# US 12,595,067 B2 · Wing for aircraft having battery modules and spars supported by flange portions of ribs > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,595,067 B2 - Document ID: US12595067B2 - Status: Granted - Kind: B2 - Application number: 18/947,663 - Filed: 2024-11-14 - Published: 2026-01-01 - Granted: 2026-04-07 - Earliest claimed: 2024-06-26 - Assignees: Hyundai Motor Company; Kia Corporation - Applicants: Hyundai Motor Company; Kia Corporation - Inventors: Yoon Cheol Jeon - Web page: https://patentgrep.com/patent/US12595067B2 ## CPC - B64D 27/31: within, or attached to, wings - B64C 3/18: Spars; Ribs; Stringers - B64C 3/185: {Spars} - B64C 3/187: {Ribs} - B64C 3/32: specially adapted for mounting power plant - B64D 27/357: using batteries - H01M 50/209: adapted for prismatic or rectangular cells (H01M50/216 takes precedence) - H01M 50/249: specially adapted for aircraft or vehicles, e.g. cars or trains (constructional details of batteries specially adapted for electric vehicles B60L50/64) - H01M 50/258: Modular batteries; Casings provided with means for assembling - H01M 50/262: with fastening means, e.g. locks - H01M 50/291: characterised by their shape - B64U 50/30: Supply or distribution of electrical power - H01M 2220/20: Batteries in motive systems, e.g. vehicle, ship, plane - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - B64C: AEROPLANES; HELICOPTERS - H01M: PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY - B64U: UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR ## Abstract A wing for an aircraft include battery modules a plurality of ribs that are spaced apart from one another in a longitudinal direction of the wing, the plurality of ribs respectively defining a plurality of first through-holes through which the battery modules pass, a plurality of first flange portions that are respectively disposed at the plurality of ribs along edges of the first through-holes, the plurality of first flange portions defining battery seating surfaces that support the battery modules, and a spar that supports the plurality of ribs. ## Claims ### Claim 1 A wing for an aircraft, comprising: battery modules; a plurality of ribs that are spaced apart from one another in a longitudinal direction of the wing, the plurality of ribs respectively defining a plurality of first through-holes through which the battery modules pass; a plurality of first flange portions that are respectively disposed at the plurality of ribs and define a plurality of battery seating surfaces configured to support the battery modules, each of the plurality of first flange portions being disposed along an edge of one of the plurality of first through-holes; and a spar that extends through and supports the plurality of ribs, wherein each of the plurality of first flange portions protrudes from one surface of one of the plurality of ribs along the edge of the one of the plurality of first through-holes. ### Claim 2 (depends on 1) The wing of claim 1, wherein each of the plurality of first flange portions comprises: a first flange disposed at a corresponding one of the plurality of ribs along an upper edge of the one of the plurality of first through-holes, the first flange supporting an upper surface of one of the battery modules; and a second flange disposed at the corresponding one of the plurality of ribs along a lower edge of the one of the plurality of first through-holes, the second flange supporting a bottom surface of the one of the battery modules. ### Claim 3 (depends on 2) The wing of claim 2, wherein at least one of the first flange or the second flange defines a fastening hole for fastening the one of the battery modules. ### Claim 4 (depends on 1) The wing of claim 1, wherein the plurality of first flange portions are in contact with the battery modules. ### Claim 5 (depends on 1) The wing of claim 1, wherein each of the plurality of ribs further defines a second through-hole that receives the spar. ### Claim 6 (depends on 5) The wing of claim 5, further comprising: a plurality of second flange portions that are respectively disposed at the plurality of ribs, each of the second flange portions being disposed along an edge of the second through-hole and defining a spar seating surface that supports the spar. ### Claim 7 (depends on 6) The wing of claim 6, wherein the plurality of second flange portions are in contact with the spar. ### Claim 8 (depends on 6) The wing of claim 6, wherein each of the plurality of second flange portions has a cross-section corresponding to the spar. ### Claim 9 (depends on 6) The wing of claim 6, further comprising: a locking part configured to restrain an arrangement state of one of the plurality of ribs with respect to the spar. ### Claim 10 (depends on 9) The wing of claim 9, wherein each of the plurality of second flange portions defines a restraint hole configured to catch the locking part. ### Claim 11 (depends on 10) The wing of claim 10, wherein the locking part is one of a plurality of locking parts that are spaced apart from one another in a longitudinal direction of the spar. ### Claim 12 (depends on 1) The wing of claim 1, wherein each of the battery modules is supported by at least two or more of the plurality of ribs. ### Claim 13 (depends on 1) The wing of claim 1, wherein the spar comprises: a front spar provided adjacent to a front end of the plurality of ribs; and a rear spar provided adjacent to a rear end of the plurality of ribs. ### Claim 14 (depends on 1) The wing of claim 1, wherein the spar extends through the one surface of each rib of the plurality of ribs in the longitudinal direction of the wing. ### Claim 15 (depends on 1) The wing of claim 1, wherein an end of each of the plurality of first flange portions defines the edge of the one of the plurality of first through-holes. ### Claim 16 (depends on 1) The wing of claim 1, wherein a length of each of the plurality of first flange portions in the longitudinal direction is an extension length of the one of the plurality of first through-holes in the longitudinal direction. ### Claim 17 A wing for an aircraft, comprising: battery modules; a plurality of ribs that are spaced apart from one another in a longitudinal direction of the wing, the plurality of ribs respectively defining a plurality of first through-holes through which the battery modules pass; a plurality of first flange portions that are respectively disposed at the plurality of ribs and define a plurality of battery seating surfaces configured to support the battery modules, each of the plurality of first flange portions being disposed along an edge of one of the plurality of first through-holes; and a spar that extends through and supports the plurality of ribs, wherein each of the plurality of ribs further defines a second through-hole that receives the spar, wherein the wing further comprises: a plurality of second flange portions that are respectively disposed at the plurality of ribs, each of the second flange portions being disposed along an edge of the second through-hole and defining a spar seating surface that supports the spar, and a locking part configured to restrain an arrangement state of one of the plurality of ribs with respect to the spar, wherein each of the plurality of second flange portions defines a restraint hole configured to catch the locking part, and wherein the locking part comprises: an inner race coupled to the spar, an outer race that surrounds a periphery of the inner race and is configured to be accommodated in one of the plurality of second flange portions, a plunger member provided between the inner race and the outer race and configured to be move between (i) a first position in which the plunger member is restrained by the restraint hole and (ii) a second position in which the plunger member is unrestrained from the restraint hole, and a plunger spring configured to elastically support movement of the plunger member, the plunger spring having (i) a first end supported on the inner race and (ii) a second end supported on the plunger member.