# US 12,006,019 B2 · Structural internal reinforcement element for a fuselage, and procedure for the manufacture of said structural element > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,006,019 B2 - Document ID: US12006019B2 - Status: Granted - Kind: B2 - Application number: 17/626,735 - Filed: 2020-07-09 - Published: 2022-09-22 - Granted: 2024-06-11 - Earliest claimed: 2019-07-12 - Assignees: Muelles Y Ballestas Hispano-Alemanas Projects, S.L. - Applicants: Muelles y Ballestas Hispano-Alemanas Projects, S.L - Inventors: Miguel Ruiz Dealbert; Juan Salamero Laorden; Roberto Estal Vera; María del Mar Cuetos Gómez - Web page: https://patentgrep.com/patent/US12006019B2 ## CPC - B64F 5/10: Manufacturing or assembling aircraft, e.g. jigs therefor - B29D 99/0014: {provided with ridges or ribs, e.g. joined ribs} - B64C 1/061: {Frames} - B64C 2001/0072: {from composite materials} - Y02T 50/40: Weight reduction - B64F: GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR - B29D: PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE (making granules B29B9/00; making preforms B29B11/00) - B64C: AEROPLANES; HELICOPTERS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract An internal structural reinforcement element for fuselages, where the internal structural reinforcement element has a longitudinal direction adapted for its placement in the longitudinal direction of the fuselage and a transversal direction perpendicular to the longitudinal direction, comprising: an external reinforcement element, an internal reinforcement element, located internally to the external reinforcement element in the transversal direction of the structural element, where both reinforcement elements are manufactured from resin-impregnated fibre, and an intermediate element, located between the external reinforcement element and the internal reinforcement element in the transversal direction of the structural element, the intermediate element being manufactured from pre-impregnated composite material. ## Claims ### Claim 1 An internal structural reinforcement element for fuselages, where the internal structural reinforcement element has a longitudinal direction adapted for its location in the longitudinal direction of the fuselage and a transverse direction perpendicular to its longitudinal direction, comprising: an external reinforcement element, an internal reinforcement element, located internally to the external reinforcement element in the transverse direction of the structural element, where both reinforcement elements are manufactured from resin-impregnated fibre, and an intermediate element, located between the external reinforcement element and the internal reinforcement element in the transverse direction of the structural element, the intermediate element being manufactured from pre-impregnated composite material, and the intermediate element comprising an H-shaped cross-section with flanges in the transverse direction of the structural element, in such a way that in the longitudinal direction of the structural element, the external and internal reinforcement elements are located between the flanges of the intermediate element. ### Claim 2 (depends on 1) The internal structural reinforcement element for fuselages, as claimed in claim 1, wherein the resin-impregnated fibre of the internal and external reinforcement elements is dry fibre impregnated in a bath of resin. ### Claim 3 (depends on 2) The internal structural reinforcement element for fuselages, as claimed in claim 2, wherein the fibre of the internal and external reinforcement elements is carbon fibre. ### Claim 4 (depends on 2) The internal structural reinforcement element for fuselages, as claimed in claim 2, wherein the impregnated fibre of the internal and external reinforcement elements is in the form of a filament. ### Claim 5 (depends on 1) The internal structural reinforcement element for fuselages, as claimed in claim 1, wherein the fibre of the internal and external reinforcement elements is carbon fibre. ### Claim 6 (depends on 5) The internal structural reinforcement element for fuselages, as claimed in claim 5, wherein the impregnated fibre of the internal and external reinforcement elements is in the form of a filament. ### Claim 7 (depends on 1) The internal structural reinforcement element for fuselages, as claimed in claim 1, wherein the impregnated fibre of the internal and external reinforcement elements is in the form of a filament. ### Claim 8 (depends on 1) The internal structural reinforcement element for fuselages, as claimed in claim 1, wherein the external reinforcement element and the internal reinforcement element have a tubular shape with their longitudinal axis in accordance with the longitudinal direction of the structural element. ### Claim 9 (depends on 1) The internal structural reinforcement element for fuselages, as claimed in claim 1, wherein the pre-impregnated composite material of the intermediate element is Sheet Moulding Compound (SMC) or Bulk Moulding Compound (BMC). ### Claim 10 (depends on 1) The internal structural reinforcement element for fuselages, as claimed in claim 1, wherein the intermediate element comprises a number of inserts for their joining to the fuselage. ### Claim 11 (depends on 10) The internal structural reinforcement element for fuselages, as claimed in claim 10, wherein the inserts are metallic. ### Claim 12 A method for the manufacture of an internal structural reinforcement element for fuselages, where the internal structural reinforcement element has a longitudinal direction adapted for its location in the longitudinal direction of the fuselage and a transverse direction perpendicular to the longitudinal direction, comprising the following steps: providing a first male mould, with the shape of an external reinforcement element, providing a second male mould, with the shape of an internal reinforcement element, the internal reinforcement element being adapted to be placed internally to the external reinforcement element in a direction transverse to the structural element, providing resin-impregnated fibre, placing part of the resin-impregnated fibre on the first male mould, placing part of the resin-impregnated fibre on the second male mould, removing the first male mould, so that the resin-impregnated fibre takes the form of the external reinforcement element, removing the second male mould, so that the resin-impregnated fibre takes the form of the internal reinforcement element, placing the internal and external reinforcement elements in a mould, the internal reinforcement element located internally to the external reinforcement element in a direction transverse to the structural element, in such a way that a transverse hollow is defined between both reinforcement elements, filling the transverse hollow between the internal and external reinforcement elements with pre-impregnated composite material, forming an intermediate element, and performing the compression moulding of the assembly, to obtain the structural reinforcement element. ### Claim 13 (depends on 12) The method for the manufacture of an internal structural reinforcement element for fuselages, as claimed in claim 12, wherein the first and second male moulds have a tubular shape. ### Claim 14 (depends on 12) The method for the manufacture of an internal structural reinforcement element for fuselages, as claimed in claim 12, wherein the step of placing the resin-impregnated fibre on the first and second male moulds is performed by means of the winding of at least one resin-impregnated fibre filament around the male mould. ### Claim 15 (depends on 12) The method for the manufacture of an internal structural reinforcement element for fuselages, as claimed in claim 12, wherein the pre-impregnated composite material of the intermediate element: is deposited in the mould, filling the intermediate space between the external and internal reinforcements, and subsequently the mould is closed, or is housed in a cavity located in the mould and is introduced into the intermediate space between the external and internal reinforcements subsequent to the closure of the mould. ### Claim 16 (depends on 12) The method for the manufacture of an internal structural reinforcement element for fuselages, as claimed in claim 12, wherein the resin-impregnated fibre is dry fibre impregnated in a resin bath prior to its placing on the male mould. ### Claim 17 (depends on 12) The method for the manufacture of an internal structural reinforcement element for fuselages, as claimed in claim 12, wherein the pre-impregnated composite material of the intermediate element is Sheet Moulding Compound (SMC) or Bulk Moulding Compound (BMC).