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-IUV-III
Part of N1 Family
N-IUV-III
N-IUV-III
Russian heavy-lift orbital launch vehicle. The N-IUV-III would replace the N-IU's conventional third stage with a LOX/LH2 cryogenic third stage. This was seen at the time as the first step in exploitation of cryogenic technology in Russia. Although pursued for some time, this large stage never went into development. The more modestly-sized Block R, Block S, and Block SR instead were put into development in the early 1970's.

Status: Study 1965. Payload: 115,000 kg (253,000 lb). Thrust: 44,000.00 kN (9,891,000 lbf). Gross mass: 2,900,000 kg (6,300,000 lb). Height: 120.00 m (390.00 ft). Diameter: 17.00 m (55.00 ft). Apogee: 220 km (130 mi).

LEO Payload: 115,000 kg (253,000 lb) to a 220 km orbit at 51.60 degrees.

Stage Data - N-IUV-III

  • Stage 1. 1 x N1U 1965 - A. Gross Mass: 1,934,000 kg (4,263,000 lb). Empty Mass: 195,000 kg (429,000 lb). Thrust (vac): 49,420.000 kN (11,110,050 lbf). Isp: 331 sec. Burn time: 110 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: NK-15. Status: Study 1965. Comments: As per N1 improvement study, 1965. Primarily improved reliability and produceability compared to first model.
  • Stage 2. 1 x N1U 1965 - B. Gross Mass: 506,000 kg (1,115,000 lb). Empty Mass: 50,000 kg (110,000 lb). Thrust (vac): 13,700.000 kN (3,079,800 lbf). Isp: 346 sec. Burn time: 110 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-15V. Status: Study 1965. Comments: As per N1 improvement study, 1965. Primarily improved reliability and produceability compared to first model.
  • Stage 3. 1 x N1 Block V-III. Gross Mass: 325,000 kg (716,000 lb). Empty Mass: 35,000 kg (77,000 lb). Thrust (vac): 2,350.000 kN (528,300 lbf). Isp: 440 sec. Burn time: 510 sec. Diameter: 8.00 m (26.20 ft). Span: 8.00 m (26.20 ft). Length: 27.00 m (88.00 ft). Propellants: Lox/LH2. No Engines: 6. Engine: RD-57. Status: Study 1965. Comments: N1 improvement study, 1965. Lox/LH2 replacement for Block V third stage. Pursued into 1966 and later, but later efforts concentrated on Block S, R, and SR cryogenic stages.



Family: heavy-lift, orbital launch vehicle. Country: Russia. Engines: RD-57, NK-15V, NK-15. Stages: N1 Block V-III, N1U 1965 - A, N1U 1965 - B. 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