Design of an Electromagnetic Launcher for Earth-to-Orbit (ETO) microsatellite systems

In this study, an alternative launcher design for earth-to-orbit (ETO) microsatellite systems is addressed. The main goal of the design is to reduce the cost of launching operation. For this aim, a new topology is introduced and a sample design is presented. The paper proposes a vertical take-off Electromagnetic Launcher (EML) for ETO microsatellite systems. Design specifications are 6 km/s muzzle velocity and 20000 Gee's acceleration for a 100 kg payloade 6 km/s muzzle velocity and 20000 Gee's acceleration for a 100 kg payload. It is expected that proposed design presents a powerful alternative to conventional launchers and existing electromagnetic launchers for ETO systems.