Abstract: Methods and systems are disclosed wherein temperature in a device such as an ambulatory infusion pump is monitored during inductive charging of the device such that temperature-sensitive contents or components, such as, for example, insulin, particular circuitry and/or other components are not damaged. Temperature can be monitored in the device at one or more locations during inductive charging. If the temperature breaches one or more predetermined thresholds and/or is rising at a rate greater than one or more predetermined thresholds, charging can be suspended or provided at reduced power to prevent the temperature from further rising and damaging the contents and/or components of the device. One or more alerts associated with these events may also be triggered so that the user is aware of the situation and may take corrective action.

Abstract: A method for modeling soft tissue includes receiving one or more images showing an anatomical geometry of a first subject. The anatomical geometry includes a soft tissue. The method also includes measuring a plurality of parameters of the anatomical geometry of the first subject using one or more sensors attached to the first subject. The method also includes receiving a first set of material properties for the soft tissue of the first subject, a second subject, or both. The method also includes identifying a second set of material properties that characterizes the soft tissue while the first subject performs a task. The method also includes determining a strain on the soft tissue, a stress on the soft tissue, or both based at least partially upon the one or more images, the parameters, the first set of material properties, and the second set of material properties.

Abstract: Heating operation control includes obtaining sensor data indicating measured temperatures within a heating vessel during a heating operation; determining sets of thermal stack parameters. Each set of candidate thermal stack parameters is descriptive of a respective configuration of a thermal stack modeled by a first machine learning model to generate one or more estimated tool temperature values. The thermal stack includes the tool and a part coupled to the tool. Heating operation control also includes determining a temperature profile for the heating operation. The temperature profile is determined, via a second machine learning model, based on the plurality of sets of thermal stack parameters and one or more process specifications of the thermal stack.

Abstract: A method of forming a composite article. One step involves applying adhesive on surfaces of a plurality of sublaminate units, each ply of each sublaminate unit comprising fibers impregnated with resin which has been initially cured to 30% to 50% of full cure. The initially cured sublaminate units are then arranged in a stack, which stack is pressed against a surface of a forming tool. While pressure is being applied, the stack is heated to an intermediate temperature above a glass transition temperature of the resin for a time interval sufficient to intermediately cure the resin to 50% to 70% of full cure to form a composite laminate having a contour defined by the surface of the forming tool. Then the resin is finally cured at a final temperature higher than the intermediate temperature.

Abstract: A method of forming a composite article. One step involves applying adhesive on surfaces of a plurality of sublaminate units, each ply of each sublaminate unit comprising fibers impregnated with resin which has been initially cured to 30% to 50% of full cure. The initially cured sublaminate units are then arranged in a stack, which stack is pressed against a surface of a forming tool. While pressure is being applied, the stack is heated to an intermediate temperature above a glass transition temperature of the resin for a time interval sufficient to intermediately cure the resin to 50% to 70% of full cure to form a composite laminate having a contour defined by the surface of the forming tool. Then the resin is finally cured at a final temperature higher than the intermediate temperature.

Abstract: A composite sandwich structure is made by compacting a first multi-ply composite facesheet and assembling a layup, including sandwiching a core between the compacted first facesheet and a second multi-ply composite facesheet. The layup is compacted and the first and second facesheets are co-cured with the core.

Abstract: A method of forming a molybdenum composite hybrid laminate is disclosed. The method includes treating a surface of each of a plurality of molybdenum foil layers. The method further includes interweaving the surface treated molybdenum foil layers with a plurality of composite material layers. The method further includes bonding with an adhesive layer each of the surface treated molybdenum foil layers to adjacent composite material layers to form a molybdenum composite hybrid laminate having improved yield strength.

Abstract: A method of manufacturing a composite laminate may include laying up bands of composite material in layers to form a composite layup. At least one layer may have at least one gap between an adjacent pair of bands. The gap may extend continuously along a lengthwise direction of the band. The gap in two or more of the layers may be fluidly interconnected and may form at least one breather path that opens to an exterior of the composite layup.

Abstract: A method of reducing residual stress in a composite assembly may include assembling a first composite part to a second composite part to form a detail assembly. The first and second composite part may each have a flange and a web connected by a bend radius. The webs may be arranged back-to-back. The detail assembly may be cured on a compensated cure tool compensated for cure shrinkage spring-in predicted to occur in the first and second composite part. The method may include allowing the first and second composite part to spring in from cure shrinkage, and assembling the detail assembly to an uncured third composite. The method may also include co-bonding the detail assembly to the third composite part on an assembly cure tool to form a composite assembly having reduced cure shrinkage residual stress in the bend radii of the first and second composite part.

Abstract: A method for forming a structural member and a structural member produced thereby includes positioning a first composite section and a second composite section within a tool. The tool has an inner surface and a wall intersection and is supported by a tool platform. The tool platform and a pressure platform are relatively movable between an open position and a closed position. The tool has a non-planar outer surface against which the member may be pressed. A composite splice member is positioned at least partially overlapping both the first composite section and the second composite section to form a joint in the composite structural member. The composite structural member is pressed against the non-planar outer surface of the tool by applying pressure to the joint from a pressure bladder. Heat is applied to the composite structural member at the joint to cure the composite splice member to the first composite section and the second composite section.

Abstract: A method of forming a composite article may include initially curing a composite laminate at an initial temperature to an initial cure stage of 30-50 percent of full cure and beyond a gel point to form an initially-cured composite laminate. The method may initially include heating the initially-cured composite laminate to an intermediate temperature higher than the initial temperature and above a resin glass transition temperature. In addition, the method may include intermediately curing the composite laminate to an intermediate cure stage of 50-70 percent of full cure while on a final forming tool to form an intermediately-cured composite laminate. Furthermore, the method may include removing the intermediately-cured composite laminate from the final forming tool, and finally curing the intermediately-cured composite laminate at a final temperature higher than the intermediate temperature to a final cure stage.

Abstract: A method of reducing residual stress in a composite assembly may include assembling a first composite part to a second composite part to form a detail assembly. The first and second composite part may each have a flange and a web connected by a bend radius. The webs may be arranged back-to-back. The detail assembly may be cured on a compensated cure tool compensated for cure shrinkage spring-in predicted to occur in the first and second composite part. The method may include allowing the first and second composite part to spring in from cure shrinkage, and assembling the detail assembly to an uncured third composite. The method may also include co-bonding the detail assembly to the third composite part on an assembly cure tool to form a composite assembly having reduced cure shrinkage residual stress in the bend radii of the first and second composite part.

Abstract: A method of manufacturing a composite laminate may include laying up bands of composite material in layers to form a composite layup. At least one layer may have at least one gap between an adjacent pair of bands. The gap may extend continuously along a lengthwise direction of the band. The gap in two or more of the layers may be fluidly interconnected and may form at least one breather path that opens to an exterior of the composite layup.

Abstract: 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.

Abstract: A method of forming a composite article may include initially curing a composite laminate at an initial temperature to an initial cure stage of 30-50 percent of full cure and beyond a gel point to form an initially-cured composite laminate. The method may initially include heating the initially-cured composite laminate to an intermediate temperature higher than the initial temperature and above a resin glass transition temperature. In addition, the method may include intermediately curing the composite laminate to an intermediate cure stage of 50-70 percent of full cure while on a final forming tool to form an intermediately-cured composite laminate. Furthermore, the method may include removing the intermediately-cured composite laminate from the final forming tool, and finally curing the intermediately-cured composite laminate at a final temperature higher than the intermediate temperature to a final cure stage.

Abstract: A method of forming a molybdenum composite hybrid laminate is disclosed. The method includes treating a surface of each of a plurality of molybdenum foil layers. The method further includes interweaving the surface treated molybdenum foil layers with a plurality of composite material layers. The method further includes bonding with an adhesive layer each of the surface treated molybdenum foil layers to adjacent composite material layers to form a molybdenum composite hybrid laminate having improved yield strength.

Abstract: In an embodiment of the disclosure, there is provided a molybdenum composite hybrid laminate. The laminate has a plurality of composite material layers. The laminate further has a plurality of surface treated molybdenum foil layers interweaved between the composite material layers. The laminate further has a plurality of adhesive layers disposed between and bonding adjacent layers of the composite material layers and the molybdenum foil layers.

Abstract: A method for forming a structural member and a structural member produced thereby includes positioning a first composite section and a second composite section within a tool. The tool has an inner surface and a wall intersection and is supported by a tool platform. The tool platform and a pressure platform are relatively movable between an open position and a closed position. The tool has a non-planar outer surface against which the member may be pressed. A composite splice member is positioned at least partially overlapping both the first composite section and the second composite section to form a joint in the composite structural member. The composite structural member is pressed against the non-planar outer surface of the tool by applying pressure to the joint from a pressure bladder. Heat is applied to the composite structural member at the joint to cure the composite splice member to the first composite section and the second composite section.

Abstract: In an embodiment of the disclosure, there is provided a molybdenum composite hybrid laminate. The laminate has a plurality of composite material layers. The laminate further has a plurality of surface treated molybdenum foil layers interweaved between the composite material layers. The laminate further has a plurality of adhesive layers disposed between and bonding adjacent layers of the composite material layers and the molybdenum foil layers.

Abstract: A composite sandwich structure is made by compacting a first multi-ply composite facesheet and assembling a layup, including sandwiching a core between the compacted first facesheet and a second multi-ply composite facesheet. The layup is compacted and the first and second facesheets are co-cured with the core.