Self-locking alignment at a nacelle interface

1. A nacelle for an aircraft propulsion system, comprising:

a nacelle structure;

a fanlet configured to translate axially along a centerline between an open position and a closed position; and

an interface assembly including first and second interlocking components, wherein one of the first and the second interlocking components is mounted to the nacelle structure, and the other one of the first and the second interlocking components is mounted to the fanlet;

the first interlocking component comprising a projection configured with a stop;

the second interlocking component comprising an aperture and a detent;

the projection comprising a pin, and the projection adapted to extend axially into the aperture and the detent adapted to engage the stop where the fanlet is in the closed position;

the stop comprising a groove in the pin; and

the detent comprising a plurality of spring elements and a base, wherein

the base is connected to a back side of the second interlocking component and extends circumferentially partially around the projection within opposing circumferential sides of the base and the plurality of spring elements is cantilevered from the base and extends circumferentially and partially around the pin within the opposing circumferential sides where the fanlet is in the closed position,

each of the spring element of the plurality of spring elements adapted to project into the groove in the pin, and the spring elements comprising

a first spring element,

a second spring element and

a third spring element;

the first spring element including

a first end segment,

a second end segment and

a curved intermediate segment between and connecting the first end segment and the second end segment, wherein

the first end segment projecting out from the base towards the curved intermediate segment and the second end segment projecting away from the curved intermediate segment and overlapping the first end segment.

2. The nacelle of claim 1 , wherein the detent is adapted to secure the fanlet in the closed position when engaged with the stop.

3. The nacelle of claim 1 , wherein

the first interlocking component further comprises a first mounting bracket, and the projection extends axially out from the first mounting bracket;

the second interlocking component further comprises a second mounting bracket, and the aperture extends axially through the second mounting bracket; and

the first mounting bracket is substantially parallel with the second mounting bracket.

4. The nacelle of claim 1 , wherein the interface assembly further includes a seal element adapted to seal an axial gap between the first and the second interlocking components.

5. The nacelle of claim 4 , wherein the seal element comprises a tubular gasket.

6. The nacelle of claim 1 , wherein the first interlocking component is mounted to the fanlet and the second interlocking component is mounted to the nacelle structure.

7. The nacelle of claim 1 , wherein the second interlocking component is mounted to the fanlet and the first interlocking component is mounted to the nacelle structure.

8. The nacelle of claim 1 , wherein the nacelle structure comprises an inner barrel comprising an acoustic panel, and the inner barrel is disposed within the fanlet.

9. The nacelle of claim 1 , wherein the nacelle structure comprises a thrust reverser sleeve.

10. The nacelle of claim 1 , wherein the fanlet includes an inlet structure and a fan cowl, and the interface assembly provides an interface between the inlet structure and the nacelle structure.

11. The nacelle of claim 1 , wherein the fanlet includes an inlet structure and a fan cowl, and the interface assembly provides an interface between the fan cowl and the nacelle structure.

12. The nacelle of claim 1 , wherein

the first interlocking component further comprises a second projection configured with a second stop;

the second interlocking component further comprises a second aperture and a second detent; and

the second projection is adapted to extend axially into the second aperture and the second detent is adapted to engage the second stop where the fanlet is in the closed position.

13. A nacelle for an aircraft propulsion system, comprising:

a forward nacelle structure configured to translate axially along a centerline between an open position and a closed position;

a second nacelle structure;

a first interlocking component mounted to the forward nacelle structure, the first interlocking component comprising

a projection configured with a stop; and

a second interlocking component mounted to the second nacelle structure, the second interlocking component comprising

an aperture and a detent;

the projection adapted to extend axially into the aperture and the detent adapted to engage the stop where the forward nacelle structure is in the closed position;

the stop comprising a groove in the projection; and

the detent comprising a plurality of spring elements and a base, wherein

and a base, wherein

the base is connected to a back side of the second interlocking component and extends circumferentially partially around the projection within opposing circumferential sides of the base and the plurality of spring elements extends circumferentially and partially around the projection within the opposing circumferential sides around the projection where the forward nacelle structure is in the closed position, each of the spring element of the plurality of spring elements adapted to directly engage the groove in the projection and thereby secure the forward nacelle structure in the closed position, and a first of the spring elements including a first segment and a second segment that radially overlaps the first segment.

14. The nacelle of claim 13 , further comprising a seal element adapted to seal an axial gap between the first and the second interlocking components, the seal element extending circumferentially about the centerline.

15. The nacelle of claim 13 , wherein the forward nacelle structure includes an inlet structure that interfaces with the second nacelle structure.

16. A nacelle for an aircraft propulsion system, comprising:

a forward nacelle structure configured to translate axially along a centerline between an open position and a closed position;

a second nacelle structure;

a first interlocking component mounted to the second nacelle structure, the first interlocking component comprising

a projection configured with a stop; and

a second interlocking component mounted to the forward nacelle structure, the second interlocking component comprising

an aperture and

a detent;

the projection adapted to extend axially into the aperture; and

the detent including a base and a plurality of spring elements connected to and cantilevered from the base, the base connected to a back side of the second mounting bracket and extending circumferentially partially around the projection within opposing circumferential sides of the base where the forward nacelle structure is in the closed position, the spring elements arranged circumferentially and partially around the projection within the opposing circumferential sides and engaged with the stop where the forward nacelle structure is in the closed position, and the plurality of spring elements comprising a first spring element, a second spring element and a third spring element.

17. The nacelle of claim 16 , wherein the stop comprises a groove in the projection; and the plurality of spring elements projects into the groove in the projection where the forward nacelle structure is in the closed position.

18. The nacelle of claim 13 , wherein the spring elements include a first spring element, a second spring element and a third spring element.