Design, analysis and development of micro-satellite structure

Abstract

The capabilities of micro satellites continue to increase every year for better utilities to carryout different types of missions which previously required much large satellite platforms. The miniaturization of electronic components enabled to develop satellites of small size, with weight ranging from 10-100 kg. The benefits of developing a micro satellite leads to a shorter development time and much lower costs than that required for larger satellite while achieving the same and high levels of performance and capability. The present work is to design, analyze and develop a mechanical structure of a micro-satellite upon which the scientific and operational instruments are placed. This structure must be lightweight, and resistant to thermal fluctuations, fatigue, fracture, and corrosion. Furthermore, it must provide stability to the instruments against undesirable vibrations and shocks during the launch and transportation, and must dissipate heat from the internal components. To model the micro satellite structure with subsystems and to perform the following analyses namely static, normal modes, frequency response, transient response and random vibration analysis commercially available Finite Element Analysis software MSC PATRAN and MSC NASTRAN were used. From the results of the analyses it was possible to (a) verify preliminary design of the structure and define the necessary changes, (b) determine the first global frequencies of the assembly, (c) determine the level of stresses and buckling instability in the structure and (d) verify the acceleration levels on the micro-satellite subjected to the sine and random vibrations. The results of the analyses serve as the bases for structural design and optimum design of the micro-satellite structure.