Preliminary analysis of hybrid rockets for launching nanosats into LEO

Abstract

This work determines the preliminary mass distribution of hybrid rockets using 98% H2O2 and solid paraffin mixed with aluminum as propellants. An iterative process is used to calculate the rocket performance characteristics and to determine the inert mass fraction from given initial conditions. It is considered a mission to place a 20 kg payload into a 300 km circular equatorial orbit by air launched and ground launched hybrid rockets using three stages. The results indicate total initial masses of about 7800 kg for a ground launched hybrid rocket and 4700 kg for an air launched hybrid rocket. © 2010 by ABCM.