System and method for preventing striking of foreign objects on an aircraft engine

A system for preventing the striking of foreign objects on an aircraft engine comprises:

• a sensing module comprising a plurality of sensors positioned at multiple locations on a front section and a lateral section of the aircraft engine wherein the plurality of sensors is configured to obtain a plurality of data related to the presence of the one or more foreign objects within a proximity of the aircraft engine;
• a processing subsystem hosted on a server, and configured to execute on a network to control bidirectional communications among a module comprising:
• an analysis module operatively coupled to the sensing module wherein the analysis module is configured to:
• enable sensor fusion upon receiving the plurality of data from the sensing module to retrieve meaningful results pertaining to the presence of the one or more foreign objects using artificial intelligence;
• detect the presence of the foreign objects based on the sensor fusion;
• and
• generate a signal upon detecting the presence of the one or more foreign objects;
• a protecting unit operatively coupled with the analysis module wherein the protective unit is configured to receive the generated signal from the analysis module, wherein the protective unit comprises:
• a blade arrangement adapted to cover the aircraft engine, wherein the blade arrangement comprises:
• a base plate operatively coupled with the aircraft engine and comprises:
• a concentric circular projection with a diameter less than the diameter of the base plate, wherein the concentric circular projection comprises at least two arc-shaped slots arranged diametrically opposite to each other;
• and
• a projected arch along the boundary of the base plate;
• a plurality of blades with a meshed structure of a predetermined shape operatively coupled with the base plate, wherein the meshed structure allows airflow and prevents overlapping of a blade pair;
• a blade actuating ring operatively coupled with the plurality of blades by means of a plurality of pins, wherein the blade actuating ring is configured to:
• oscillate based on the generated signal thereby opening and closing of the plurality of blades wherein the closing of the plurality of blades prevents the one or more foreign bodies to strike the aircraft engine,
• wherein the blade actuation ring is coupled with a top plate by means of a plurality of pins, wherein the top plate comprises a circular structure with the at least two arc-shaped slots on the surface of the circular structure.