The Boeing Company

Paul Stanley Nordman

Jiangtian Cheng

Robert Graham Albers

Paul Elfes Nelson

Xiaobo Zhang

Hojun Yoon

Jeffery Lee Marcoe

Stephen T Brown

Geoffrey Allen Butler

Willard N Westre

Richard John Loftis

Andrew Lewis Armatorio

William G Roeseler

Justin David Boynton Malcolm

Terry K Isomura

Andy Armatorio

Eder A Martins

William G Reeseler

A vehicle window assembly includes at least one body panel and a window pane. The at least one body panel defines a window opening along an exterior surface of a vehicle body. The vehicle body defines an internal cabin. The window pane is secured to the at least one body panel and positioned to cover the window opening. The window pane is a laminate stack of multiple tempered glass sheets bonded together.

Vehicle window assembly

A method for producing a window assembly includes producing a structural panel. Producing the structural panel includes depositing one or more structural reinforcement layers. Each of the one or more structural reinforcement layers includes a plurality of nanolaminated layers. The nanolaminated layers include AlO, SiO, graphene, or a combination thereof. Producing the structural panel also includes depositing a structural transparent polymer layer on the one or more structural reinforcement layers. The structural transparent polymer layer includes a transparent thermoplastic material.

One piece multifunctional nanolaminated composite window panel

A multifunctional composite panel and a system for fabricating the multifunctional composite panel are disclosed. The multifunctional composite panel may include a plurality of structural layers and a plurality of photovoltaic layers disposed adjacent the plurality of structural layers. The structural layers may include a plurality of alternating layers where each of the alternating layers includes a first layer and a second layer. The first layer may include one or more polymers and the second layer may include one or more inorganic materials. The system for fabricating the multifunctional composite panel may include a based configured to support the multifunctional composite panel and a plurality of application heads disposed proximal the based and configured to form layers of the multifunctional composite panel.

Multifunctional composite panels and methods for the same

One piece, multifunctional window assemblies for use in vehicles, equipment, or structures and methods for making them is provided. The disclosed window assembly can include a protection panel and a structural panel each formed of a plurality of nanolaminated layers. The nanolaminated window assembly is self-supporting and does not need a frame. For particular applications, such as in an aircraft, the one piece, multifunctional, nanolaminated window can be directly attached to the fuselage to provide load bearing capability, a larger window area, impact protection, ice buildup prevention, and/or electromagnetic effect protection.

A joint for a metallic skin structure includes a first end portion of the metallic skin structure and a second end portion of the metallic skin structure, wherein the first end portion and the second end portion of the metallic skin structure are secured together along a line of securement. The joint further includes at least one reinforcing fiber embedded within at least one of the first end portion of the metallic skin structure or the second end portion of the metallic skin structure extends orthogonal relative to the line of securement.

Joint for a metal airplane skin using metal matrix composite

A method for fabricating a structural part is disclosed. The method can include forming a plurality of layers on a base of a system having one or more application heads. Forming the plurality of layers can include forming alternating layers of a first material and a second material. Forming the alternating layers can include forming a first layer from the first material, and forming a second layer adjacent the first layer from the second material. The plurality of layers can form the structural part, and one or more dimensions of the structural part can be greater than or equal to about 0.05 cm.

Laminate composite structural components and methods for the same

A method for fabricating a multifunctional composite panel is disclosed. The method can include forming a plurality of structural layers, and forming a plurality of photovoltaic layers adjacent the plurality of structural layers. Forming the plurality of structural layers can include forming alternating layers of a conductive organic material and an inorganic material. Forming the alternating layers can include forming a first layer from the conductive organic material, and forming a second layer adjacent the first layer from the inorganic material. The multifunctional composite panel can have a thickness of from about 1 mm to about 30 mm.

A stabilization assembly for a door frame secured to a fuselage skin of an aircraft and positioned about an opening defined in the fuselage skin including a strap, wherein a first end portion of the strap is secured to the fuselage skin with a first fastener which extends through the first end portion of the strap and through at least a portion of the fuselage skin. A second end portion of the strap is coupled to the door frame and a third portion of the strap extends between the first and second end portions of the strap and spaced apart from the fuselage skin.

Door frame stabilization

A door frame for an aircraft includes first and second beams, each having a first end and a second end. The second beam is substantially parallel to the first beam. A third beam extends from the first end of the first beam to the first end of the second beam. The third beam is substantially perpendicular to the first beam and the second beam. A first flange extends from the second end of the first beam in a direction that is away from the second beam. The first flange is substantially perpendicular to the first beam.

Hat section door frame with integral gussets

A method comprises embedding tear straps in a metal aircraft structure having a fully formed contour and thickness. The tear straps include strips of fibers that are substantially stronger and stiffer than the metal aircraft structure. The fibers are embedded beneath at least one surface of the metal aircraft structure via ultrasonic consolidation.

Embedded tear straps in metal structures

There is provided in an embodiment a composite radius filler for a composite structure. The composite radius filler has two or more radius laminates. Each radius laminate has a laminate of stacked composite plies formed in a desired radius with a desired radial orientation of the stacked composite plies substantially matching a radial orientation of adjacent stacked composite plies of a composite structure surrounding the two or more radius laminates. Each radius laminate is preferably trimmed to have at least one side align adjacent to the others to form a composite radius filler having a shape substantially corresponding to a radius filler region of the composite structure.

Composite radius fillers and methods of forming the same

An airfoil includes at least one precured composite spar having a web and at least one flange integrated with an end of the web. A precured composite skin is attached to the spar by adhesive bonding the skin to the flange.

Bonded composite airfoil

A structural substrate for an aircraft structure and methods are presented. A multi-layer hybrid composite material comprises an outermost layer, an intermediate layer, and an innermost layer. The outermost layer comprises an electrically conductive metal matrix composite that conducts electricity to provide electric heating. The intermediate layer comprises an electrical insulator coupled to the outermost layer. The innermost layer comprises a composite coupled to the intermediate layer. The intermediate layer electrically insulates the outermost layer from the innermost layer.

Metal matrix composite used as a heating element

There is provided a box structure for carrying load having upper and lower composite integrated sandwich panels. The panels have facesheets sandwiching one or more core portions and adjacent dense packs oriented in an axial direction. The box structure further has a plurality of spars. Each spar has a web and web attachments and has a spar length in the axial direction. The plurality of spars are connected to the panels with the web attachments located at the dense packs. The facesheets are configured to carry primarily torsion and pressure loads in shear and no significant axial loads. The dense packs are configured to carry all significant box bending in axial tension and compression loads.

Box structures for carrying loads and methods of making the same

An apparatus for an aircraft structure comprising first and second stringers, each having a vertical stringer portion defining a lengthwise gap. The structure may include a fitting having a central rib attachment member and first and second extensions extending in opposite directions from said central rib attachment member. Stringer attachment portions extending up from said first and second extensions are inserted into the lengthwise gaps of the first and second stringer portions, respectively. The rib attachment member may be attached to a side-of-body rib.

Growing community of inventors

Renton, WA, United States of America

Paul Stanley Nordman