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Engine Model: RD-192. Manufacturer Name: RD-192. Designer: Glushko. Developed in: 1996-. Propellants: Lox/LCH4. Thrust(vac): 2,138.000 kN (480,641 lbf). Isp: 356 sec. Isp (sea level): 330 sec. Mass Engine: 3,300 kg (7,200 lb). Diameter: 2.00 m (6.50 ft). Length: 4.05 m (13.28 ft). Chambers: 1. Chamber Pressure: 257.00 bar. Oxidizer to Fuel Ratio: 3.50. Thrust to Weight Ratio: 66.06. Country: Russia. Status: Developed 1996-.

Proposed methane-variant of RD-191. Gimbaling +/- 8 degree in two planes. Status 1996 was project based on RD-191 prototype, development estimated for four years. Nozzle expansion ratio is 262/0.75=349.

Engine Model: RD-192.2. Manufacturer Name: RD-192.2. Designer: Glushko. Developed in: 1996-. Propellants: Lox/LCH4. Thrust(vac): 1,942.000 kN (436,578 lbf). Isp: 354 sec. Isp (sea level): 325 sec. Diameter: 1.45 m (4.75 ft). Length: 3.62 m (11.87 ft). Chambers: 1. Chamber Pressure: 196.00 bar. Oxidizer to Fuel Ratio: 3.50. Country: Russia. Status: Developed 1996-on.

Proposed variant of RD-192. Staged combustion cycle with fuel-rich gas generator. Gimbaling +/- 8 degree in two planes. Status 1998 was project based on RD-191 protoype, development estimated to take four years.

Engine Model: RD-192.3. Manufacturer Name: RD-192.3. Designer: Glushko. Developed in: 1996-. Propellants: Lox/LCH4. Thrust(vac): 2,089.000 kN (469,625 lbf). Isp: 341 sec. Isp (sea level): 311 sec. Diameter: 1.45 m (4.75 ft). Length: 3.62 m (11.87 ft). Chambers: 1. Chamber Pressure: 245.00 bar. Oxidizer to Fuel Ratio: 3.00. Country: Russia. Status: Developed 1996-on.

Proposed variant of RD-192. Gas generator cycle. Gimbaling +/- 8 degree in two planes. Status 1998 was project based on RD-191 protoype, development estimated for four years.

Engine Model: RD-192S. Manufacturer Name: RD-192S. Designer: Glushko. Developed in: 1996-. Propellants: Lox/LCH4. Thrust(vac): 2,128.000 kN (478,393 lbf). Isp: 372 sec. Diameter: 2.40 m (7.80 ft). Length: 4.82 m (15.81 ft). Chambers: 1. Chamber Pressure: 196.00 bar. Oxidizer to Fuel Ratio: 3.50. Country: Russia. Status: Developed 1996-on.

Proposed variant of RD-192. Staged combustion cycle with oxidizer-rich gas generator. Gimbaling +/- 8 degree in two planes. Status 1998 project based on RD-191 protoype, development estimated for four years.

Bibliography:

  • Klepikov, Katorgin, Chvanov, IAF-Congress Turin, 1997, "The New Generation of Rocket Engines, Operating by Ecologically Safe Propellant ...", IAF-97-S.1.03 via Dietrich Haeseler.
  • Katorgin, B; Klepikov, I, Aviapanorama, "Metanovye ZhRD NPO Energomash im. V.P. Glushko", 7-8/98, Moscow, 1998.
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