# US 2024/0199233 A1 · Method for manufacturing an aircraft window frame comprising seams offset from a visible surface, window frame obtained from this method and aircraft comprising at least one such window frame > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2024/0199233 A1 - Document ID: US20240199233A1 - Status: Published application - Kind: A1 - Application number: 18/538,454 - Filed: 2023-12-13 - Published: 2024-06-20 - Earliest claimed: 2022-12-15 - Applicants: Airbus Operations SAS; Airbus Operations S.L. - Inventors: Asuncion BUTRAGUENO-MARTINEZ; Rodolphe TROUVE; Patrice ARTIGUES - Web page: https://patentgrep.com/patent/US20240199233A1 ## CPC - B64F 5/10: Manufacturing or assembling aircraft, e.g. jigs therefor - B32B 5/073: {characterised by the fibrous or filamentary layer being mechanically connected to another layer by sewing, stitching, hook-and-loop fastening or stitchbonding} - B32B 5/26: another layer {next to it} also being fibrous or filamentary {(relative arrangement of fibres or filaments of different layers B32B5/12)} - B64C 1/1492: {Structure and mounting of the transparent elements in the window or windscreen} - B64C 2001/0072: {from composite materials} - 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 - B32B: LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM - B64C: AEROPLANES; HELICOPTERS ## Abstract A method for manufacturing an aircraft window frame, the frame including a first surface that has a curved joining zone extending about the entire perimeter of the frame, this latter being made of composite material and including a stack of fiber layers, as well as at least one reinforcement positioned in the joining zone. The manufacturing method includes a step of assembling the different fiber layers and the reinforcement during which at least a first seam is made to join at least the reinforcement and some layers, the first seam including stitches offset from the first surface. A window frame is provided using this method, as well as an aircraft including the frame. ## Claims ### Claim 1 A method for manufacturing an aircraft window frame, said frame comprising a first surface that has at least first and second faces extending about an entire perimeter of the aircraft window frame, said first and second faces being joined by a curved joining zone, said frame being made of a composite material comprising fibers embedded in a resin matrix, the manufacturing method comprising: a step of assembling into an assembly, a reinforcement and a stack comprising a first layer positioned on the first surface and internal fiber layers, into a mold, a step of consolidating or polymerizing the assembly, and a step of demolding the aircraft window frame, the reinforcement having first and second peripheral edges, being interposed between the first layer on one side and the internal fiber layers on the other side, and being positioned in the joining zone, the first layer and the internal fiber layers extending on both sides of the reinforcement and being stacked on both sides of the reinforcement, wherein during the step of assembling, at least a first seam is made to join at least the reinforcement and some fiber layers, the first seam comprising stitches offset, in a direction perpendicular to the first surface, in relation to the first surface at least in the first face and in the joining zone so that the stitches do not reach the first surface and are not visible from the first surface. ### Claim 2 (depends on 1) The method for manufacturing an aircraft window frame as claimed in claim 1, wherein the stitches of the first seam do not traverse any fiber layers between the reinforcement and the first surface, at least in the first face. ### Claim 3 (depends on 1) The method for manufacturing an aircraft window frame as claimed in claim 1, wherein the aircraft window frame comprises at least one intermediate layer interposed between the first layer and the internal fiber layers, and wherein the first seam traverses the reinforcement, the internal fiber layers and at least one intermediate layer and does not traverse the first layer. ### Claim 4 (depends on 1) The method for manufacturing an aircraft window frame as claimed in claim 1, wherein during the assembly step, at least a second seam is made, offset from the joining zone and from the first face, the second seam comprising through-stitches visible from the first surface. ### Claim 5 (depends on 1) The method for manufacturing an aircraft window frame as claimed in claim 1, wherein a barrier layer is positioned between the reinforcement and the first surface to cover the reinforcement and to form a barrier limiting a spread of resin toward the first surface. ### Claim 6 (depends on 1) The method for manufacturing an aircraft window frame as claimed in claim 1, wherein the method comprises a step of sprinkling a resin between the fiber layers and heating to a temperature below a polymerization or consolidation temperature to activate a tack of the resin in order to keep the fiber layers bonded together before the consolidation or polymerization step. ### Claim 7 (depends on 1) An aircraft window frame manufactured using the method as claimed in claim 1, said frame comprising: a first surface that has at least first and second faces that extend about an entire perimeter of the aircraft window frame and that are joined by a curved joining zone, said aircraft window frame being made of a composite material comprising fibers embedded in a resin matrix, said aircraft window frame comprising a stack comprising a first layer positioned on the first surface and internal layers, as well as at least one reinforcement interposed between the first layer on one side and the internal layers on the other side, and positioned in the joining zone, the first layer and the internal layers extending on both sides of the reinforcement and being stacked on both sides of the reinforcement, wherein the aircraft window frame comprises at least a first seam joining at least the reinforcement and some layers, the first seam comprising stitches offset, in a direction perpendicular to the first surface, in relation to the first surface at least in the first face and in the joining zone so that the stitches do not reach the first surface and are not visible from the first surface. ### Claim 8 (depends on 7) The aircraft window frame as claimed in claim 7, wherein the aircraft window frame comprises at least a second seam offset from the joining zone and from the first face, the second seam comprising through-stitches visible from the first surface. ### Claim 9 (depends on 7) The aircraft window frame as claimed in claim 7, wherein the stitches of the first seam do not traverse any fiber layers between the reinforcement and the first surface, at least in the first face. ### Claim 10 (depends on 7) The aircraft window frame as claimed in claim 7, further comprising at least one intermediate layer interposed between the first layer and the internal layers, and wherein the first seam traverses the reinforcement, the internal layers and the at least one intermediate layer and does not traverse the first layer. ### Claim 11 (depends on 7) The aircraft window frame as claimed in claim 7, wherein the aircraft window frame comprises at least one barrier layer covering the reinforcement, positioned between the reinforcement and the first surface and configured to form a barrier limiting a spread of resin toward the first surface. ### Claim 12 (depends on 7) An aircraft comprising at least one window frame as claimed in claim 7.