A comprehensive theoretical/numerical model for treating AP/HTPB composite-propellant combustion in a rocket-motor environment is presented. The formulation takes into account the conservation equations in both the gas and condensed phases, and accommodates finiterate chemical kinetics and variable thermophysical properties. The processes in the two phases are coupled at the surface to determin...

A visualization facility has been developed at Stanford University in order to study flow in a turbulent combustion boundary layer. The motivation for the facility arises from recent studies of fast burning fuels for hybrid rocket propulsion where droplet lift-off from the melting fuel surface is the dominant mass transfer mechanism. The facility, shown in Figure 1, has been used to image the c...

Acrylonitrilebutadiene-styrene (ABS) thermoplastic is evaluated as a potential fuel for hybrid rocket motors and compared to the widely used fuel material Hydroxyl-Terminated Polybutadiene (HTPB). For this project Nitrous Oxide (N2O) is used as the matching oxidizer. ABS is widely mass-produced for non-combustion applications including household plumbing and structural materials. Analytical pre...

Abstract The interfacial interaction between the main oxidant filler ammonium perchlorate (AP) and hydroxyl-terminated polybutadiene (HTPB) matrix in AP/HTPB propellants were studied via an all-atom molecular dynamics simulation. results of simulation showed effects microscopic cross-linked structure matrix, stretching rate during uniaxial stretching, contact area on mechanical properties, such...

Molecular dynamics simulations were carried out to study the effects of interface interactions between a crystalline structure and a plastic bonded explosive (PBX) system. In this work, the hydroxyl-terminated polybutadiene (HTPB) represents the polymer, isophorone diisocyanate (IPDI) is the diisocyanate and dioctyl adipate (DOA) is the plasticizer. Two different crystal high explosives compone...