Solid propellants are materials with controlled burning and one of the type used as fuel is solid propellant type composite, NH4ClO4 using as oxidizing agent and certain additives. Among them, stands out as CuCr2O4 accelerator burning (Shen, 1983; West, 1984; Meyer, 1987; Campos et al, 2010). Some of sites are activated by adsorption of reagents and because of this, increase the speed of decomposition of NH4ClO4 (Rastogi, 1978). In the present study, we performed the synthesis of compound CuCr2O4 by the methods of coprecipitation and ceramic, for the purpose of comparing structural differences, thermal and resulting morphological methods employed using the techniques XRD, FT-IR, TGA, DSC, SEM and density determination. The results show the best aspects to the compound synthesized by ceramic method, with higher crystallinity, thermal stability up to 1000°C and morphology more defined, with grains having geometries tetrahedral and octahedral and approximate size of 3750nm, very close to the literature, 3700nm (Smith and Snyder, 1969). However, the ceramic method becomes more expensive to use high purity raw materials, as well as use elevated temperatures for the synthesis of the product, which is used widely in manufacturing propellants for various purposes.
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