Blade fold system monitoring

Patent metadata

Field	Value
Publication number	US-9108727-B2
Application number	US-201113086003-A
Country	US
Kind code	B2
Filing date	Apr 13, 2011
Priority date	Jun 16, 2010
Publication date	Aug 18, 2015
Grant date	Aug 18, 2015

Abstract

A rotor blade fold system for an aircraft includes one or more actuators operably connected to one or more blade components of one or more rotor blades of the aircraft. One or more sensors are located at the one or more rotor blades and are configured to sense operation of the one or more blade components. A fold control system is configured to monitor output from the one or more sensors and is capable of stopping operation of the blade fold system, via communication with the one or more actuators, if the one or more blade components are not operating within predetermined limits.

First claim

The invention claimed is:

1. A rotor blade fold system for an aircraft comprising:
one or more actuators operably connected to one or more blade components of a plurality of rotor blades of the aircraft;
one or more sensors disposed at the plurality of rotor blades configured to sense operation of the one or more blade components; and
a fold control system which is configured to monitor output from the one or more sensors and capable of stopping operation of the blade fold system, via communication with the one or more actuators, if the one or more blade components are not operating within predetermined limits, the fold control system monitoring progress and rate of the folding of a first blade of the plurality of rotor blades and comparing it to a progress and rate of the folding of a second, adjacent blade of the plurality of rotor blades.

2. The blade fold system of claim 1 , wherein the one or more blade components include a pitch lock, a hinge lock, a fold hinge and a fold actuator.

3. The blade fold system of claim 2 , wherein a first sensor of one or more sensors is disposed at the pitch lock.

4. The blade fold system of claim 3 , wherein the first sensor is configured to determine if the pitch lock is engaged and/or position of the actuator along its stroke.

5. The blade fold system of claim 2 , wherein a second sensor of the one or more sensors is disposed at the hinge lock.

6. The blade fold system of claim 5 , wherein the second sensor is configured to determine if the hinge lock is released.

7. The blade fold system of claim 5 , wherein the fold control system compares a release time for the hinge lock to release to a predetermined limit, and is capable of stopping operation of the blade fold system if the release time exceeds the predetermined limit.

8. The blade fold system of claim 2 , wherein a third sensor of one or more sensors is disposed at the hinge.

9. The blade fold system of claim 8 , wherein the third sensor is configured to determine a rate of movement of the a rotor blade of the plurality of rotor blades at the hinge.

10. The blade fold system of claim 8 , wherein the fold control system compares a rate of movement of the rotor blade at the hinge to a predetermined limit, and is capable of stopping operation of the blade fold system if the rate of movement exceeds the predetermined limit.

11. An aircraft comprising:
a rotor including:
a rotor hub; and
a plurality of rotor blades extending from the rotor hub; and

a rotor blade fold system as recited in claim 1 .

12. A method of folding plurality of rotor blades of an aircraft comprising:
activating one or more actuators operably connected to the plurality of rotor blades;
urging the plurality of blades toward a folded position via activation of the one or more actuators;
monitoring one or more blade components of the plurality of rotor blades via one or more sensors disposed at the plurality of rotor blades;
determining if the one or more blade components are operating within a predetermined limit;
stopping operation of the blade fold system if the one or more blade components are not operating within the predetermined limit;
monitoring progress and rate of the folding of a first blade of the plurality of rotor blades and comparing it to a progress and rate of the folding of a second, adjacent blade of the plurality of rotor blades;
slowing or stopping the blade fold operation if the progress of the second blade is slower than desired, compared to the progress of the first blade.

13. The method of claim 12 , wherein the one or more blade components include a pitch lock, a hinge lock, and/or a hinge.

14. The method of claim 13 , further comprising monitoring the pitch lock via a first sensor of one or more sensors.

15. The method of claim 14 , further comprising:
comparing an engagement time for the pitch lock to engage to a predetermined limit; and
stopping operation of the blade fold system if the engagement time exceeds the predetermined limit.

16. The method of claim 13 , further comprising monitoring the hinge lock via a second sensor of the one or more sensors.

17. The method of claim 16 , further comprising:
comparing a release time for the hinge lock to release to a predetermined limit; and
stopping operation of the blade fold system if the release time exceeds the predetermined limit.

18. The method of claim 13 , further comprising monitoring the hinge via a third sensor of the one or more sensors.

19. The method of claim 18 , further comprising:
comparing a rate of movement of the rotor blade at the hinge to a predetermined limit; and
stopping operation of the blade fold system if the rate of movement exceeds the predetermined limit.

Assignees

• Hoover Eric D
• Sikorsky Aircraft Corp

Inventors

• Hoover Eric D

Classifications

• B64C27/50 Primary

  Blades foldable to facilitate stowage of aircraft · CPC title