Mast lockout systems for tiltrotor aircraft

Patent metadata

Field	Value
Publication number	US-10843798-B2
Application number	US-201816229296-A
Country	US
Kind code	B2
Filing date	Dec 21, 2018
Priority date	Feb 15, 2018
Publication date	Nov 24, 2020
Grant date	Nov 24, 2020

Abstract

A mast lockout system for a tiltrotor aircraft having a proprotor assembly. The system includes a mast coupled to and rotatable with the proprotor assembly. A proprotor gearbox having a proprotor gearbox housing is configured to transmit torque and rotation energy to the mast. A lock assembly has first and second lock members. The first lock member is coupled to the mast between first and second mast bearings and configured to rotate with the mast. The second lock member is coupled to the proprotor gearbox housing. The lock assembly has a first position in which the first and second lock members are disengaged, thereby allowing rotation of the mast. The lock assembly has a second position in which the first and second lock members are engaged, thereby preventing rotation of the mast. The lock assembly is actuatable between the first and second positions.

First claim

What is claimed is:

1. A mast lockout system for a tiltrotor aircraft having a proprotor assembly, the system comprising:
a mast coupled to and rotatable with the proprotor assembly;
a proprotor gearbox having a proprotor gearbox housing, the proprotor gearbox configured to transmit torque and rotation energy to the mast;
first and second mast bearings configured to react loads from the mast to the proprotor gearbox housing; and
a lock assembly having first and second lock members, the first lock member coupled to the mast between the first and second mast bearings and configured to rotate with the mast, the second lock member coupled to the proprotor gearbox housing and configured to be nonrotatable;
wherein, the lock assembly has a first position in which the first and second lock members are disengaged, thereby allowing rotation of the mast;
wherein, the lock assembly has a second position in which the first and second lock members are engaged, thereby preventing rotation of the mast; and
wherein, the lock assembly is actuatable between the first and second positions.

2. The system as recited in claim 1 wherein the first lock member further comprises a collar assembly that is configured to be coupled to an exterior of the mast at a splined connection to prevent relative rotation therebetween.

3. The system as recited in claim 2 wherein the collar assembly further comprises an upper ring and a lower ring that are coupled together with a cone seat positioned therebetween, the cone seat configured to be received between the collar assembly and a groove of the mast to prevent axial movement of the collar assembly relative to the mast.

4. The system as recited in claim 3 wherein the upper ring further comprises first and second upper ring elements and wherein the lower ring further comprises first and second lower ring elements, the first upper ring element coupled to each of the first and second lower ring elements and the second upper ring element coupled to each of the first and second lower ring elements.

5. The system as recited in claim 4 wherein the first and second upper ring elements are out of phase with the first and second lower ring elements.

6. The system as recited in claim 4 wherein the first and second upper ring elements are ninety degrees out of phase with the first and second lower ring elements.

7. The system as recited in claim 1 wherein the second lock member further comprises at least one lock pin and wherein the first lock member further comprises at least one v-block, the at least one v-block configured to receive the at least one lock pin therein when the first and second lock members are engaged, thereby rotationally clocking the proprotor assembly and preventing rotation of the mast.

8. The system as recited in claim 7 further comprising a radial bearing coupled to the lock pin.

9. The system as recited in claim 1 wherein the second lock member further comprises a pair of oppositely disposed lock pins and wherein the first lock member further comprises a pair of oppositely disposed v-blocks, each of the v-blocks configured to receive one of the lock pins therein when the first and second lock members are engaged, thereby rotationally clocking the proprotor assembly and preventing rotation of the mast.

10. The system as recited in claim 9 further comprising a radial bearing coupled to each of the lock pins.

11. The system as recited in claim 1 wherein the second lock member further comprises a piston that is configured to actuate the lock assembly between the first and second positions.

12. The system as recited in claim 11 wherein the piston further comprises a hydraulically actuated piston.

13. The system as recited in claim 11 further comprising a generally cylindrical guide coupled to the proprotor gearbox housing and wherein, the piston is coupled to the guide by a splined connection to prevent relative rotation therebetween.

14. A mast lockout system for a tiltrotor aircraft having a proprotor assembly, the system comprising:
a mast coupled to and rotatable with the proprotor assembly;
a proprotor gearbox having a proprotor gearbox housing, the proprotor gearbox configured to transmit torque and rotation energy to the mast;
first and second mast bearings configured to react loads from the mast to the proprotor gearbox housing;
a first lock member coupled to the mast between the first and second mast bearings and configured to rotate with the mast, the first lock member including a collar assembly having first and second oppositely disposed v-blocks; and
a second lock member coupled to the proprotor gearbox housing and configured to be nonrotatable, the second lock member including first and second oppositely disposed lock pins;
wherein, the second lock member has a first position in which the first and second lock members are disengaged, thereby allowing rotation of the mast;
wherein, the second lock member has a second position in which each of the lock pins of the second lock member is received within a respective one of the v-blocks of the first lock member, thereby rotationally clocking the proprotor assembly and preventing rotation of the mast; and
wherein, the second lock member is configured to be actuated between the first and second positions.

15. The system as recited in claim 14 wherein the first lock member further comprises a collar assembly that is configured to be coupled to an exterior of the mast at a splined connection to prevent relative rotation therebetween and wherein the collar assembly further comprises an upper ring and a lower ring that are coupled together with a cone seat positioned therebetween, the cone seat configured to be received between the collar assembly and a groove of the mast to prevent axial movement of the collar assembly relative to the mast.

16. The system as recited in claim 15 wherein the upper ring further comprises first and second upper ring elements and wherein the lower ring further comprises first and second lower ring elements, the first upper ring element coupled to each of the first and second lower ring elements and the second upper ring element coupled to each of the first and second lower ring elements.

17. The system as recited in claim 16 wherein the first and second upper ring elements are out of phase with the first and second lower ring elements.

18. The system as recited in claim 14 wherein each of the lock pins is configured to slide against one of the v-blocks as the second lock member engages the first lock member to rotationally clock the proprotor assembly.

19. The system as recited in claim 14 further comprising a radial bearing coupled to each of the lock pins and wherein each of the radial bearings are configured to rotate against one of the v-blocks as the second lock member engages the first lock member to rotationally clock the proprotor assembly.

20. 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, for each proprotor assembly the aircraft comprising:
a mast coupled to and rotatable with the proprotor assembly;
a proprotor gearbox having a proprotor gearbox housing, the proprotor gearbox configured to transmit torque and rotation energy to the mast;
first and second mast bearings configured to react loads from the mast to the proprotor gearbox housing; and

Assignees

• Textron Innovations Inc

Inventors

• Przybyla Mark Alan
• Speller Charles Hubert

Classifications

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title

• B64C11/28

  Collapsible or foldable blades · CPC title

• B64D27/14

  within, or attached to, fuselages · CPC title

• B64D35/00

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