Encyclopedia Astronautica
N1F Sr



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N1F - Sr
N1F with Sr Lox/LH2 upper stage
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N1 Variants
N1 Launch Vehicle Family
Credit: © Mark Wade
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Blok SR
Credit: RKK Energia
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Blok SR
Credit: © Mark Wade
Russian heavy-lift orbital launch vehicle. The final more modest version of the N1F replaced the fourth and fifth stages of the N1 with the single liquid oxygen/liquid hydrogen Block Sr stage. Development of the Sr stage was from May 1971 until cancellation of the N1 project in May 1974.

Stage Data - N1F Sr

  • 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 Sr. Gross Mass: 77,900 kg (171,700 lb). Empty Mass: 11,500 kg (25,300 lb). Thrust (vac): 147.880 kN (33,245 lbf). Isp: 441 sec. Burn time: 1,910 sec. Diameter: 5.20 m (17.00 ft). Span: 5.20 m (17.00 ft). Length: 16.50 m (54.10 ft). Propellants: Lox/LH2. No Engines: 2. Engine: RD-56M. Status: Development 1974. Comments: Upper stage developed 1971-1974 to support manned lunar expedition. Replaced Blok R/Blok S previously under development. Capable of five restarts and 11 days of flight. Could insert 24 tonnes into lunar orbit or 20 tonnes into geosynch orbit.

Status: Development ended 1974.
Gross mass: 2,677,900 kg (5,903,700 lb).
Height: 94.00 m (308.00 ft).
Diameter: 10.00 m (32.00 ft).
Thrust: 38,990.00 kN (8,765,300 lbf).

More... - Chronology...


Associated Countries
Associated Engines
  • 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-56M Isayev lox/lh2 rocket engine. 73.580 kN. Proton and Angara upper stage KVRB, 12KRB upper stage for GSLV (India). In development. Isp=461s. First flight 2001. 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 Sr Lox/LH2 propellant rocket stage. Loaded/empty mass 77,900/11,500 kg. Thrust 147.88 kN. Vacuum specific impulse 441 seconds. Upper stage developed 1971-1974 to support manned lunar expedition. Replaced Blok R/Blok S previously under development. Capable of five restarts and 11 days of flight. Could insert 24 tonnes into lunar orbit or 20 tonnes into geosynch orbit. 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 Sr Chronology


1971 May - . LV Family: N1. Launch Vehicle: N1F Sr.
  • Block Sr Lox/LH2 stage development begins - . Nation: USSR. Summary: The final version of the N1M replaced the fourth and fifth stages of the N1 with the single liquid oxygen/liquid hydrogen Block Sr stage..

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