Design, manufacturing, cold and hot-fire test of a liquid subscale engine with single swirl double base injector

The ongoing developmental studies on the application of subscale liquid rocket engines as small thruster and laboratory tester are briefly reviewed. Then a detailed design & manufacturing process of a laboratory liquid subscale engine with single swirl double base injector of 300 N thrust for this reaserch is presented. For the preparation of pressurized water, fuel and oxide, a test facility has been prepared. Results of water analogy tests are presented. Initial firings using the real fuel and oxide were not successful. Low fuel flow, low mixing area of the fuel and oxide, and contamination in the TR-1 were considered to be the reasons. Overcoming to these problems resulted in successful firing of the subscale engine. obtained results were adapted to design expected results.