Lox/Kerosene/LH2

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RD-701 Credit - © Mark Wade Propellant Formulation: Lox/Kerosene/LH2. Optimum Oxidizer to Fuel Ratio: 4.80. Density: 0.50 g/cc. Isp (vac): 440. Fuel: Kerosene/LH2. Fuel Density: 0.133 g/cc. Fuel Freezing Point: -259 deg C. Fuel Boiling Point: -253 deg C. Tripropellant motors use high-density kerosene for the boost phase, then low-density, high-performance liquid hydrogen for the later stages of ascent. However the propellants are stored in seperate tanks. The fuel density indicated is the average for the MAKS design, which burned 17,850 kg LH2 and 18,698 Kerosene to reach orbit using 175,758 kg of liquid oxygen oxidiser. Engines Using Lox/Kerosene/LH2 Motor Thrust(vac) kN Thrust(sl) kN Isp sec Isp (sl) sec Designed for Status RD-0120TD 1,317.000   419 295 Upper Stages Developed 1990's RD-0750 1,412.000   455 415 Upper Stages Developed 1997- RD-704 1,966.000 1,720.100 407 356 Upper Stages Developed 1990's RD-701 4,003.000 1,406.100 415 330 First Stages Development ended 1988 Contact us with any corrections, additions, or comments. Conditions for use of drawings, pictures, or other materials from this site.. To contact astronauts or cosmonauts. © Mark Wade, 1997 - 2008 except where otherwise noted.