Isayev monopropellant rocket engine. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by an iridium-based catalyst, which heated to increase stability. 40,000 ignitions
Status: In Production. Thrust: 10 N (2 lbf). Unfuelled mass: 0.60 kg (1.32 lb). Specific impulse: 229 s. Burn time: 1,500 s.
Engine: 0.60 kg (1.32 lb). Chamber Pressure: 10.00 bar. Area Ratio: 46. Thrust to Weight Ratio: 1.7.