| Summary: | Since the introduction of the concept of insensitive weapons, rocket motor designers must now ensure that their vulnerability is as low as possible. One of the inherent characteristics of a sugar-based propellant is the obvious plume coming out from the nozzle as a result of chemical reactions. The present work characterises a novel minimum signature composite solid propellant based on Ammonium perchlorate/Sorbitol with magnesium metal as a fuel and chlorine scavenger. The elemental stoichiometric coefficient and oxygen balance for the propellant mixture were calculated to find the optimum ratio between the oxidizer and fuel. The solid propellant of AP was prepared by mixing it with melted sorbitol and casting it into the cylindrical hollow tube using the freestanding method. The burning rate for five samples was measured at atmospheric pressure. The morphology was characterized by a scanning electron microscope. Calculation results reveal that ammonium perchlorate at 0.77% weight produced the best elemental stoichiometric coefficient and oxygen balance. The sample with the additive metal showed a significant increase in the burning rate. In all formulation samples of magnesium and ferrous oxide, the maximum burning rate at 0.126 cm/s showed that the metal additive and the propellant worked synergistically with each other. Results from SEM indicate that ammonium perchlorate spherical particles were uniformly dispersed within sorbitol. The addition of ferrous oxide increases the interaction between the component, and at the same time it gives the oxidizer the ability to interact more efficiently with the fuel and improve the physical strength of the solid propellant. This research is a minor step for Malaysia to become a top competitor in the aerospace industry in the future. © (2024) College of Engineering, Universiti Teknologi MARA (UiTM), Malaysia.
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