The Boeing Company

Patrick Joseph Thrash

Roger Alan Burgess

Alan M Markus

Alexander Velicki

Branko Sarh

Thomas Karl Tsotsis

David Michael Miller

Chad L Boger

Michael James Farrell

Cole Standish

Joseph Benson Black, Jr

Robert Eugene Turley

A preform forming machine for producing a three-dimensional dry fiber preform may include a forming block assembly and a clamping plate assembly. The forming block assembly may have a forming table and a forming block and may be positionable in a series of forming block assemblies. The clamping plate assembly may have a clamping table and a clamping plate and may be positionable in a series of clamping plate assemblies arranged in opposing relation to the series of forming block assemblies. Each forming block may be configured to fold a ply stack over onto itself to form a web of a preform. Each clamping plate may be configured to clamp the ply stack to the forming table during the folding of the ply stack.

System and method for producing a three-dimensional dry fiber preform

The present disclosure is directed to a composite armor system and method of manufacturing the same including a composite armor system that includes a first bulk bonded fibrous layer, a second bonded fibrous layer bonded to the first bulk bonded fibrous layer and a third bonded fibrous layer. At least one release layer is disposed between the second bonded fibrous layer and the third bonded fibrous layer and a joining mechanism that joins the second bonded fibrous layer to the third bonded fibrous layer through apertures in the release layer into a joined bonded substratum layer. The release layer prevents bonding between the second bonded fibrous layer and the third bonded fibrous layer at opposite portions of the release layer contacting both the second bonded fibrous layer and the third bonded fibrous layer.

System of composite armor including release layers

A composite structure is provided including a first fabric and a second fabric. A substantially elongate and substantially rigid first member is spaced apart from and coupled with the first fabric via the second fabric. A resin substantially is infused into the first fabric and the second fabric, and substantially encapsulates the first member to form a unitary structure.

Composite fabric with rigid member structure

A method and apparatus for manufacturing. A fiber layer and a porous bonding layer are formed to form a unidirectional lay-up of fibers. The lay-up of fibers is heated under pressure to form a unidirectional composite tape of desired thickness to substantially maintain the fibers in a desired configuration. The unidirectional composite tape is slit to a desired width, and the slit unidirectional composite tape is loaded into a multiaxial fabric machine. A first layer is built from the composite tape in the multiaxial machine, and a second layer is built from the composite tape on the first layer at a predetermined angle from the first layer in the multiaxial machine. The first and second layers are consolidated to form a composite fabric in a continuous process.

Method and apparatus for low-bulk toughened fabrics for low-pressure molding processes

The different advantageous embodiments provide an inner barrel structure comprising an outer skin, an inner skin, a number of septa, and a truss core.

Unitized engine nacelle structure

A resin infusion mold tool system for use in a vacuum assisted resin transfer molding process with a subsequent pressure bleed step. The mold tool system includes a mold assembly having an outer mold line tool connected to resin supply lines and supplying resin to the preform. A plurality of inner mold line tools form a hard interface with the inner mold line of the fiber preform and are held to within tight tolerances by an external locating fixture. Excess resin is drawn out of the fiber preform using a vacuum bag connected to vacuum lines and disposed over the inner mold line tools but not between the tools and the fiber preform. The mold assembly is placed in an autoclave, the resin supply lines are detached and the autoclave pressurized to bleed additional resin out of the preform to raise the fiber volume of the composite structure.

Resin infusion mold tool system and vacuum assisted resin transfer molding with subsequent pressure bleed

A method of forming a unitary, composite structural member, and a member formed in accordance with the process. The process involves stitching a plurality of warp knit panel sections together to generally form a plurality of independent panel sections. The sections are placed within the dies of a molding tool such that a rib portion of each section aligns. Inflatable bladders are then slipped into voids formed in between the various panel sections of the assembly. The bladders are inflated to hold with one another. Resin is then infused into the panels that make up the assembly. The assembly is then cured. When the panels are removed from the molding tool a unitary, complexly shaped, composite structural member is formed.

Growing community of inventors

Corona, CA, United States of America

Patrick Joseph Thrash