Abstract
This paper presents an alternative launcher design for Earth-to-orbit (ETO) micro- and nanosatellite systems. The main goal of the design is to reduce the cost of the launching operation. This paper also addresses the calculation of the energy required for the launching operation and the selection of a power source for the designed satellite launcher. The method introduced here proposes a vertical-takeoff electromagnetic launcher for ETO micro- and nanosatellite systems. The design specifications are 7-km/s muzzle velocity and 30000-gee acceleration for a 10-kg payload. It is expected that the proposed design would present a viable alternative to conventional launchers for ETO systems.
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