Patent ID: 8753072

Claim:
A turbojet engine nacelle comprising: an air intake structure to channel a flow of air towards a fan of the turbojet engine and comprising at least one longitudinal outer panel incorporating an air intake lip; a middle structure surrounding said fan and to which the air intake structure is attached in such a way as to provide aerodynamic continuity; at least one inner panel comprising an acoustic shroud, fixed at a downstream end to an upstream end of the middle structure forming therewith a fixed structure of the nacelle; means of guiding the outer panel(s) to allow a substantially rectilinear movement of the outer panel in the upstream direction of the nacelle so as to open the air intake structure; and reinforcing means to react mechanical loads of the guide means beyond a predetermined deformation thereof as the air intake structure opens, wherein said reinforcing means only reacts the mechanical loads when a deformation of the guide means occurs.