Natural Frequency Determination and Modal Analysis of Prototype Structure of Honeycomb Sandwich Panels

Abstract

A box shape Prototype Structure of Honeycomb Sandwich Panels of Aluminum 5052 Facings was fabricated with Fabrication of desired shape and size Honeycomb Sandwich One-Shot Fabrication technique which is an effective tool for Cost Panel structures for spacecraft and satellite is an important reduction, reduced number of parts for assembly and Constellation type space programs where mass production is issue regarding cost and weight reduction with maximum required. Mathematical Model was generated from Lagrange's stiffness. Newly developed fabrication techniques for desired Method and Influence Coefficient Method. Eigen Values were shape structures of Honeycomb Sandwich Panels and then calculated for 3-dof system for validation of Mathematical Model investigation by analytical and experimental methods followed generated for Prototype Structure. Sine Sweep Testing was by many researchers [1-5]. Sasano [1] applied One-Shot performed on Prototype Structure to investigate the survivability Fabrication Technique for Spacecraft Structure and tested of applied fabrication techniques and validation of Mathematical survivability of Fabrication Technique under static and Model. Modal Analysis, Normalization of Modes and dynamic loading for spacecraft environment. Seidhgi [2]Orthonormalization of Eigen Vectors were performed to calculate observed static and dynamic response of satellite structure by the Mode Shapes, Modal Matrix and uncoupled equations of FEA and selected optimum shape of the satellite structure. motion in Principal coordinate system. Lotfi [3] proposed a modal analysis method which is dependent

Finite Element Model Updating of Satellite Sailboard Based on Sensitivity Analysis

“…In particular, when a spacecraft launches and reenters the atmosphere at high speeds, the resulting random high-frequency vibrations and noise vibrations within the fairing can produce a mean square response acceleration of up to 50 g for the satellite structure. erefore, it is necessary to carry out comprehensive dynamic analysis before launch to obtain accurate response prediction results for flight safety and good operation [10][11][12].…”