Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
N-IF 1965
Part of N1 Family
N-IF Variants
N-IF Variants
N-IF Versions, from left: N1-L3; N-IF; N-IUV-III; N-IFV-III; N-IFV-III,II
Russian heavy-lift orbital launch vehicle. The N-IF would be the first follow-on version with increased performance. The first stage engines would be increased in thrust from an average of 150 metric tons to 175 metric tons, and those in the second stage from 150 metric tons to 200 metric tons. The second and third stages would be substantially enlarged.

Status: Study 1965. Payload: 100,000 kg (220,000 lb). Thrust: 51,500.00 kN (11,577,600 lbf). Gross mass: 2,950,000 kg (6,500,000 lb). Height: 110.00 m (360.00 ft). Diameter: 17.00 m (55.00 ft). Apogee: 220 km (130 mi).

LEO Payload: 100,000 kg (220,000 lb) to a 220 km orbit at 51.60 degrees.

Stage Data - N-IF 1965

  • Stage 1. 1 x N1F 1965 - A. Gross Mass: 1,940,000 kg (4,270,000 lb). Empty Mass: 200,000 kg (440,000 lb). Thrust (vac): 57,560.000 kN (12,940,000 lbf). Isp: 331 sec. Burn time: 100 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: 11D51F. Status: Study 1965. Comments: As per N1 improvement study, 1965. Block A engine thrust increased but little additional propellant.
  • Stage 2. 1 x N1F 1965 - B. Gross Mass: 590,000 kg (1,300,000 lb). Empty Mass: 60,000 kg (132,000 lb). Thrust (vac): 15,600.000 kN (3,507,000 lbf). Isp: 346 sec. Burn time: 115 sec. Diameter: 6.80 m (22.30 ft). Span: 9.80 m (32.10 ft). Length: 26.00 m (85.00 ft). Propellants: Lox/Kerosene. No Engines: 8. Engine: 11D52F. Status: Study 1965. Comments: As per N1 improvement study, 1965. Engine thrust increased from 150 t each to 200 t and stretched propellant tanks.
  • Stage 3. 1 x N1F 1965 - V. Gross Mass: 300,000 kg (660,000 lb). Empty Mass: 20,000 kg (44,000 lb). Thrust (vac): 2,450.000 kN (550,780 lbf). Isp: 347 sec. Burn time: 380 sec. Diameter: 4.80 m (15.70 ft). Span: 6.80 m (22.30 ft). Length: 16.00 m (52.00 ft). Propellants: Lox/Kerosene. No Engines: 4. Engine: 11D53F. Status: Study 1965. Comments: As per N1 improvement study, 1965. Engine thrust increased and stretched propellant tanks with almost 50% increase.



Family: heavy-lift, orbital launch vehicle. Country: Russia. Engines: 11D51F, 11D52F, 11D53F. Stages: N1F 1965 - A, N1F 1965 - B, N1F 1965 - V. Agency: Korolev bureau.

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
© 1997-2017 Mark Wade - Contact
© / Conditions for Use