Helicopter pitch link with accessible adjustment features
AssigneeThe Boeing Company
InventorDaniel Podgurski
Life of this patent
Estimating the term…
Abstract
A helicopter pitch link assembly as described herein includes a length adjustment mechanism, such as a turnbuckle, that is accessible when the pitch link assembly is installed on a helicopter that utilizes a weather cover or canopy and a protective boot. The adjustment mechanism extends above the canopy and the protective boot, even when the rotor blades are in a neutral pitch position. This enables quick and easy access to the adjustment mechanisms while eliminating the need to support the rotor blades, which might otherwise be necessary to alleviate stress on the rotor blade hinge points and pitch link assembly.
Claims24
A helicopter blade pitch link assembly comprising:
- a first link member having a first end configured to be coupled to a pitch control mechanism for the helicopter;
- a protective boot interface feature located on said first link member;
- a second link member coupled to said first link member, said second link member having a first end configured to be coupled to a rotor blade for the helicopter, said first link member and said second link member defining a length for the helicopter blade pitch link assembly;
- and
- an adjustment mechanism coupled to said first link member and to said second link member, said adjustment mechanism being configured to adjust said length, and said protective boot interface feature being located between said adjustment mechanism and said first end of said first link member.
A helicopter blade pitch link assembly comprising:
- a first link member having a first end configured to be coupled to a pitch control mechanism for the helicopter;
- a second link member coupled to said first link member, said second link member having a first end configured to be coupled to a rotor blade for the helicopter, said first link member and said second link member defining a length for the helicopter blade pitch link assembly;
- an adjustment mechanism coupled to said first link member and to said second link member, said adjustment mechanism being configured to adjust said length;
- and
- a protective boot coupled to said first link member at a location between said adjustment mechanism and said first end of said first link member.
A helicopter assembly comprising:
- a pitch link assembly comprising:
- a first end configured to be coupled to a pitch control mechanism for the helicopter;
- a second end configured to be coupled to a rotor blade for the helicopter, said first end and said second end defining a length for said pitch link assembly;
- and
- an adjustment mechanism located between said first end and said second end, said adjustment mechanism being configured to adjust said length;
- a canopy configured to cover the pitch control mechanism for the helicopter, said canopy comprising a hole formed therein that receives said pitch link assembly, said first end being located below said canopy, and said second end being located above said canopy;
- and
- a protective boot coupled to said canopy, and coupled to said pitch link assembly at a location between said adjustment mechanism and said first end, said protective boot spanning space between said pitch link assembly and said canopy.
A helicopter blade pitch link assembly comprising:
- a link member configured to be coupled between a pitch control mechanism for the helicopter and a rotor blade for the helicopter;
- and
- a protective boot interface feature located on said link member, said protective boot interface feature comprising:
- a resilient material surrounding said link member, said resilient material having an inner surface attached to said link member, and having an outer surface;
- and
- a rigid outer shell surrounding said resilient material, said rigid outer shell having an inner surface attached to said outer surface of said resilient material, and having a contoured outer surface that forms a protrusion around said link member.
Dependencies are inferred from the claim text.