Trim tab retention system, an aircraft employing same and a method of retaining a trim tab within a blade housing

Patent metadata

Field	Value
Publication number	US-10589849-B2
Application number	US-201615136077-A
Country	US
Kind code	B2
Filing date	Apr 22, 2016
Priority date	Apr 24, 2015
Publication date	Mar 17, 2020
Grant date	Mar 17, 2020

Abstract

A trim tab for use in a blade housing includes a cavity connected to an opening extending from the cavity out a trailing edge of the blade housing, the cavity has a first dimension which is greater than a second dimension of the opening at a same spanwise location of the blade housing. The trim tab has a trim portion, a head portion having a head dimension substantially similar to the first dimension, and a tail portion connecting the trim portion and the head portion. The tail portion has a tail dimension substantially similar to the second dimension such that the trim tab is retainable by the blade housing when the head portion is disposed within the cavity and the tail portion is disposed within the opening.

First claim

What is claimed is:

1. A method of retaining a trim tab within a blade housing, comprising:
providing a blade housing having a cavity including a first portion having a first dimension and a second portion having a second dimension, wherein the first dimension and the second dimension are orthogonal to both a spanwise and a chordwise direction of the blade housing;
elastically deforming a portion of the blade housing to permit a head portion of the trim tab to pass through the second portion of the cavity;
positioning the head portion of a trim tab within the first portion of the cavity in the blade housing; and
positioning a tail portion of the trim tab within the second portion of the cavity, wherein the first dimension is larger than the second dimension such that the trim tab is retained within the blade housing with a head dimension of the head portion being larger than the second dimension.

2. An aircraft comprising:
a fuselage;
an engine in operable communication with the fuselage; and
a rotor assembly in operable communication with the engine having at least one rotor blade, the rotor blade including a blade housing having a cavity connected to an opening extending from the cavity out a trailing edge of the blade housing, the cavity having a first dimension which is greater than a second dimension of the opening at a same spanwise location of the blade housing; and
a trim tab including a trim portion, a head portion having a head dimension substantially similar to the first dimension, and a tail portion connecting the trim portion and the head portion, the tail portion having a tail dimension substantially similar to the second dimension such that the trim tab is retainable by the blade housing when the head portion is disposed within the cavity and the tail portion is disposed within the opening;
wherein the blade housing is elastically deformable to permit the head portion to pass through the second portion of the cavity.

3. The aircraft of claim 2 , wherein the first dimension and the second dimension are oriented in a direction of lift for the blade relative to the aircraft.

4. The aircraft of claim 2 , wherein the head dimension prevents the head portion from moving through the second dimension in a chordwise direction of the blade housing during operation.

5. The aircraft of claim 2 , wherein the head portion is tapered in a direction away from the tail portion to cause the second dimension of the opening to temporarily increase when the head portion is moved through the opening into the cavity.

6. The aircraft of claim 2 , wherein the at least one trim tab is metal.

7. The aircraft of claim 2 , wherein the at least one trim tab is aluminum.

8. The aircraft of claim 2 , further comprising a retainer portion comprising the cavity, the retainer portion comprises a material that isolates strain from the at least one trim tab.

9. The aircraft of claim 2 , further comprising a retainer portion comprising the cavity, the retainer portion comprises a member made of fibers of carbon or glass in an epoxy resin.

10. The aircraft of claim 9 , wherein the at least one trim tab is a plurality of trim tabs oriented adjacent one another in a spanwise direction.

11. The aircraft of claim 9 , wherein the at least one trim tab is removable from the cavity by first moving the at least one trim tab spanwise relative to the blade housing to an area of the cavity such that the head portion can be moved out of the cavity in a chordwise direction.

12. The aircraft of claim 9 , wherein the head portion is tapered toward the tail portion to cause the second dimension to temporarily increase when the head portion is moved therethrough.

13. The aircraft of claim 2 , further comprising a retainer portion comprising the cavity, the retainer portion comprises a member made of titanium.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Conti Timothy James
• Schmaling David N
• Meyer Leon M
• Chen Yih-Fam

Classifications

• B64C27/467

  Aerodynamic features · CPC title

• B64C27/473 Primary

  Constructional features · CPC title

• B64C27/10

  arranged coaxially · CPC title