Aircraft nacelle comprising at least one fan cowl door which is mounted so as to be able to rotate about the longitudinal axis of the nacelle
A nacelle having a longitudinal axis and comprising a chassis, two articulated fan cowl doors and a sliding fan cowl door. Each articulated fan cowl door is rotatably mounted in an upper portion of the chassis, each about their own opening axis. The opening axes are parallel to the longitudinal axis. The articulated doors pivot between a closed position and an open position. The sliding fan cowl door, in its closed position, is placed between free edges of the articulated fan cowl doors. A sliding arrangement for the sliding door is configured such that, in the open position of either articulated door, the sliding fan cowl door can rotate about the longitudinal axis. The nacelle has fan cowl doors which take up less space when in the open position and which are more compact, in comparison to articulated fan cowl doors without a sliding fan cowl door.
1. A nacelle having a longitudinal axis and comprising:
a chassis,
two articulated fan cowl doors, each being rotatably mounted in a portion of the chassis about their own opening axis, and each having a free edge opposite the opening axis, the opening axes being parallel to the longitudinal axis, and each of the articulated fan cowl doors being rotatable between a closed position and an open position about their own opening axis,
a sliding fan cowl door which, in the closed position of both articulated fan cowl doors, is placed between the free edges of the articulated fan cowl doors, and
a sliding arrangement configured such that the sliding fan cowl door is configured to rotate about the longitudinal axis only when one or both of the articulated fan cowl doors are in the open position.
2. The nacelle according to claim 1 , wherein the sliding arrangement comprises two circular rail systems which are secured to the chassis and of which one is arranged at a front portion of the sliding fan cowl door and of which the other is arranged at a rear portion of the sliding fan cowl door.
3. The nacelle according to claim 2 , wherein each circular rail system has a C-shaped groove secured to the chassis and one or more pegs which are secured to the sliding fan cowl door and are free to move in the groove.
4. The nacelle according to claim 1 , further comprising, for each articulated fan cowl door, a locking system provided between the sliding fan cowl door and said articulated fan cowl door to lock the sliding fan cowl door and the articulated fan cowl door to each other in the closed position.
5. The nacelle according to claim 1 , further comprising:
an air intake zone at a front, in an upstream direction of an aerodynamic flow,
a thrust-reversal system zone at a rear, in a downstream direction of the aerodynamic flow,
a central zone of fan cowl doors, located between said air intake zone and said thrust-reversal system zone,
said two articulated fan cowl doors and said sliding fan cowl door being located in said central zone of fan cowl doors.
6. An aircraft comprising:
a pylon,
a nacelle having a longitudinal axis and being attached below the pylon, the nacelle comprising:
a chassis,
two articulated fan cowl doors, each being rotatably mounted in a portion of the chassis about their own opening axis, and each having a free edge opposite the opening axis, the opening axes being parallel to the longitudinal axis, and each of the articulated fan cowl doors being rotatable between a closed position and an open position,
a sliding fan cowl door which, in the closed position of both articulated fan cowl doors, is placed between the free edges of the articulated fan cowl doors, and
a sliding arrangement configured such that the sliding fan cowl door is configured to rotate about the longitudinal axis only when one or both of the articulated fan cowl doors are in the open position.
7. The aircraft according to claim 6 , wherein the sliding arrangement comprises two circular rail systems which are secured to the chassis and of which one is arranged at a front portion of the sliding fan cowl door and of which the other is arranged at a rear portion of the sliding fan cowl door.
8. The aircraft according to claim 7 , wherein each circular rail system has a C-shaped groove secured to the chassis and one or more pegs which are secured to the sliding fan cowl door and are free to move in the groove.
9. The aircraft according to claim 6 , further comprising, for each articulated fan cowl door, a locking system provided between the sliding fan cowl door and said articulated fan cowl door to lock the sliding fan cowl door and the articulated fan cowl door to each other in the closed position.
10. The aircraft according to claim 6 , further comprising:
an air intake zone at a front, in an upstream direction of an aerodynamic flow,
a thrust-reversal system zone at a rear, in a downstream direction of the aerodynamic flow,
a central zone of fan cowl doors, located between said air intake zone and said thrust-reversal system zone,
said two articulated fan cowl doors and said sliding fan cowl door being located in said central zone of fan cowl doors.