# US 12,006,064 B2 · Manufacturing method of a control surface of an aircraft and aircraft control surface > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,006,064 B2 - Document ID: US12006064B2 - Status: Granted - Kind: B2 - Application number: 17/991,947 - Filed: 2022-11-22 - Published: 2023-05-25 - Granted: 2024-06-11 - Earliest claimed: 2021-11-24 - Assignees: Airbus Operations S.L.U. - Applicants: Airbus Operations S.L.U. - Inventors: Robert Kobierecki; David Martin Palomares; Alberto Balsa-Gonzalez - Web page: https://patentgrep.com/patent/US12006064B2 ## CPC - B64C 3/20: Integral or sandwich constructions - B64F 5/10: Manufacturing or assembling aircraft, e.g. jigs therefor - B29B 11/16: comprising fillers or reinforcement {(non-woven fabrics per se D04H1/00, D04H3/00)} - B29C 70/30: Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core - B29C 70/86: Incorporated in coherent impregnated reinforcing layers, {e.g. by winding} - B64C 3/28: Leading or trailing edges attached to primary structures, e.g. forming fixed slots - B64C 5/10: adjustable - B64C 9/00: Adjustable control surfaces or members, e.g. rudders (trimming stabilising surfaces B64C5/10) - B29D 99/0014: {provided with ridges or ribs, e.g. joined ribs} - B29D 99/0028: {hollow blades} - B64C: AEROPLANES; HELICOPTERS - 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 - B29B: PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS - 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) ## Abstract A manufacturing method of a control surface of an aircraft, the control surface including an upper skin, a lower skin, ribs joining the upper skin and the lower skin and located along a chordwise direction of the control surface. The manufacturing method includes the steps of providing a single composite preform comprising the upper skin, the lower skin and the ribs, and curing the single composite preform such that an integrated box comprising the upper skin, the lower skin and the ribs is formed. ## Claims ### Claim 1 A manufacturing method of a control surface of an aircraft, the control surface comprising: an upper skin, a lower skin, ribs joining the upper skin and the lower skin and located along a chordwise direction of the control surface, wherein the manufacturing method comprises the steps of: providing a single composite preform comprising the upper skin, the lower skin and the ribs, and curing said single composite preform such that an integrated box comprising the upper skin, the lower skin and the ribs is formed, wherein after the curing step of the integrated box, a curing tool located between the upper skin and the lower skin is extracted from the integrated box in a chordwise direction towards a front edge of the control surface, wherein the ribs are manufactured with their chordwise length shorter than the upper and lower skins chordwise length, and wherein the curing tool comprises a first part in contact with the upper skin and the lower skin and a second part having a L-shape in contact with the upper skin, the lower skin and a rib, a portion of the second part located in the chordwise direction being located in a space between the rib and a rear edge of the control surface. ### Claim 2 (depends on 1) The manufacturing method of a control surface of an aircraft, according to claim 1, the control surface further comprising: a spar located along a span direction of the control surface at a front edge or at a rear edge of the control surface, fittings joined to the spar, and wherein the manufacturing method further comprises providing a single composite preform comprising the spar and the fittings and curing said single composite preform such that an integrated end comprising the spar and the fittings is formed. ### Claim 3 (depends on 2) The manufacturing method of a control surface of an aircraft, according to claim 2, further comprising mechanically joining the integrated box and the integrated end of the control surface. ### Claim 4 (depends on 3) The manufacturing method of a control surface of an aircraft, according to claim 3, wherein the integrated box and the integrated end are mechanically joined providing at least a T-shape element located along a chord direction of the integrated box and joined to a rib of the integrated box and to the spar of the integrated end. ### Claim 5 (depends on 3) The manufacturing method of a control surface of an aircraft, according to claim 3, wherein at least a rib comprises an extension extending at least partially in a spanwise direction of the control surface at its front edge or at its rear edge such that the extension is mechanically joined to the spar. ### Claim 6 (depends on 2) The manufacturing method of a control surface of an aircraft, according to claim 2, wherein the composite preform of the upper skin, the lower skin and the ribs and the composite preform of the spar and the fittings are dry fiber composite preforms. ### Claim 7 (depends on 2) The manufacturing method of a control surface of an aircraft, according to claim 2, wherein the fittings are configured for attaching the control surface to at least one of a lifting surface of the aircraft or actuators of the control surface. ### Claim 8 (depends on 1) The manufacturing method of a control surface of an aircraft, according to claim 1, wherein the ribs are manufactured with their chordwise length shorter than the upper and lower skins chordwise length. ### Claim 9 (depends on 1) The manufacturing method of a control surface of an aircraft, according to claim 1, additionally comprising a step of providing at least a panel covering a joint of the integrated box and an integrated end along a span direction of the control surface. ### Claim 10 (depends on 9) The manufacturing method of a control surface of an aircraft, according to claim 9, further comprising a step of providing a non-metallic insert along the span direction of the control surface between the upper skin and lower skin at a rear edge of the control surface. ### Claim 11 (depends on 10) The manufacturing method of a control surface of an aircraft, according to claim 10, further comprising a step of providing a metallic profile along the span direction of the control surface and covering the non-metallic insert at the rear edge. ### Claim 12 A manufacturing method of a control surface of 16. an aircraft, the control surface comprising: an upper skin, a lower skin, ribs joining the upper skin and the lower skin and located along a chordwise direction of the control surface, wherein the manufacturing method comprises the steps of: providing a single composite preform comprising the upper skin, the lower skin and the ribs, and curing said single composite preform such that an integrated box comprising the upper skin, the lower skin and the ribs is formed, wherein at least a panel covering a joint of the integrated box and an integrated end along a span direction of the control surface is provided, wherein a non-metallic insert is provided along the span direction of the control surface between the upper skin and lower skin at a rear edge of the control surface; and, wherein a metallic profile is provided along the span direction of the control surface and covering the non-metallic insert at the rear edge.