The Raman-II engine, built by Skyroot to produce 820 N (Sea Level) and 1460 N (Vacuum) thrust with a nominal chamber pressure of 8.5 bar absolute, was used in the test. Mono Methyl Hydrazine and Nitrogen Tetroxide are used as propellants in the additively built, regeneratively cooled engine. The start transient, steady state, and shut-off performance of the 10-second test met expectations. Skyroot aims to include the Raman-II engine into the Vikram-I’s fourth stage.

Throughout the test, the test facility systems operated normally and met the T0 engine inlet conditions. Additionally guaranteeing the correctness and dependability of the test results were the instrumentation systems’ performance in line with expectations.

This assistance demonstrates ISRO’s dedication to supporting start-ups, NGEs, and private stakeholders in the growth of the nation’s space eco-system. The capabilities of the Raman-II engine will be further validated and improved in the future through a number of further tests.