Encyclopedia Astronautica
N111



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N-III 1962
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N-III 1962
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N1 Variants
N1 Launch Vehicle Family
Credit: © Mark Wade
Russian heavy-lift orbital launch vehicle. It was originally planned the N1 would form the basis of a family of launch vehicles that could replace existing ICBM-derived boosters. The N111 would use the third and fourth stages of the N1, and the second stage of Korolev's R-9 ICBM. This would result in a lift-off mass of 200 tonnes and a five tonne payload. It could replace the R-7 derived boosters (Vostok and Soyuz) in this payload category.

LEO Payload: 5,000 kg (11,000 lb) to a 300 km orbit at 51.60 degrees.

Stage Data - N-111

  • Stage 1. 1 x N-111 - A. Gross Mass: 192,000 kg (423,000 lb). Empty Mass: 20,000 kg (44,000 lb). Thrust (vac): 2,540.000 kN (571,010 lbf). Isp: 331 sec. Burn time: 216 sec. Isp(sl): 296 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: 12. Engine: NK-19. Status: Study 1963. Comments: Variant of N1 Block V for first stage use. Number of engines would have to be increased and reduced expansion ratio nozzles fitted for sea level use. Least attractive of N1 variants and seems not to have been pursued after draft project.
  • Stage 2. 1 x N-11GR - V. Gross Mass: 8,200 kg (18,000 lb). Empty Mass: 1,700 kg (3,700 lb). Thrust (vac): 88.200 kN (19,828 lbf). Isp: 346 sec. Burn time: 246 sec. Diameter: 2.40 m (7.80 ft). Span: 2.40 m (7.80 ft). Length: 5.00 m (16.40 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: 8D726. Status: Study 1963. Comments: Orbital MIRV stage. Six of these stages clustered around Block B; each stage would have had a 1500 kg nuclear warhead.

AKA: 11A54; 11K54.
Status: Study 1962.
Gross mass: 215,900 kg (475,900 lb).
Payload: 5,000 kg (11,000 lb).
Height: 33.00 m (108.00 ft).
Diameter: 4.80 m (15.70 ft).
Thrust: 2,325.50 kN (522,793 lbf).
Apogee: 300 km (180 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • 8D726 Korolev Lox/Kerosene rocket engine. 66.7 kN. GR-1 Stage 3, N-11GR - V. Development based on S1.5400. Isp=350s. 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-11GR - V Lox/Kerosene propellant rocket stage. Loaded/empty mass 8,200/1,700 kg. Thrust 88.20 kN. Vacuum specific impulse 346 seconds. Orbital MIRV stage. Six of these stages clustered around Block B; each stage would have had a 1500 kg nuclear warhead. More...
  • N-111-A Lox/Kerosene propellant rocket stage. Loaded/empty mass 192,000/20,000 kg. Thrust 2,540.00 kN. Vacuum specific impulse 331 seconds. Variant of N1 Block V for first stage use. Number of engines would have to be increased and reduced expansion ratio nozzles fitted for sea level use. Least attractive of N1 variants and seems not to have been pursued after draft project. More...

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