The nonlinear response and failure characteristics of internally pressurized 4- to 16-ply cylindrical panels of graphite/epoxy are experimentally and analytically studied. Tests simulated the skin of a typical transport aircraft fuselage under loading to eventual failure. Aluminum test specimens were similarly tested and compared. All graphite/epoxy panels are found to withstand the internal pressures applied, which are well above the proof pressure loading expected for transport fuselage structures.
Nonlinear response and failure characteristics of clamped internally pressurized graphite-epoxy cylindrical panels
01.01.1984
Aufsatz (Konferenz)
Keine Angabe
Englisch
Impact response of graphite/epoxy cylindrical panels
AIAA | 1991
|Impact response of graphite/epoxy cylindrical panels
Tema Archiv | 1992
|Impact response of graphite/epoxy cylindrical panels
AIAA | 1992
|