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The subject of this paper is the buckling behavior of thin bar stiffeners attached to plates which are subjected to normal pressure loadings. The stiffeners are mathematically modeled by a nonlinear beam theory recently derived. An analytical solution is obtained to the beam buckling equations. The curvature of the centerline along the beam's base at the buckling load is expressed in terms of the beam's thickness, height, and rotational stiffness. Analytical results are compared with an experiment recently performed.
DESIGN EQUATIONS FOR TRIPPING OF STIFFENERS UNDER INPLANE AND LATERAL LOADS
Abstract : A series of design oriented equations to predict the tripping (lateral-torsional instability) of stiffeners under inplane and lateral loads has been developed which will allow this mode of failure to be more comprehensively addressed in the early stages of structural design. This type of failure is characterized by a twisting of the stiffener about its line of attachment to the plating and has been demonstrated by some recent British grillage tests to have serious potential as a primary mode of failure. The solutions developed take into account the effects of the rotational resistance provided by the plating to which the stiffener is attached, non-linear material and structural behavior by means of a tangent modulus type approach, and stiffener web deformations (for inplane loading). The equations are suitable for manual calculations but particularly powerful applications are possible when they are teamed up with a desk-top type mini-computer.
THE DYNAMIC PLASTIC BEHAVIOR OF SHELLS
Abstract : A survey has been made of the literature published previously on the inelastic behavior of shells subjected to dynamic loads. An experimental investigation has also been undertaken to examine the behavior of various cylindrical shell panels which were loaded with an impulse on the inner surface. The panels were fully clamped along the two longitudinal edges and free on the other two. The initial kinetic energy of the dynamic loads was sufficiently large to cause inelastic behavior and to produce maximum permanent transverse deflections of up to nearly twice the corresponding panel thickness. Tests were conducted on mild steel and aluminum 6061 T6 panels which had various thicknesses and an included angle of 90 degrees approximately. (Author)