Experiments on two-dimensional model propellants using cylindrical oxidizer (ammonium perchlorate) pellets in a fuel matrix (CTPB) are described. Measurements show that burning rate of AP in the fuel environment is lower than of pure AP. The oxidizer-to-fuel ratio seems to be fuel-rich when the oxidizer particles are imbedded in contact with the fuel and it becomes oxidizer-rich for a non-zero separation between oxidizer particle and the fuel.

Some Experiments on Model Composite Solid Propellants

The Deflagration of Ammonium Perchlorate-Polymeric Binder Sandwich Models

In order to obtain information essential to the future success of analytical modeling of solid propellant combustion, an experimental investigation was conducted using the quench combustion of two-dimensional propellant sandwiches prepared with AP oxidizer and four conventional propellant binders—polysulfide (PS), polyurethane (PU), polybutadiene acrylic acid (PBAA), and carboxy terminated polybutadiene (CTPB). Propellant sandwiches, prepared with both single crystal sheets and compacted polycrystalline sheets, were burned and quenched at combustion pressure levels from 300 psig (20 kg/sq cm) to 2400 psig (163 kg/sq cm) for a range of binder lamination thicknesses varying between 25 and 200 microns. The features of the quenched sandwiches indicate that there is considerable interplay between the binder and oxidizer species on the oxidizer portion of the sandwich surface, primarily through the ability of the binder to form a flowable melt prior to gasification; sandwiches prepared with all four fu...

Some Experiments on Model Composite Solid Propellants

References

The Deflagration of Ammonium Perchlorate-Polymeric Binder Sandwich Models

Experimental Combustion Studies of Two-Dimensional Ammonium Perchlorate-Binder Sandwiches

Related Papers (5)

A thermal layer mechanism of combustion of solid composite propellants: Application to ammonium nitrate propellants

A model describing combustion of solid composite propellants containing ammonium nitrate

Development and characterization of high performance solid propellants containing nano-sized energetic ingredients

Effect of Oxidizer Particle Size on Burning Rate and Thermal Decomposition of Composite Solid Propellants

Effect of the physical state of the activators on the combustion of composite rocket propellants. I. The applied catalysts