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Mechanical Compression Behaviour of "Green" Rocket Propellants

Dîrloman Florin M., Rotariu Traian, Rotariu Adrian N., Toader Gabriela, Matache Liviu C., Noja Gabriel F.

Problemy Mechatroniki : uzbrojenie, lotnictwo, inżynieria bezpieczeństwa

2023

Vol. 14, Nr 2 (52)

9--18

The issues related to mechanical resistance of solid rocket propellants, which can appear during storage or handling of the launching system, are considered to directly influence the burning performance. Thus, in this study, four new types of composite rocket propellants, based on an environmentally friendly oxidizer (phase-stabilized ammonium nitrate), a metallic fuel (aluminium), and a "green" polyurethane-based binder (synthesized from an oligomeric isocyanate and a blend of polyester-polyols obtained through the catalytic degradation of polyethylene terephthalate), were subjected to compression mechanical analysis in order to highlight the importance of the binder on the response given by the tested materials subjected to compressive loads. The samples showed remarkable mechanical performances, the experiments allowing us also to determine the influence of the binder composition and fuel granulation on mechanical properties of the composite propellant.

Theoretical and Experimental Research on Gun Propellant Burning

Noja Gabriel F., Rotariu Adrian N., Mărmureanu Marius I., Malciu Adrian, Pulpea Bogdan G., Dîrloman Florin M.

Problemy Mechatroniki : uzbrojenie, lotnictwo, inżynieria bezpieczeństwa

2022

Vol. 13, Nr 4 (50)

9--22

The paper presents a method to determine the burning rate law and the progressivity coefficient of the fine-grained propellants shape. To achieve the objective of this paper, a series of tests were performed in a closed vessel. The results obtained from these tests were processed to determine experimentally the burning rate and the progressivity coefficient of the propellant shape starting from the premise that the burning surface has identical values for the same value of the volume fraction of burned propellant in two closed vessel tests at different loading densities. The experimental determination of the progressivity coefficient of the propellant shape shows that irregularities of the shape of the fine-grained propellants and gradual ignition lead to values completely different from the theoretical ones.