公开(公告)号：US20150048213A1

公开(公告)日：2015-02-19

申请号：US13966678

申请日：2013-08-14

Applicant: Bell Helicopter Textron Inc.

Inventor： Brent C. Ross ,  David R. Bockmiller ,  John R. McCullough ,  David G. Carlson

IPC: B64C27/26 ,  B64C27/28

CPC classification number: B64C29/0033

Abstract: A tiltrotor aircraft includes a fuselage; a wing member having a first rib, a second rib, a first spar, second spar; and an upper wing skin; an engine disposed at a fixed location relative to the wing member; and a proprotor having a spindle gearbox, rotor mast, and a plurality of rotor blades drivable in rotation about the rotor mast, the spindle gearbox being rotatable about a conversion axis. The spindle gearbox is located above the upper wing skin of the wing member.

Abstract translation: 一架俯仰式飞机包括机身; 翼构件，具有第一肋，第二肋，第一翼梁，第二翼梁; 和上翼皮; 设置在相对于翼构件的固定位置的发动机; 以及具有主轴齿轮箱，转子桅杆和可围绕转子桅杆旋转驱动的多个转子叶片的推进器，所述主轴齿轮箱可围绕转换轴线旋转。 主轴齿轮箱位于机翼构件的上翼面上方。

公开(公告)号：US20140115853A1

公开(公告)日：2014-05-01

申请号：US13663925

申请日：2012-10-30

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Ramesh Thiagarajan ,  Robert Mark Chris ,  John R. McCullough ,  Suvankar Mishra

IPC: B23P6/00

CPC classification number: B23P6/00 ,  B23P6/002 ,  B23P2700/00 ,  B29C44/18 ,  B29C73/063 ,  B29C73/10 ,  B29C2073/264 ,  B29L2031/082 ,  B29L2031/608 ,  Y10T29/49318 ,  Y10T29/49723 ,  Y10T29/49725 ,  Y10T29/49726 ,  Y10T29/49732 ,  Y10T29/49734 ,  Y10T29/49746 ,  Y10T428/24157

Abstract: A method of the present disclosure includes of repairing a core stiffened structure with structural foam. Another method includes splicing core members together using structural foam. Another method includes joining a core member to a structure using structural foam. Another method includes using structural foam to stabilize a core member during a machining process. Another method includes stabilizing a core member with structural foam to prevent the core member from crushing in autoclave pressure. The present disclosure further includes a core stiffened structure have a core member with structural foam therein.

Abstract translation: 本公开的方法包括用结构泡沫修复芯加固结构。 另一种方法包括使用结构泡沫将芯部件拼接在一起。 另一种方法包括使用结构泡沫将芯构件连接到结构上。 另一种方法包括在加工过程中使用结构泡沫来稳定芯构件。 另一种方法包括用结构泡沫稳定芯部件以防止芯件在高压釜压力下破碎。 本公开还包括具有在其中具有结构泡沫的芯构件的芯加强结构。

公开(公告)号：US10669021B2

公开(公告)日：2020-06-02

申请号：US14022524

申请日：2013-09-10

Applicant: Bell Helicopter Textron Inc.

Inventor： Paul K. Oldroyd ,  Wei-Yueh Lee ,  James D. Hethcock, Jr. ,  John R. McCullough ,  Patrick R. Tisdale

IPC: B64C27/473 ,  B64C3/20

Abstract: An airfoil member can have a root end, a tip end, a leading edge, and a trailing edge. The airfoil member can include an upper skin, a lower skin, and a composite core member having a plurality of cells, an upper surface network of the cells can be bonded to the upper skin, a lower surface network of the cells can be bonded to the lower skin. The composite core can have a septum layer embedded in the cells that form the composite core, the septum layer being configured to provide tailored characteristics of the airfoil member.

公开(公告)号：US20190300167A1

公开(公告)日：2019-10-03

申请号：US15936866

申请日：2018-03-27

Applicant: Bell Helicopter Textron Inc.

Inventor： Jeffrey Paul Nissen ,  John R. McCullough

IPC: B64C27/473

Abstract: An erosion protection system (EPS) has a first erosion protection unit (EPU) having a first ligament and a first scale attached to the first ligament, the first scale having an outer hardness that is greater than a hardness of the first ligament. The EPS also has a second EPU having a second ligament and a second scale attached to the second ligament, the second scale having an outer hardness that is greater than a hardness of the second ligament. The EPS also has an interstitial space between the first ligament and the second ligament wherein at least one of (1) the first scale overlaps at least a portion of the second EPU and (2) the second scale overlaps at least a portion of the first EPU.

公开(公告)号：US10289770B2

公开(公告)日：2019-05-14

申请号：US15092969

申请日：2016-04-07

Applicant: Bell Helicopter Textron Inc.

Inventor： Jonathan A. Knoll ,  Jeffrey P. Nissen ,  John R. McCullough

IPC: G06F17/50

Abstract: A method of performing structural analysis relating to a component having CAD-based geometry, refined CAD-based geometry and CAD-based FEA data associated therewith. The method includes scanning the component to obtain scan-based point cloud geometry of the component, aligning the scan-based point cloud geometry with the CAD-based geometry of the component, generating scan-based geometry of the component by refining the scan-based point cloud geometry, comparing the scan-based geometry with the refined CAD-based geometry of the component to quantify geometric differences therebetween, generating scan-based FEA geometry of the component by meshing the scan-based geometry, performing finite element analysis on the scan-based FEA geometry to obtain scan-based FEA data and comparing the scan-based FEA data with the CAD-based FEA data of the component to quantify the effect of geometric difference therebetween.

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.

公开(公告)号：US20140120298A1

公开(公告)日：2014-05-01

申请号：US13664010

申请日：2012-10-30

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Ramesh Thiagarajan ,  Theodore W. Ingram, III ,  John R. McCullough ,  Suvankar Mishra ,  Carl May

IPC: B32B3/06 ,  B32B3/26 ,  B32B3/12

CPC classification number: B32B3/12 ,  B29C73/06 ,  B29C73/10 ,  B29C2073/264 ,  B29L2031/082 ,  B29L2031/608 ,  Y10T428/24008 ,  Y10T428/24157 ,  Y10T428/249953

Abstract: A method of the present disclosure includes of repairing a core stiffened structure with structural foam. Another method includes splicing core members together using structural foam. Another method includes joining a core member to a structure using structural foam. Another method includes using structural foam to stabilize a core member during a machining process. Another method includes stabilizing a core member with structural foam to prevent the core member from crushing in autoclave pressure. The present disclosure further includes a core stiffened structure have a core member with structural foam therein.

公开(公告)号：US20140119930A1

公开(公告)日：2014-05-01

申请号：US13663954

申请日：2012-10-30

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Ramesh Thiagarajan ,  Robert Mark Chris ,  John R. McCullough ,  Suvankar Mishra

IPC: B32B38/00 ,  B64C27/46 ,  B32B3/12 ,  B32B3/26

CPC classification number: B29C44/1228 ,  B29L2031/082 ,  B29L2031/608 ,  B32B3/12 ,  B32B5/20 ,  B32B7/02 ,  B32B7/12 ,  B32B2307/304 ,  B32B2307/306 ,  B32B2603/00 ,  B64F5/40 ,  Y10T428/192

Abstract: A method of the present disclosure includes of repairing a core stiffened structure with structural foam. Another method includes splicing core members together using structural foam. Another method includes joining a core member to a structure using structural foam. Another method includes using structural foam to stabilize a core member during a machining process. Another method includes stabilizing a core member with structural foam to prevent the core member from crushing in autoclave pressure. The present disclosure further includes a core stiffened structure have a core member with structural foam therein.