A typical spacecraft is constructed in a cuboid shape, consisting of a central cylinder and interconnected decks made of honeycomb sandwich construction. This structure houses electronic packages and provides the necessary strength and stiffness to endure the launch loads. The honeycomb sandwich payload support structure, a crucial component of the spacecraft, is constructed with an aluminum honeycomb core bonded with aluminum face sheets using adhesive. Throughout the launch, the spacecraft encounters various loads such as vibration, acoustic, and shock loads, necessitating a design that can withstand these forces. Dynamic analysis is essential to determine the panel’s natural frequencies, mode shapes, and acceleration responses at key locations. This study focuses on free vibration of the payload support structure, aiming to predict the structure’s response to static and dynamic loads. The analyses including free vibration are conducted using MSC. NASTRAN/PATRAN software was used to identify major modes and to assess strength margins for the aluminum sandwich structural components.