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S1
LOx/UDMH propellant rocket stage. .

Status: Out of production. Thrust: 105.51 kN (23,720 lbf). Gross mass: 8,595 kg (18,948 lb). Unfuelled mass: 840 kg (1,850 lb). Specific impulse: 352 s. Specific impulse sea level: 220 s. Burn time: 250 s. Height: 7.80 m (25.50 ft). Diameter: 1.60 m (5.20 ft). Span: 1.60 m (5.20 ft).

Cost $ : 3.000 million.

Subtopics

S1.35800 Korolev LOx/Kerosene rocket engine. R-7 verniers. Out of Production. Thrust variable 2.5-3.1 metric tons

RD-0105 Kosberg LOx/Kerosene rocket engine. Luna 8K72, Vostok 8K72 upper stage. Out of production. Developed jointly with OKB-1 in nine months on the basis of OKB-1's steering chamber from the RD-107 engine. First flight 1958.

RD-0109 Kosberg LOx/Kerosene rocket engine. 8A92 Vostok stage 3, 8K72K stage 3 (block E-Vostok). Out of production. Developed in 15 months. First flight 1960.

S1.5400A Korolev LOx/Kerosene rocket engine. Molniya 8K78M-3. First flight 1964.

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.

8D726 Korolev LOx/Kerosene rocket engine. GR-1 Stage 3, N-11GR - V. Development based on S1.5400.

Country: Ukraine. Engines: RD-119. Launch Vehicles: Kosmos 63S1, Kosmos 11K63, Kosmos 63S1M. Propellants: Lox/UDMH. More at: 11721.

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