Performance and Combustion Analysis of Solid Rocket Propellant Using Aluminum Powder, Ammonium Perchlorate, and HTPB

In this paper, the design and performance evaluation of a small-scale solid propellant rocket were discussed to be made up of a mixture of powdered aluminum (Al), ammonium perchlorate (NH₄ClO₄), and hydroxyl-terminated polybutadiene (HTPB). A 92.5 cm with a diameter of 5 cm and total mass of 0.854 kg, well-designed rocket using Creo software with optimal structural and aerodynamic performance was considered. Parametric parameters include a center of gravity located at 69.4 cm with a center of pressure of 61.8 cm, therefore developing excellent stability in the case of flight. The propellant formulation consisting of aluminum as fuel, ammonium perchlorate as an oxidizer, and HTPB as binder was selected in such a way that burning efficiently would optimize thrust output. Static tests were conducted on the launch vehicle using calibrated gauge instruments to measure the thrust force, specific impulse (Iₛₚ), and burn rate. The static tests were complemented by a GPS-enabled launch test that provided real-time recording of altitude and trajectory. Preliminary results of thrust profiles show well-defined shapes, and the value of specific impulses also is quite satisfactory. Detailed analysis of the thrust-time curve, the specific impulse, and the burn rate indicates the performance of the propellant composition. Such studies and findings add to the greater understandability regarding the efficiencies of solid rockets, and it has potential applications towards the improvement of small-scale rocketry along with further advancements in propellant formulation.