Most conventional rockets are of an either solid fuel or liquid fuel configuration. Nearly all production rocket motors produced throughout modern history are one of these two types. Conversely, a hybrid rocket utilizes a solid fuel grain and liquid oxidizer, thus capitalizing on the inherent advantages of both designs. A hybrid rocket exploits the power density (power per unit volume) of a solid fuel rocket, and the start-stop and throttling capability of a liquid fuel rocket. To date, only a few hybrid rocket designs have been developed to a production level configuration. This type of rocket motor technology remains largely in the experimental domain. [1] The Concept Hybrid Rocket Demonstrator (CHRD) is a small scale, modular, low-cost hybrid rocket design, for use in hybrid rocket research as well as educational applications in senior capstone curriculum for an undergraduate Mechanical or Aerospace Engineering or Engineering Technology program. Basic research activities include investigations of rocket fuel types and fuel grain port configurations, ignition systems, oxidizer delivery systems, rocket nozzle materials and aerodynamics, instrumentation schemes, and analytic modeling of rocket performance using computational software.The first generation of CHRD has been designed, fabricated, and tested successfully. A small rocket motor approximately two inches in diameter and ten inches long was fired multiple times during the spring of 2021, with preliminary results of rocket performance being documented. The current rocket prototype was the product of two consecutive academic years of senior capstone teams' efforts. The design, fabrication, and testing were supervised by a Mechanical Engineering faculty, who assumed the role of project manager and chief investigator.