Encyclopedia Astronautica
N11 1963



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N2
Credit: © Mark Wade
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 tonnes 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.

AKA: 11A53.
Status: Study 1963.
Gross mass: 770,000 kg (1,690,000 lb).
Payload: 24,000 kg (52,000 lb).
Height: 60.00 m (196.00 ft).
Diameter: 9.80 m (32.10 ft).
Thrust: 10,610.00 kN (2,385,220 lbf).
Apogee: 300 km (180 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • NK-15V Kuznetsov Lox/Kerosene rocket engine. 1648 kN. Development ended 1964. Isp=325s. Developed from the NK-9. 8 engines, featuring high-expansion nozzles, used on N1 Stage 2. First flight 1969. More...
  • NK-19 Kuznetsov Lox/Kerosene rocket engine. N-1 stage 4. Development ended 1964. Based on NK-9 engine. Originally developed for the modernized second stage of the R-9 (abandoned). Also to have been used on GR-1 / 8K713 Stage 2. First flight 1969. More...

See also
  • N1 The N1 launch vehicle, developed by Russia in the 1960's, was to be the Soviet Union's counterpart to the Saturn V. The largest of a family of launch vehicles that were to replace the ICBM-derived launchers then in use, the N series was to launch Soviet cosmonauts to the moon, Mars, and huge space stations into orbit. In comparison to Saturn, the project was started late, starved of funds and priority, and dogged by political and technical struggles between the chief designers Korolev, Glushko, and Chelomei. The end result was four launch failures and cancellation of the project five years after Apollo landed on the moon. Not only did a Soviet cosmonaut never land on the moon, but the Soviet Union even denied that the huge project ever existed. More...

Associated Manufacturers and Agencies
  • Korolev Russian manufacturer of rockets, spacecraft, and rocket engines. Korolev Design Bureau, Kaliningrad, Russia. More...

Associated Stages
  • N-11 Block B Lox/Kerosene propellant rocket stage. Loaded/empty mass 192,000/18,000 kg. Thrust 1,560.00 kN. Vacuum specific impulse 347 seconds. Derived from N1 Block V. More...
  • N-11 1963 - V Lox/Kerosene propellant rocket stage. Loaded/empty mass 70,000/6,000 kg. Thrust 784.00 kN. Vacuum specific impulse 347 seconds. Conjectural stage derived from GR-1 stage 1 to match total mass given of launch vehicle. More...
  • N-11 Block A Lox/Kerosene propellant rocket stage. Loaded/empty mass 485,000/47,000 kg. Thrust 11,960.00 kN. Vacuum specific impulse 330 seconds. 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. More...

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