DE-ORBITING ELECTRO-MECHANICAL SYSTEM DESIGN FOR MICRO SPACECRAFT

Abstract

The number of small and micro satellites in LEO is rapidly increasing. There is a risk of collision due to the lack of active orbital control of these satellites which also raises concerns about the debris. Existing low-orbit satellites pose dangers for new low-orbit satellites to be sent into orbit. A de-orbiting system to be activated at the end of the lifetime of the satellites is seen as the most effective solution to this danger. In this study, an electromagnetic satellite de-orbiting system is designed using aerodynamic principle. This system has been developed for a micro satellite with maximum edge dimensions of 100 cm. When the satellite lifetime is over, the system will be activated and will drop the satellite at the latest of 11 years. This system can de-orbit a micro satellite with a maximum weight of 50 kilograms. This system is activated with a command from the earth after the lifetime of the satellite is over. In this study, a de-orbiting electromechanical system (DES) is designed with an assumption of 750 km of satellite altitude and 98.4 degrees of orbital slope.

Keywords

• de-orbiting
• electro mechanic
• nano-micro spacecraft
• satellite

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