Nanohybrids of reduced graphene oxide and cobalt hydroxide (Co(OH)₂|rGO) for the thermal decomposition of ammonium perchlorate

Abstract

Cobalt hydroxide nanoparticles supported on reduced graphene oxide increased the energy release and lowered the decomposition temperature of ammonium perchlorate.

Heterobimetallic Catalysts for the Thermal Decomposition of Ammonium Perchlorate: Efficient Burning Rate Catalysts for Solid Rocket Motors and Missiles

“…Therefore, the impact on the thermal degradation of AP is often used to evaluate the combustion effect of a burning rate catalyst candidate on the combustion behavior of composite solid propellants . Nowadays, BR catalysts include nanometal particles, − metal chelates, − and ferrocene derivatives. ,− Within this variety, the ferrocene derivatives have become an indispensable component in HTPB/AP (HTPB=Hydroxyl-terminated polybutadiene) composite propellants due to their extraordinary effects in enhancing the burning rates and bringing down pressure indexes of the propellants . Organometallic ferrocene-like compounds are chemically compatible with other ingredients of the propellant composition.…”

Influence of BaZnCuO3 and BaZnCuO3/rGO on the thermal decomposition of AP and NTO

“…The comparisons of previously reported additives (3 % by mass) on the thermal decomposition of AP is given in Table 3. [27][28][29][30] From Table 3, it was evident that BZC containing AP composition decomposes at low temperature and hence, it can influence the burning rate properties of AP based propellants and formulations to compare to other catalysts with same content reported in Table 3.Figure 6. DTA curve of (a) NTO, and (b) AP with and without BZC, and BZC/rGO additive was used to calculate the activation energy (E a ) and the pre-exponential factor (A).…”

Catalytic Effects of Ruthenocene Bimetallic Compounds Derived from Fused Aromatic Ring Ligands on the Main Oxidizing Agent for Solid Rocket Motor

“…1 Nevertheless, considering the limited loading of AP used for the development of rockets, it is imperative to increase its decomposition effectiveness further to produce a large amount of energy as far as possible and to decrease its combustion temperature for easy operation and control. 1 Different types of burning rate (BR) catalysts such as nanoparticles, [2][3][4][5][6][7][8] coordination complexes, [9][10][11] and ferrocene derivatives [12][13][14][15][16][17] have been studied to improve the decomposition efficiency of AP. Among them, ferrocenelike homobimetallic compounds have recently reached huge attention due to their microscopic homogeneity in the distribution with the binder agent (HTPB: hydroxyl-terminated polybutadiene) and the astonishing effects over the burning rates and pressure indexes of the propellants.…”