# US 11,111,948 B2 · Aircraft assembly > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,111,948 B2 - Document ID: US11111948B2 - Status: Granted - Kind: B2 - Application number: 16/392,721 - Filed: 2019-04-24 - Published: 2019-10-31 - Granted: 2021-09-07 - Earliest claimed: 2018-04-25 - Assignees: Safran Landing Systems UK LTD - Applicants: Safran Landing Systems UK Ltd - Inventors: Matthew Hilliard - Web page: https://patentgrep.com/patent/US11111948B2 ## CPC - F16B 33/008: {Corrosion preventing means} - F16B 33/02: Shape of thread; Special thread-forms ({F16B25/00 takes precedence; used to remove paint or dirt layers F16B35/007, F16B37/002}; used as screw-locking device F16B39/30) - B21H 3/02: external screw-threads {; Making dies for thread rolling} - B64C 25/36: Arrangements or adaptations of wheels, tyres or axles in general - B64C 25/58: Arrangements or adaptations of shock-absorbers or springs (shimmy-dampers B64C25/50) - F16B 7/18: using screw-thread elements {(F16B7/025 takes precedence; for turnbuckles F16B7/06)} - F16B 37/12: with thread-engaging surfaces formed by inserted coil-springs, discs, or the like; Independent pieces of wound wire used as nuts; Threaded inserts for holes {(mounting devices B25B27/143)} - F16B 39/34: Locking by deformable inserts or like parts - B23G 2225/44: Titanium - F16B: DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING (couplings for transmitting rotation F16D) - B21H: MAKING PARTICULAR METAL OBJECTS BY ROLLING, e.g. SCREWS, WHEELS, RINGS, BARRELS, BALLS (essentially from sheet metal B21D) - B64C: AEROPLANES; HELICOPTERS - B23G: THREAD CUTTING; WORKING OF SCREWS, BOLT HEADS, OR NUTS, IN CONJUNCTION THEREWITH (making helical grooves by turning B23B5/48, by milling B23C3/32, by forging, pressing, or hammering B21K1/56, by grinding B24B19/02; arrangements for copying or controlling B23Q; thread-forming by corrugating tubes B21D15/04, by rolling B21H3/02) ## Abstract An aircraft assembly having a titanium rod comprising a first threaded portion, and a titanium nut comprising a second threaded portion conforming with the first threaded portion for mating engagement with it. One of the first and second threaded portions defines a male thread and the other one of the first and second threaded portions defines a female thread such that the nut can be wound in threading engagement along the rod. A threaded insert formed from a first metal of different hardness in comparison to titanium is coupled to the rod or the nut to define the first threaded portion or the second threaded portion respectively such that one of the first and second threaded portions is formed from titanium and the other one of the first and second threaded portions is formed from the first metal. ## Claims ### Claim 1 An aircraft assembly comprising: a titanium rod comprising a first threaded portion; a titanium nut comprising a second threaded portion conforming with the first threaded portion for mating engagement with the first threaded portion, wherein one of the first threaded portion and the second threaded portion defines a male thread and the other one of the first threaded portion and the second threaded portion defines a female thread such that the nut can be wound in threading engagement along the rod; and a threaded insert formed from a first metal of different hardness in comparison to titanium, the threaded insert being coupled to the rod or the nut to define the first threaded portion or the second threaded portion respectively such that one of the first threaded portion and the second threaded portion is formed from titanium and the other one of the first threaded portion and the second threaded portion is formed from the first metal; wherein the rod defines a bore, the first threaded portion defines the female threaded portion within the bore and the nut is a gland nut defining the male threaded portion, wherein the titanium rod comprises an outer cylinder of an aircraft landing gear shock absorbing strut. ### Claim 2 (depends on 1) The aircraft assembly according to claim 1, wherein the one of the first threaded portion and the second threaded portion that is formed from titanium comprises threads formed by a cold forging thread rolling process. ### Claim 3 (depends on 1) The aircraft assembly according to claim 1, wherein the body of the nut or rod to which the insert is coupled is at least 80% of the volume of the nut or rod respectively. ### Claim 4 (depends on 1) The aircraft assembly according to claim 1, wherein the insert defines the female threaded portion. ### Claim 5 (depends on 1) The aircraft assembly according to claim 1, wherein the insert comprises a self-locking thread insert. ### Claim 6 (depends on 1) The aircraft assembly according to claim 1, wherein the insert is formed from die drawn wire. ### Claim 7 (depends on 1) The aircraft assembly according to claim 1, wherein the insert is formed from a copper nickel tin alloy comprising at least 75% by weight copper and at least 15% nickel and at least 5% tin. ### Claim 8 (depends on 1) The aircraft assembly according to claim 1, wherein the first threaded portion, defined by the rod, defines the male threaded portion and the nut body defines a bore, the insert being located within the bore and defining the female threaded portion. ### Claim 9 (depends on 1) The aircraft assembly according to claim 1, wherein the titanium rod comprises an outer cylinder of an aircraft landing gear shock absorbing strut. ### Claim 10 (depends on 1) The aircraft assembly according to claim 1, wherein the insert is coupled to the rod. ### Claim 11 An aircraft assembly comprising: a titanium rod comprising a first threaded portion; a titanium nut comprising a second threaded portion conforming with the first threaded portion for mating engagement with the first threaded portion, wherein the first threaded portion defines a male thread and the second threaded portion defines a female thread such that the nut can be wound in threading engagement along the rod; and a threaded insert formed from a first metal of different hardness in comparison to titanium, the threaded insert being coupled to the nut to define the second threaded portion such that the first threaded portion is formed from titanium and the second threaded portion is formed from the first metal, wherein the nut body defines a bore, the insert being located within the bore and defining the female threaded portion and wherein the titanium rod comprises an aircraft landing gear axle. ### Claim 12 An aircraft assembly comprising: a titanium rod comprising a first threaded portion; a titanium nut comprising a second threaded portion conforming with the first threaded portion for mating engagement with the first threaded portion, wherein one of the first threaded portion and the second threaded portion defines a male thread and the other one of the first threaded portion and the second threaded portion defines a female thread such that the nut can be wound in threading engagement along the rod; and a threaded insert formed from a first metal of different hardness in comparison to titanium, the threaded insert being coupled to the rod or the nut to define the first threaded portion or the second threaded portion respectively such that one of the first threaded portion and the second threaded portion is formed from titanium and the other one of the first threaded portion and the second threaded portion is formed from the first metal; wherein the insert is formed from a copper nickel tin alloy comprising at least 75% by weight copper and at least 15% nickel and at least 5% tin.