Design and Thermal analysis of ISRASAT1 Cube satellite structure

Abstract

ISRASAT1 is the cube satellite being devolved by the Institute of Space Research and Aerospace (ISRA) to orbits at 450 km above the Earth. The main mission of ISRASAT1 is to take images from space, transmit it to ISRA ground station while transmitting a beacon signal all the time. ISRASAT1 subsystems are the onboard computer subsystem (OBC), electrical power subsystem (EPS), attitude determination and control subsystem (ADCS), communication subsystem (COMM) and payload subsystem (PS), which are integrated to achieve its mission. All these subsystems of ISRASAT1 are enclosed in one structural unit that designed to meets the mechanical dimensions of P-POD launcher and to provide housing for ISRASAT1 subsystems, together with adequate interfaces to each subsystem to ensure safe operation through all phases of the ISRASAT1 mission. The structure designed to prevents ISRASAT1 subsystem form space environment such as the effect of the thermal transfer, radiation, and the solar particles energy. Also to absorb the shocks and vibrations during the launching phase and the different disturbance torques acting on it. Furthermore, the structure designed to ensure the continuity of power generation from solar cells for ISRSAT1 subsystems. This thesis discusses the design and manufacturing of ISRASAT1 structure, including material selection, 3D CAD design, yield strength analysis, weight distribution, mechanical antenna release and attachment, camera attachment, kill switch mechanism, power generation, and thermal analysis.