• 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.