DESIGN AND PRODUCTION OF HYBRID ROCKET ENGINE STATIC IGNITION TESTING MACHINERY AND DETERMINATION OF IMPULSE-TIME CHANGE OF PVC/OXYGEN FUEL/OXIDIZER
Project no. 20626 · Status: Kapanmış · 2019
Summary
DESIGN AND PRODUCTION OF HYBRID ROCKET ENGINE STATIC IGNITION TESTING MACHINERY AND DETERMINATION OF IMPULSE-TIME CHANGE OF PVC/OXYGEN FUEL/OXIDIZER Rockets are generally used for defense purposes, for civilian purposes, for satellite launching and for orbiting and keeping the satellite in orbit. Chemical fuel rockets are examined in three groups as solid fuel rockets, liquid fuel rockets and hybrid fuel rockets. Due to the cost and complexity of liquid fuel rockets, the explosion hazard and thrust control problems of solid fuel rockets, studies on the use of hybrid rockets have recently become more common, taking into account the safety advantage. There are a limited number of rocket and hybrid rocket test setups in our country. With this project, Ege University's first “Hybrid Rocket Engine Static Ignition Testing Machinery”, which can provide experimental support to researchers doing or wanting to do research on rocket engines, was designed and produced. As a result of the experiments, the thrust-time change was determined for the PVC/Oxygen fuel/oxidizer’s inner space of the cylindrical fuel with straight and square channel. When straight fuel and square channel fuel were compared, it was determined that using square channel in the fuel cavity provided 48.6% improvement in maximum thrust, 52% in total impulse, 64.8% in specific impulse and 64.8% in effective exhaust velocity. Keywords: Hybrid Rocket Motor, Thrust, Experimental Method