# US 2017/0284337 A1 · Controlling a relative position at an interface between translating structures of an aircraft nacelle > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2017/0284337 A1 - Document ID: US20170284337A1 - Status: Published application - Kind: A1 - Application number: 15/088,761 - Filed: 2016-04-01 - Published: 2017-10-05 - Earliest claimed: 2016-04-01 - Assignees: Rohr, Inc. - Applicants: Rohr, Inc. - Inventors: Johann S. Schrell - Web page: https://patentgrep.com/patent/US20170284337A1 ## CPC - F02K 1/605: {the aft end of the engine cowling being movable to uncover openings for the reversed flow} - B64D 29/06: Attaching of nacelles, fairings or cowlings - F02K 1/72: the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow - F02K 1/766: {with blocking systems or locking devices; Arrangement of locking devices for thrust reversers} - F05D 2260/30: Retaining components in desired mutual position - F05D 2260/36: by a form fit connection, e.g. by interlocking - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A nacelle is provided for an aircraft propulsion system. This nacelle includes a stationary support, a fanlet, a thrust reverser sleeve and an interface assembly providing an interface between the stationary support, the fanlet and the thrust reverser sleeve where the fanlet and the thrust reverser sleeve are respectively in stowed positions. The stationary support extends circumferentially about an axial centerline. The fanlet includes an inlet structure and a fan cowl. The fanlet is configured to translate axially along the centerline. The thrust reverser sleeve is configured to translate axially along the centerline. The interface assembly includes a pair of interlocking components, wherein a first of the interlocking components is mounted to the fanlet at the aft end of the fanlet. ## Claims ### Claim 1 A nacelle for an aircraft propulsion system, comprising: a stationary support extending circumferentially about an axial centerline; a fanlet including an inlet structure and a fan cowl, the fanlet configured to translate axially along the centerline; a thrust reverser sleeve configured to translate axially along the centerline; and an interface assembly providing an interface between the stationary support, the fanlet and the thrust reverser sleeve where the fanlet and the thrust reverser sleeve are respectively in stowed positions; the interface assembly configured to maintain a relative position between an aft end of the fanlet and a forward end of the thrust reverser sleeve at the interface; and the interface assembly including a pair of interlocking components, wherein a first of the interlocking components is mounted to the fanlet at the aft end of the fanlet. ### Claim 2 (depends on 1) The nacelle of claim 1, wherein the relative position comprises a relative axial position. ### Claim 3 (depends on 1) The nacelle of claim 1, wherein the relative position comprises a relative radial position. ### Claim 4 (depends on 1) The nacelle of claim 1, wherein the interface assembly is configured to maintain the relative position between the aft end of the fanlet and the forward end of the thrust reverser sleeve such that: a predetermined axial gap is maintained between the aft end of the fanlet and the forward end of the thrust reverser sleeve; and an exterior surface of the fanlet is substantially radially flush with an exterior surface of the thrust reverser sleeve. ### Claim 5 (depends on 1) The nacelle of claim 1, wherein the first of the interlocking components is configured with an aperture; and a second of the interlocking components is configured with a projection that extends axially into the aperture where the second of the interlocking components is mated with the first of the interlocking components. ### Claim 6 (depends on 1) The nacelle of claim 1, wherein the interface assembly further includes a lock configured to selectively lock the interlocking components together where the fanlet and the thrust reverser sleeve are respectively in the stowed positions. ### Claim 7 (depends on 1) The nacelle of claim 1, wherein the second of the interlocking components is mounted to the thrust reverser sleeve at the forward end of the thrust reverser sleeve. ### Claim 8 (depends on 7) The nacelle of claim 7, wherein the interface assembly further includes a rub strip disposed radially between and contacting the first of the interlocking components and the stationary structure. ### Claim 9 (depends on 1) The nacelle of claim 1, wherein the second of the interlocking components is mounted to the stationary structure. ### Claim 10 (depends on 9) The nacelle of claim 9, wherein the interface assembly further includes a rub strip disposed radially between and contacting the fanlet and the stationary structure. ### Claim 11 (depends on 9) The nacelle of claim 9, wherein the interface assembly further includes a pair of second interlocking components; a first of the second interlocking components is mounted to the thrust reverser sleeve at the forward end of the thrust reverser sleeve; and a second of the second interlocking components is mounted to the stationary support. ### Claim 12 (depends on 11) The nacelle of claim 11, wherein the first of the interlocking components is configured with an aperture; the second of the interlocking components is configured with a projection that extends axially into the aperture where the second of the interlocking components is mated with the first of the interlocking components; the first of the second interlocking components is configured with a second aperture; and the second of the second interlocking components is configured with a second projection that extends axially into the second aperture where the second of the second interlocking components is mated with the first of the second interlocking components. ### Claim 13 (depends on 11) The nacelle of claim 11, wherein the interface assembly further includes a lock configured to selectively lock the second interlocking components together where the thrust reverser sleeve is in the stowed position. ### Claim 14 (depends on 11) The nacelle of claim 11, wherein the interface assembly further includes a rub strip disposed radially between and contacting the thrust reverser sleeve and the stationary structure. ### Claim 15 A nacelle for an aircraft propulsion system, comprising: a stationary support extending circumferentially about an axial centerline; a forward nacelle structure configured to translate axially along the centerline between a stowed position and a deployed position; an aft nacelle structure configured to translate axially along the centerline between a stowed position and a deployed position; and an interface assembly at an interface between the stationary support, the forward nacelle structure and the aft nacelle structure where the forward nacelle structure and the aft nacelle structure are respectively in the stowed positions, the interface assembly including a pair of interlocking components, wherein a first of the interlocking components is mounted to the forward nacelle structure at the aft end of the forward nacelle structure, and a second of the interlocking components is mounted to the stationary support. ### Claim 16 A nacelle for an aircraft propulsion system with an axial centerline, comprising: a fanlet configured to translate axially along the centerline; a thrust reverser sleeve configured to translate axially along the centerline; and an interface assembly at an interface between the fanlet and the thrust reverser sleeve where the fanlet and the thrust reverser sleeve are respectively in stowed positions, the interface assembly including a plurality of interlocking components, wherein a first of the interlocking components is mounted to the fanlet at the aft end of the fanlet, and a second of the interlocking components is mounted to the thrust reverser sleeve at the forward end of the thrust reverser sleeve. ### Claim 17 (depends on 16) The nacelle of claim 16, wherein the first of the interlocking components is configured to interlock with the second of the interlocking components at the interface. ### Claim 18 (depends on 16) The nacelle of claim 16, further comprising: a stationary support extending circumferentially about the centerline; wherein a third of the interlocking components is mounted to the stationary support and is configured to interlock with the first of the interlocking components at the interface; and wherein a fourth of the interlocking components is mounted to the stationary support and is configured to interlock with the second of the interlocking components at the interface.