Development Of A Gas Propelled Rocket Engine

ABSTRACT

This thesis examines the development of a gas propellant rocket motor using cheap local materials. The fabrication of the prototype rocket engine was achieved by using machine tools like the lathe and drilling machines. The internal radius around the nozzle throat area was made without using any special tools for curves. The engine was tested twice and readings or data taken for pressure and temperature. Two thermocouples were damaged because the temperature exceeded their temperature limit. Hence, temperature estimates were used in the analyses of the test results. Though some variations ranging from 0 to 15% were observed between the first test and their corresponding theoretical results in some parameters but the test results were in most cases found to lie between 70% and 80% of the assumptions. There was the sonic boom at Mach one and a bright yellow flame thrust 1.70 m long. Exit velocity of 1664 m/s at Mach 1.87 was attained and generated thrust was calculated from the product of exhaust velocity and propellant mass flow rate to be 7.65 KN. Combustion pressure of 16 bar was achieved at temperatures of about 2000 oC The second test provided useful information on the consequence of improper rocket engine operation.