# US 9,751,608 B2 · Composite material structure, and aircraft wing and aircraft fuselage provided therewith > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,751,608 B2 - Document ID: US9751608B2 - Status: Granted - Kind: B2 - Application number: 13/881,590 - Filed: 2012-01-26 - Published: 2013-09-12 - Granted: 2017-09-05 - Earliest claimed: 2011-02-04 - Assignees: Mitsubishi Heavy Industries, Ltd. - Applicants: Yuya Tanaka; Hideyuki Suzuki; Yutaka Kanayama; Kazuki Sato; Masatake Hatano; Satoru Saito; Akihisa Watanabe; Ryo Abe - Inventors: Yuya Tanaka; Hideyuki Suzuki; Yutaka Kanayama; Kazuki Sato; Masatake Hatano; Satoru Saito; Akihisa Watanabe; Ryo Abe - Web page: https://patentgrep.com/patent/US9751608B2 ## CPC - B64C 3/20: Integral or sandwich constructions - B29C 70/545: {Perforating, cutting or machining during or after moulding} - B29C 70/86: Incorporated in coherent impregnated reinforcing layers, {e.g. by winding} - B32B 3/10: characterised by a discontinuous layer, i.e. formed of separate pieces of material - B32B 3/14: characterised by a face layer formed of separate pieces of material {which are juxtaposed side-by-side (B32B5/02 takes precedence)} - B32B 3/263: {characterised by a layer having non-uniform thickness} - B32B 3/266: {characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12} - B32B 5/26: another layer {next to it} also being fibrous or filamentary {(relative arrangement of fibres or filaments of different layers B32B5/12)} - B32B 7/08: by mechanical means - B32B 7/14: applied in spaced arrangements, e.g. in stripes - B32B 15/08: of synthetic resin - B32B 15/14: next to a fibrous or filamentary layer - B32B 15/20: comprising aluminium or copper {(B32B15/016 and B32B15/017 take precedence)} - B32B 27/08: of synthetic resin - B64C 1/064: {Stringers; Longerons} - B64C 3/182: {Stringers, longerons} - B64C 3/26: Construction, shape, or attachment of separate skins, e.g. panels - B29K 2705/00: Use of metals, their alloys or their compounds, for preformed parts, e.g. for inserts - B29K 2705/02: Aluminium - B32B 2260/021: Fibrous or filamentary layer - B32B 2260/046: Synthetic resin - B32B 2262/0269: Aromatic polyamide fibres - B32B 2262/101: Glass fibres - B32B 2262/106: Carbon fibres, e.g. graphite fibres - B32B 2307/718: Weight, e.g. weight per square meter - B32B 2307/732: Dimensional properties - B32B 2605/08: Cars - B32B 2605/12: Ships - B32B 2605/18: Aircraft - B64C 1/14: Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens {accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers}(fairings movable in conjunction with undercarriage elements B64C25/16; bomb doors B64D1/06) - B64C 3/34: Tanks constructed integrally with wings, e.g. for fuel or water - B64C 2001/0072: {from composite materials} - Y02T 50/40: Weight reduction - Y10T 428/24322: Composite web or sheet - B64C: AEROPLANES; HELICOPTERS - 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) - B32B: LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM - B29K: INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR {MOULDS, } REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract A composite material structure reinforced against stress concentration in peripheral edge portions of holes and enabled to be reduced in weight. A wing (1) is formed in a box structure. A lower surface outer plate (3) of the wing (1) includes: a center section (3b) made of metal extending in one direction and having access holes (5) formed therein; a front section (3a); and a rear section (3c) made of fiber reinforced plastics extending in the one direction and connected to both side portions of the center section (3b). As the metal used for the center section (3b), a titanium alloy or an aluminum alloy is suitable. ## Claims ### Claim 1 A composite material structure for an aircraft comprising: a structure member with holes consisting of metal, the structure member with holes extending in one direction and having holes formed therein; an adjacent structure member formed as a composite material consisting of fiber reinforced plastics, the adjacent structure member extending in the one direction and being connected to a side portion of the structure member with holes and to a portion avoiding positions of the holes formed in the structure member with holes; and a plurality of stringers provided so as to extend in the one direction, wherein the structure member with holes includes: a fixed thickness region; and peripheral edge regions reinforcing peripheral edge portions of the holes, each of the peripheral edge regions being further increased in thickness compared to the fixed thickness region, and wherein regions other than the peripheral edge regions are not increased in thickness, wherein the side portion of the structure member with holes is connected to the side portion of the adjacent structure member at division surfaces extending in the one direction, or the division surfaces are provided so as to incline with respect to a plate thickness direction and are connected to each other, wherein one of the stringers extends in the one direction along the division surfaces, and wherein the one stringer is placed on the division surfaces, and is fixed to an inner surface of the structure member with holes and the adjacent structure member by fasteners configured by a bolt, a nut, and/or bonding. ### Claim 2 (depends on 1) The composite material structure according to claim 1, wherein a lower surface outer plate of a wing of an aircraft is configured by a plurality of members extending in a longitudinal direction of the wing, and among the members, a member including access holes as the holes formed in the lower surface outer plate is the structure member with holes and another member is the adjacent structure member. ### Claim 3 (depends on 1) The composite material structure according to claim 1, wherein an outer plate of a fuselage of an aircraft is configured by a plurality of members extending in a longitudinal direction of the fuselage, and among the members, a member including window holes as the holes formed in the outer plate is the structure member with holes and another member is the adjacent structure member. ### Claim 4 (depends on 2) An aircraft wing comprising the composite material structure according to claim 2. ### Claim 5 (depends on 3) An aircraft fuselage comprising the composite material structure according to claim 3. ### Claim 6 A composite material structure for an aircraft comprising: a structure member with holes extending in one direction and having holes formed therein, wherein the structure member with holes consists of metal; an adjacent structure member formed of a composite material consisting of fiber reinforced plastics, wherein the adjacent structure member extends in the one direction and is connected to a side portion of the structure member with holes so that the adjacent structure member and the structure member with holes do not overlap at an edge of the hole; and a plurality of stringers provided in the one direction of the composite material structure at a position in which the structure member with holes is connected to the adjacent structure member, wherein the structure member with holes includes: a fixed thickness region; and peripheral edge regions reinforcing peripheral edge portions of the holes, each of the peripheral edge regions being increased in thickness compared to the fixed thickness region, wherein regions other than the peripheral edge regions are not increased in thickness relative to the fixed thickness region, wherein one of the stringers extends in the one direction along division surfaces at which the side portion of the structure member with holes is connected to the side portion of the adjacent structure member, and wherein the one stringer is placed on the division surfaces, and is fixed to inner surfaces of the structure member with holes and the adjacent structure member by fasteners configured by a bolt, a nut, and/or bonding.