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This research designs and builds a prototype Hybrid Fuel Rocket in order to study and develop ignition system and combustion mechanism of Hybrid Fuel Rocket. In addition, this prototype unit will able to support further study and development of Hybrid Fuel Rocket. Two (2) type of ignition systems; spark plugs system and glow plug system have been developed. The main focus of this research is to study the ignition mechanism, investigate and determine combustion efficiency and trust between the two (2) types of ignition system, Spark Plug and Glow Plug. Both ignition systems had been commissioned, tested and compared. The researchers used paper for a solid fuel and oxygen (GOX) as an oxidizer. Both ignition systems have been tested three (3) times and the mean static has been used for comparing the result form both ignition systems. From the test result, the combustion time of both ignition systems demonstrate the same characteristic, 5 seconds combustion time. For the measuring trust, Glow Plug System generate higher trust than the Spark Plug System 0.367 Ibf, due to less weight and lower friction of glow plug system. In conclusion, both types of ignition systems are able to operate and have the same operating characteristic. However, glow plug system has beneficial on ability to use with wide range of fuels which more difficulty to ignite. One caution on glow plug system is, when using with fuel that difficult to ignite, the accumulated heat in the combustion chamber before igniting may damage the rocket and equipment.