FIELD: engines and pumps.
SUBSTANCE: claimed actuator comprises the thrust reverser, thrust reverser drive system and locking appliances. Said thrust reverser comprises the cowling linearly driven between closed position whereat it allows the nacelle aerodynamic continuity and open position whereat it opens the deflected flow passage. Said cowling is extended by adjustable nozzle section comprising the panel arranged to turn to at least one position whereat nozzle exit section is changed. Drive system comprises the actuators to displace the cowling and nozzle panel which include a simple linear drive coupled with the panel. Locking appliances feature two reversible states one being a closed state whereat locking appliances can lock the nozzle panel with the coaling to position of nozzle exit section variation. Another invention of this set relates to bypass turbojet nacelle equipped with aforesaid device.
EFFECT: simplified design, engine thrust reversing with displacement of nozzle to appropriate position.
13 cl, 10 dwg
