Combustion of Liquefying Hybrid Propellants: Part 1, General Theory

Abstract

In this paper classical hybrid combustion theory is generalized to solid fuels that form a liquid layer on their burning surface. For several classes of liquefying fuels, the layer is hydrodynamically unstable in a gas e ow environment leading to substantial droplet entrainment into the gas stream. The susceptibility of a given fuel to this shear driven instability increases with decreasing viscosity and surface tension of the melt layer. The entrainment mass transfer, which acts in addition to the conventional gasie cation mechanism, is not affected by the blocking phenomenon induced by blowing from the surface. For practical oxidizer e ux levels encountered in hybrid rocket applications, droplet entrainment can dominate direct gasie cation. Such liquefying fuels can exhibit greatly increased surface regression rates compared to classical materials such as Hydroxyl Terminated Polybutadiene. One application of the theory is to solid cryogenic hybrids, which utilize frozen materials for the solid propellant. The theory successfully predicts why high regression rates are observed in tests of cryogenic solid pentane, solid methane, and solid oxygen. In addition, the theory explains the dependence of the burning rates of other tested cryogenic materials on the physical properties of the liquid layer. The theory also leads to the conclusion that certain noncryogenic materials such as parafe n and Polyethylene waxes will also exhibit high regression rates. This important result is cone rmed by lab scale tests performed at Stanford University on a high melting point parafe n wax.