Kenneth D Cominsky from Lake Stevens, WA, age 59

Us Patents

Method Of Fabricating A Mandrel For Cobond Assembly
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US Patent:

20050023721, Feb 3, 2005
Filed:

Aug 26, 2004
Appl. No.:

10/926700
Inventors:

Kenneth Cominsky - Mansfield TX, US
International Classification:

B29C033/40
B29C035/08
B29C041/02
B29C045/00
US Classification:

264219000, 264401000, 264328100, 264236000, 264334000, 264328200, 425174400, 425542000
Abstract:

A method and system for fabricating mandrels which are used as pressure intensifiers for cobonding or consolidation fabrication of composite assemblies. Mandrel molds are created using rapid prototyping, such as stereolithography, generated directly from a virtual model which is created with a processor aided design type program requiring little or no engineering drawings. A curable fluid material is then injected into a mold cavity which defines the mandrel. The mandrel can be applied in a specific process for cobonding cured detailed parts using an uncured element enabling intensified pressure to the joint or fillet area during the bonding process.

Method And Apparatus For Z-Direction Reinforcement Of Composite Laminates
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US Patent:

20060113027, Jun 1, 2006
Filed:

Nov 3, 2003
Appl. No.:

10/533427
Inventors:

J. Hethcock - Colleyville TX, US
J. Drennan - Dallas TX, US
Kenneth Cominsky - Mansfield TX, US
International Classification:

B29C 47/00
US Classification:

156148000, 156245000
Abstract:

A method and apparatus for Z-direction reinforcement of composite laminates is disclosed. Discrete fibers () are pulled through a fiber composite preform () in the Z-direction by needles (27) having bars () thereon to insert the Z-direction reinforcement () into the composite preform () from a discrete fiber mat (23) having discrete fibers () therein.

Composite Hat Stiffener, Composite Hat-Stiffened Pressure Webs, And Methods Of Making The Same
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US Patent:

20130344291, Dec 26, 2013
Filed:

Jun 24, 2012
Appl. No.:

13/531583
Inventors:

Steven E. Pearson - Lynnwood WA, US
Matthew M. Whitmer - Seattle WA, US
Rebecca M. Dixon - Wilmington DE, US
Jason L. Firko - Wilmington DE, US
Douglas G. Marciniak - Lake Stevens WA, US
Kenneth D. Cominsky - Mukilteo WA, US
Martin G. Andrews - Chadds Ford PA, US
Assignee:

The Boeing Company - Seal Beach CA
International Classification:

B32B 1/00
B64C 1/10
B32B 1/04
B32B 37/02
US Classification:

428157, 156212, 244121, 428174
Abstract:

There is provided a composite hat stiffener, a composite hat-stiffened pressure web, and a method of making the same. The composite hat stiffener has a composite hat section having a first side and a second side. The composite hat stiffener further has a plurality of composite stiffening plies coupled to the composite hat section. The plurality of composite stiffening plies include a body ply coupled to the first side of the composite hat section, a wrap ply coupled the body ply, and a base ply coupled to the body ply and the wrap ply. The composite hat stiffener further has a pair of radius filler noodles coupled to the composite hat section and disposed between the plurality of composite stiffening plies. The composite hat stiffener further has an outer ply coupled to the second side of the composite hat section.

Mandrel Fabrication For Cobond Assembly
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US Patent:

20020125613, Sep 12, 2002
Filed:

Mar 8, 2001
Appl. No.:

09/801461
Inventors:

Kenneth Cominsky - Mansfield TX, US
International Classification:

B29C033/40
B29C035/08
B29C041/02
B29C045/00
US Classification:

264/401000, 264/219000, 264/328100, 264/334000, 425/174400, 425/542000
Abstract:

A method and system for fabricating mandrels which are used as pressure intensifiers for cobonding or consolidation fabrication of composite assemblies. Mandrel molds are created using rapid prototyping, such as stereolithography, generated directly from a virtual model which is created with a processor aided design type program requiring little or no engineering drawings. A curable fluid material is then injected into a mold cavity which defines the mandrel. The mandrel can be applied in a specific process for cobonding cured detailed parts using an uncured element enabling intensified pressure to the joint or fillet area during the bonding process.

Fuselage Sections Having Tapered Wing Rib Interfaces
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US Patent:

20210107619, Apr 15, 2021
Filed:

Oct 9, 2019
Appl. No.:

16/597081
Inventors:

- Chicago IL, US
Kenneth D. Cominsky - Lake Stevens WA, US
Branko Lakic - Kirkland WA, US
International Classification:

B64C 1/26
B64C 3/18
Abstract:

Fuselage sections having tapered wing rib interfaces are disclosed. A disclosed example apparatus includes a rib associated with a fuselage section, and a wing interface surface defined by the rib, where the wing interface surface is tapered relative to a longitudinal axis of the fuselage section from an aft end of the fuselage section to a fore end of the fuselage section.

Beaded Panels And Method Of Forming Beaded Panels
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US Patent:

20200115026, Apr 16, 2020
Filed:

Oct 11, 2018
Appl. No.:

16/158028
Inventors:

- Chicago IL, US
Kenneth D. Cominsky - Mukilteo WA, US
International Classification:

B64C 1/06
B29C 70/34
Abstract:

Beaded panels and method of forming beaded panels. A beaded panel as described herein includes a base structure comprising a sheet of material, and beads that comprise a protrusion on a first side of the base structure, and a concavity on an opposing second side of the base structure. A geometry of the beads comprises a center section having a conic shape about a longitudinal axis, flared sections symmetric about the center section along the longitudinal axis, and a transition section that curves outward from a base of the center section and the flared sections to blend with a flat surface on the first side of the base structure.

Friction Stir Welded Wingtip Torque Box
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US Patent:

20180015996, Jan 18, 2018
Filed:

Jul 14, 2016
Appl. No.:

15/209974
Inventors:

- Chicago IL, US
Kenneth D. Cominsky - Mukilteo WA, US
Steven S. Heer - Lake Stevens WA, US
David P. Heck - St. Charles MO, US
Benjamin D. Smith - Maryland Heights MO, US
John A. Baumann - St. Charles MO, US
Matthew D. Uhlman - Kirkland WA, US
Burke L. Reichlinger - Kent WA, US
Eric E. Thomas - St. Charles MO, US
James P. Dobberfuhl - Clinton WA, US
Assignee:

The Boeing Company - Chicago IL
International Classification:

B64C 3/18
B64C 3/26
C25D 11/04
B23K 20/233
B23K 20/12
B23K 103/10
B23K 101/12
Abstract:

Provided are wingtip torque boxes and methods of fabricating such boxes using friction stir welding. Specifically, a wingtip torque box may be formed by friction stir welding two monolithic clamshells along their respective spars thereby forming a new monolithic structure. Use of the friction stir welding and monolithic clamshells simplifies the overall fabrication process and yields a robust wingtip torque box that can be bolted on or otherwise attached to an aircraft wing. The wingtip torque box may include internal grid stiffeners and/or external stiffeners that may be also monolithic with other components of the box. For example, the stiffeners may be machined in spars or skin portions of the clamshells during fabrication of clamshells. The wingtip torque box may have a continuous cavity extending between the ends and, in some embodiments, between spars of the box and providing access for performing various operations inside the box.