Proprotor lockout systems for tiltrotor aircraft

Patent metadata

Field	Value
Publication number	US-11964757-B2
Application number	US-202217825278-A
Country	US
Kind code	B2
Filing date	May 26, 2022
Priority date	May 26, 2022
Publication date	Apr 23, 2024
Grant date	Apr 23, 2024

Abstract

A lockout system for an aircraft having a rotor assembly. The lockout system includes a drive shaft coupled to and rotatable with the rotor assembly, a nonrotating airframe structure disposed proximate the drive shaft and a lock assembly having first and second lock members. The first lock member is rotatable with the drive shaft and includes a plurality of bearing assemblies. The second lock member is coupled to the nonrotating airframe structure and includes a cradle having a plurality of asymmetric slots each with a leading ramp and a trailing stop. The lock assembly has a disengaged position in which rotation of the drive shaft is allowed and an engaged position in which each of the bearing assemblies is seated within one of the asymmetric slots to prevent rotation of the drive shaft. The lock assembly is actuatable between the engaged and disengaged positions.

First claim

What is claimed is:

1. A lockout system for an aircraft having a rotor assembly, the lockout system comprising:
a drive shaft coupled to and rotatable with the rotor assembly;
a nonrotating airframe structure disposed proximate the drive shaft; and
a lock assembly having first and second lock members, the first lock member coupled to and rotatable with the drive shaft, the second lock member coupled to the nonrotating airframe structure, the first lock member including a plurality of bearing assemblies, the second lock member including a cradle having a plurality of asymmetric slots, each asymmetric slot including a leading ramp having a curved upper profile with a progressively decreasing angle and a trailing stop having a surface that is substantially parallel with a central axis of the second lock member;
wherein, the lock assembly has a plurality of positions including a disengaged position in which rotation of the drive shaft is allowed and an engaged position in which each of the bearing assemblies is seated within one of the asymmetric slots to prevent rotation of the drive shaft;
wherein, the lock assembly is actuatable between the disengaged and engaged positions;
wherein, each of the bearing assemblies has a diameter and each of the asymmetric slots has a height; and
wherein, the height is greater than the diameter.

2. The lockout system as recited in claim 1 wherein the drive shaft is disposed in a wing of the aircraft.

3. The lockout system as recited in claim 1 wherein the drive shaft further comprises a proprotor mast.

4. The lockout system as recited in claim 1 wherein the nonrotating airframe structure further comprises a gearbox housing.

5. The lockout system as recited in claim 1 wherein the nonrotating airframe structure further comprises a wing airframe structure.

6. The lockout system as recited in claim 1 wherein each of the bearing assemblies further comprises a spherical roller bearing.

7. The lockout system as recited in claim 1 wherein each of the bearing assemblies further comprises at least one of a hardened roller surface or a high lubricity roller surface.

8. The lockout system as recited in claim 1 wherein the plurality of bearing assemblies further comprises first, second and third bearing assemblies.

9. The lockout system as recited in claim 8 wherein the first, second and third bearing assemblies are uniformly circumferentially distributed at 120 degree intervals.

10. The lockout system as recited in claim 1 wherein the first lock member further comprises a collar assembly having internal splines configured to couple with external splines of the drive shaft to prevent relative rotation therebetween.

11. The lockout system as recited in claim 1 wherein the plurality of asymmetric slots further comprises first, second and third asymmetric slots.

12. The lockout system as recited in claim 11 wherein the first, second and third asymmetric slots are uniformly circumferentially distributed at 120 degree intervals.

13. The lockout system as recited in claim 1 wherein the second lock member further comprises a sleeve and a piston, the sleeve coupled to the nonrotating airframe structure to prevent relative rotation and relative translation therebetween, the piston slidably disposed within the sleeve and configured to translate relative thereto to shift the lock assembly between the disengaged and engaged positions.

14. The lockout system as recited in claim 13 wherein the sleeve and the piston include a nonrotation feature to prevent relative rotation therebetween.

15. The lockout system as recited in claim 1 wherein, for each of the asymmetric slots, the progressively decreasing angle of the curved upper profile of the leading ramp transitions from between about 60 degrees to about 30 degrees.

16. The lockout system as recited in claim 1 wherein, for each of the asymmetric slots, an entry gap is at least twice as wide as a base gap.

17. The lockout system as recited in claim 1 wherein each of the bearing assemblies is seated within one of the asymmetric slots when the bearing assembly contacts both the leading ramp and the trailing stop of the respective asymmetric slot and is disposed entirely within the respective asymmetric slot.

18. A tiltrotor aircraft having rotary and non-rotary flight modes, in the rotary flight mode, the tiltrotor aircraft operating at least two proprotor assemblies each having a plurality of proprotor blades, in the non-rotary flight mode, the proprotor assemblies are rotationally locked and circumferentially clocked for blade folding, for each proprotor assembly, the aircraft comprising:
a proprotor drive shaft coupled to and rotatable with the proprotor assembly;
a nonrotating airframe structure disposed proximate the proprotor drive shaft; and
a lock assembly having first and second lock members, the first lock member coupled to and rotatable with the proprotor drive shaft, the second lock member coupled to the nonrotating airframe structure, the first lock member including a plurality of bearing assemblies, the second lock member including a cradle having a plurality of asymmetric slots, each asymmetric slot including a leading ramp having a curved upper profile with a progressively decreasing angle and a trailing stop having a surface that is substantially parallel with a central axis of the second lock member;
wherein, the lock assembly has a plurality of positions including a disengaged position in which rotation of the proprotor drive shaft is allowed and an engaged position in which each of the bearing assemblies is seated within one of the asymmetric slots to prevent rotation of the proprotor drive shaft;
wherein, the lock assembly is actuatable between the disengaged and engaged positions;
wherein, each of the bearing assemblies has a diameter and each of the asymmetric slots has a height; and
wherein, the height is greater than the diameter.

Assignees

• Textron Innovations Inc

Inventors

• Beall Grant Michael
• Cravener Kyle Thomas
• Atkins Brady Garrett
• Morales Gilberto

Classifications

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title

• B64C11/28 Primary

  Collapsible or foldable blades · CPC title

• B64D35/00

  Transmitting power from power plants to propellers or rotors; Arrangements of transmissions · CPC title

• F16D71/00

  Mechanisms for bringing members to rest in a predetermined position (combined with or controlling clutches F16D43/26; means for initiating operation of brakes at a predetermined position F16D65/14; means for securing members after operation F16B1/02) · CPC title

• B64C27/50

  Blades foldable to facilitate stowage of aircraft · CPC title