ABSTRACT This preliminary study aimed to develop and test a solid propellant composition that would ensure a high burning rate. The burning rate measurement was conducted using the laboratory rocket micromotor. The materials were prepared using ammonium perchlorate (AP), hydroxyl‐terminated polybutadiene or poly(glycidyl azide) (GAP), and various additives: catocene, iron(III) oxide (Fe 2 O 3 ), aluminum, octogen, trimethylolethane trinitrate (TMETN), and others. The results showed that GAP‐based solid rocket propellants have the highest performance among the tested materials. Applying an energetic GAP binder and plasticizer TMETN with the bimodal fine and coarse oxidizer AP system improved the viscosity while increasing the burning rate and specific impulse. The highest in terms of the burning rate were the compositions, which contain a mixture of catocene and nano‐sized Fe 2 O 3 as a catalyst. This solid rocket propellant composition achieved a burning rate approx. 60 mm/s in the 300–350 bar range. A gas‐dynamic control system is one potential application for the developed propellant.
Wacko et al. (Tue,) studied this question.