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 si
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.
대표청구항▼
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 int
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, andwherein the second cover and the third cover are configured to open independently of each other. 2. A nacelle according to claim 1, wherein the length of the arc of at least one bottom cover is arranged so that its free end lies under the nacelle when said at least one bottom cover is open. 3. A nacelle according to claim 1, wherein each bottom cover of the at least one bottom cover is hinged about a pivot axis lying in the vertical plane of symmetry. 4. A nacelle according to claim 1, wherein each top cover of the at least one top cover is hinged about a pivot axis that is disposed in the vertical plane of symmetry. 5. A nacelle according to claim 1, further comprising a lock configured to lock each top cover with the at least one bottom cover situated on the same side of the vertical plane of symmetry. 6. A nacelle according to claim 5, wherein the lock is provided on each of opposite sides of the aircraft turbojet nacelle. 7. A nacelle according to claim 5, wherein the lock is disposed above a bottom edge of the aircraft turbojet nacelle in each of the open position and the closed position. 8. A nacelle according to claim 1, further comprising actuators for opening and closing the at least one top cover, and wherein the at least one bottom cover is not coupled to actuators for opening and closing. 9. A nacelle according to claim 1, wherein a bottom cover of the at least one bottom cover is shielded. 10. A nacelle according to claim 9, wherein only the bottom cover is shielded. 11. A nacelle according to claim 9, wherein a shield of the shielded bottom cover extends radially about the at least one bottom cover. 12. An aircraft, the aircraft comprising: at least one aircraft turbojet nacelle according to claim 1,wherein the at least one bottom cover extends in arcuate shape from a fixed first end that is hinged to an opposite second end that is free,wherein, when the aircraft is standing on ground and the at least one bottom cover is in the open position, difference in height between the height of the fixed first end of said at least one bottom cover and the opposite second end is equal to a difference in height between said first fixed end and the ground. 13. A nacelle according to claim 1, wherein the first pivot axis and the second pivot axis are arranged in parallel and in a spaced relation on each side of the vertical plane. 14. A nacelle according to claim 1, wherein the third pivot axis and the fourth pivot axis are arranged in parallel and in a spaced relation on each side of the vertical plane. 15. An aircraft turbojet nacelle of elongate shape extending around and along a longitudinal central axis, the aircraft turbojet nacelle comprising: a cowling assembly 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 the longitudinal central axis, and a transition from the closed position to the open position is obtained by moving the cowling assembly to give access to said internal space,wherein the cowling assembly comprises a pair of top covers and a pair of bottom covers, wherein each of the covers has an arcuate shape in cross section and extends partially around the longitudinal central axis, and the pair of top covers and the pair of bottom covers, while the cowling assembly is in the closed position, collectively extend around the internal space;wherein an arc length of the pair of bottom covers is shorter than an arc length of the pair of top covers;the pair of top covers includes a first cover and a second cover attached by a hinge aligned with a vertical plane extending through the longitudinal central axis; andthe pair of bottom covers include a third cover and a fourth cover, wherein the third cover is attached to a third cover hinge parallel to and offset in a first direction from the vertical plane and the fourth cover is attached to a fourth cover hinge parallel to and offset in a second direction, opposite to the first direction, from the vertical plane.
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이 특허에 인용된 특허 (4)
Regard, Sebastien, Fairing device for nacelle of an aircraft propulsion power unit.
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