PW-R02 was a proof-of-concept concept liquid engine to test the feasibility of a liquid propellant-catalyst bed design.
Similar to the cold thruster, it used a 50% hydrogen peroxide solution, decomposed with solid potassium permanganate catalyst, producing gaseous oxygen and steam.(2 KMnO4 (aq) + 3 H2O2 (aq) → 3 O2 (g) + 2 MnO2 (s) + 2 KOH (aq) + 2 H2O (l)).
The first firing was successful, during the secondary firing and following thrust tests, a fuel leak in the injector coupling caused the destruction of the engine.
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