Hybrid rockets are featured by restarting capability, increased safety, high performance and
moderate cost. These combined unique characteristics pose then as prominent candidates to replace solid
rockets in tactical missiles and launch vehicles in the near future. However, the behavior of hybrid rockets
is not fully understood, with issues specifically related to combustion instability and lowered regression
rate. To investigate the characteristics of hybrid rocket performance we develop generic algorithm code.
This script may serve as a valuable teaching resource in hybrid rocket motor design. This paper uses
Hydroxyl Terminated Polybutadiene (HTPB) as a solid fuel and liquid oxygen as an oxidizer for evaluation
purposes. Later, we introduce the results of the preliminary design and performance analysis of the hybrid
rocket system. An interior ballistic model was used for the analysis of hybrid rocket performance.
MATLAB® environment was used to develop the design and performance analysis codes, and visualize the
temporal variation of performance characteristics
