Robert Chad Self

Author:

Robert C. Self

ISBN #:

0521551579

Author:

Robert C. Self

ISBN #:

0754656152

Author:

Robert C. Self

ISBN #:

0824019318

Author:

Robert Self

ISBN #:

0754652661

Author:

Robert T. Self

ISBN #:

0700615512

Author:

Robert T. Self

ISBN #:

0805771603

Author:

Robert T. Self

ISBN #:

0816637903

Author:

Robert O. Self

ISBN #:

0691070261

US Patent:

20130287571, Oct 31, 2013

Filed:

Apr 15, 2013

Appl. No.:

13/862515

Inventors:

Paul B. Sherrill - Grapevine TX, US
Robert A. Self - Euless TX, US

Assignee:

Bell Helicopter Textron Inc. - Fort Worth TX

International Classification:

F01D 5/14

US Classification:

416146 R

Abstract:

The electrical harness system is configured for routing a harness between a rotor yoke and a rotor blade. A recess in an inboard cap member is configured to house a connector and an associated harness. As the recess extends along a radial path in the chordwise direction of the rotor blade, the harness is configured to lie within the recess. Operationally induced centrifugal forces promote positioning the slack of harness within the recess, while the slack in the harness remains available for relative dynamic movements between the rotor blade and the rotor yoke. Such a routing of the harness reduces aerodynamic drag and minimizes damage that could otherwise occur to the harness.

US Patent:

20210078699, Mar 18, 2021

Filed:

Sep 18, 2019

Appl. No.:

16/575329

Inventors:

- Fort Worth TX, US
Robert Patrick Wardlaw - Keller TX, US
Robert Alan Self - Fort Worth TX, US

International Classification:

B64C 27/473
B64C 27/00
F01D 5/28
B29D 99/00

Abstract:

In an implementation, a rotor blade for a helicopter may include an outer layer. The outer layer may have a leading edge region and a trailing edge region and may define a cavity. The leading edge region may include a first shape at least partially corresponding with an airfoil, e.g., a wing. An insert may be included within the cavity and be encompassed thereby. The insert may include a shape that substantially corresponds with the first shape, e.g., the insert may substantially correspond with a leading edge of an airfoil. The insert may have a plurality of weight shot each of which may be surrounded by a binding agent.

US Patent:

20180327089, Nov 15, 2018

Filed:

May 9, 2017

Appl. No.:

15/590736

Inventors:

- Fort Worth TX, US
Nathan Patrick Green - Mansfield TX, US
Robert Alan Self - Ft. Worth TX, US
Mark Adam Wiinikka - Hurst TX, US

International Classification:

B64C 27/51
B64C 27/39

Abstract:

A system and method for attaching a damper to a tail rotor blade includes a cuff that is integral with the rotor blade. The cuff has upper and lower lugs formed by extending a skin over a blade core of the rotor blade. The skin extends past the blade core to the root end of the rotor blade. The rod end of the damper is inserted into an opening between the lugs. The rod end of the damper is coupled to the blade with a bolt through aligned holes in the lugs. The cuff also couples the rotor blade to the grip inside the cuff. The cuff includes a same material as that forming the skin. Sacrificial buffer pads are applied to interior faces of the lugs. The buffer pads permit a distance between the lugs to be machined within a tolerance without removing skin from the cuff.