Patent ID: 8128022

Claim:
An aircraft nacelle, comprising: aerodynamic surface of an outside of the nacelle; an air intake ( 58 ); on an inside of the nacelle, an inside pipe ( 56 ) emptying out toward a front at the air intake ( 58 ); on an outside of the nacelle, an aerodynamic wall extending from the air intake ( 58 ) up to a rear end of the nacelle; and a hood ( 62 ) comprised of said air intake ( 58 ) and a cylindrical wall ( 64 ) that forms at least one portion of the aerodynamic surface of the outside of the nacelle; a stationary part; slides ( 72 ), each slide ( 72 ) comprising a guide element ( 74 ) connected by a connecting part ( 82 ) to the hood and a conduct ( 78 ) connected to the stationary part, said guide element ( 74 ) having a rectilinear bar shape with a cylindrical section that can slide into the conduct ( 78 ) of the sliding element ( 76 ) that is connected to the stationary part; wherein said hood ( 62 ) is movable translationally, relative to the stationary part, toward a front of the nacelle along the slides ( 72 ), wherein the conduct ( 78 ) has an oblong section with a width essentially equal to a diameter of the bar and a length allowing a rotation of the hood ( 62 ) to immobilize the hood in the closed state, wherein the sliding element ( 76 ) has a slot ( 80 ) extending parallel to the guide element ( 74 ), said slot ( 80 ) being positioned so as not to allow passage of the connecting part ( 82 ) and the translation of the hood ( 62 ) when the hood ( 62 ) is in the closed state, wherein the connecting part ( 82 ) is arranged to the right of the slot when the hood has pivoted and allows the translational movement of said hood, said slot ( 80 ) having a width suited to the connecting part ( 82 ) so as not to allow the rotation of the hood ( 62 ) when the hood is not in the closed state.