Burning Properties of Uncured HTPB Propellant

HTPB-Polyurethane: A Versatile Fuel Binder for Composite Solid Propellant

A Model of Ap/htpb Composite Propellant Combustion in Rocket-motor Environments

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...

Response of a Burning Propellant Surface to Erosive Transients

مقایسه خواص پیشرانه‌های جامد مرکب بر پایه HTPB و NHTPB/HTPB

Hydroxyl terminated polybutadiene (HTPB) is the most commonly used binder in composite solid propellants. However, due to its non-energetic character, in practice it is just a dead weight; Therefore, replacing HTPB with an energetic polymer is essential. In this research, nitrated hydroxyl terminated polybutadiene resin (NHTPB) with 12.2% nitration rate, in combination with HTPB resin was used ...

تأثیرات مقدار نانو اکسید تیتانیوم (IV) زیر میکرون بر خواص پیشرانه HTPB/AP/Al

Titanium (IV) oxide as a burning rate catalyst is commonly used in some of the solid composite propellants. As the particle size of this component decreases, the final properties of the propellant will be changed. In this research, effects of using submicron titanium oxide, up to 0.5 percent by weight, have been investigated on properties of an HTPB/AP/Al propellant. TiO2 powder has relatively ...