Desenvolvimento de motor foguete bipropelente utilizando querosene e ar

Abstract

In this work, a small scale test bench 600 mm long, 400 mm wide and 900 mm high, was developed for use in low thrust propellers. This type of equipment has didactic application. In addition, it can be considered that the results reported in this work will serve as a subsidy for the construction of larger combustors in the medium term, in addition to the finalization of the project and future tests with the prototype already manufactured. In this work the characteristics of fuel bipropellants (kerosene and compressed air) were explored through experiments of low complexity and low cost, which are easily reproducible in teaching environments. The rocket motor was designed and manufactured in stainless steel 304. The engine was divided into three parts: combustion chamber and outlet nozzle, injection and fuel tank. Compressed air was obtained by using a commercial compressor. The calculated fuel-air mixture was 0.06846 and regulated by means of a retaining screw. The rocket motor was mounted on top of a counterweight, which in turn was coupled to a low cost balance, which served for the direct measurement of the generated thrust. The tests were done without the combined combustion chamber in the reservoir and injection. The results indicate stable combustion within the flammability limits of kerosene, indicating that for the used pressure of 5 bar there is possibility of burning inside the combustor.