Preliminary system design of the modular satellite

The main scope of the present thesis centres around two key points: modular block and binding interface of 4 types (mechanical/electrical/data/thermal). Throughout the development process, the preliminary design of the modular block and mechanical interface was continuously modified, that eventually evolved into the micro-satellite platform of different unit sizes for various mission applications. Similar to CubeSat platforms, it opens perspectives for a cheaper and faster satellite deployment by means of modularization and standardization of future satellite systems. The proposed design is fully analysed from different perspectives and later compared to the satellite built in accordance with the traditional approach. This gives the assurance of the validity of the comparison due to the similar mission. As a part of the validation process, the economic analysis was conducted for three different approaches in spacecraft design, which led to the determination of the feasibility of small-mass production and plans for the future satellite constellation.