Dynamic Analysis And Experimental Modal Analysis Of Spacecraft Structural Components

Abstract

It is very necessary to characterize the dynamic behavior of the space structures to ensure its survivability against vibration loads during launch. Uncertain behavior in satellite structure may cause calamitous failure in structural component or damage the other payload during launch. In this thesis, attempts are made to characterized the dynamic behavior of the spacecraft structures i.e. Thermal Shield and Antenna Feed System employing well established numerical method i.e Finite Element Technique. Moreover, experimental validation of analysis results is also carried out using conventional vibration tests as well as Experimental Modal Analysis (EMA) employing advanced computing software i.e LMS Test Lab and hardware like LMS SCADAS front end system. Conclusions are drawn based on experimental modal analysis results.