Binder melt: Composite propellants with RDX**

Abstract

The binder melt on the surface of aluminized composite propellants with RDX has been quantified using experimental and computational approaches. A scanning electron microscope in conjunction with energy dispersive spectroscopy was used to analyze the surface of unburnt and extinguished propellant samples. Rapid depressurization technique was used to obtain the extinguished propellants. Five propellants were prepared, keeping the aluminum and binder fraction constant at 4 % and 16 %, respectively. The RDX fraction in the propellants was varied from 3 % to 12 %. It was found that the melt on the surface of the propellant increased from 36.7 % to 43.9 % when the RDX fraction was changed from 3 % to 12 % in the propellant. For propellants containing 3 % to 9 % RDX, a region of plateau burning was observed in the pressure range of 5–7 MPa, while propellants containing 12 % RDX showed plateau burning between 7–10 MPa.