Performance evaluation of commercial copper chromites as burning rate catalyst for solid propellants

Abstract

Copper chromites are well known as burning rate catalysts for the combustion of composite solid propellants, used as a source of energy for rocket propulsion. The propellant burning rate depends upon the catalyst characteristics such as chemical composition and specific surface area. In this work, copper chromite samples from different suppliers were characterized by chemical analysis, FT-IR spectroscopy and by surface area measurement (BET). The samples were then evaluated as burning rate catalyst in a typical composite propellant formulation based on HTPB binder, ammonium perchlorate and aluminum. The obtained surface area values are very close to those informed by the catalyst suppliers. The propellant processing as well as its mechanical properties were not substantially affected by the type of catalyst. Some copper chromite catalysts caused an increase in the propellant burning rate in comparison to the iron oxide catalyst. The results show that in addition to the surface area, other parameters like chemical composition, crystalline structure and the presence of impurities might be affecting the catalyst performance. All evaluated copper chromite samples may be used as burning rate catalyst in composite solid propellant formulations, with slight advantages for the SX14, Cu-0202P and Cu-1800P samples, which led to the highest burning rate propellants.

Hydroxyl Terminated Polybutadiene: Chemical Modification and Application of these Modifiers in Propellants and Explosives

“…As a common and conventional way, TMOs (e.g. iron oxide [106], CuCh [107] and cobalt oxide [108]) could be easily used as BR catalysts in propellants and affect the BR by lowering the thermal decomposition of AP and the binder [109,110]. However, since this kind of catalyst of high content may lead to poor processing, ageing and mechanical characteristics of the resultant propellants, it seems difficult to realize workable propellants with high BR requirements.…”

Thermal Decomposition of Ammonium Perchlorate in the Presence of Copper Tungsten Oxide (CuWO4)

“…Mixed metal oxides have been found advantageous than single metal oxide in composite propellant formulations. Various mixed oxides such as chromites [15][16], ferrites [17][18], etc. have been investigated as burning rate modifiers in composite propellant formulations by various researchers.…”

Solution Combustion Synthesis of Nanosized Copper Chromite and Its Use as a Burn Rate Modifier in Solid Propellants

“…Several materials have been studied and examined as potential burn-rate additives for composite solid propellants. The transition-metal oxides such as Fe 2 O 3 , Co 2 O 3 , Ni 2 O 3 , MnO 2 , and CuCr 2 O 4 were found to increase the burning rate of composite solid propellants. , The catalytic effect of these materials were examined on the thermal decomposition of ammonium perchlorate and also on the combustion of the ammonium perchlorate based propellants. ,− Besides these solid materials, liquid derivatives from iron and boron are also used as burning rate catalysts . The disadvantage in using the liquid derivatives is their diffusion within the propellant mixture causes varying concentrations in the propellant.…”

“…Copper chromite oxide is widely synthesized by two methods namely the ceramic method (oxide method) and the coprecipitation method. In the ceramic method, , copper(II) oxide (CuO) and chromium(III) oxide (Cr 2 O 3 ) are mixed in stoichiometric amounts and calcined at 700–800 °C. If the calcination temperature is increased to 900 °C, copper chromite reacts with copper oxide to form cuprous(I) chromite (Cu 2 Cr 2 O 4 ) .…”