# US 2014/0154458 A1 · Composite material structures with integral composite fittings and methods of manufacture > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0154458 A1 - Document ID: US20140154458A1 - Status: Published application - Kind: A1 - Application number: 13/760,872 - Filed: 2013-02-06 - Published: 2014-06-05 - Earliest claimed: 2012-12-04 - Assignees: Elbit Systems - Cyclone Ltd. - Applicants: Elbit Systems - Cyclone Ltd. - Inventors: Lior ZILBERMAN; Oran KATZUNI; Leve COHEN - Web page: https://patentgrep.com/patent/US20140154458A1 ## CPC - B32B 3/06: for securing layers together; for attaching the product to another member, e.g. to a support {, or to another product, e.g. groove/tongue, interlocking} - B29C 70/682: {Preformed parts characterised by their structure, e.g. form} - B29C 70/86: Incorporated in coherent impregnated reinforcing layers, {e.g. by winding} - B29D 99/0014: {provided with ridges or ribs, e.g. joined ribs} - B64C 1/1461: {Structures of doors or surrounding frames} - B64C 3/20: Integral or sandwich constructions - B29C 70/48: and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM] {, e.g. by vacuum} - B29L 2031/3076: {Aircrafts (blades, propellers B29L2031/08)} - B64C 2001/0072: {from composite materials} - Y02T 50/40: Weight reduction - Y10T 428/24008: including fastener for attaching to external surface - B32B: LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM - B29C: SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING (making preforms B29B11/00; making laminated products by combining previously unconnected layers which become one product whose layers will remain together B32B37/00 - B32B41/00) - B29D: PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE (making granules B29B9/00; making preforms B29B11/00) - B64C: AEROPLANES; HELICOPTERS - B29L: INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract Composite material structures prepared from at least one reinforcement material and at least one matrix material are disclosed. The invention provides a simple solution for combining two or more components made of a composite material into a monolithic “fastener free” structure of a composite material having a smooth contour. The composite material structure includes a main frame with at least one load bearing beam having at least one beam surface. To this beam surface at least one composite material fitting is integrally attached. The main frame and the composite material fitting are conjoined by at least one matrix material. In addition, the disclosed technique provides for methods of production of a composite material structure with fittings made of a composite material. ## Claims ### Claim 1 A composite material structure comprising at least one reinforcement material and at least one matrix material, said composite material structure comprising: a main frame with at least one load bearing beam having at least one beam surface to which at least one composite material fitting is integrally attached, said at least one composite material fitting comprising: at least one mount portion comprising a bore for receiving a tubular bushing; and an anchoring structure extending from or coupled with said at least one mount portion, wherein said anchoring structure is comprised of at least one anchoring surface, at least one of said at least one anchoring surfaces is locally aligned with a beam surface; wherein each of said main frame and said composite material fitting is prepared from at least one reinforcement material and at least one matrix material; and wherein said main frame and said composite material fitting are conjoined by said at least one matrix material. ### Claim 2 (depends on 1) A composite material structure according to claim 1, wherein said main frame comprises at least one main frame surface to which at least one anchoring surface is locally aligned. ### Claim 3 (depends on 1) A composite material structure according to claim 1, for use in an aircraft. ### Claim 4 (depends on 1) A composite material structure according to claim 1, for use in a vehicle. ### Claim 5 (depends on 1) A composite material structure according to claim 1, which is selected from the list consisting of: a wing, a control surface, a flap, an aileron, a spoiler, a rudder, a stabilizer, an external fuel tank sections or a complete external fuel tank, an airplane cabin door, an airplane barrel section, a nacelle section, a body or chassis section and a fairing or a cover. ### Claim 6 (depends on 1) A composite material structure according to claim 1 that comprises at least one reinforcement material which is a fabric. ### Claim 7 (depends on 1) A composite material structure according to claim 1 wherein said at least one reinforcement material is selected from the list consisting of: glass, carbon, silicon carbide, aramid and a high strength polyethylene fiber. ### Claim 8 (depends on 1) A composite material structure according to claim 1, wherein said at least one matrix material is a thermoplastic or a thermoset polymer. ### Claim 9 (depends on 1) A composite material structure according to claim 1 wherein said composite material structure comprises a matrix material which is selected from the list consisting of: epoxy, phenolic, polyester, silicone, bismaleimide, polyimide and polybenzimidazole. ### Claim 10 (depends on 1) A composite material structure according to claim 1 wherein said composite material structure is manufactured by any one of the production methods selected from the list consisting of: closed mold RTM, compression molding, autoclave processing, open mold RI (resin infusion), vacuum bag molding and filament winding of tows or tapes. ### Claim 11 (depends on 1) A composite material structure according to claim 1 wherein said fitting is reinforced with metal plates. ### Claim 12 (depends on 1) A composite material structure according to claim 1 wherein said fitting comprises a tubular bushing made of metal. ### Claim 13 (depends on 1) A composite material structure according to claim 1 wherein said composite material structure is a flap which comprises a co-bonded protection element which covers a substantive portion of its leading edge. ### Claim 14 (depends on 1) A composite material structure according to claim 1 wherein said main frame is constructed from layers of reinforcement material, and wherein said layers of reinforcement material are draped over a portion of said fitting. ### Claim 15 (depends on 14) A composite material structure according to claim 14 wherein said layers of reinforcement material constructing said main frame are separated such that in between them said composite material fitting is positioned. ### Claim 16 (depends on 1) A composite material structure according to claim 1 wherein said at least one composite material fitting comprises at least one anchoring surface which is locally aligned with a beam surface, being substantially perpendicular to a center axis of said tubular bushing. ### Claim 17 (depends on 1) A composite material structure according to claim 1 wherein said at least one composite material fitting comprises at least one anchoring surface which is locally aligned with a beam surface, being substantially parallel to a center axis of said tubular bushing. ### Claim 18 (depends on 1) A composite material structure according to claim 1 wherein one of said at least one anchoring surfaces is in an angle in a range of between 70 to 110 degrees with respect to a center axis of said tubular bushing.