N1F
Launch vehicle · Russia
Original archive entry. The text, images and links below are kept as they were written.
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. 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.
Related
- Family
- heavy-lift, orbital launch vehicle
- Country
- Russia
- Stages
- N1 Block G, N1 Block D, N1F Block A, N1F Block B, N1F Block V
- Agency
- Korolev bureau
Chronology
4 events
1970 June
LV Family: N1. Launch Vehicle: N1F.- Development of engines for N1F authorised - .
Nation: Russia.
Spacecraft Bus: L3M.
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: Russia. Spacecraft Bus: L3M. Spacecraft: L3M-1972. 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: Russia. Spacecraft Bus: OS. Spacecraft: MKBS. Decree 'On work on the technical proposal for the creation of the MOK' was issued..