Experimental demonstration of an end-burning swirling flow hybrid rocket engine

Abstract

Within the framework of the European H2020 HYPROGEO program, an innovative hybrid engine combustion chamber compatible with satellite requirements (constant thrust over very long burn-times) had to be developed. A first test rig was designed and tested in order to better understand the functioning of this innovative combustion chamber, and to help the design of a breadboard to demonstrate the efficiency of this new engine with respect to the mission requirements. Two test campaigns, the first on the test rig with 87.5% hydrogen peroxide, and the second on the hybrid engine breadboard with 98% hydrogen peroxide, were performed under various operating conditions to demonstrate the catalytic ignitability of this new hybrid engine, and the sustainment of a stable combustion over firing durations up to 180 s. The test campaigns also enabled the identification of the main influencing parameter on the fuel regression rate for this innovative combustion chamber.