| 摘要 |
The invention relates to a nacelle (1) for a turbojet engine, including a stationary portion (5) and a thrust reversal means (15), including: - a reverser cowl, the downstream portion of which forms an exhaust nozzle; cascades; thrust reversal flaps; and an actuation means. The thrust reversal means (15) translates, by means of the actuation means, between a position in which the reverser cowl is stowed, corresponding to a direct-jet operation of the nacelle, and a position in which the reverser cowl is deployed, corresponding to a reverse-jet operation of the nacelle (1). The nacelle (1) is characterized in that stretching said actuation means has the sole effect of causing a variation in the cross-section of the nozzle as long as said stretching is less than a predetermined value, and of uncovering the cascades and deploying the flaps after said predetermined value is exceeded. |
