# US 10,246,177 B2 · Leading-edge structure for aircraft, aircraft wing, and aircraft > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,246,177 B2 - Document ID: US10246177B2 - Status: Granted - Kind: B2 - Application number: 15/240,068 - Filed: 2016-08-18 - Published: 2017-03-02 - Granted: 2019-04-02 - Earliest claimed: 2015-08-26 - Assignees: Mitsubishi Aircraft Corporation - Applicants: Mitsubishi Aircraft Corporation - Inventors: Kazuki Tachibana; Kohei Hara - Web page: https://patentgrep.com/patent/US10246177B2 ## CPC - B64C 3/28: Leading or trailing edges attached to primary structures, e.g. forming fixed slots - B64C 3/185: {Spars} - B64C 3/187: {Ribs} - B64C 3/26: Construction, shape, or attachment of separate skins, e.g. panels - B64C: AEROPLANES; HELICOPTERS ## Abstract The present invention has an objective to provide a leading-edge structure for an aircraft that is capable of, in the case of a collision with an airborne object, effectively absorbing the energy of the collision with the airborne object, with no increase in its weight. A leading-edge structure (10) for an aircraft according to the present invention includes a spar (11) extending in a predetermined direction, a plurality of ribs (13) provided in the predetermined direction of the spar (11) at intervals, and a skin (17) supported by the plurality of ribs (13). The ribs (13) includes first ribs 14 and a plurality of second ribs 15 that are disposed between the pair of first ribs (14). The second ribs (15) do not support the skin in the vicinity of their front ends. ## Claims ### Claim 1 A leading-edge structure for an aircraft that constitutes any leading-edge portion in an airframe of the aircraft, the leading-edge structure comprising: a spar that extends in a predetermined direction; a plurality of ribs that are provided in the predetermined direction of the spar at intervals; and a skin that is supported by the plurality of ribs, wherein: among the plurality of ribs, one or more of the ribs have a front end that is provided with a gap with the skin, as the plurality of ribs, the leading-edge structure comprises: a pair of first ribs that are disposed at a predetermined interval, and a plurality of second ribs that are disposed between the pair of first ribs, the second ribs each having the front end provided with the gap with the skin, the pair of first ribs are fixed to the spar, and the second ribs are not fixed to the spar. ### Claim 2 (depends on 1) The leading-edge structure for an aircraft according to claim 1, wherein the pair of first ribs have a stiffness higher than a stiffness of the second ribs. ### Claim 3 (depends on 1) A wing of an aircraft comprising the leading-edge structure according to claim 1 and a wing body that is connected to the leading-edge structure. ### Claim 4 (depends on 3) The wing of an aircraft according to claim 3, wherein the leading-edge structure and the wing body constitute at least one of a main wing, a horizontal tail, and a vertical tail. ### Claim 5 (depends on 3) The wing of an aircraft according to claim 3, wherein the leading-edge structure and the wing body constitute a vertical tail. ### Claim 6 (depends on 3) An aircraft comprising the wing according to claim 3. ### Claim 7 (depends on 1) The leading-edge structure for an aircraft according to claim 1, wherein the spar is located at a boundary between the leading-edge structure and a wing body that is connected to the leading-edge structure. ### Claim 8 (depends on 3) The wing of an aircraft according to claim 3, wherein the spar is located at a boundary between the leading-edge structure and the wing body. ### Claim 9 (depends on 1) The leading-edge structure for an aircraft according to claim 1, wherein the first ribs and the second ribs have different shapes from each other. ### Claim 10 (depends on 1) The leading-edge structure for an aircraft according to claim 1, wherein each of the second ribs has a linear front end that faces the skin. ### Claim 11 (depends on 9) The leading-edge structure for an aircraft according to claim 9, wherein the second ribs are configured to have a small dimension in a front-rear direction with respect to the first ribs. ### Claim 12 (depends on 2) A wing of an aircraft comprising the leading-edge structure according to claim 2 and a wing body that is connected to the leading-edge structure. ### Claim 13 (depends on 7) A wing of an aircraft comprising the leading-edge structure according to claim 7 and a wing body that is connected to the leading-edge structure. ### Claim 14 (depends on 9) A wing of an aircraft comprising the leading-edge structure according to claim 9 and a wing body that is connected to the leading-edge structure. ### Claim 15 (depends on 10) A wing of an aircraft comprising the leading-edge structure according to claim 10 and a wing body that is connected to the leading-edge structure. ### Claim 16 (depends on 12) An aircraft comprising the wing according to claim 12. ### Claim 17 (depends on 13) An aircraft comprising the wing according to claim 13. ### Claim 18 (depends on 14) An aircraft comprising the wing according to claim 14. ### Claim 19 (depends on 15) An aircraft comprising the wing according to claim 15.