Patent ID: 8448896

Claim:
A nacelle for turbojet of an aircraft, including a downstream structure comprising: an outer structure, a concentric inner structure surrounding a downstream portion of the turbojet and including an upstream section having a relatively small diameter and a downstream section having a relatively large diameter, wherein said inner structure defines together with the outer structure an annular flow channel, and a guiding system for connecting the inner structure and the downstream portion of the turbojet engine or a portion of a suspension mast, wherein the guiding system includes a means for combining a translation and rotation movement of at least a portion of said inner structure between a working position, in which the inner structure is used as a cowling for the turbojet downstream portion, and a maintenance position in which the inner structure exposes said turbojet downstream portion, thus enabling movement of said portion of the inner structure along the profile of the upstream section having a relatively small diameter, and then of the downstream section having a relatively large diameter, wherein the inner structure rotates about an axis transverse to a longitudinal axis of the nacelle.