N1 Block B

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Model: N1 1964 - 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: 106 sec. Propellants: Lox/Kerosene. Diameter: 6.80 m (22.30 ft). Span: 9.80 m (32.10 ft). Length: 20.00 m (65.00 ft). Country: Russia. No Engines: 8. Motor: NK-15V. Status: Development ended 1964. First Flight: 1963. Last Flight: 1965. No Launched: 4.

Second stage of the N1 superbooster. As per draft project for N1-L3, 1964. Specific impulse estimate down one second from 1962 draft project. Thrust said to be increased 2% but not reflected in figures given.

Model: N-11 Block A. Gross Mass: 485,000 kg (1,069,000 lb). Empty Mass: 47,000 kg (103,000 lb). Thrust (vac): 11,960.000 kN (2,688,710 lbf). Isp: 330 sec. Burn time: 117 sec. Propellants: Lox/Kerosene. Isp(sl): 293 sec. Diameter: 6.80 m (22.30 ft). Span: 9.80 m (32.10 ft). Length: 20.00 m (65.00 ft). Country: Russia. No Engines: 8. Motor: NK-15V. Status: Study 1963.

Derived from N1 Block B, with large number of engines and expansion ratio adjusted for sea level operation. Includes 3500 kg Stage 2-Stage 3 interstage.

Model: N1 1962 - B. Gross Mass: 506,000 kg (1,115,000 lb). Empty Mass: 50,000 kg (110,000 lb). Thrust (vac): 13,778.000 kN (3,097,417 lbf). Isp: 347 sec. Burn time: 106 sec. Propellants: Lox/Kerosene. Diameter: 6.80 m (22.30 ft). Span: 9.80 m (32.10 ft). Length: 20.00 m (65.00 ft). Country: Russia. No Engines: 8. Motor: NK-15V. Status: Study 1962. First Flight: 1964. Last Flight: 1964. No Launched: 2.

Includes 3500 kg Stage 2-Stage 3 interstage. Compared to total fuelled mass excludes 1,000 kg in propellants lost to boil-off prior to stage ignition. Values as in draft project as defended on 2-16 July 1962.

Model: 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. Propellants: Lox/Kerosene. Diameter: 6.80 m (22.30 ft). Span: 9.80 m (32.10 ft). Length: 20.00 m (65.00 ft). Country: Russia. No Engines: 8. Motor: NK-15V. Status: Study 1965.

As per N1 improvement study, 1965. Primarily improved reliability and produceability compared to first model.

Model: 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. Propellants: Lox/Kerosene. Diameter: 6.80 m (22.30 ft). Span: 9.80 m (32.10 ft). Length: 26.00 m (85.00 ft). Country: Russia. No Engines: 8. Motor: 11D52F. Status: Study 1965.

As per N1 improvement study, 1965. Engine thrust increased from 150 t each to 200 t and stretched propellant tanks.

Model: N1M 1965 - B. Gross Mass: 620,000 kg (1,360,000 lb). Empty Mass: 75,000 kg (165,000 lb). Thrust (vac): 21,960.000 kN (4,936,800 lbf). Isp: 346 sec. Burn time: 85 sec. Propellants: Lox/Kerosene. Diameter: 6.80 m (22.30 ft). Span: 9.80 m (32.10 ft). Length: 30.00 m (98.00 ft). Country: Russia. No Engines: 8. Motor: 11D52M. Status: Study 1965.

As per N1 improvement study, 1965. Further stretch of Block B and thrust increased again to 280 tonnes per engine.

Model: N1 Block B. Gross Mass: 560,700 kg (1,236,100 lb). Empty Mass: 55,700 kg (122,700 lb). Thrust (vac): 14,039.980 kN (3,156,313 lbf). Isp: 346 sec. Burn time: 120 sec. Propellants: Lox/Kerosene. Diameter: 6.80 m (22.30 ft). Span: 9.80 m (32.10 ft). Length: 20.50 m (67.20 ft). Country: Russia. No Engines: 8. Motor: NK-15V. Status: Retired 1972. First Flight: 1969. Last Flight: 1972. No Launched: 4.

Model: 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. Propellants: Lox/Kerosene. Diameter: 6.80 m (22.30 ft). Span: 9.80 m (32.10 ft). Length: 20.00 m (65.00 ft). Country: Russia. No Engines: 8. Motor: NK-43. Status: Development ended 1974. First Flight: 1970. Last Flight: 1973. No Launched: 6.

Includes 3,500 kg for Stage 2-3 interstage.

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