Small solid propellant rocket motor is studied and is presented in this thesis. A rocket motor is designed, fabricated, tested in static test rig to get experimental result, and finally the rocket will be launch after assemble the rocket including rocket motor, rocket body ,recovery system and nose contain altimeter.
The oxidizer used is Potassium Nitrate. The propellant is fabricated using cold method. The designed is to achieve the mission to fly a rocket to 1000 m. The project is begun by deciding design specifications and parameters. Total impulse required was the first thing to be decided. Then, the rocket motor (motor casing, nozzle and bulkhead) would be scale. Another bulkhead that contained holes that connect to pressure gauge is designed and is fabricated to investigate the actual chamber pressure. The design process is continued with fabrication process where all the components including propellant grains have been fabricated. Three different propellants ratio had been made in three different static test. Static test is conducted to determine actual thrust and actual total impulse experimentally. However, the first static test does not give satisfaction result. The propellant was broken then bring less thrust to the rocket motor .The solution improving first static test had been made by generate burn rate test and another series of static test. Rocket is scheduled to launch after viva and thesis submitting
Solid propellant rocket motor 2012_Mohammad Hafizi Jamaluddin_A2_2012_NI