| N1 Block A |
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First stage of the N1 superbooster. As per draft project for N1-L3, 1964. Block A modified with six additional engines and propellant increased by 550 tonnes by using chilled propellants. Model: N1 1962 - A. Gross Mass: 1,384,000 kg (3,051,000 lb). Empty Mass: 117,000 kg (257,000 lb). Thrust (vac): 39,420.000 kN (8,861,960 lbf). Isp: 331 sec. Burn time: 103 sec. Propellants: Lox/Kerosene. 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). Country: Russia. No Engines: 24. Motor: NK-15. Status: Study 1963. First Flight: 1962. Last Flight: 1964. No Launched: 2. Earlier design for the Block A. Includes 14,000 kg for Stage 1-2 interstage and payload fairing. Compared to total fuelled mass excludes 15,000 kg propellant expended in thrust build-up and boil-off prior to liftoff. Values as in draft project as defended on 2-16 July 1962. Model: 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. Propellants: Lox/Kerosene. 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). Country: Russia. No Engines: 30. Motor: NK-15. Status: Study 1965. As per N1 improvement study, 1965. Primarily improved reliability and produceability compared to first model. Model: 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. Propellants: Lox/Kerosene. 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). Country: Russia. No Engines: 30. Motor: 11D51F. Status: Study 1965. As per N1 improvement study, 1965. Block A engine thrust increased but little additional propellant. Model: N1M 1965 - A. Gross Mass: 3,800,000 kg (8,300,000 lb). Empty Mass: 375,000 kg (826,000 lb). Thrust (vac): 85,300.000 kN (19,176,200 lbf). Isp: 330 sec. Burn time: 130 sec. Propellants: Lox/Kerosene. Isp(sl): 296 sec. Diameter: 10.00 m (32.00 ft). Span: 17.00 m (55.00 ft). Length: 50.00 m (164.00 ft). Country: Russia. No Engines: 30. Motor: 11D51M. Status: Study 1965. As per N1 improvement study, 1965. Huge modification of Block A, almost double propellant capacity, engines increased from 175 tonnes thrust to 250 tonnes. Model: N1 Block A. Gross Mass: 1,880,000 kg (4,140,000 lb). Empty Mass: 130,000 kg (280,000 lb). Thrust (vac): 50,300.000 kN (11,307,800 lbf). Isp: 330 sec. Burn time: 125 sec. Propellants: Lox/Kerosene. Isp(sl): 284 sec. Diameter: 10.30 m (33.70 ft). Span: 16.90 m (55.40 ft). Length: 30.10 m (98.70 ft). Country: Russia. No Engines: 30. Motor: NK-15. Status: Retired 1972. First Flight: 1967. Last Flight: 1972. No Launched: 6. No Failed: 4. Includes 14,000 kg for Stage 1-2 interstage and payload fairing. Compared to total fuelled mass excludes 15,000 kg propellant expended in thrust build-up and boil-off prior to liftoff. Values as in draft project as defended on 2-16 July 1962. Model: 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. Propellants: Lox/Kerosene. 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). Country: Russia. No Engines: 30. Motor: NK-33. Status: Development ended 1974. First Flight: 1970. Last Flight: 1973. No Launched: 6. Includes 14,000 kg for Stage 1-2 interstage. Used on Launch Vehicles:
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