Turbojet equipped with a double-action actuator, which can be used to control reverse thrust

Turbojet comprising a device comprising a first rod 7 fixed to a second element 2 (e.g. rear nacelle portion), a second rod 6 concentric with the first rod, an actuator shaft 5 concentric with both rods and mounted on a first element 1 (e.g. main nacelle portion). Nut and screw links 8, 9 connect the second rod to the actuator shaft and first rod. The shaft and rods are coaxial with a central axis X' of the device. An actuator 12 (e.g. removable electric motor) pivots the shaft 5. Removable locking means 10, 11 are provided between first and second rods, and between second rod and actuator shaft. Preferably locking means comprise pins 13, 14 and grooves 15, 16, 17 for independent engagement. Displacement of one rod may open a reverse thrust slot 3. Translating the other rod may fully deploy rear nacelle portion for maintenance. Preferably the actuator shaft 5 is a sleeve around a hollow rod 6 within which the first rod 7 is nested for telescopic extension.