Thanks rb1957 for your answer.
Although permanent deformation is expected according to the residual compressive strains in the strain gages after unloading, visual inspections in the skin corner after test did not reveal any damage or significative deformation in the area, and therefore rule...
In a static test campaing, for some critical load cases we have found that the skin at the fuselage door corner reaches compressive stress values 30%-40% higher than the Fty of the skin material (Al 2024)at limit load, so we have started to think in the necessity of introducing additional...
