N-IU

Russian heavy-lift orbital launch vehicle. The N-IU would be the initial production version of the N1 following the mad rush to make the lunar landings. It would have essentially the same payload but would be substantially re-engineered for sharply improved reliability, most notably with autonomously operating engines. It is interesting to note that four years before the disastrous first flight Korolev already foresaw the potential engine problems that would be the downfall of the project.

LEO Payload: 95,000 kg (209,000 lb) to a 220 km orbit at 51.60 degrees.

Stage Data - N-IU

• 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 N1U 1965 - V. Gross Mass: 193,000 kg (425,000 lb). Empty Mass: 15,000 kg (33,000 lb). Thrust (vac): 1,560.000 kN (350,700 lbf). Isp: 347 sec. Burn time: 380 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-19. Status: Study 1965. Comments: As per N1 improvement study, 1965. Primarily improved reliability and produceability compared to first model.