Encyclopedia Astronautica
N1F



n1f1974.jpg
N1F - 1974
N1F - 1974 Configuration (N1 s/n 8L)
Russian heavy-lift orbital launch vehicle. The N1F would have been the definitive flight version of the N1, incorporating all changes resulting from the four flight tests of the vehicle, including the new Kuznetsov engines and 10% greater liftoff mass by using superchilled propellants in all stages. N1 8L would have been the first N1F configuration flight, with launch planned in the third quarter of 1975 at the time the project was cancelled.

LEO Payload: 105,000 kg (231,000 lb) to a 220 km orbit at 51.60 degrees.

Stage Data - N1F

  • Stage 1. 1 x N1F Block A. Gross Mass: 2,070,000 kg (4,560,000 lb). Empty Mass: 126,230 kg (278,280 lb). Thrust (vac): 49,675.500 kN (11,167,497 lbf). Isp: 331 sec. Burn time: 125 sec. Isp(sl): 297 sec. Diameter: 10.00 m (32.00 ft). Span: 15.60 m (51.10 ft). Length: 30.00 m (98.00 ft). Propellants: Lox/Kerosene. No Engines: 30. Engine: NK-33. Status: In Production. Comments: Includes 14,000 kg for Stage 1-2 interstage.
  • Stage 2. 1 x N1F Block B. Gross Mass: 620,000 kg (1,360,000 lb). Empty Mass: 55,700 kg (122,700 lb). Thrust (vac): 14,040.004 kN (3,156,318 lbf). Isp: 346 sec. Burn time: 120 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-43. Status: In Production. Comments: Includes 3,500 kg for Stage 2-3 interstage.
  • Stage 3. 1 x N1F Block V. Gross Mass: 210,000 kg (460,000 lb). Empty Mass: 13,700 kg (30,200 lb). Thrust (vac): 1,608.000 kN (361,492 lbf). Isp: 353 sec. Burn time: 370 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-39. Status: In Production.
  • Stage 4. 1 x N1 Block G. Gross Mass: 61,800 kg (136,200 lb). Empty Mass: 6,000 kg (13,200 lb). Thrust (vac): 445.996 kN (100,264 lbf). Isp: 353 sec. Burn time: 443 sec. Diameter: 4.40 m (14.40 ft). Span: 4.40 m (14.40 ft). Length: 9.10 m (29.80 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: NK-19. Status: Out of Production. Comments: Empty mass estimated.
  • Stage 5. 1 x N1 Block D. Gross Mass: 18,200 kg (40,100 lb). Empty Mass: 3,500 kg (7,700 lb). Thrust (vac): 83.300 kN (18,727 lbf). Isp: 349 sec. Burn time: 600 sec. Isp(sl): 0.0000 sec. Diameter: 2.90 m (9.50 ft). Span: 2.90 m (9.50 ft). Length: 5.70 m (18.70 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-58. Status: Out of Production. Comments: Block D adapted as lunar crasher stage.

Status: Development ended 1974.
Gross mass: 3,025,000 kg (6,668,000 lb).
Payload: 105,000 kg (231,000 lb).
Height: 105.00 m (344.00 ft).
Diameter: 17.00 m (55.00 ft).
Thrust: 44,400.00 kN (9,981,500 lbf).
Apogee: 220 km (130 mi).

More... - Chronology...


Associated Countries
Associated Spacecraft
  • L3M-1972 Russian manned lunar lander. Study 1972. Revised L3M design of the L3M lunar lander for use with the Block Sr crasher stage. The Soyuz return capsule was completely enclosed in a pressurized 'hangar'. More...

Associated Engines
  • 11D121 Korolev GOX/Kerosene rocket engine. 68.650 kN. N-1 stage 1 (block A) roll control engine. Developed 1969-74. Gimbaling +/- 45 degree. Propellants are fed from main engine (NK-15, NK-33) turbopumps. Isp=313s. Chamber Pressure: 71.60 bar. 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-33 Kuznetsov Lox/Kerosene rocket engine. 1638 kN. N-1F, Kistler stage 1, Taurus II stage 1. Isp=331s. Modified version of original engine with multiple ignition capability. Never flown and mothballed in 1975 after the cancellation of the N1. Resurrected for Kistler, then for Taurus. More...
  • NK-39 Kuznetsov Lox/Kerosene rocket engine. 402 kN. N-1F stage 3. Development ended 1971. Isp=352s. Modified version of original engine with multiple ignition capability. Never flown and mothballed after the cancellation of the N1. More...
  • NK-43 Kuznetsov Lox/Kerosene rocket engine. 1755 kN. N-1F, Kistler stage 2. Design 1975. Isp=346s. Modified version of original engine with multiple ignition capability. Never flown and mothballed after the cancellation of the N1. Resurrected for Kistler. More...
  • RD-58 Korolev Lox/Kerosene rocket engine. 83.4 kN. Isp=349s. High-performance upper-stage engine developed for N1 lunar crasher stage, but saw general use as restartable Block D upper stage of Proton launch vehicle. First flight 1967. 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 G Lox/Kerosene propellant rocket stage. Loaded/empty mass 61,800/6,000 kg. Thrust 446.00 kN. Vacuum specific impulse 353 seconds. Empty mass estimated. More...
  • N1 Block D Lox/Kerosene propellant rocket stage. Loaded/empty mass 18,200/3,500 kg. Thrust 83.30 kN. Vacuum specific impulse 349 seconds. Block D as originally designed as a lunar crasher stage More...
  • N1F Block A Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,070,000/126,230 kg. Thrust 49,675.50 kN. Vacuum specific impulse 331 seconds. Includes 14,000 kg for Stage 1-2 interstage. More...
  • N1F Block B Lox/Kerosene propellant rocket stage. Loaded/empty mass 620,000/55,700 kg. Thrust 14,040.00 kN. Vacuum specific impulse 346 seconds. Includes 3,500 kg for Stage 2-3 interstage. More...
  • N1F Block V Lox/Kerosene propellant rocket stage. Loaded/empty mass 210,000/13,700 kg. Thrust 1,608.00 kN. Vacuum specific impulse 353 seconds. More...

N1F Chronology


1970 June - . LV Family: N1. Launch Vehicle: N1F.
  • Development of engines for N1F authorised - . Nation: USSR. Spacecraft: L3M-1970. Full go-ahead to develop a liquid hydrogen/liquid oxygen high energy upper stage for the N1F. The multi-engine Block Sr would have a propellant mass of 66.4 tonnes. In July Kuznetsov was given authorisation to design substantially improved versions of the N1 lower stage rocket engines. The N1 that would utilise these engines was designated the N1F and would have a payload to a 225 km orbit of 105,000 kg.

1972 February 16 - . LV Family: N1. Launch Vehicle: N1F.
  • N1-L3M moon landing draft project work authorised. - . Nation: USSR. Spacecraft: L3M-1972. Summary: Military-Industrial Commission (VPK) Decree 'On approval of work on the draft project for the N1-L3M two-launch lunar landing proposal' was issued..

1972 February 23 - . LV Family: N1. Launch Vehicle: N1F.
  • MOK technical proposal authorised. - . Nation: USSR. Spacecraft: MKBS. Summary: Decree 'On work on the technical proposal for the creation of the MOK' was issued..

1972 May 15 - . LV Family: N1. Launch Vehicle: N1F.
  • N1-L3M development authorised. - . Nation: USSR. Spacecraft: L3M-1972. Summary: Council of Chief Designers Decree 'On approval of the N1-L3M proposal' was issued..

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