| 摘要 |
The invention relates to a thrust reverser device (10) for a turbojet engine nacelle comprising at least one cowl (20) mounted with the ability to move in a translational manner in a directional substantially parallel to a longitudinal axis of the nacelle, the mobile cowl being associated with at least one blocking flap (30) mounted such that it can pivot via one end on the mobile cowl, the blocking flap being equipped with at least one drive mechanism comprising at least one assembly forming a lever (50) mounted such as to be able to pivot on the cowl and articulated at each of its ends, via drive links (51, 52) to the flap and to a fixed structure of the device, respectively, characterized in that the assembly forming a lever and the associated links are articulated in a plane substantially perpendicular to the flap and substantially radially with respect to the thrust reverser device.
|
