Transient modes of double-base propellant combustion in a semiclosed volume

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

“…[3], the depressurization is induced by opening a nozzle at a stable chamber pressure. Different depressurization rates are obtained by varying the nozzle diameter, enabling studying its effect on the transient combustion behaviours of the propellant.…”

“…Kuo and Coates [1] and Gusachenko and Zarko [2] reviewed the previous works. Recently, the extinction problem of solid propellant during depressurization was investigated by Marshakov et al [3,4] using the phenomenological theory. However, when the base bleed projectile is propelled out of the muzzle, the AP/HTPB propellant in the base bleed unit suffers a much more severe transient depressurization than that in the rocket motor, which may destabilize the propellant combustion and bring unfavourable effect to the firing precision.…”

Modelado de la combustión de propulsantes sólidos

“…Aoki and Kubuta [77] also used a chimney-type strand burner with four transparent widows to analyse the burning rate of twelve different kinds of propellant previously prepared with different compositions. Finally, Markov et al [78] studied the combustion of a double-base propellant in a semi-closed volume. They also presented a short theoretical model in order to interpret and define several experiments performed in steady and non-steady conditions.…”