Method and apparatus for curing large composite panels
AssigneeThe Boeing Company
InventorsDouglas A. McCarville, David F. Taylor
Life of this patent
Estimating the term…
Loading patent…
AssigneeThe Boeing Company
InventorsDouglas A. McCarville, David F. Taylor
Estimating the term…
A method and apparatus for curing large composite parts. The method utilizes a fiber metal mesh sheet (40) situated against a composite material(34) during a curing process. The fiber metal mesh sheet (40) provides a porous network for flow of the reaction by-products during a curing and vacuuming process, yet gives adequate structure to prevent both mark-off by vacuum ports (52, 70) and crushing of the porous network as a result of autoclave and vacuum pressure. External vacuum ports (52) are located in a bagging film (50) surrounding the composite material (34). Alternatively, vacuum ports (70) are located below the composite material (34). The use of the external vacuum ports (52), vacuum ports (70) located beneath the composite material (34), or both, shortens by-product flow path and provides adequate vacuum pressure over all areas of the composite material (34) to remove reaction by-products.
An apparatus for use in curing a composite part generally made from a volatile-emitting resin, comprising:
An apparatus for use in curing a composite part, comprising:
A method of forming a composite part, generally from a volatile-emitting resin comprising:
A method of removing reaction by-products from resin in a composite part during a curing cycle to a vacuum port overlying the resin without causing mark-off on the part by channeling the reaction-reaction by-products through a porous structural spacer, wherein the porous structural spacer includes two metal mesh sheets of different density and porosity.
An apparatus for use in curing a composite part generally made from a volatile-emitting resin, comprising:
Dependencies are inferred from the claim text.