초록

Fluted core sandwich panels are joined together to form a composite structure. Variations in panel ends are accommodated by a core stiffener insert installed in a joint between ends of the panels.

대표청구항 ▼

1. A method of fabricating a composite structure, comprising: forming first and second panels each having a fluted core and an end, the first and second panels each having a core sandwiched between first and second facesheets, the core comprising a support between the first and second facesheets, th

1. A method of fabricating a composite structure, comprising: forming first and second panels each having a fluted core and an end, the first and second panels each having a core sandwiched between first and second facesheets, the core comprising a support between the first and second facesheets, the fluted cores being mismatched at the first and second panel ends, creating mismatched cores, the first and the second panels each comprising a truss panel having a fluted core, the fluted core being a series of hollow isosceles trapezoidal flutes with inclined side walls extending traverse to a plane of the first and second face sheets;altering the first and second panel ends to match-up the mismatched cores, so as to form altered panel ends, the altering including removing at least a portion of the flutes between the first and second facesheets;installing a composite core stiffener insert between the altered panel ends, the composite core stiffener comprising a plurality of fibers that form a web and a set of flanges, the set of flanges adhered to the first panel and the second panel, the web comprising a substantially straight portion extending between the first panel and the second panel such that the set of flanges contact an inner surface of the first panel and an inner surface of the second panel; andjoining the altered panel ends together at a joint. 2. The method of claim 1, wherein altering the first and second panel ends includes removing a portion of the end of the core of at least one of the altered panel ends, such that the altered panel ends are matched. 3. The method of claim 1, wherein the core stiffener insert is configured to mate with the cores of the first and second panels such that the set of flanges do not extend past the inner surface of the first and second panels. 4. The method of claim 1, wherein the composite core stiffener insert is a substantially 90 degree I-beam relative to a surface of the panel. 5. The method of claim 1, wherein the composite core stiffener insert is substantially symmetric about a centerline passing through the joint. 6. The method of claim 1, wherein the composite core stiffener insert is bonded to portions of the cores of the first and second panels. 7. The method of claim 1, wherein the joint further includes first and second scarf splices each substantially flush with a surface of each panel. 8. The method of claim 7, wherein the first scarf splice joins a first facesheet of first and second panels, and the second scarf splice joins a second facesheet of the first and second panels. 9. The method of claim 7, wherein each of the scarf splices is joined to the core stiffener insert. 10. The method of claim 7, wherein the core stiffener insert is adhesively bonded to the fluted core of each of the panels and to each of the first and second scarf splices. 11. The method of claim 7, wherein the joint further includes scarf slices bonded to the core stiffener insert and to facesheets of the first and second panels. 12. A method of fabricating a composite structure, comprising: providing a first and a second composite panel, the first composite panel having an end and the second composite panel having an end each composite panel having a core sandwiched between first and second facesheets, each of the cores comprising a support between the first and second facesheets, the ends of the cores being mismatched, creating mismatched core ends, the first and the second panels each comprising a truss panel having a fluted core, the fluted core being a series of hollow isosceles trapezoidal flutes with inclined side walls extending traverse to the plane of the first and second face sheets;altering each of the ends of the composite panels, including removing at least a portion of the flutes between the first and second facesheets of each composite panel;installing a composite core stiffener insert between the mismatched core ends, the composite core stiffener comprising a plurality of fibers that form a web and a set of flanges, the web comprising a substantially straight portion;bonding the set of flanges the first panel and the second panel such that the set of flanges do not extend past the first panel and the second panel; andjoining the panel ends along joints with the core stiffener insert that mates the mismatched core ends and transfers load between the facesheets and across the panels. 13. The method of claim 12, further comprising: matching the mismatched core ends to the core stiffener insert by removing at least a portion of one of the mismatched core ends. 14. The method of claim 12, further comprising: removing material from a first exterior surface of a first panel and a second panel to form a first ramp where the a first panel meets the second panel;removing material from a second exterior surface of the first panel and the second panel to form a second ramp where the a first panel meets the second panel;installing a first splice over the first ramp between the first facesheets of the panels, andinstalling a second splice over the second ramp between the second facesheets of the panels. 15. The method of claim 14, further comprising: bonding each of the first and second splices with the core stiffener insert. 16. The method of claim 12 further comprising forming a scarf in at least one panel substantially flush with a surface of the at least one panel. 17. The method of claim 12, wherein the core comprises a fluted core. 18. A method of fabricating a composite barrel section for aerospace applications, comprising: forming a plurality of curved sandwich panels each having a fluted core sandwiched between a pair of face sheets, each core of each panel comprising a support between the first and second facesheets, the sandwich panels including a first and a second panel each comprising a truss panel having a fluted core, the fluted core being a series of hollow isosceles trapezoidal flutes with inclined side walls extending traverse to the plane of the first and second face sheets;altering each of the ends of the first and second panels, including removing at least a portion of the flutes between the first and second facesheets of each composite panel;joining ends of the panels together along joints;trimming the ends of the panels at a final joint between the panel to form a preselected inter-panel gap;scarfing facesheets in an area of the inter-panel gap, creating scarfed facesheets;fabricating and pre-curing a pair of composite laminate scarf splices;fabricating and precuring a composite core stiffener insert, the composite core stiffener insert comprising a plurality of fibers that form a web and a set of flanges, the web comprising a substantially straight portion;installing the stiffener insert in the inter-panel gap;applying a film adhesive over the combination of the scarfed facesheets and the insert;bonding the set of flanges to an inner surface of a first panel and an inner surface of the second panel;placing the scarf splices on the scarfed facesheets;compacting the scarf splices against the facesheets; andhot bonding the joint, including curing the film adhesive. 19. The method of claim 18, wherein the composite core stiffener is positioned at substantially 90 degrees relative to the face sheets. 20. The method of claim 18, wherein the composite core stiffener comprise radius corners at opposing ends, and further comprising filling a void defined by the radius corners.