which the rotational axes of adjacent wheels are generally perpendicular with each other and the rotational axis of each wheel intersects the rotational axis of the aircraft.

9. The aircraft as recited in claim 7 wherein, the tail assemblies have a passive brake configuration in which the rotational axes of adjacent wheels are generally perpendicular with each other and the rotational axis of each wheel does not intersect the rotational axis of the aircraft.

10. The aircraft as recited in claim 1 wherein, for each propulsion assembly, the rotor assembly and the tail assembly have non complementary configurations in which the horizontal component of the thrust vector generated by the rotor assembly is not perpendicular to the rotational axis of the wheel.

11. The aircraft as recited in claim 1 wherein, the rotor assemblies have common tilting configurations in which each rotor hub is tilted in the same direction.

12. The aircraft as recited in claim 1 wherein, the rotor assemblies have non common tilting configurations in which the rotor hubs are tilted in a plurality of directions.

13. The aircraft as recited in claim 1 wherein, the rotor assemblies have non common tilting configurations in which each rotor hub is tilted in a different direction.

14. An aircraft having omnidirectional ground maneuver capabilities, the aircraft comprising:

an airframe including first and second wings;

a plurality of propulsion assemblies including at least two propulsion assemblies attached to the first wing and at least two propulsion assemblies attached to the second wing, each of the propulsion assemblies including a nacelle having a mast axis, a rotor assembly including a ball joint and a rotor hub that is rotatable and tiltable relative to the ball joint such that the rotor hub has a tilting degree of freedom relative to the mast axis and a tail assembly rotatable about the mast axis, the tail assembly including at least one wheel having a rotational axis; and

a flight control system operable to independently control each of the propulsion assemblies including tilting each rotor assembly and rotating each tail assembly;

wherein, for each propulsion assembly, the rotor assembly and the tail assembly have complementary configurations in which a thrust vector generated by the rotor assembly has a horizontal component that is generally perpendicular to the rotational axis of the wheel; and

wherein, for each propulsion assembly, the rotor assembly and the tail assembly have non complementary configurations in which the horizontal component of the thrust vector generated by the rotor assembly is not perpendicular to the rotational axis of the wheel.

15. The aircraft as recited in claim 14 wherein, the tail assemblies have a fore/aft ground maneuver configuration in which the rotational axes of the wheels are generally parallel with the wings;

wherein, the tail assemblies have a lateral ground maneuver configuration in which the rotational axes of the wheels are generally perpendicular with the wings; and

wherein, the tail assemblies have a plurality of radial ground maneuver configurations in which the rotational axes of the wheels are between generally parallel and generally perpendicular with the wings, thereby enabling omnidirectional ground maneuvers.

16. The aircraft as recited in claim 14 wherein, the tail assemblies have a first turning ground maneuver configuration in which the rotational axes of a first pair of the wheels are generally parallel with the wings and the rotational axes of a second pair of the wheels are between generally parallel and generally perpendicular with the wings; and

wherein, the tail assemblies have a second turning ground maneuver configuration in which the rotational axes of the first and third a third pair of the wheels are generally perpendicular with the wings and the rotational axes of the second and fourth a fourth pair of the wheels are between generally parallel and generally perpendicular with the wings.

17. The aircraft as recited in claim 14 wherein, the tail assemblies have a rotation ground maneuver configuration in which the rotational axes of adjacent wheels are generally perpendicular with each other and the rotational axis of each wheel intersects a rotational axis of the aircraft.

18. The aircraft as recited in claim 14 wherein, the tail assemblies have a passive brake configuration in which the rotational axes of adjacent wheels are generally perpendicular with each other and the rotational axis of each wheel does not intersect a rotational axis of the aircraft.

19. The aircraft as recited in claim 14 wherein the aircraft is operable to transition between a forward flight mode and a vertical takeoff and landing flight mode.

20. The aircraft as recited in claim 19 further comprising a pod assembly rotatably coupled to the airframe such that the pod assembly remains in a generally horizontal attitude in the forward flight mode, the vertical takeoff and landing flight mode and transitions therebetween;

wherein, in the vertical takeoff and landing flight mode, the first wing is forward of the pod assembly and the second wing is aft of the pod assembly; and

wherein, in the forward flight mode, the first wing is below the pod assembly and the second wing is above the pod assembly.