Initial direction based off of preliminary research

     Hybrid rocket motors offer several theoretical advantages over solid and liquid propulsive systems. When compared to liquid bipropellant systems, hybrids offer increased simplicity and as a result have a lower cost to develop. Also, hybrids with metallized fuel grains are theoretically superior for high speed endo-atmospheric flight since their propellants are more volumetrically energy-dense than liquids. When compared to solids, hybrids offer increased specific impulse and safety due to the ability to throttle a hybrid rocket motor, and even shut it down completely if need be. These characteristics make hybrids the ideal propulsive system for civilian space flight and reliable, cheap, possibly single-stage, transportation. Hybrids have not received as much attention as theory would dictate because of the low regression rate of hybrid propellants and the complex, dynamic nature of their combustion process, which is not fully understood.
     These problems lend themselves easily to the two part, engineering project that I currently envision, spanning the classes of Advanced Computer Science and Innovations (ACSI) and Research Science. Both parts can be explored simultaneously. Part one is the application of a Finite Pointset Method (FPM) for Computational Fluid Dynamics (CFD), coupled with iterative equations of gas phase kinetics and equilibrium in order solve the Navier Stokes and Energy Equations for the 3D turbulent flows and dynamic combustion and regression in hybrid rocket motors. My model will be completely free and open to the public for improvement and implementation. Part two is the synthesis and application of green oxidizers (not containing halogens) to be dissolved in low concentration hydrogen peroxide solution. This safe, storable, liquid oxidizer is to be combusted with solid fuel grains containing high energy-density aluminum particles, hydrogen-rich compounds like borohydrides, and nitrogen rich additives like tetrazoles to increase the burn rate. Such additives will be suspended in a polymer matrix of Hydroxyl Terminated PolyButadiene (HTPB).
     At this stage, work has already been done on the successful preparation of HTPB composite fuels. Research shows that sodium borohydride is easily acquired and other boranes and borohydrides may be synthesized in the lab. Also, some possible preparations of green oxidizers like ammonium dinitramide (ADN) and HydroxylAmine Nitrate (HAN), and Hydrazinium Nitroformate (HNF) are documented, yet some may be more challenging than others. Further research is needed on the synthesis of these substances so that some may be eliminated due to complexity. Procedures for the synthesis of tetrazoles are documented, as well as their physical and chemical properties. Of course, this research will start small, with the synthesis and characterization of each additive in HTPB and then in combinations. The oxidizer used in initial tests will be standard and well documented like nitrous oxide, hydrogen peroxide, or gaseous oxygen.