Aircraft Structural Analysis

  • Static strength of aircraft components and installations is analyzed by obtaining internal loads through free-body, shear and bending
moment diagrams, or numerical methods such as NASTRAN with PATRAN, and then doing a structural analysis using classical
handbook solutions.

  • Damage tolerance (crack growth) is analyzed with NASGRO or AFGROW to determine the required inspection intervals of principal
structural elements per 14 CFR 25.571 and 26.43(d)(e).

  • High cycle fatigue due to flight, acoustic, and random vibration loads is analyzed using stress-life methods. Low cycle fatigue due to
mechanical or thermal loads is analyzed using strain-life methods.

  • Advanced composite sandwich and solid laminate panels are analyzed using classical laminated plate theory for ply-level failure
modes, core shear and compression, edge band, and insert strength.
FAA Data Approval