# US 9,434,470 B2 · Split spiroid > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,434,470 B2 - Document ID: US9434470B2 - Status: Granted - Kind: B2 - Application number: 14/719,925 - Filed: 2015-05-22 - Published: 2016-06-09 - Granted: 2016-09-06 - Earliest claimed: 2011-06-09 - Assignees: Aviation Partners, Inc. - Applicants: Aviation Partners, Inc. - Inventors: Louis B. Gratzer - Web page: https://patentgrep.com/patent/US9434470B2 ## CPC - B64C 23/065: {at the wing tips} - B64C 23/069: {using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips} - Y02T 50/10: Drag reduction - B64C: AEROPLANES; HELICOPTERS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract The spiroid wing tip according to embodiments of the invention including a continuous segmental assembly having a closed loop frontal profile comprising a lower near vertical segment, a horizontal segment, a vertical segment, a second horizontal upper segment, and a near vertical segment. Accordingly to some embodiments of the invention, the spiroid profile is lowered with respect to the wing chord plane, such that a portion of the spiroid wing tip extends below the wing chord plane. ## Claims ### Claim 1 A spiroid wing tip designed for attachment to an aircraft wing having an aircraft wing leading edge and an aircraft wing trailing edge, the spiroid wing tip comprising: an enclosed loop, comprising: a beginning section including a leading edge generally continuous with the aircraft wing leading edge; an ending section having a trailing edge swept rearward with respect to the aircraft wing trailing edge; and middle section between the beginning section and the ending section, the middle section including a portion extending above a chord plane of the aircraft wing. ### Claim 2 (depends on 1) The spiroid wing tip according to claim 1, wherein the ending section trailing edge is generally continuous with the aircraft wing trailing edge. ### Claim 3 (depends on 1) The spiroid wing tip according to claim 1, wherein the middle section is swept rearward with respect to the aircraft wing trailing edge. ### Claim 4 (depends on 1) The spiroid wing tip according to claim 1, wherein the middle section includes a portion extending below the chord plane of the aircraft wing. ### Claim 5 (depends on 1) The spiroid wing tip according to claim 1, wherein the beginning section extends from the aircraft wing in the chord plane thereof. ### Claim 6 (depends on 1) The spiroid wing tip according to claim 1, wherein the beginning section tapers from a first chord length at an aircraft wing attachment section to a second chord length smaller than the first chord length remote from the aircraft wing attachment section. ### Claim 7 (depends on 6) The spiroid wing tip according to claim 6, wherein the middle section tapers from the second chord length to a third chord length smaller than the second chord length. ### Claim 8 (depends on 7) The spiroid wing tip according to claim 7, wherein the ending section has an increasing chord length in a direction toward the aircraft wing. ### Claim 9 (depends on 1) The spiroid wing tip according to claim 1, wherein the middle section includes a first section connected to the beginning section and a second section connected to the ending section. ### Claim 10 (depends on 1) The spiroid wing tip according to claim 1, wherein each of the beginning section, ending section, and middle section are generally planar. ### Claim 11 (depends on 1) The spiroid wing tip according to claim 1, wherein the beginning section extends below the chord plane of the aircraft wing. ### Claim 12 (depends on 11) The spiroid wing tip according to claim 11, wherein the middle section traverses the chord plane of the aircraft wing. ### Claim 13 (depends on 1) The spiroid wing tip according to claim 1, wherein the middle section extends a distance h1 above the chord plane of the aircraft wing and a distance h2 below the chord plane of the aircraft wing, wherein the ratio of h2/h1 is between approximately 0.4 and 1.0. ### Claim 14 (depends on 1) The spiroid wing tip according to claim 1, wherein the enclosed loop has a horizontal width of w and a vertical height of h, wherein the ratio of w/h is approximately 1.0. ### Claim 15 (depends on 1) The spiroid wing tip according to claim 1, wherein a y-axis along an aircraft wing attachment section in the chord plane of the aircraft wing originates at the aircraft wing leading edge and extends toward the aircraft wing trailing edge, wherein an x-axis orthogonal to the y-axis is in the chord plane of the aircraft wing, and wherein a z-axis is orthogonal to both the y-axis and the x-axis, the beginning section extending from the aircraft wing attachment section in a positive x direction and a negative z direction, the ending section extending from the aircraft wing attachment section in the positive x direction and a positive z direction. ### Claim 16 (depends on 15) The spiroid wing tip according to claim 15, wherein the middle section includes a first part and a third part generally parallel to an x-y plane and a second part between the first and third parts orthogonal to the x-y plane. ### Claim 17 (depends on 1) The spiroid wing tip according to claim 1, wherein a portion of the ending section overlaps a portion of the beginning section.