Spring-loaded link

Patent metadata

Field	Value
Publication number	US-11052993-B2
Application number	US-201916599483-A
Country	US
Kind code	B2
Filing date	Oct 11, 2019
Priority date	Oct 11, 2019
Publication date	Jul 6, 2021
Grant date	Jul 6, 2021

Abstract

An exemplary spring-loaded link for an aircraft including a spring interposed between a first and a second rod, the spring, when compressed, urging the first rod and the second rod away from each other.

First claim

What is claimed is:

1. A spring-loaded link for an aircraft, the spring-loaded link comprising:
a first rod having a cavity formed therein, the cavity comprising a cavity shoulder;
a second rod comprising a head shoulder and a head end extending from the head shoulder, the second rod slidingly disposed in the cavity, the head shoulder corresponding to the cavity shoulder;
a spring disposed in the cavity against the head shoulder and the cavity shoulder, the head end extending through a central portion of the spring;
wherein the spring, when compressed, urges the first rod and the second rod away from each other; and
a rod connector fixedly coupled to an exterior of the first rod and slidably coupled to an exterior of the second rod.

2. The spring-loaded link of claim 1 , wherein the first rod carries a first end connector and the second rod carries a second end connector.

3. The spring-loaded link of claim 1 , wherein the spring comprises a coned-disc.

4. The spring-loaded link of claim 1 , comprising:
a first connector end coupled to the first rod; and
a second connector end coupled to the second rod.

5. A blade lock for a tiltrotor aircraft to enable and disable a folding degree of freedom and a pitching degree of freedom of a rotor blade assembly, the blade lock comprising:
a lever;
a bellcrank; and
a spring-loaded link pivotally connected to the lever and the bellcrank, the spring-loaded link comprising a spring interposed between a first rod and a second rod, the spring, when compressed, urging the first rod and the second rod away from each other:
wherein the spring-loaded link is in a center position when the lever is in a locked position disabling the folding degree of freedom and the lever is secured in the locked position when the spring-loaded link is positioned in an over-center position.

6. The blade lock of claim 5 , wherein:
the first rod comprises a cavity disposing the spring; and
the second rod has a head end slidingly disposed in the cavity.

7. The blade lock of claim 5 , wherein the spring is one of a mechanical spring or a gas spring.

8. The blade lock of claim 5 , wherein the bellcrank is in contact with a hard stop when the spring-loaded link is in the over-center position.

9. The blade lock of claim 8 , further comprising a hard stop adjustment mechanism configured to selectively position the over-center position relative to the center position.

10. The blade lock of claim 9 , wherein:
the first rod comprises a cavity disposing the spring; and
the second rod has a head end slidingly disposed in the cavity.

11. The blade lock of claim 5 , wherein:
the bellcrank is a pitch lock configured to enable the pitching degree of freedom when the lever is in the locked position and to disable the pitching degree of freedom when the lever is moved out of the locked position; and
the bellcrank is in contact with a hard stop when the spring-loaded link is in the over-center position.

12. The blade lock of claim 11 , wherein:
the first rod comprises a cavity disposing the spring; and
the second rod has a head end slidingly disposed in the cavity.

13. The blade lock of claim 11 , further comprising a hard stop adjustment mechanism configured to selectively position the over-center position relative to the center position.

14. The blade lock of claim 13 , wherein:
the first rod comprises a cavity disposing the spring; and
the second rod has a head end slidingly disposed in the cavity.

15. A method for enabling and disabling a folding degree of freedom and a pitching degree of freedom of a rotor blade assembly of a tiltrotor aircraft, the method comprising:
rotating a blade lock comprising a spring-loaded link pivotally connecting a pitch lock to a fold lock from a pitch locked position to a fold locked position, wherein in the fold locked position the spring-loaded link is located in a center position; and
rotating the pitch lock into contact with a hard stop thereby positioning the spring-loaded link in an over-center position:
wherein the spring-loaded link comprises a spring interposed between a first rod and a second rod, the spring, when compressed, urging the first rod and the second rod away from each other.

16. The method of claim 15 , wherein:
the first rod comprises a cavity disposing the spring; and
the second rod has a head end slidingly disposed in the cavity.

17. The method of claim 15 , further comprising a hard stop adjustment mechanism coupled to one of the hard stop or the pitch lock.

18. The method of claim 15 , further comprising a set screw threadedly connected to one of the hard stop or the pitch lock, the set screw configured to set the over-center position relative to the center position.

19. The method of claim 18 , wherein:
the first rod comprises a cavity disposing the spring; and
the second rod has a head end slidingly disposed in the cavity.

Assignees

• Bell Textron Inc

Inventors

• Cravener Kyle Thomas
• Foskey Christopher Edward
• Maresh Andrew

Classifications

• B64C27/605

  including swash plate, spider or cam mechanisms · CPC title

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title

• B64C11/385

  comprising feathering, braking or stopping systems · CPC title

• B64C27/57

  automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust · CPC title

• B64C27/64

  using fluid pressure, e.g. having fluid power amplification · CPC title