Martin J Hansen

US Patent:

20130149164, Jun 13, 2013

Filed:

Dec 13, 2011

Appl. No.:

13/324254

Inventors:

Martin Wayne Hansen - Edgewood WA, US

Assignee:

THE BOEING COMPANY - Chicago IL

International Classification:

F01D 5/14
B32B 37/10
B32B 37/02

US Classification:

416226, 156178, 156 92, 156538

Abstract:

An airfoil is fabricated by assembling cured skins with spars having cured spar webs and uncured spar chords. The skins are bonded to the spars by curing the spar chords.

US Patent:

20200368977, Nov 26, 2020

Filed:

Aug 12, 2020

Appl. No.:

16/991933

Inventors:

- Chicago IL, US
Samuel F. Zambrana - Auburn WA, US
Daniel M. Rotter - Lake Forest Park WA, US
Michael Robert Chapman - Federal Way WA, US
Stephen K. Halladin - Renton WA, US
Benjamin Bowen Lee - Tacoma WA, US
Joshua Dee Little - Marysville WA, US
Douglas Alan McCarville - Bonney Lake WA, US
Jason A. Medenciy - Seattle WA, US
Russell D. Chiupka - Kirkland WA, US
Marcin Artur Rabiega - Kent WA, US
Andrey F. Yurchik - Redmond WA, US
Martin W. Hansen - Edgewood WA, US
Thomas P. Harper - Seattle WA, US

International Classification:

B29C 70/30
B29C 70/38
B29C 31/08
B29C 65/02

Abstract:

Composite structure fabrication systems and methods. The systems include a plurality of ply carriers, each of which is configured to support at least one ply segment, and an elongate forming mandrel, which defines an elongate ply forming surface that is shaped to define a surface contour of the composite structure. The systems further include a carrier transfer device, which is configured to selectively convey a selected ply carrier from a ply kitting area to an intermediate location, and a forming machine, which is configured to deform the selected ply carrier and a respective ply segment over a selected portion of the elongate ply forming surface. The forming machine further is configured to separate the selected ply carrier from the respective ply segment and return the selected ply carrier to the carrier transfer device. The methods include methods of operating the systems.

US Patent:

20160368226, Dec 22, 2016

Filed:

Jun 16, 2015

Appl. No.:

14/740493

Inventors:

- Huntington Beach CA, US
Samuel F. Zambrana - Auburn WA, US
Daniel M. Rotter - Lake Forest Park WA, US
Michael Robert Chapman - Federal Way WA, US
Stephen K. Halladin - Renton WA, US
Benjamin Bowen Lee - Tacoma WA, US
Joshua Dee Little - Marysville WA, US
Douglas Alan McCarville - Bonney Lake WA, US
Jason A. Medenciy - Seattle WA, US
Russell D. Chiupka - Kirkland WA, US
Marcin Artur Rabiega - Kent WA, US
Andrey F. Yurchik - Redmond WA, US
Martin W. Hansen - Edgewood WA, US
Thomas P. Harper - Seattle WA, US

Assignee:

The Boeing Company - Huntington Beach CA

International Classification:

B29C 70/30
B64F 5/00
B29C 65/02

Abstract:

Composite structure fabrication systems and methods. The systems include a plurality of ply carriers, each of which is configured to support at least one ply segment, and an elongate forming mandrel, which defines an elongate ply forming surface that is shaped to define a surface contour of the composite structure. The systems further include a carrier transfer device, which is configured to selectively convey a selected ply carrier from a ply kitting area to an intermediate location, and a forming machine, which is configured to deform the selected ply carrier and a respective ply segment over a selected portion of the elongate ply forming surface. The forming machine further is configured to separate the selected ply carrier from the respective ply segment and return the selected ply carrier to the carrier transfer device. The methods include methods of operating the systems.

US Patent:

20160339605, Nov 24, 2016

Filed:

Aug 4, 2016

Appl. No.:

15/228973

Inventors:

- Chicago IL, US
Martin Wayne Hansen - Puyallup WA, US

International Classification:

B29C 33/30
B29C 70/34

Abstract:

A stiffened composite panel is fabricated using modular tooling. Composite pre-preg is laid up and formed over forming block modules each of which is assembled by co-linearly arranging a plurality of forming block segments. The formed stiffeners are respectively transferred to individual cure tool modules that are assembled by co-linearly arranging a plurality of cure tool module segments. The stiffeners are assembled by arranging the cure tool modules side-by-side, and a composite skin is placed on the assembled stiffeners. The panel is vacuum bagged using a segmented vacuum bag.

US Patent:

20140374013, Dec 25, 2014

Filed:

Feb 4, 2013

Appl. No.:

13/758505

Inventors:

The Boeing Company - , US
Martin Wayne Hansen - Puyallup WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B29C 70/02

US Classification:

156243, 156349

Abstract:

A stiffened composite panel is fabricated using modular tooling. Composite pre-preg is laid up and formed over forming block modules each of which is assembled by co-linearly arranging a plurality of forming block segments. The formed stiffeners are respectively transferred to individual cure tool modules that are assembled by co-linearly arranging a plurality of cure tool module segments. The stiffeners are assembled by arranging the cure tool modules side-by-side, and a composite skin is placed on the assembled stiffeners. The panel is vacuum bagged using a segmented vacuum bag.