Controlling a relative position at an interface between translating structures of an aircraft nacelle

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 axial centerline;

a thrust reverser sleeve configured to translate axially along the axial 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;

the interface assembly including a pair of interlocking components, wherein a first of the pair of interlocking components is mounted to the fanlet at the aft end of the fanlet;

the first of the pair of interlocking components configured with an aperture; and

a second of the pair of interlocking components configured with a projection that extends axially into the aperture where the second of the pair of interlocking components is mated with the first of the pair of interlocking components.

2. The nacelle of claim 1 , wherein the relative position comprises a relative axial position.

3. The nacelle of claim 1 , wherein the relative position comprises a relative radial position.

4. 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.

5. The nacelle of claim 1 , wherein the interface assembly further includes a lock configured to selectively lock the pair of interlocking components together where the fanlet and the thrust reverser sleeve are respectively in the stowed positions.

6. The nacelle of claim 1 , wherein the second of the pair of interlocking components is mounted to the thrust reverser sleeve at the forward end of the thrust reverser sleeve.

7. The nacelle of claim 6 , wherein the interface assembly further includes a rub strip disposed radially between and contacting the first of the pair of interlocking components and the stationary support.

8. The nacelle of claim 1 , wherein the second of the pair of interlocking components is mounted to the stationary support.

9. The nacelle of claim 8 , wherein

the interface assembly further includes a pair of second interlocking components;

a first of the pair of second interlocking components is mounted to the thrust reverser sleeve at the forward end of the thrust reverser sleeve; and

a second of the pair of second interlocking components is mounted to the stationary support.

10. The nacelle of claim 9 , wherein the interface assembly further includes a lock configured to selectively lock the pair of second interlocking components together where the thrust reverser sleeve is in the stowed position.

11. The nacelle of claim 9 , wherein the interface assembly further includes a rub strip disposed radially between and contacting the thrust reverser sleeve and the stationary support.

12. 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 axial centerline;

a thrust reverser sleeve configured to translate axially along the axial 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;

the interface assembly including a pair of interlocking components, wherein a first of the pair of interlocking components is mounted to the fanlet at the aft end of the fanlet;

a second of the pair of interlocking components mounted to the stationary support; and

the interface assembly further including a rub strip disposed radially between and contacting the fanlet and the stationary support.

13. 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 axial centerline;

a thrust reverser sleeve configured to translate axially along the axial 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;

the interface assembly including a pair of interlocking components, wherein a first of the pair of interlocking components is mounted to the fanlet at the aft end of the fanlet;

a second of the pair of interlocking components mounted to the stationary support;

the interface assembly further including a pair of second interlocking components;

a first of the pair of second interlocking components mounted to the thrust reverser sleeve at the forward end of the thrust reverser sleeve;

a second of the pair of second interlocking components mounted to the stationary support;

the first of the pair of interlocking components configured with an aperture;

the second of the pair of interlocking components configured with a projection that extends axially into the aperture where the second of the pair of interlocking components is mated with the first of the pair of interlocking components;

the first of the pair of second interlocking components configured with a second aperture; and

the second of the pair of second interlocking components configured with a second projection that extends axially into the second aperture where the second of the pair of second interlocking components is mated with the first of the pair of second interlocking components.