Nacelle forward part of a propulsion assembly comprising an inclined stiffening frame

An anterior part of a nacelle of an aircraft propulsive assembly, said anterior part having a front end allowing the inlet of air and a rear end, said anterior part comprising:

• an air inlet lip arranged at said front end;
• an inner structure extending an inner surface of the air inlet lip;
• an outer panel extending an outer surface of the air inlet lip, the outer panel forming an outer aerodynamic surface of the anterior part;
• an annular rigidifying frame around an axis of revolution, said rigidifying frame arranged at said rear end of said anterior part and linking said outer panel to said inner structure, said rigidifying frame comprising an inner peripheral edge linked to said inner structure and an outer peripheral edge linked to said outer panel;
• and
• a rear flange comprising a front end and a rear end, said front end fixed to said inner peripheral edge of said rigidifying frame, said rear end adapted to be fixed to an engine flange,
• wherein said rigidifying frame has an inclination relative to the axis of revolution, such that the rigidifying frame has a slope oriented toward the front end of said anterior part of the nacelle, said rigidifying frame configured to deflect out of the nacelle of the propulsive assembly, towards the outer aerodynamic surface, an object entering through the front end of the anterior part and striking said rigidifying frame
• wherein the outer peripheral edge of the rigidifying frame is linked to said outer panel by an interface ring, and wherein the interface ring does not extend in continuity of the rigidifying frame.