What is it about?
Kerosene and concentrated hydrogen peroxide were used to power a rotating detonation rocket engine. A chug instability mode powered by individual detonation events was observed. Cycle periods and operation frequencies were stochastic and not normally distributed. Large wavespeeds (exceeding the Chapman-Jouguet speed) were also observed. Large pits in the chamber walls were likely caused by condensed phase detonations after only a few seconds of operation.
Featured Image
Photo by NASA on Unsplash
Why is it important?
This test campaign demonstrated liquid/liquid (kerosene/90% HP) propellant operation, a novel operating mode, wavespeeds exceeding CJ, and evidence of condensed phase detonation.
Read the Original
This page is a summary of: Experimental Study of Liquid Bipropellant Rotating Detonation Rocket Engines Using RP-2 and Hydrogen Peroxide Propellants, January 2024, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/6.2024-2249.
You can read the full text:
Contributors
The following have contributed to this page
