# US 12,214,876 B2 · Cover panel > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,214,876 B2 - Document ID: US12214876B2 - Status: Granted - Kind: B2 - Application number: 18/029,071 - Filed: 2021-08-11 - Published: 2023-11-23 - Granted: 2025-02-04 - Earliest claimed: 2020-09-29 - Assignees: Airbus Operations GmbH - Applicants: Airbus Operations Limited - Inventors: Thomas Barnett; Lee Proudler - Web page: https://patentgrep.com/patent/US12214876B2 ## CPC - B64C 1/12: Construction or attachment of skin panels - B64C 3/26: Construction, shape, or attachment of separate skins, e.g. panels - B64C 1/069: {Joining arrangements therefor} - B64C 3/20: Integral or sandwich constructions - B64C 23/069: {using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips} - B64C 2001/0072: {from composite materials} - Y02T 50/10: Drag reduction - Y02T 50/40: Weight reduction - B64C: AEROPLANES; HELICOPTERS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A cover panel for an aircraft including: a first region, a second region for forming an overlap with a second panel, and a ramp, wherein at least a portion of the ramp is between the first and second regions, wherein the ramp includes a tapered region such that a width of the ramp tapers towards a free-edge of the first region, and wherein the free-edge is configured to form a butt-joint with the second panel. ## Claims ### Claim 1 A cover panel for an aircraft comprising: a first region with a first external aerodynamic surface of the aircraft, a second region configured to underlie a portion of a second panel, wherein the second panel includes a second external aerodynamic surface of the aircraft adjacent the first external aerodynamic surface, and a ramp spanning a gap between the first and second external aerodynamic surfaces, wherein the gap is parallel to the first and second external aerodynamic surfaces, wherein at least a portion of the ramp is between the first region and the second region, wherein a thickness of the cover panel varies to form the portion of the ramp between the first region towards the second region, wherein the ramp includes a tapered region such that a width of the ramp tapers towards a free-edge of the first region, and wherein the free-edge forms a butt-joint with the second panel. ### Claim 2 (depends on 1) The cover panel according to claim 1, wherein the tapered region extends in a direction angled with respect to a portion of the ramp adjacent to the tapered region. ### Claim 3 (depends on 1) The cover panel according to claim 1, wherein a thickness of the first region is greater than a thickness of the second region. ### Claim 4 (depends on 1) The cover panel according to claim 1, wherein a side of the cover panel is substantially planar. ### Claim 5 (depends on 1) The cover panel according to claim 1, wherein the cover panel comprises a carbon fiber reinforced polymer composite material. ### Claim 6 (depends on 5) The cover panel according to claim 5, wherein the ramp includes one or more ply drops. ### Claim 7 (depends on 5) The cover panel according to claim 5, wherein the cover panel is a laminate comprising: a plurality of dropped plies across the first region, and a location of the dropped plies coincides with the tapered region such that a height of the tapered region decreases towards the free-edge. ### Claim 8 A cover panel for an aircraft, comprising: a first region including a first external aerodynamic surface of the aircraft, a second region configured to underline a portion of the second panel, wherein the second panel include a second external aerodynamic surface of the aircraft adjacent the first external aerodynamic surface, and a ramp spanning a gap between the first and second external aerodynamic surfaces, wherein the gap is parallel to the first and second external aerodynamic surfaces, wherein at least a portion of the ramp is between the first region and the second region, wherein the ramp includes a tapered region such that a width of the ramp tapers towards a free-edge of the first region, wherein the free-edge forms a butt-joint with the second panel, and wherein the ramp includes a first portion and a second portion each between the first region and the second region, the first portion of the ramp extends in a direction angled with respect to the second portion. ### Claim 9 (depends on 8) The cover panel according to claim 8, wherein the first portion extends in a direction substantially perpendicular to the second portion. ### Claim 10 An assembly comprising: a cover panel comprising a first region, a second region, a ramp, wherein the first region includes a first external aerodynamic surface of the aircraft, and a second panel including a second external aerodynamic surface of the aircraft, wherein the second region underlies a portion of the second panel; wherein at least a portion of the ramp is between the first region and the second region, wherein the ramp spans a gap between and parallel to the first and second external aerodynamic surfaces, wherein the ramp includes a tapered region such that a width of the ramp tapers towards a free-edge of the first region, and wherein the free-edge forms a butt-joint with the second panel, and wherein a thickness of the cover panel varies to form the portion of the ramp between the first region towards the second region, and wherein the second panel forms an overlap with the second region of the cover panel. ### Claim 11 (depends on 10) The assembly according to claim 10, wherein the second panel has a substantially straight edge that extends across a portion of the second region and abuts the free-edge of the first region. ### Claim 12 (depends on 10) The assembly according to claim 10, wherein the cover panel is an aircraft wing tip cover panel and the second panel is a removable aircraft wing tip cover panel. ### Claim 13 (depends on 12) The assembly according to claim 12, wherein at least a portion of the ramp and the free-edge extend in a generally chordwise direction. ### Claim 14 (depends on 10) The assembly according to claim 10, wherein the free-edge is aft of the ramp and is configured to extend towards a trailing edge of a wing tip device. ### Claim 15 (depends on 8) The cover panel according to claim 8, wherein the first portion of the ramp extends in a generally chordwise direction and the second portion of the ramp extends in a generally spanwise direction. ### Claim 16 (depends on 15) The assembly according to claim 15 wherein the second portion of the ramp extends inboard towards an inboard end of a wing tip device. ### Claim 17 (depends on 1) An aircraft wing tip device comprising the cover panel of claim 1.