Development of A Gas Propelled Rocket Engine

Abstract

When it comes to getting people and cargo into space, the rocket engine is king. This research paper looks at how a gas propellant rocket motor could be built with readily available, low-cost components. The lathe and the drilling machine were among the several machine tools used to create the prototype rocket engine. No specialised curved-surface techniques were used to create the internal radius around the nozzle throat area. Two runs were made with the engine's temperature and pressure recorded. The temperature was too high, and two thermocouples were ruined as a result. Therefore, the analyses of the test findings made use of temperature estimates. Some parameters showed a range of 0-15% in discrepancy between the initial test and the corresponding theoretical results, but in most cases, the test results were determined to lay between 70 and 80% of the assumptions. The sonic boom occurred at Mach 1, and a 1.70-meter-long, bright yellow flame was pushed out. The exit velocity was measured to be 1664 m/s at Mach 1.87, and the resultant thrust was determined to be 7.65 KN by multiplying the exhaust velocity by the propellant mass flow rate. At roughly 2000 degrees Celsius, a combustion pressure of 16 bar was reached. The second trial taught us a lot about the repercussions of mishandling a rocket engine.