Rotor assembly having collective pitch control

Patent metadata

Field	Value
Publication number	US-10351232-B2
Application number	US-201715606257-A
Country	US
Kind code	B2
Filing date	May 26, 2017
Priority date	May 26, 2017
Publication date	Jul 16, 2019
Grant date	Jul 16, 2019

Abstract

A rotor assembly for an aircraft operable to generate a variable thrust output at a constant rotational speed. The rotor assembly includes a mast rotatable at the constant speed about a mast axis. A rotor hub is coupled to and rotatable with the mast. The rotor hub includes a plurality of spindle grips extending generally radially outwardly. Each of the spindle grips is coupled to one of a plurality of rotor blades and is operable to rotate therewith about a pitch change axis. A collective pitch control mechanism is coupled to and rotatable with the rotor hub. The collective pitch control mechanism is 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 control the pitch of the rotor blades, thereby generating the variable thrust output.

First claim

What is claimed is:

1. A rotor assembly for an aircraft operable to generate a variable thrust output at a constant rotational speed, the rotor assembly comprising:
a mast rotatable at the constant speed about a mast axis;
a rotor hub coupled to and rotatable with the mast, the rotor hub including a plurality of spindle grips extending generally radially outwardly, each of the spindle grips operable to rotate about a pitch change axis and each of the spindle grips including a pinion gear;
a plurality of rotor blades each coupled to one of the spindle grips and rotatable about the respective pitch change axis; and
a collective pitch control mechanism coupled to and rotatable with the rotor hub, the collective pitch control mechanism including a spider assembly having a plurality of arms each including a rack gear that mates with one of the pinion gears;
wherein, actuation of the collective pitch control mechanism translates the spider assembly relative to the rotor hub to rotate each spindle grip about the respective pitch change axis to collectively control the pitch of the rotor blades, thereby generating the variable thrust output.

2. The rotor assembly as recited in claim 1 wherein the collective pitch control mechanism further comprises at least one actuator operable to translate the spider assembly relative to the rotor hub.

3. The rotor assembly as recited in claim 1 further comprising a joint assembly providing a torque path from the mast to the rotor hub.

4. The rotor assembly as recited in claim 3 wherein the joint assembly further comprises a constant velocity joint assembly providing the torque path from the mast to the rotor hub.

5. The rotor assembly as recited in claim 4 wherein the rotor hub further comprises a drive arm assembly coupled to the constant velocity joint assembly.

6. The rotor assembly as recited in claim 5 wherein the drive arm assembly is operable to rotate with and translate relative to the constant velocity joint assembly during rotary operations.

7. The rotor assembly as recited in claim 1 further comprising a ball joint positioned about and non rotatable with the mast and a tilt control assembly positioned on and having a tilting degree of freedom relative to the ball joint, the tilt control assembly non rotatable with the mast; and
wherein, the rotor hub is rotatably coupled to and tiltable with the tilt control assembly such that actuation of the tilt control assembly changes the rotational plane of the rotor hub relative to the mast axis.

8. The rotor assembly as recited in claim 7 wherein, actuation of the tilt control assembly to change the rotational plane of the rotor hub relative to the mast axis generates a variable thrust vector.

9. The rotor assembly as recited in claim 8 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.

10. The rotor assembly as recited in claim 9 wherein the thrust vector cone has a maximum angle relative to the mast axis of between about ten degrees and about thirty degrees.

11. The rotor assembly as recited in claim 7 further comprising a low friction bearing assembly disposed between the tilt control assembly and the rotor hub to enable relative rotation therebetween.

12. The rotor assembly as recited in claim 11 wherein the low friction bearing assembly further comprises a ball bearing assembly.

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 at the constant speed about a mast axis;
a rotor hub coupled to and rotatable with the mast, the rotor hub including a plurality of spindle grips extending generally radially outwardly, each of the spindle grips operable to rotate about a pitch change axis and each of the spindle grips including a pinion gear;
a plurality of rotor blades each coupled to one of the spindle grips and rotatable about the respective pitch change axis; and
a collective pitch control mechanism coupled to and rotatable with the rotor hub, the collective pitch control mechanism including a spider assembly having a plurality of arms each including a rack gear that mates with one of the pinion gears;
wherein, actuation of the collective pitch control mechanism translates the spider assembly relative to the rotor hub to rotate each spindle grip about the respective pitch change axis to collectively control the pitch of the rotor blades, thereby generating the variable thrust output.

14. The aircraft as recited in claim 13 wherein each of the collective pitch control mechanisms further comprises at least one actuator operable to translate the spider assembly relative to the rotor hub.

15. 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.

16. The aircraft as recited in claim 13 further comprising a passenger pod assembly rotatably attachable to the airframe such that the passenger pod assembly remains in a generally horizontal attitude in a vertical takeoff and landing fight mode, a forward flight mode and transitions therebetween.

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

18. The aircraft as recited in claim 13 wherein each of the rotor assemblies further comprises a ball joint positioned about and non rotatable with the mast and a tilt control assembly positioned on and having a tilting degree of freedom relative to the ball joint, the tilt control assembly non rotatable with the mast; and
wherein, the rotor hub is rotatably coupled to and tiltable with the tilt control assembly such that actuation of the tilt control assembly changes the rotational plane of the rotor hub relative to the mast axis, thereby generating a variable thrust vector.

19. The aircraft as recited in claim 18 wherein each of the tilt control assemblies 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 enabling resolution of the thrust vector within a thrust vector cone having a maximum angle relative to the mast axis of between about ten degrees and about thirty degrees.

20. The aircraft as recited in claim 18 wherein each of the rotor assemblies further comprises a ball bearing assembly disposed between the tilt control assembly and the rotor hub to enable relative rotation therebetween.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Mccullough John Richard
• Oldroyd Paul K

Classifications

• B64U70/60

  Take-off or landing of UAVs from a runway using their own power · CPC title

• B64C5/02

  Tailplanes · CPC title

• B64C29/02

  having its flight directional axis vertical when grounded · CPC title

• B64C3/385

  Variable incidence wings · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title