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Thermal Decomposition of Ammonium Perchlorate Encapsulated with Copper(II)/Iron(III) Oxide Nanoparticles

Gržetić Jelena D., Mijatov Slavko, Fidanovski Bojana, Kovačević Tihomir, Pavlović Vladimir B., Brzić Saša, Bajić Danica

Central European Journal of Energetic Materials

2023

Vol. 20, no. 2

114-137

Thermal decomposition of ammonium perchlorate (AP), as a high energy oxidizer in composite solid rocket propellants (CSRP), greatly affects the burning rate of the propellant. This paper summarizes the results of a study of the synergistic catalytic activity of nano-CuO/Fe₂O₃ nanoparticles on thermal decomposition of AP. AP micro-particles are efficiently encapsulated with 1 and 5 wt.% of nano-CuO and/or nano-Fe₂O₃ nanoparticles by the fast-crash solventantisolvent technique. The efficiency of the encapsulation method was confirmed using FT-IR spectroscopy. Morphological characterization, performed using SEM-EDS microscopy, showed that encapsulation provides recrystallization and deagglomeration of AP and uniform nano-catalyst distribution. The catalytic efficiency of nano-CuO/ nano-Fe₂O₃ nanoparticles on the thermal decomposition of AP was investigated using DSC, and an increase in released heat was observed from 1453 to 1628 J/g. The catalytic activities of performed nano-catalysts were proven by decreasing the HTD and merging with the low decomposition temperature peak. The highest catalytic effect was obtained after encapsulating with 5 wt.% of nano-CuO and nano-Fe₂O₃ combined in a 50/50 mass ratio due to multiple mechanisms of catalytic activity of nano-Fe₂O₃. The effect of AP encapsulation with nano-Fe₂O₃ on the burning rate of CSRP was investigated and the obtained results showed a favorable effect on the combustion rate law.

Comparative closed vessel tests : influence of ignition and loading conditions on propellant burning rate

Leciejewski Z. K.

Materiały Wysokoenergetyczne

2011

T. 3

57--63

The most widely used experimental method to determine and to compare energetic and ballistic properties (force, co-volume, coefficients of burning rate law) of different propellants is burning a specific amount of propellant in a closed chamber. The procedure of determining the values of the individual material constants recommends similar conditions of closed vessel investigations like limited range of loading density and determined mass of black powder (igniter material) for determined loading density. There also often occurs the need for performing of closed vessel comparative tests (carried out for two or more numbers of propellants), where one of them serves the role of a reference propellant and in relation to which described are the differences between the characteristics of the remaining propellants are described. Comparative tests of propellants should be understood to be such tests performed for identical loading conditions, including firstly the same closed chamber capacity, mass of the propellant burned (thereby the identical loading density) as well as identical ignition conditions which are understood as the same mass and the same type of igniter material. In the present paper the influence of ignition and combustion conditions during closed vessel tests on possible deviations in determination of burning rate is analysed as a function of incident heat flux.