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N1F
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Part of N1 Family
N1F - 1974
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.

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

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.


More at: N1F.

Family: heavy-lift, orbital launch vehicle. Country: Russia. Engines: NK-19, 11D121, NK-39, NK-43, NK-33, RD-58. Spacecraft: L3M-1970, MKBS, L3M-1972. Stages: N1 Block G, N1 Block D, N1F Block A, N1F Block B, N1F Block V. Agency: Korolev bureau.

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