Abstract
Recently, the satellite research is more focused towards the development of micro and nano satellites. The reason behind this is that the development and launching of micro and nano satellites have less risk and less cost involved. This paper is about the attitude control of micro/nano satellites which are relatively smaller in size and weight if compared to the conventional satellites. The barriers, for the attitude control of these satellites, are the less mass and the less power budget. Hence, the normal attitude sensors and actuators cannot be used. The attitude control system of the micro and nano satellites relies on a novel technology known as Micro Electro-Mechanical Systems (MEMS) technology. In this paper, use of high temperature superconductor (HTS) magnet momentum wheel has been proposed for the attitude control system of micro and nano satellites and the design, working principles and the mathematical model of the HTS momentum wheel are elaborated. In the end the mathematical model of the HTS momentum wheel has been analyzed on the basis of simulation results.
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