Structural health monitoring system for aircraft

PURPOSE: A structural integrity monitoring system for an aircraft is provided to guarantee the safety of the aircraft by monitoring damage to the aircraft with multiple optical fiber lattice sensors and piezoelectric sensors. CONSTITUTION: A structural integrity monitoring system(100) for an aircraft comprises a transformation detecting part(110), an impact detecting part(120), a damage detecting part(130), and a control part. The transformation detecting part comprises multiple first optical fibers(f1) and multiple first optical fiber lattice sensors and detects the transformation of a wing. The impact detecting part comprises multiple second optical fibers(f2) and multiple second optical fiber lattice sensors and detects impact applied to the wing. The damage detecting part has multiple piezoelectric sensors(P) and is installed in a part where the wing is connected to a body to detect cracks and bolt loosening. The control part stops operating the aircraft when the cracks and bolt loosening are generated, and continuously operates the aircraft when the cracks and bolt loosening are not generated.