N11 1963

Russian heavy-lift orbital launch vehicle. A military variant of the N-11 which would use a powerful third stage, probably derived from the first stage of the 8K713 GR-1, to put up to 24 metric tons in low earth orbit. This was a competitor with Chelomei's UR-500K, which was selected instead for the heavy military payload mission.

LEO Payload: 24,000 kg (52,000 lb) to a 300 km orbit at 51.60 degrees.

Stage Data - N-11 1963

• Stage 1. 1 x N-11 Block A. Gross Mass: 485,000 kg (1,069,000 lb). Empty Mass: 47,000 kg (103,000 lb). Thrust (vac): 11,960.000 kN (2,688,710 lbf). Isp: 330 sec. Burn time: 117 sec. Isp(sl): 293 sec. Diameter: 6.80 m (22.30 ft). Span: 9.80 m (32.10 ft). Length: 20.00 m (65.00 ft). Propellants: Lox/Kerosene. No Engines: 8. Engine: NK-15V. Status: Study 1963. Comments: Derived from N1 Block B, with large number of engines and expansion ratio adjusted for sea level operation. Includes 3500 kg Stage 2-Stage 3 interstage.

• Stage 2. 1 x N-11 Block B. Gross Mass: 192,000 kg (423,000 lb). Empty Mass: 18,000 kg (39,000 lb). Thrust (vac): 1,560.000 kN (350,700 lbf). Isp: 347 sec. Burn time: 372 sec. Diameter: 4.80 m (15.70 ft). Span: 6.80 m (22.30 ft). Length: 12.00 m (39.00 ft). Propellants: Lox/Kerosene. No Engines: 8. Engine: NK-19. Status: Study 1963. Comments: Derived from N1 Block V.

• Stage 3. 1 x N-11 1963 - V. Gross Mass: 70,000 kg (154,000 lb). Empty Mass: 6,000 kg (13,200 lb). Thrust (vac): 784.000 kN (176,250 lbf). Isp: 347 sec. Burn time: 273 sec. Diameter: 2.68 m (8.79 ft). Span: 2.68 m (8.79 ft). Length: 18.00 m (59.00 ft). Propellants: Lox/Kerosene. No Engines: 4. Engine: NK-19. Status: Study 1963. Comments: Conjectural stage derived from GR-1 stage 1 to match total mass given of launch vehicle.