TURBOJET ENGINE NACELLE

摘要

The invention relates to a bypass turbojet engine nacelle (1) fitted with a thrust reverser device (20) comprising at least one cap (30) and flow deflection means (40), said cap (30) being able to move translationally in a direction substantially parallel to a longitudinal axis of the nacelle and able to move alternately from a closed position in which it ensures the aerodynamic continuity of the nacelle and covers the deflection means (40), into an open position in which it opens up a passage in the nacelle and uncovers the deflection means (40), said deflection means (40) being able to move translationally in a direction substantially parallel to the longitudinal axis of the nacelle and designed to move alternately from a retracted position in which they are retracted into a fixed structure of the nacelle, into at least one deployed position in which they are deployed into the passage opened by said cover (30) in order to deflect the flow, characterized in that the thrust reverser device (20) further comprises actuating means (60) designed to allow the deflection means (40) to move into the their deployed or retracted position through a travel that is shorter than that of the cap (30) as it moves into its open or closed position.