Hybrid Rocket systems, propelled by a combination of a solid propellant and liquid oxidizer, have significant advantages such as safety, easy handling and low costs. A joint team has been organized by Hokkaido University, Muroran Institute of Technology, Hokkaido Institute of Technology, Tokai University, Tokyo Metropolitan Institute of Technology, National Space Development Agency, Japan, and some private sectors, so as to investigate the feasibility of suborbital/orbital reuseable hybrid rocket systems. A preliminary analysis of the rocket motor performance and winged flight trajectories predicts the capability of developing a payload of 190kg into a suborbital micro-G environment for three minutes using hybrid rocket based on polystyrene and LOx fed by an LE-5B turbopump
