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Soyuz M-1
Part of R-7 Block A stage series Family
LOx/Kerosene propellant rocket stage. Proposed improved version. Not developed.

Status: Development ended 2000. Thrust: 872.00 kN (196,033 lbf). Gross mass: 100,500 kg (221,500 lb). Unfuelled mass: 6,000 kg (13,200 lb). Specific impulse: 336 s. Specific impulse sea level: 298 s. Burn time: 310 s. Height: 28.00 m (91.00 ft). Diameter: 2.95 m (9.67 ft). Span: 2.95 m (9.67 ft).



Country: Russia. Engines: RD-120K. Launch Vehicles: Soyuz M. Propellants: Lox/Kerosene.

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