Sikorsky Aircraft Corporation

United Technologies Corporation

Richard Joseph Simkulak

Kevin P Leahy

Wonsub Kim

Frank M Caputo

David A Kovalsky

Terry M Boustead

Kenneth M Adams

Michael J Shimkus

Daniel Ciesielski

George N Sepe

Robert L Folts

A rotor blade is provided. The rotor blade includes a blade portion, a tip cap formed to define a dimple, a fastener and a doubler. The fastener includes a flat-headed shaft and is disposable such that the flat-headed shaft extends through the blade portion and the tip cap at the dimple. The fastener is configured to urge the blade portion toward the tip cap. The doubler includes a dimpled portion disposable between the tip cap and a portion of the flat-headed shaft at the dimple and an exterior portion. The exterior portion is disposable flush with respective exterior surfaces of the blade portion and the flat-headed shaft.

Metallic dimpled doubler

A main rotor blade assembly is provided including a spar which comprises a main section. A main core is positioned adjacent a trailing side of the main section of the spar. A tip assembly includes a main tip core and a tip end pocket core. The tip assembly is positioned adjacent an outboard end of the main core and the spar such that the main tip core is substantially aligned with a longitudinal axis of the main core and the tip end pocket core is substantially aligned with a longitudinal axis of the spar. At least a portion of both the main tip core and the tip end pocket core comprises a high density core. An upper composite skin and a lower composite skin extend over the spar, the main core, the main tip core, and the tip end pocket core. A portion of the upper composite skin and the lower composite skin has a thickness sufficient to be load bearing.

Main rotor blade with composite integral skin and cuff

A rotor blade for a rotary-wing aircraft includes a core member having a first end that extends to a second end, and a spar member positioned about the core member. The spar member includes a first end section that extends to a second end section. A tip core assembly is mounted at the second end section of the spar member. The tip core assembly is formed from a honeycombed material. The rotor blade also includes a rotor blade skin mounted about the spar member and the tip core assembly.

Rotor blade for a rotary-wing aircraft

A main rotor blade assembly includes a main spar with an integral cuff. The main spar is directly to a rotor hub assembly through the integral cuff.

Main rotor blade with integral cuff

A main rotor blade assembly includes a tip cap removably mountable to an outboard end section of a forward tip spar section and an aft tip spar section.

Main rotor blade with removable tip cap

A main rotor blade assembly having a blade skin bonded to a main spar and a tip spar.

Main rotor blade with integral tip section

A main rotor blade assembly includes a tip spar which defines a tip spar non-straight form, an upper blade skin which defines an upper blade skin non-straight form adjacent to the tip spar non-straight form and a lower blade skin which defines a lower blade skin non-straight form adjacent to the tip spar non-straight form.

A composite braiding apparatus has a rotatable cantilever mandrel support 20 that is capable of supporting multiple mandrels 17a and 17b. The mandrels can be properly oriented to be braided without removing them from the mandrel support 20. Once the braiding operation has begun on one mandrel 17, subsequent mandrels can be mounted on the mandrel support 20 while braiding is taking place. Then, when a braiding operation is completed, the other mandrel 17 can be moved into proper position for braiding. The invention also allows one mandrel 17a (or 17b) to be braided while the opposite mandrel 17b (or 17a) that is not being braided can be worked on manually without stopping the braiding operation. In accordance with another embodiment of the invention, a braiding apparatus 10' has two braid ring assemblies 11a and 11b. Both braiding rings 12a and 12b are mounted at opposite ends of a guide track 26. The inclusion of the second braiding ring 12b allows a second set of composite filaments 28 to be wound onto a mandrel 17a (or 17b) by a 180 degree rotation of the mandrel support 20, and possibly allows simultaneous braiding of two mandrels 17a and 17b.

Multiple mandrel/braiding ring braider

An apparatus for molding hollow composite articles having a plurality of internal webs. A mandrel assembly apparatus includes slidable sidewall members, an inflatable pressure membrane surrounding the length of the slidable sidewall members and actuator means mounted on the interior of the sidewall members for lateral displacement thereof together with the inflatable membrane. Adjacent mandrel assemblies accurately position the internal webs of the composite article mechanically, while the inflatable membranes serve to compact the web laminates. The expandable sidewall members also prevent bridging or tearing of the pressure membrane associated with the formation of inner corner radii.

Growing community of inventors

Meriden, CT, United States of America

Richard Joseph Simkulak