Encyclopedia Astronautica
N-IU



n119642.jpg
N1-L3 - 1964
N1-L3 as per advanced project, 1964
Russian heavy-lift orbital launch vehicle. The N-IU would be the initial production version of the N1 following the mad rush to make the lunar landings. It would have essentially the same payload but would be substantially re-engineered for sharply improved reliability, most notably with autonomously operating engines. It is interesting to note that four years before the disastorous first flight Korolev already foresaw the potential engine problems that would be the downfall of the project.

LEO Payload: 95,000 kg (209,000 lb) to a 220 km orbit at 51.60 degrees.

Stage Data - N-IU

  • Stage 1. 1 x N1U 1965 - A. Gross Mass: 1,934,000 kg (4,263,000 lb). Empty Mass: 195,000 kg (429,000 lb). Thrust (vac): 49,420.000 kN (11,110,050 lbf). Isp: 331 sec. Burn time: 110 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: NK-15. Status: Study 1965. Comments: As per N1 improvement study, 1965. Primarily improved reliability and produceability compared to first model.
  • Stage 2. 1 x N1U 1965 - B. Gross Mass: 506,000 kg (1,115,000 lb). Empty Mass: 50,000 kg (110,000 lb). Thrust (vac): 13,700.000 kN (3,079,800 lbf). Isp: 346 sec. Burn time: 110 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 1965. Comments: As per N1 improvement study, 1965. Primarily improved reliability and produceability compared to first model.
  • Stage 3. 1 x N1U 1965 - V. Gross Mass: 193,000 kg (425,000 lb). Empty Mass: 15,000 kg (33,000 lb). Thrust (vac): 1,560.000 kN (350,700 lbf). Isp: 347 sec. Burn time: 380 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: 4. Engine: NK-19. Status: Study 1965. Comments: As per N1 improvement study, 1965. Primarily improved reliability and produceability compared to first model.

Status: Study 1965.
Gross mass: 2,750,000 kg (6,060,000 lb).
Payload: 95,000 kg (209,000 lb).
Height: 105.00 m (344.00 ft).
Diameter: 17.00 m (55.00 ft).
Thrust: 44,000.00 kN (9,891,000 lbf).
Apogee: 220 km (130 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • NK-15 Kuznetsov Lox/Kerosene rocket engine. 1544 kN. N-1 stage 1 (block A). Development ended 1964. On the basis of NK-9 the NK-15 was developed for the N-1 launcher. 30 were used on the Block A (Stage 1) of the N-1. Isp=318s. 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...
  • 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...

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
  • N1U 1965 - A Lox/Kerosene propellant rocket stage. Loaded/empty mass 1,934,000/195,000 kg. Thrust 49,420.00 kN. Vacuum specific impulse 331 seconds. As per N1 improvement study, 1965. Primarily improved reliability and produceability compared to first model. More...
  • N1U 1965 - B Lox/Kerosene propellant rocket stage. Loaded/empty mass 506,000/50,000 kg. Thrust 13,700.00 kN. Vacuum specific impulse 346 seconds. As per N1 improvement study, 1965. Primarily improved reliability and produceability compared to first model. More...
  • N1U 1965 - V Lox/Kerosene propellant rocket stage. Loaded/empty mass 193,000/15,000 kg. Thrust 1,560.00 kN. Vacuum specific impulse 347 seconds. As per N1 improvement study, 1965. Primarily improved reliability and produceability compared to first model. More...

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