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: 50 N (11 lbf). Unfuelled mass: 1.10 kg (2.40 lb). Specific impulse: 229 s. Burn time: 1,500 s.
Engine: 1.10 kg (2.40 lb). Chamber Pressure: 8.00 bar. Area Ratio: 42. Thrust to Weight Ratio: 4.63.