Method for operating an air intake of a turbojet engine nacelle during a thrust phase and during a reverse thrust phase

A method for operating an air intake of an aircraft turbojet engine nacelle extending along an axis X oriented from upstream to downstream in which an internal air flow circulates from upstream to downstream during a thrust phase and a reverse air flow from downstream to upstream during a thrust reversal phase, the air intake circumferentially extending about axis X and comprising an internal wall pointing to axis X, and configured to guide the internal air flow and the reverse air flow, and an external wall, opposite to the internal wall, and configured to guide an external air flow, the internal wall and the external wall being connected to each other by an air intake lip so as to form an annular cavity, the air intake lip comprising at least one elastically deformable portion, the air intake comprising at least one connection member, mounted in the annular cavity integral with the elastically deformable portion and at least one controllable moving member connected mechanically to the connection member and configured to move said connection member, method wherein:

• during a thrust phase of the turbojet engine, the controllable moving member moves the connection member a first position, in which the elastically deformable portion of the air intake lip comprises an aerodynamic profile so as to guide the internal air flow on the internal wall in order to promote a thrust phase, and
• during a thrust reversal phase of the turbojet engine, the controllable moving member moves the connection member into a second position, in which the elastically deformable portion of the air intake lip comprises an irregular profile so as to allow a separation of the reverse air flow from the elastically deformable portion.