Aircraft structure failure mode analysis method based on fracture analysis

• Main Authors: ZHAI XINKANG, TIAN XIAOXING
• Format: Patent
• Language: Chinese; English
• Published: 07.05.2021
• Subjects: AIRCRAFT; AVIATION; COSMONAUTICS; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING ORREPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLYADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFTCOMPONENTS, NOT OTHERWISE PROVIDED FOR; INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIRCHEMICAL OR PHYSICAL PROPERTIES; MEASURING; PERFORMING OPERATIONS; PHYSICS; TESTING; TRANSPORTING

The invention discloses an aircraft structure failure mode analysis method based on fracture analysis. The method comprises the following steps: performing fracture electron microscope scanning analysis on a fractured structural member; obtaining the crack growth rate by measuring the distance between adjacent fatigue strips of the fracture; calculating a crack tip stress intensity factor in the crack propagation direction according to a fracture mechanics method; deducing the maximum value of the crack far-end stress according to the crack tip stress intensity factor; and by judging whether the maximum stress value exceeds the equivalent maximum stress of the corresponding part in the solution of the full-aircraft fatigue finite element model, judging whether the failure mode of the fractured structural part belongs to failure modes except normal fatigue failure or not. The theoretical analysis method adopted by the aircraft structure damage mode analysis method is correct, the engineering concept is clear,