Encyclopedia Astronautica
N-IFV-III



n1fv2.jpg
N1FV-III
N-IFV-III design of 1965
Russian heavy-lift orbital launch vehicle. Then N-IFV-III would add the Block V-III cryogenic third stage to the first and second stages of the N-IF.

LEO Payload: 125,000 kg (275,000 lb) to a 220 km orbit at 51.60 degrees.

Stage Data - N-IFV-III

  • Stage 1. 1 x N1F 1965 - A. Gross Mass: 1,940,000 kg (4,270,000 lb). Empty Mass: 200,000 kg (440,000 lb). Thrust (vac): 57,560.000 kN (12,940,000 lbf). Isp: 331 sec. Burn time: 100 sec. Isp(sl): 296 sec. Diameter: 10.00 m (32.00 ft). Span: 17.00 m (55.00 ft). Length: 30.00 m (98.00 ft). Propellants: Lox/Kerosene. No Engines: 30. Engine: 11D51F. Status: Study 1965. Comments: As per N1 improvement study, 1965. Block A engine thrust increased but little additional propellant.
  • Stage 2. 1 x N1F 1965 - B. Gross Mass: 590,000 kg (1,300,000 lb). Empty Mass: 60,000 kg (132,000 lb). Thrust (vac): 15,600.000 kN (3,507,000 lbf). Isp: 346 sec. Burn time: 115 sec. Diameter: 6.80 m (22.30 ft). Span: 9.80 m (32.10 ft). Length: 26.00 m (85.00 ft). Propellants: Lox/Kerosene. No Engines: 8. Engine: 11D52F. Status: Study 1965. Comments: As per N1 improvement study, 1965. Engine thrust increased from 150 t each to 200 t and stretched propellant tanks.
  • Stage 3. 1 x N1 Block V-III. Gross Mass: 325,000 kg (716,000 lb). Empty Mass: 35,000 kg (77,000 lb). Thrust (vac): 2,350.000 kN (528,300 lbf). Isp: 440 sec. Burn time: 510 sec. Diameter: 8.00 m (26.20 ft). Span: 8.00 m (26.20 ft). Length: 27.00 m (88.00 ft). Propellants: Lox/LH2. No Engines: 6. Engine: RD-57. Status: Study 1965. Comments: N1 improvement study, 1965. Lox/LH2 replacement for Block V third stage. Pursued into 1966 and later, but later efforts concentrated on Block S, R, and SR cryogenic stages.

Status: Study 1965.
Gross mass: 3,000,000 kg (6,600,000 lb).
Payload: 125,000 kg (275,000 lb).
Height: 125.00 m (410.00 ft).
Diameter: 17.00 m (55.00 ft).
Thrust: 51,500.00 kN (11,577,600 lbf).
Apogee: 220 km (130 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • 11D51F Kuznetsov Lox/Kerosene rocket engine. 1918 kN. N1F 1965 - A. Study 1965. As described in N1 improvement study, 1965. Block A engine thrust increased. Isp=331s. More...
  • 11D52F Kuznetsov Lox/Kerosene rocket engine. 1961 kN. N1F 1965 - B. Study 1965. As per N1 improvement study, 1965. Engine thrust increased from 150 t each to 200 t. Isp=347s. More...
  • RD-57 Lyulka lox/lh2 rocket engine. 392 kN. N1 Block S (N-1M). Study 1965. One to have been used in N1 Block S. In fixed chamber version, 3 to 6 to have been used in N1 Block V-III. Engine system includes roll control thruster with 1.29 kN thrust. Isp=456s. 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
  • N1 Block V-III Lox/LH2 propellant rocket stage. Loaded/empty mass 325,000/35,000 kg. Thrust 2,350.00 kN. Vacuum specific impulse 440 seconds. N1 improvement study, 1965. Lox/LH2 replacement for Block V third stage. Pursued into 1966 and later, but later efforts concentrated on Block S, R, and SR cryogenic stages. More...
  • N1F 1965 - B Lox/Kerosene propellant rocket stage. Loaded/empty mass 590,000/60,000 kg. Thrust 15,600.00 kN. Vacuum specific impulse 346 seconds. As per N1 improvement study, 1965. Engine thrust increased from 150 t each to 200 t and stretched propellant tanks. More...
  • N1F 1965 - A Lox/Kerosene propellant rocket stage. Loaded/empty mass 1,940,000/200,000 kg. Thrust 57,560.00 kN. Vacuum specific impulse 331 seconds. As per N1 improvement study, 1965. Block A engine thrust increased but little additional propellant. More...

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