Design Construction And Tests Of A Rocket Propulsion Motor With Hybrid Propellant In A Static Bank PDF Download

The degree project arises from the interest in hybrid rocket engines since it is a modern global technology among rocket engines, and has not been built or tested in Colombia. The main objective of the project is to design, build and test a Design, build and test a 250 N hybrid thrust rocket motor. For this, the motor was designed with paraffin as the solid fuel, and nitrous oxide as the liquid oxidant when designing a methodology for design, construction and testing. In the conceptual design stage, different input parameters were defined, in which the pressure of the combustion chamber was 290 psi, nozzle temperature of 2856 K, flight time of 5 seconds, specific impulse of 185 seconds, with which the different elements of the combustion chamber could be designed, including the nozzle. Additionally, the oxidant tank and the valves system were designed for their subsequent manufacture and purchase, respectively. At the same time, the electronic system was proposed in order to measure the thrust, pressure in the combustion chamber and temperature in the nozzle; and the UCAND-3 benching test was redesigned to carry out the experiments, which were planned with a sample of three fuel grains. However, it was found that the igniter did not burn completely in any test to make the reaction between fuel and oxidant be carried out satisfactorily because the burning surface area was not enough for the reaction to take place, so it is necessary to change the ignition system. However, both the hybrid rocket engine and the benching test are ready to be used in the near future.