Encyclopedia Astronautica
N-IMV-III



n1mv3.jpg
N-IMV-III
Russian heavy-lift orbital launch vehicle. Then N-IMV-III would add the Block V-III cryogenic third stage to the first and second stages of the N-IM. This provided the second-highest performance of the variations considered and would certainly have been cheaper than the N-IFV-II, III.

LEO Payload: 185,000 kg (407,000 lb) to a 220 km orbit at 51.60 degrees.

Stage Data - N-IMV-III

  • Stage 1. 1 x N1M 1965 - A. Gross Mass: 3,800,000 kg (8,300,000 lb). Empty Mass: 375,000 kg (826,000 lb). Thrust (vac): 85,300.000 kN (19,176,200 lbf). Isp: 330 sec. Burn time: 130 sec. Isp(sl): 296 sec. Diameter: 10.00 m (32.00 ft). Span: 17.00 m (55.00 ft). Length: 50.00 m (164.00 ft). Propellants: Lox/Kerosene. No Engines: 30. Engine: 11D51M. Status: Study 1965. Comments: As per N1 improvement study, 1965. Huge modification of Block A, almost double propellant capacity, engines increased from 175 tonnes thrust to 250 tonnes.
  • Stage 2. 1 x N1M 1965 - B. Gross Mass: 620,000 kg (1,360,000 lb). Empty Mass: 75,000 kg (165,000 lb). Thrust (vac): 21,960.000 kN (4,936,800 lbf). Isp: 346 sec. Burn time: 85 sec. Diameter: 6.80 m (22.30 ft). Span: 9.80 m (32.10 ft). Length: 30.00 m (98.00 ft). Propellants: Lox/Kerosene. No Engines: 8. Engine: 11D52M. Status: Study 1965. Comments: As per N1 improvement study, 1965. Further stretch of Block B and thrust increased again to 280 tonnes per engine.
  • 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: 4,950,000 kg (10,910,000 lb).
Payload: 185,000 kg (407,000 lb).
Height: 145.00 m (475.00 ft).
Diameter: 17.00 m (55.00 ft).
Thrust: 74,000.00 kN (16,635,000 lbf).
Apogee: 220 km (130 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • 11D51M Kuznetsov Lox/Kerosene rocket engine. 2843 kN. N1M 1965 - A. Study 1965. As described in N1 improvement study, 1965. Huge modification of Block A engines - sea level thrust increased from 175 tonnes thrust to 250 tonnes. Isp=346s. More...
  • 11D52M Kuznetsov Lox/Kerosene rocket engine. 2745 kN. N1M 1965 - B. Study 1965. As per N1 improvement study, 1965. Thrust increased to 280 tonnes per engine. Isp=330s. 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...
  • N1M 1965 - A Lox/Kerosene propellant rocket stage. Loaded/empty mass 3,800,000/375,000 kg. Thrust 85,300.00 kN. Vacuum specific impulse 330 seconds. As per N1 improvement study, 1965. Huge modification of Block A, almost double propellant capacity, engines increased from 175 tonnes thrust to 250 tonnes. More...
  • N1M 1965 - B Lox/Kerosene propellant rocket stage. Loaded/empty mass 620,000/75,000 kg. Thrust 21,960.00 kN. Vacuum specific impulse 346 seconds. As per N1 improvement study, 1965. Further stretch of Block B and thrust increased again to 280 tonnes per engine. More...

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