Rocky Mountain Composites, Inc.

Other

Toyota Motor Sales, U.s.a., Inc.

Spectrum Aeronautical, LLC

Craig Bjamson Simpson

Larry Jed Ashton

Mike Glen Allman

Steven Taylor Tuttle

Troy Larry White

Rex W Kay

Alan H Anderson

Michael G Allman

Benko S Ta'ala

Benko Samasoni Ta'ala

A modular attachment system is disclosed having one or more surfaces designed to compatibly interconnect with a receptacle formed by a grid pattern of a structural support of a gun stock. The grid pattern can be an is a grid pattern, an orthogrid pattern, or a pattern having a combination of both isogrid and orthogrid portions.

Modular attachment system for gun stock

A composite material made of multiple filament bands is disclosed. The filament bands are wound to create a composite material. The filament bands may be impregnated with a solid or semi-solid resin. The filament bands are wound in multiple orientations to form a sheet of composite material. Additionally, the composite material may be made to have a varying number of layer and fiber orientations throughout the sheet of composite material. In another embodiment, a composite component requiring multiple layers and fiber orientations may be substantially manufactured during a filament winding process.

Resin impregnated multi orientation composite material

A light weight stiffened gun stock is disclosed herein. The gun stock utilizes structural members oriented in a grid pattern resulting in a high strength-to-weight ratio. The grid pattern can be an isogrid, orthogrid, hoop-grid pattern, or a combination thereof. The structural members define the form of the gunstock, and provide recoil absorption to reduce the amount of recoil experienced by the shooter.

Light weight stiffened gun stock

A reinforced panel, made of a composite material, includes a single base layer. A first plurality of mutually parallel ridges is affixed to the surface of the base layer. A second plurality of mutually parallel ridges is also affixed to the surface of the base layer, but oriented transverse to the first plurality. Structurally, the ridges and the base layer are co-cured to create an integral, continuous structure that provides stiffness and rigidity to the panel.

Reinforced composite panel

The present invention relates to apparatus and methods for winding filament to create a structure. In one embodiment, the invention includes the application of filament to a rotating mandrel to create a desired shape. The invention includes the filament winding of both simple and complex shapes.

Filament winding apparatus and methods of winding filament

A single piece co-cured composite wing is disclosed. The wing has a flying surface and structural members. In one embodiment the structural members may be a plurality of spars. The spars may have various shapes to increase the buckling strength. The spars may be wave shaped, such as a sinusoidal shape. The flying surface and the structural members are co-cured in order to form a single piece, integral wing structure. A process for manufacturing a single piece co-cured wing is also disclosed. The process may include laying out composite sheets for the flying surface of the wing. Then, the composite material of the spars is arranged around a plurality of pressurizable forms. Finally, the composite material is cured in a clamshell frame. A single piece co-cured composite structure is also disclosed that includes an outer skin, and inner skin, a frame, and a stringer.

Single piece co-cure composite wing

A single piece co-cured composite wing is disclosed. The wing has a flying surface and structural members. In one embodiment the structural members may be a plurality of spars. The spars may have various shapes to increase the buckling strength. The spars may be wave shaped, such as a sinusoidal shape. The flying surface and the structural members are co-cured in order to form a single piece, integral wing structure. A process for manufacturing a single piece co-cured wing is also disclosed. The process may include laying out composite sheets for the flying surface of the wing. Then, the composite material of the spars is arranged around a plurality of pressurizable forms. Finally, the composite material is cured in a clamshell frame.

Process for forming a single piece co-cure composite wing

A method for manufacturing a composite structure is disclosed herein. The process uses a frame and selectively pressurizable forms. The forms define the interior members of the composite structure and frames define the exterior surface of the composite structure. Composite material is wrapped around the forms and the forms and composite material are placed in the frame. Selective forms are then pressurized and the composite material is co-cured together. A single piece co-cured fuselage incorporating a plurality of stiffeners is also disclosed in the application. The stiffeners are co-cured to the fuselage and may be in various patterns. The patterns may include an iso-grid pattern, and ortho-grid pattern, and a hoop-grid pattern.

Method of assembling a single piece co-cured structure

A method and apparatus for manufacturing fiber-reinforced, composite materials relies on one or more processes improving over conventional forming, filling, and processing techniques. A homogeneous resin-stitching process provides for resin stitching for using only 5-20 percent of the rovings in a preform as wetted rovings, cured to maintain a stitching together of the structure. A resin-packet transfer process provides infusion of resins from directly beside a wall of a preform, rather than passing resins throughout the longitudinal length of fibers in a perform. A cyclic vacuum bagging process alternately applied over pressure and outside vacuum to a vacuum bag process, thus relieving pressure, and later, optionally, applying pressure to improve structural strength. Relieving pressure tends to improve (reduce) porosity.

Growing community of inventors

Mapleton, UT, United States of America

Craig Bjamson Simpson