A hypersonic leading edge structure subjected to intense localized transient heating is modeled using the finite element method and a three-dimensional assembly of CST-DKT plate elements in the shape of a half cylinder and incorporates the large deflection uon Krmn assumptions. The thermoviscoplastic material behavior is characterized by the Bodner-Partom constitutive model. This article compares the results of a dynamic structural analysis with a quasi-static structural analysis using a representative transient temperature field similar to that which may be encountered with shock-shock interference on a hypersonic leading edge structure.