METHOD FOR USING AN AIR INTAKE OF A TURBOJET ENGINE NACELLE DURING A THRUST PHASE AND A REVERSE THRUST PHASE

A method for using an air intake (2) of a turbojet engine (1) nacelle comprising at least one elastically deformable portion (230), at least one connecting member (3) mounted in an annular cavity (20) integrally with the elastically deformable portion (230), and at least one controllable displacement member (9), in which method: during a thrust phase of the turbojet engine (1), the controllable displacement member (9) moves the connecting member (3) into a first position (A) in which the elastically deformable portion (230) of the air intake lip (23) has an aerodynamic profile, and during a thrust reversal phase of the turbojet engine (1) the controllable displacement member (9) moves the connecting member (3) into a second position in which the elastically deformable portion (230) of the air intake lip (23) has an irregular profile so as to allow a release (D) of the reverse air flow from the elastically deformable portion (230). 本发明公开了一种使用飞行器涡轮喷射引擎短舱(1)的进气管(2)的方法，短舱包括至少一个弹性变形部(230)、至少一个与弹性变形部(230)一体成型且安装在环形