Analysis of Harmonic Vibration Characteristics for a Composite Honeycomb Panel of the Spacecraft Scanner

Abstract

The coordinate and frequency distributions of the values of displacement and acceleration amplitudes, the vibration acceleration amplification factors, and the equivalent von Mises stresses are obtained from the data on the simulation modeling of harmonic vibration of the composite honeycomb panel for spacecraft scanner and its related operational equipment (a scanner, magnetometer, optical devices, etc.) mounted on it. A dynamic simulation model of the composite honeycomb panel was developed using modern finite element analysis tools, such as ANSYS APDL. Carbon fiber reinforced plastic plates with an aluminum foil honeycomb core in the form of regularly shaped hexagonal cells that make up the honeycomb panel are approximated by multilayer plate finite elements. The related operational equipment, such as optical devices, a scanner and magnetometer, are represented in the model by lumped masses rigidly attached to the panel. The spectrum of natural frequencies and vibration modes of the spacecraft scanner honeycomb panel is determined using the developed simulation model. The resonant displacement and acceleration amplitudes, the vibration acceleration amplification factors as well as the distributions of the amplitudes of the equivalent von Mises stresses are obtained in the operating frequency range of the investigated harmonic vibration mode of the spacecraft scanner honeycomb panel.