An increasing trend , Low cost space access with Microsatellites, and so the need of an efficient, simple, reliable equally cost effective Carrier was considered with rapid designing and fast prototyping design concept so the small Liquid Propellant Rocket engine with "solid propellant gas generator" pressure feed system is resulted. The abstract discusses the perspective design of the upper stage of the Rocket "Shivastra-1". The design features a co-axially arranged propellant tankage fed with burning a cordite powder charge yielding a rapid initial acceleration and 3 M burn out velocity providing 10KN thrust at 30 km enough to reach 100 -180 km altitude carrying 2 kg of payload. The combustion chamber wall is enameled, protecting from high temperature of combustion. The preliminary design work is performed with CATIA-V5 and was optimized on ANSYS. The results obtained were optimistic for the static test fire on test stand providing a perspective design of a reliable Liquid Rocket Engine. Key words: Rocket, Shivastra, solid propellant, gas generator, Sounding Rocket, Upper stage, Microsatellite, Cub-Sat.
