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N1 Block A

NK-15 / 11D51

NK-15 / 11D51
NK-15 / 11D51 rocket engine for first stage of N1
Credit: © Mark Wade

LOx/Kerosene propellant rocket stage. 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.

Status: Retired 1972. Thrust: 50,300.00 kN (11,307,800 lbf). Gross mass: 1,880,000 kg (4,140,000 lb). Unfuelled mass: 130,000 kg (280,000 lb). Specific impulse: 330 s. Specific impulse sea level: 284 s. Burn time: 125 s. Height: 30.10 m (98.70 ft). Diameter: 10.30 m (33.70 ft). Span: 16.90 m (55.40 ft).

No Engines: 30.

Subtopics

Superraket Block A LOx/Kerosene propellant rocket stage. Ancestor of N1 Block A; conical liquid oxygen/kerosene stage using massive cluster of Kuznetsov engines. Gross mass estimated based on 2,000 metric ton total vehicle weight; empty mass estimated.

N1 1962 - A LOx/Kerosene propellant rocket stage. 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.

N1 1964 - A LOx/Kerosene propellant rocket stage. 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 metric tons by using chilled propellants.

N1F 1965 - A LOx/Kerosene propellant rocket stage. As per N1 improvement study, 1965. Block A engine thrust increased but little additional propellant.

N1U 1965 - A LOx/Kerosene propellant rocket stage. As per N1 improvement study, 1965. Primarily improved reliability and produceability compared to first model.

N1M 1965 - A LOx/Kerosene propellant rocket stage. As per N1 improvement study, 1965. Huge modification of Block A, almost double propellant capacity, engines increased from 175 metric tons thrust to 250 metric tons.

N1-MOK stage Air/LOx/LH2 propellant rocket stage. Ultimate derivative of N1 Block A: Propellants changed to LH2/LOX, 16 x modified NK-33 engines + 4 Liquid Air Cycle Engine Liquid Air/LH2 boosters. All figures estimated based on tank volume of Block A and delivery of 90,000 kg payload to 400 kg MKBS orb

N1F Block A LOx/Kerosene propellant rocket stage. Includes 14,000 kg for Stage 1-2 interstage.

Country: Russia. Engines: NK-15. Launch Vehicles: N1M, N1, N1 1969. Propellants: Lox/Kerosene.
Photo Gallery

NK15 engineNK15 engine
NK-15 / 11D51 rocket engine for first stage of N1
Credit: © Mark Wade



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