公开(公告)号：US20200346382A1

公开(公告)日：2020-11-05

申请号：US16814622

申请日：2020-03-10

Applicant: Bell Helicopter Textron Inc.

Inventor： David G. Carlson ,  Douglas K. Wolfe ,  James A. Cordell

IPC: B29C48/05 ,  B29C63/00 ,  B64C11/16 ,  B32B27/02 ,  B64C3/00 ,  B29C70/52 ,  B29C64/118 ,  B29C33/38

Abstract: In one embodiment, an assembly fixture may include a base structure including a plurality of strands of a fiber-reinforced thermoplastic material comprising a thermoplastic embedded with a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is aligned within each strand of the plurality of strands, and wherein the base structure further comprises an anisotropic thermal expansion property based on an orientation of the plurality of reinforcement fibers within the base structure, The assembly fixture may further include a plurality of fastening structures coupled to the base structure, wherein the plurality of fastening structures is configured to fasten a plurality of components of a composite structure for assembly using a heated bonding process.

公开(公告)号：US10654208B2

公开(公告)日：2020-05-19

申请号：US15710797

申请日：2017-09-20

Applicant: Bell Helicopter Textron Inc.

Inventor： David G. Carlson ,  Douglas K. Wolfe ,  James A. Cordell

IPC: B29C41/02 ,  B29C48/05 ,  B29C63/00 ,  B64C11/16 ,  B32B27/02 ,  B64C3/00 ,  B29C70/52 ,  B29C64/118 ,  B29C33/38 ,  B29K105/10 ,  B29K105/14 ,  B29L31/00

Abstract: In one embodiment, a method may comprise heating a composite material into a viscous form, wherein the composite material comprises a thermoplastic and a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is randomly arranged within the thermoplastic. The method may further comprise extruding a plurality of strands of the composite material, wherein extruding the plurality of strands causes the plurality of reinforcement fibers within each strand to align. The method may further comprise arranging the plurality of strands of the composite material to form an assembly fixture, wherein the assembly fixture comprises an anisotropic thermal expansion property, and wherein the anisotropic thermal expansion property is based on an orientation of the plurality of reinforcement fibers within the assembly fixture.

公开(公告)号：US20180001579A1

公开(公告)日：2018-01-04

申请号：US15423939

申请日：2017-02-03

Applicant: Bell Helicopter Textron Inc.

Inventor： David G. Carlson ,  John R. McCullough ,  Douglas K. Wolfe ,  Andrew G. Baines ,  George R. Decker

IPC: B29C70/34 ,  B29C70/54 ,  B29C35/02 ,  B29C70/06 ,  B29D99/00 ,  B29L31/30 ,  B64C1/12 ,  B64C3/26 ,  B64C29/00

CPC classification number: B29C70/34 ,  B29C35/02 ,  B29C65/48 ,  B29C70/06 ,  B29C70/30 ,  B29C70/545 ,  B29C2793/009 ,  B29D99/001 ,  B29D99/0089 ,  B29L2031/3076 ,  B29L2031/3085 ,  B32B3/12 ,  B32B7/12 ,  B32B2250/05 ,  B32B2305/024 ,  B32B2605/18 ,  B64C1/12 ,  B64C3/185 ,  B64C3/24 ,  B64C3/26 ,  B64C29/0033 ,  B64F5/00 ,  B64F5/10 ,  Y02T50/43

Abstract: In one aspect, there is a method of making a pre-cured laminate having a total number of plies in a mold, the mold having a periphery defined by a forward edge, an aft edge, and outboard ends. The method includes selecting a first plurality of resin impregnated plies that continuously extend beyond the periphery of the mold, the first plurality of resin impregnated plies includes at least 50 percent of the total number of plies; laying the plies in a mold; compacting the plies in a mold; and pre-curing the plies to form a pre-cured laminate, which can extend beyond the periphery of the mold. In an embodiment, a pre-cured laminate includes a first plurality of resin impregnated plies that continuously extend beyond the periphery of the mold, the first plurality of resin impregnated plies includes at least 50 percent of the total number of plies.

公开(公告)号：US20170225765A1

公开(公告)日：2017-08-10

申请号：US15424588

申请日：2017-02-03

Applicant: Bell Helicopter Textron Inc.

Inventor： Douglas K. Wolfe ,  David G. Carlson ,  John R. McCullough ,  George R. Decker

IPC: B64C3/18

Abstract: In one aspect, there is provided a spar member for an aircraft wing including a support beam having an interior surface, an exterior surface, and opposing ends configured for an aircraft wing, the interior surface and exterior surface disposed between the opposing ends; and a first spar flange extending generally laterally from the exterior surface, the first spar flange configured for attachment with a first wing skin. The first spar flange can be an upper or lower spar flange. In some embodiments, the first spar flange is at an acute angle relative to the exterior surface of the support beam. In certain embodiments, the first spar flange is at an angle of from about 50 degrees to about 85 degrees relative to the exterior surface of the support beam.

公开(公告)号：US11059561B2

公开(公告)日：2021-07-13

申请号：US15870977

申请日：2018-01-14

Applicant: Bell Helicopter Textron Inc.

Inventor： James Everett Kooiman ,  David G. Carlson ,  George Ryan Decker ,  Jeffrey Matthew Williams ,  Douglas K. Wolfe

IPC: B64C3/18 ,  B64C29/00 ,  B64C3/26

Abstract: A torque box rib includes an upper rib cap configured to be coupled to an upper skin of a wing, a lower rib cap configured to be coupled to a lower skin of the wing, a forward post configured to be coupled to a forward spar of the wing, an aft post configured to be coupled to an aft spar of the wing, and a rib web configured to be coupled to the upper rib cap, the lower rib cap, the forward post, and the aft post.

公开(公告)号：US10850474B2

公开(公告)日：2020-12-01

申请号：US15878301

申请日：2018-01-23

Applicant: Bell Helicopter Textron Inc.

Inventor： James Everett Kooiman ,  David M. Carlson ,  Douglas K. Wolfe ,  Jonathan Alexander Freeman

IPC: B32B3/26 ,  B32B3/12 ,  B32B37/10 ,  B64C3/26 ,  B32B27/06 ,  B29C70/34 ,  B32B38/00 ,  B32B37/14

Abstract: A method of fabricating a panel includes laying up a first laminate on a tooling surface, laying a first layer of thermoplastic on an inner surface of the first laminate, laying a large cell carbon core on the first layer of thermoplastic, laying a second layer of thermoplastic across the large cell carbon core, laying a second laminate on the second layer of thermoplastic, creating a sealed core pocket by bonding the edges of the first and second layers of the thermoplastic surrounding a perimeter of the core, increasing pressure within the core pocket, increasing pressure on the outer surface of the second laminate, heating the panel to a desired curing temperature, and maintaining the increased pressures and temperature for a desired curing duration.

公开(公告)号：US20180001590A1

公开(公告)日：2018-01-04

申请号：US15423981

申请日：2017-02-03

Applicant: Bell Helicopter Textron Inc.

Inventor： David G. Carlson ,  John R. McCullough ,  Douglas K. Wolfe ,  Andrew G. Baines ,  George R. Decker

IPC: B32B3/12 ,  B29C65/48 ,  B29D99/00 ,  B32B7/12 ,  B64C29/00 ,  B29L31/30 ,  B64C1/12 ,  B64C3/26

CPC classification number: B29C70/34 ,  B29C35/02 ,  B29C65/48 ,  B29C70/06 ,  B29C70/30 ,  B29C70/545 ,  B29C2793/009 ,  B29D99/001 ,  B29D99/0089 ,  B29L2031/3076 ,  B29L2031/3085 ,  B32B3/12 ,  B32B7/12 ,  B32B2250/05 ,  B32B2305/024 ,  B32B2605/18 ,  B64C1/12 ,  B64C3/185 ,  B64C3/24 ,  B64C3/26 ,  B64C29/0033 ,  B64F5/00 ,  B64F5/10 ,  Y02T50/43

Abstract: In one aspect, there is a method of making a composite skin for a tiltrotor aircraft including providing a first skin in a mold, the first skin having a periphery defined by a forward edge, an aft edge, and outboard ends; providing a plurality of honeycomb panels having an array of large cells onto the first skin, each cell having a width of at least 1 cm; assembling the plurality of honeycomb panels along the longitudinal axis of the first skin to form a honeycomb core having an outer perimeter within the periphery of the first skin; positioning a second skin onto the honeycomb core, the second skin having an outer perimeter within the periphery of the first skin; and curing an adhesive to create a bond between the first skin, the honeycomb core, and the second skin to form a composite skin.