Rotor assembly having a ball joint for thrust vectoring capabilities

1. A rotor assembly for an aircraft operable to generate a variable thrust vector, the aircraft including an airframe, the rotor assembly comprising:

a mast rotatable relative to the airframe about a mast axis;

a ball joint coupled to the airframe and non rotatable with the mast;

a tilt control assembly positioned on the ball joint and having a tilting degree of freedom relative to the ball joint, the tilt control assembly non rotatable with the mast;

a constant velocity joint assembly coupled to the mast and rotated therewith, the constant velocity joint assembly disposed at least partially within the ball joint;

a rotor hub coupled to the constant velocity joint assembly and rotated therewith in a rotational plane about the mast axis, the rotor hub rotatably coupled to the tilt control assembly and tiltable therewith, the rotor hub including a plurality of grips; and

a plurality of rotor blades each coupled to one of the grips;

wherein, the tilt control assembly is configured to be actuated in the tilting degree of freedom to change the rotational plane of the rotor hub relative to the mast axis, thereby generating the variable thrust vector.

2. The rotor assembly as recited in claim 1 wherein the tilt control assembly further comprises a tilting plate and a plurality of actuators operable to tilt the tilting plate relative to the ball joint to change the rotational plane of the rotor hub relative to the mast axis, thereby enabling resolution of the thrust vector within a thrust vector cone.

3. The rotor assembly as recited in claim 2 wherein the thrust vector cone has a maximum angle relative to the mast axis of between ten degrees and thirty degrees.

4. The rotor assembly as recited in claim 2 wherein the thrust vector cone has a maximum angle relative to the mast axis of between fifteen degrees and twenty-five degrees.

5. The rotor assembly as recited in claim 2 wherein the thrust vector cone has a maximum angle relative to the mast axis of twenty degrees.

6. The rotor assembly as recited in claim 1 further comprising a bearing assembly disposed between the tilt control assembly and the rotor hub to enable relative rotation therebetween.

7. The rotor assembly as recited in claim 6 wherein the bearing assembly further comprises a ball bearing assembly.

8. The rotor assembly as recited in claim 1 wherein the constant velocity joint assembly further comprises a splined connector.

9. The rotor assembly as recited in claim 8 wherein the rotor hub further comprises a drive arm assembly having a splined portion that is coupled to the splined connector of the constant velocity joint assembly.

10. The rotor assembly as recited in claim 9 wherein the drive arm assembly is configured to translate relative to the constant velocity joint assembly during rotary operations.

11. The rotor assembly as recited in claim 1 wherein each of the grips further comprises a spindle grip rotatable about a pitch change axis; and

wherein, each of the rotor blades is rotatable with the respective spindle grip about the respective pitch change axis.

12. The rotor assembly as recited in claim 11 further comprising a collective pitch control mechanism coupled to and rotatable with the rotor hub, the collective pitch control mechanism operably associated with each spindle grip such that actuation of the collective pitch control mechanism rotates each spindle grip about the respective pitch change axis to collectively adjust the pitch of the rotor blades.

13. An aircraft comprising:

an airframe;

a propulsion system attached to the airframe, the propulsion system including a plurality of propulsion assemblies each having a rotor assembly; and

a flight control system operable to independently control each of the propulsion assemblies;

the rotor assemblies each comprising:

a mast rotatable relative to the airframe about a mast axis;

a ball joint coupled to the airframe and non rotatable with the mast;

a tilt control assembly positioned on the ball joint and having a tilting degree of freedom relative to the ball joint, the tilt control assembly non rotatable with the mast;

a constant velocity joint assembly coupled to the mast and rotated therewith, the constant velocity joint assembly disposed at least partially within the ball joint,

a rotor hub coupled to the constant velocity joint assembly and rotated therewith in a rotational plane about the mast axis, the rotor hub rotatably coupled to the tilt control assembly and tiltable therewith, the rotor hub including a plurality of grips; and

a plurality of rotor blades each coupled to one of the grips;

wherein, the tilt control assembly is configured to be actuated in the tilting degree of freedom to change the rotational plane of the rotor hub relative to the mast axis, thereby generating a variable thrust vector.

14. The aircraft as recited in claim 13 wherein each of the tilt control assemblies further comprises a tilting plate and a plurality of actuators operable to tilt the tilting plate about the ball joint to change the rotational plane of the rotor hub relative to the mast axis, thereby enabling resolution of the thrust vector within a thrust vector cone.

15. The aircraft as recited in claim 14 wherein the thrust vector cone has a maximum angle relative to the mast axis of between ten degrees and thirty degrees.

16. The aircraft as recited in claim 14 wherein the thrust vector cone has a maximum angle relative to the mast axis of between fifteen degrees and twenty-five degrees.

17. The aircraft as recited in claim 14 wherein the thrust vector cone has a maximum angle relative to the mast axis of twenty degrees.

18. The aircraft as recited in claim 13 wherein the airframe further comprises first and second wings each having an M-wing design with two leading apexes, each of the rotor assemblies positioned proximate one of the leading apexes.

19. The aircraft as recited in claim 13 further comprising a passenger pod assembly rotatably attached to the airframe.

20. The aircraft as recited in claim 13 wherein the flight control system is configured to control the propulsion assemblies responsive to at least one of onboard pilot flight control, remote flight control, autonomous flight control and combinations thereof.