Comparison of propellant characteristics

With the advent of new technologies in space science, numerous missions and programs to launch satellites of various scales have received significant attention in the scientific community. However, there are a few complexities involved to encourage activities such as space tourism and exploration due to the technical constraints that the launch vehicle poses. To surmount these challenges, a novel hybrid rocket engine must be designed which allows us to tailor the characteristics during its endurance simulations. In the current work, we have investigated the propellant’s thermal and flow characteristics such as glass transition and melting temperature, specific impulse, characteristic velocity, regression rate, and thrust, respectively, without compromising the performance of likewise liquid propellant engine. In the current work, we investigated propellant characteristics for pure paraffin wax with oxidizers, such as liquid oxygen and nitrous oxide, and pure paraffin with additives of aluminum, magnesium, and oxidizers. It was observed that pure paraffin with liquid oxygen and additive aluminum (30% weight) resulted in the highest specific impulse among other combinations, whereas differential scanning calorimeter investigations reported a reduction in latent heat with the increase in weight% of paraffin and aluminum powder. It is also suggested that heat flow at 10% weight complies with the hybrid rocket engine.