Patent ID: 9604728
Date: 2017-03-28
CPC Classifications: B64D

Claim:
1. An aircraft turbojet nacelle of elongate shape extending around and along a longitudinal central axis, the aircraft turbojet nacelle comprising: a cowling assembly that is pivotally movable between a closed position and an open position, the cowling assembly in the closed position defining an internal space that extends radially around said longitudinal central axis and parallel thereto, the transition from the closed position to the open position being obtained by moving the cowling assembly radially away from the longitudinal central axis in order to give access to said internal space, wherein the cowling assembly comprises four covers each extending in arcuate shape around part of the longitudinal central axis and in a manner that is symmetrical about a vertical plane containing the longitudinal central axis, the cowling assembly comprising on either side of said plane at least one top cover hinged at its top portion and at least one bottom cover, hinged at its bottom portion, the arcuate shape of the at least one bottom cover extending in cross-section over an arc of length that is shorter than the length of the arc of the at least one top cover; wherein the at least one top cover comprises a first cover on one side of the vertical plane and a second cover on an opposite side of the vertical plane, wherein the at least one bottom cover comprises a third cover on the one side of the vertical plane and a fourth cover on the opposite side of the vertical plane, wherein the first cover and the fourth cover are configured to open independently of each other, and wherein the second cover and the third cover are configured to open independently of each other.