Thermodynamic Calculation Of Composite Propellant Rocket Motor

Nanoscale aluminum and water propellants have received considerable interest as of late because of their application to underwater and space propulsion.The thesis is made metal/water reaction fuel as a propellant, and is established the mathematical model of thermodynamic calculation. According to the Gibbs free energy minimization, the thesis is established a set of thermodynamic calculation procedure using the language development tool of Visual FORTRAN, and develops the simulation software of thermodynamic calculation for metal/water combustion reaction.Thermodynamic calculation and energy characteristics comparison on the different types of fuel for Al/water propellant rocket motor has been done, and the result is showing that energy characteristics of aluminum powder fuel is higher then different proportion aluminum matrix fuel. The energy characteristic of HTPB based fuel is poor, so is not suitable to Al/water propellant rocket motor. GAP can greatly improve the energy characteristic of aluminum matrix fuel. Under the same proportion, energy characteristic of GAP/aluminum matrix fuel is higher then HTPB/aluminum matrix fuel.Thermodynamic calculation was conducted to determine the relative propulsive performance and viability of novel solid propellants comprised of ALICE using Gibbs free energy minimization method. The result is showing that the maximum specific impulse and the optimum water ratio for the formulation 80/20 are 2327.6 N.s/Kg and 0.9 respectively.