This chapter offers a broad and in-depth description of all the subsystems of a space launcher, with a high level of detail thanks to the legacy of the Scout launcher at the School of Aerospace Engineering in Rome. Although retired in 1994, Scout is representative of the format of the new generation of launchers designed for the microsatellite market. It used all the control systems that can be accommodated on a launcher: aerodynamic control, thrust vector control, gas jet control and spin stabilisation. Scout was launched from the San Marco sea platform in Malindi (Kenya), owned by the School of Aerospace Engineering of Rome. The launch activity in Malindi started in 1967 and ended in 1988 without a failure. Today, the sea platform is one of the new options for autonomous access to space for those countries that do not have a suitable geographical position. A detailed description of the infrastructures and operations of the launch base is given in the chapter. The chapter is divided into nine sections, including optimal staging, description of stage separation systems (hot and cold), propulsion system, safe and arm, actuators and aerodynamics. Launch windows, launch azimuth selection and launch operations are described. Problems and solutions are presented.