GOX/Kerosene
Propellant
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GOX/Kerosene propellant. Gaseous oxygen was used together with the main engine propellant kerosene in the Buran spaceplane's maneuvering engine and orientation thrusters.
Propellant Formulation: GOX/Sintin. Oxidizer Freezing Point: -219 deg C. Oxidizer Boiling Point: -183 deg C. Fuel Density: 0.806 g/cc. Fuel Freezing Point: -73 deg C. Fuel Boiling Point: 147 deg C.
Subtopics
- 11D121 Korolev GOX/Kerosene rocket engine. N-1 stage 1 (block A) roll control engine. Developed 1969-74. Gimbaling +/- 45 degree. Propellants are fed from main engine (NK-15, NK-33) turbopumps. Chamber Pressure: 71.60 bar.
- RDMT-200K NII Mash GOX/Kerosene rocket engine. Buran. Out of Production. Low-thrust attitude control thruster. Mass in ref. NIIMash 95 given as only 2.5 kg.