Experimental test analysis of a 300 N hybrid rocket engine

Abstract

A hybrid rocket engine test bench experiment carried out the thrust 300 N, retaining nitrous gas as an oxidant, and 70 weight percent paraffin and 30 weight percent aluminum as fuel. To enhance the regression rate, new fuels such as paraffin-based fuel have been created, allowing for more compact engine designs with high thrust densities. As a result, the use of hybrid rocket engines in several domains, such as sounding rockets and small satellites for educational purposes and launch vehicle propulsion systems, has become possible. The solid fuel grain diameter is assumed to spread the characterization under different conditions. Estimate the rocket performance in the assumed condition and develop the test bench setup. In this paper, the data are composed of a 165 mm length of grain, external diameter is 79.6 mm and internal/port diameter is 8 mm. The injector plate used in this experiment is three injector holes with 120°. This injector is a showerhead that is simple in design and it is frequently used in hybrid rocket engines. Constraints such as the pressure in the combustion chamber being 50 bar and the SS304 nozzle, thrust were measured. Four separate test series were conducted. In the first test, one hole in the showerhead injector geometry was studied. In the 2nd, 3rd, and 4th tests, injector plates with three injector holes were used. The test bench of a hybrid rocket engine has many components (oxidizer/pressure tank, combustion chamber with the pre-combustion, post-combustion chamber, conical shape nozzle, igniter, injector plate, etc.).