Patent classifications
B29C66/721
Joining method and assembly for an aircraft
A joining method and assembly for an aircraft. To improve the characteristics or permit hitherto impossible connections between thermoplastic and thermoset components, a multi-material joining method is disclosed in which a thermoplastic connecting region is formed on the thermoplastic component. The connecting region is connected to the thermoset component by interdiffusion. For this purpose, the uncured second component is brought into contact with the connecting region and heat is supplied. An interdiffusion layer is formed which fixedly connects the second component and the connecting region to one another and thus joins the first component to the second component.
Systems and methods for joining components by riveting
A riveting system, for use in mechanically linking adjacent workpieces, including a rivet having a height greater than a sum of thicknesses, measured along a line of riveting, of the workpieces being linked, so that the rivet can pass fully through the workpieces. The system also includes a riveting die, which may be a separate product. The die includes a protrusion extending from a peak toward a transition point; and a trough having a trough surface. The trough surface includes a trough inner wall, extending from the transition point to a trough bottom, and a trough outer wall, extending from the trough bottom to a trough outer edge. The technology also includes computerized systems for comparing a load-displacement profile of riveting to a pre-set profile to determine whether the riveting was performed properly.
Fastening objects to each other
A method of fastening at least one second object to at least one first object, wherein mechanical vibration acts from a sonotrode on the second object to fasten the second object to the first object. Between the sonotrode and the second object, an auxiliary sheet is placed, for example of paper. After the vibration stops, the auxiliary sheet is displaced relative to the sonotrode for a next fastening step.
Method for producing a frame component for a door frame structure of an aircraft, frame component, and door frame structure
A method for producing a frame component for a door frame structure of an aircraft. A connecting zone is generated on a first and a second assembly surface of a connecting component in each case by generating a surface texture on the assembly surfaces, wherein the connecting component is formed from a metal material. The assembly surfaces of the connecting component are placed against a door frame member and against an attachment member, wherein the door frame member and the attachment member are each formed from a fiber-reinforced thermoplastics material. Furthermore, the connecting component and the door frame member are welded, and the connecting component and the attachment member are welded. A frame component and a door frame structure are also described.
HEAT SHIELD WITH COIL RECESS FOR INDUCTION WELDING
An assembly is provided for induction welding. This assembly utilizes a heat shield (e.g., a mica heat shield) with a recess. An induction welding coil may be disposed within this heat shield recess during induction welding operations. The wall thickness of the heat shield within the recess may be reduced to enhance heat transfer to a workpiece during induction welding operations. Members may engage the heat shield on opposite sides of the recess (and that have an increased wall thickness) to support both the heat shield and the workpiece during induction welding operations, during which a biasing force may be exerted on both the heat shield and workpiece.
INDUCTION WELDING WITH AN ELECTROMAGNETIC FIELD CONCENTRATOR
During a manufacturing method, an induction welder is provided that includes a concentrator and a coil. The concentrator includes a receptacle and a face surface. The receptacle projects vertically into the concentrator from the face surface to an end of the receptacle. The receptacle extends laterally within the concentrator between opposing sides of the receptacle. The receptacle extends longitudinally within the concentrator along a centerline. The coil is seated and extends longitudinally along the centerline within the receptacle. A first thermoplastic body arranged with a second thermoplastic body are provided. The first thermoplastic body is located vertically next to the face surface. The first thermoplastic body is induction welded to the second thermoplastic body. The induction welding includes: generating an electromagnetic field with the coil; and concentrating the electromagnetic field with the concentrator onto a region of the first thermoplastic body.
INDUCTION WELDING WITH AN ELECTROMAGNETIC FIELD CONCENTRATOR
During a manufacturing method, an induction welder is provided that includes a concentrator and a coil extending through a receptacle in the concentrator. The receptacle projects into the concentrator from a face surface of the concentrator. A first thermoplastic body arranged with a second thermoplastic body are provided. The first thermoplastic body is located next to the face surface. The first thermoplastic body is induction welded to the second thermoplastic body to provide a weld seam between the first thermoplastic body and the second thermoplastic body. The concentrator extends along a portion of the weld seam. The induction welding includes: generating an electromagnetic field with the coil; and concentrating a portion of the electromagnetic field with the concentrator onto a region of the first thermoplastic body.
VIBRATION WELDING FIBER-REINFORCED COMPOSITE AIRCRAFT STRUCTURES
During a formation method, a first component and a second component are provided. The first component is configured from or otherwise includes a first fiber-reinforced thermoplastic composite. The first component also includes a base and a material buildup on a portion of the base. The second component is configured from or otherwise includes a second fiber-reinforced thermoplastic composite. The second component is arranged with the first component. The second component abuts the material buildup. The second component is vibration welded to the first component to provide a weld joint between the first component and the second component. At least a portion of the material buildup is displaced during the vibration welding.
INDUCTION WELDING OF THERMOPLASTIC WITH METALLIC STRIPS
Methods and apparatus' for induction welding a first workpiece to a second workpiece at a welding region may include a metallic strip. The metallic strip may be a mesh. The properties of the metallic strip, such as, for example, pore size, thickness, and density, may be configured to conduct heat uniformly across the welding region and prevent eddy current formation across a workpiece. The metallic strip may be embedded in a workpiece or may be fixed to an induction welding tool that acts on the welding region during induction welding. A removable polymer tape may be disposed between a workpiece and a metallic strip fixed to an induction welding tool. The workpieces may be thermoplastic composite structures and thermoplastic composite stiffeners in aircraft structures.
USE OF REMOVABLE METAL FRAMES TO CONTROL INDUCTION WELDING OF THERMOPLASTIC COMPOSITE EDGES
Systems and methods for induction welding a stiffener to a thermoplastic composite structure using a removeable metal mask to reduce excess heat along the edges of the stiffener generated from an electromagnetic field of an induction welding tool.