According to one implementation, a composite material structure includes a corrugated stringer and a panel. The corrugated stringer has a corrugated structure including portions each having hat-shaped cross section. The corrugated stringer is made of a composite material. The panel is integrated with the corrugated stringer. The panel is made of a composite material. Further, according to one implementation, a manufacturing method of a composite material structure includes: setting a textile on a laminated body of prepregs; and producing the composite material structure by covering the laminated body with a bagging film, forming a vacuum state in a space covered with the bagging film, impregnating the textile with the resin, and thermal curing of the laminated body of the prepregs. The laminated body is a panel before curing. The textile has a structure corresponding to a corrugated stringer.

This disclosure is directed to a thermoplastic composite material forming method and tooling used to perform the method. More specifically, this disclosure is directed to a method of fabricating large, complex thermoplastic composite part shapes with a consolidation tool having a conformable tooling bladder that heat thermoplastic material in the tool and provide thermoplastic material consolidation pressure in directions in the tool to form a part shape of thermoplastic composite material. A novel tooling concept is used to fabricate large, complex thermoplastic composite part shapes which are not easily producible using traditional methods. The tooling concept employs a consolidation tool that provides a method to apply thermoplastic material consolidation pressure by a conformable tooling bladder that provides thermoplastic material consolidation pressure in directions in the tool that are not achievable by conventional clamshell type molds where the mold parts move in substantially vertical tool opening and tool closing directions.

According to one implementation, a preform shaping apparatus includes a rigid mold and a pressurizing jig. The rigid mold has a shape corresponding to a shape of a preform which has been shaped. The pressurizing jig presses an unshaped material of the preform to the rigid mold at different positions and different timings. Further, according to one implementation, a method of shaping a preform includes: producing the shaped preform by pressing an unshaped material of the preform to a rigid mold at different positions and different timings; and using a pressurizing jig for pressing the material. The rigid mold has a shape corresponding to a shape of the preform. The pressurizing jig is adapted to apply pressures on the material at the different positions and the different timings.

A controlled shear vacuum forming method that includes forming a three-dimensional (3D) structure from a preform material on a molding tool using restraints during vacuuming to prevent wrinkling. The restraints are withdrawn during vacuuming to allowing the preform material to come into contact with the sidewalls of the molding tool in a gradual manner. Such forming method is particularly suitable for forming wing spars with bent sections and/or curved contours.

A molding method for making a monolithic component made of C-SMC and internally including a cavity, including preparing a press including first and second half molds and movable side carriages defining a molding space, and placing a core inside the molding space. The core comprises a membrane, delimiting a containing space shaped to form the cavity, and at least one connector engaged with the membrane. The method includes wrapping a charge of material to be molded around the core, fixing the core inside one between the first and the second half molds, and filling the containing space of the membrane with a filling material. After closing the half molds, applying a molding pressure and then emptying the containing space of the filling material and, after opening the half molds, removing the core from the molded monolithic component.

A molding method for making a monolithic component made of C-SMC and internally including a cavity, including preparing a press including first and second half molds and movable side carriages defining a molding space, and placing a core inside the molding space. The core comprises a membrane, delimiting a containing space shaped to form the cavity, and at least one connector engaged with the membrane. The method includes wrapping a charge of material to be molded around the core, fixing the core inside one between the first and the second half molds, and filling the containing space of the membrane with a filling material. After closing the half molds, applying a molding pressure and then emptying the containing space of the filling material and, after opening the half molds, removing the core from the molded monolithic component.

Methods of manufacturing composite workpieces that include positioning a heat-generating element proximate to an uncured composite workpiece, triggering the heat-generating element to produce an exothermic chemical reaction or exothermic physical reaction so that the temperature of the uncured composite workpiece is raised to a predetermined first temperature, and curing the composite workpiece while it is at a temperature that is at least the predetermined first temperature.

Advanced single vacuum bag (ASVB) fabrication methods and assemblies are provided to manufacture and repair polymer composites whereby a rigid check plate is mounted over an uncured laminate by a thermally collapsible check plate stand. The check plate stand thereby maintains a gap between the check plate and the uncured laminate during first stage processing conditions, yet is capable of thermally collapsing during subsequent second stage processing conditions to thereby allow the check plate to fall into compressive contact with the uncured laminate After the check plate collapses onto the uncured laminate, the compressive force of the check plate will be transferred to the laminate to consolidate the laminate as desired and thereby form an at least partially cured polymer composite structure of high quality.

A controlled shear vacuum forming method that includes forming a three-dimensional (3D) structure from a preform material on a molding tool using restraints during vacuuming to prevent wrinkling. The restraints are withdrawn during vacuuming to allowing the preform material to come into contact with the sidewalls of the molding tool in a gradual manner. Such forming method is particularly suitable for forming wing spars with bent sections and/or curved contours.

Systems and methods are provided for fabricating composite parts. One embodiment is a method of fabricating a composite part. The method includes providing a preform on a tool mandrel, positioning sensors around the preform according to a target shape of the composite part, and sealing the preform with a vacuum bag to form a chamber. The method also includes applying temperature and pressure to the chamber to infuse a resin into the preform to create a composite preform undergoing infusion, monitoring a thickness of the composite preform prior to completing cure, and adjusting at least one of the temperature and the pressure prior to completing cure based on the thickness.