| 摘要 |
The invention relates to an aircraft turbojet nacelle including a cowling assembly (60) made up of four covers (62, 64, 66, 68). Each cover extends in arcuate shape around part of the longitudinal axis of the nacelle, in symmetrical manner about a vertical plane (P) containing the axis. On either side of said plane, the cowling assembly comprises a top cover (62, 66) hinged at its top portion and a bottom cover (64, 68) hinged at its bottom portion. Access to the internal space (e) of the nacelle is obtained by moving the covers away from the longitudinal axis by pivoting them about their hinge axes. A top cover is less heavy for handling purposes than is a single cover of the prior art. |
| 主权项 |
1. An aircraft turbojet nacelle (36, 38) of generally elongate shape extending around and along a longitudinal central axis (X), the nacelle including a cowling assembly (60) that is pivotally movable between a closed position and an open position, with the cowling assembly in the closed position defining an internal space (e) that extends radially around said axis and parallel thereto, the transition from the closed position to the open pivoted position being obtained by moving the cowling assembly radially away from the longitudinal central axis in order to give access to said internal space, the nacelle being characterized in that the cowling assembly comprises four covers (62, 64, 66, 68) each extending in arcuate shape around part of the longitudinal central axis and in a manner that is symmetrical about a vertical plane (P) containing the longitudinal central axis, the cowling assembly comprising on either side of said plane a top cover (62, 66) hinged at its top portion and a bottom cover (64, 68), hinged at its bottom portion, the arcuate shape of the bottom cover (64, 68) extending in cross-section over an arc of length that is shorter than the length of the arc of the top cover (62, 66). |
