Burning Characteristics and Thermochemical Behavior of AP/HTPB Composite Propellant Using Coarse and Fine AP Particles

Abstract

The burning rate of AP/HTPB composite propellant increases with increasing AP content and with decreasing AP size. In addition, the burning rate can be enhanced with the addition of Fe2O3. The burning characteristics and thermal decomposition behavior of AP/HTPB composite propellant using coarse and fine AP particles with and without Fe2O3 at various AP contents were investigated to obtain an exhaustive set of data. As the AP content decreased, the burning rate decreased and the propellants containing less than a certain AP content self‐quenched or did not ignite. The self‐quenched combustion began at both lower and higher pressures. The lower limit of AP content to burn the propellant with coarse AP was lower than that with fine AP. The lower limit of AP content to burn was decreased by the addition of Fe2O3. The thermal decomposition behavior of propellants prepared with 20–80 % AP was investigated. The decrease in the peak temperature of the exothermic decomposition suggested an increased burning rate. However, a quantitative relationship between the thermochemical behavior and the burning characteristics, such as the burning rate and the lower limit of AP content to burn, could not be determined.

Application of Al/B/Fe2O3 Nano Thermite in Composite Solid Propellant

“…As the nano structure and the existence of Fe2O3, Al/B/Fe2O3 has a positive effect on the decomposition of AP primarily [13]. The DSC curves of sample 2, 3 and 4 show a noticeable difference in the decomposition patterns of AP.…”

Numerical analysis of AP/HTPB composite propellant combustion under rapid depressurization

“…1, AP oxidizer locates in the region jxj aL below the burning surface, and HTPB binder locates in the region aL < jxj L, equivalent to an AP layer sandwiched by two HTPB slices. In order to validate the model, a type of AP/HTPB propellant tested by Kohga [21], of which the average AP particle size is 110 mm and the AP content is 80%, is selected as the object in the study. The chemical kinetics and thermophysical properties are taken from Ref.…”

Evaluation of Nano‐Co3O4 in HTPB‐Based Composite Propellant Formulations

“…AP is used in composite propellantf ormulationsa st he major ingredient (oxidizer) [3] in different size fractions to enhance the burning rate. However,f ine and superfine particle fractions of AP increase the burning rate as well as the propellant slurry viscosity thus casting of slurry becomes difficult [4].Therefore, to cope with suchp roblems, burning rate modifiersa re preferred. The burning rate modifiers are transition metal oxides (TMOs) or their complexes.…”