Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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 Al2O3, SiO2, 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.

Abstract: 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.

Abstract: A joint for a metallic skin structure includes a first end portion and a second end portion positioned in an overlying relationship with each other. A first row of a first plurality of bores, within the first end portion, have adjacent bores spaced apart from one another. A second row of a second plurality of bores, within the second end portion have adjacent bores spaced apart from one another. First common central axis is defined by a first bore of each of the first and second plurality of bores. Second common central axis is defined by a second bore of each of the first and second plurality of bores. A line of securement extends between the first and second common central axes. At least one reinforcement fiber embedded within one of the first or second end portion extending orthogonal to and on either side of the line of securement.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.