The design of solid propellant rocket motor requires the incorporation of many aspects of engineering. Initially the specifications of the rocket motor was identified in accordance to the desired thrust of 60N. Then a review on the types of solid propellant rocket motors was done, in order to choose the ost convenient type. Once the end burning type was chosen the design aspects were carried out. The characteristics of the rocket motor such as chamber size, throat area and propellant burning rate were determined. Next, the propellant composition was formulated. The process of formulating the prppellant was on trial and error basis as there was no standard composition available which could produce the required burning rate of 1.143 cm/s. Consequently, after obtaining the desired propellant composition, the fabrication process was undertaken. The parts that made up the rocket motor were fabricated with a high degree of precision. Once the fabrication was over the rocket motor was put through a static test to determined whether it performs in accordance to the desired specifications. The test equipment was designed with simplicity and reliability in mind. Finally the test results were obtained, but it was not as expected. Nevertheless the results provided invaluable experience and information on the possibilities of improving the design in the future.