N1M 1974 - N1M of 1974 3,951 bytes. 60 x 310 pixels.

The N1M was to be the first Soviet launch vehicle to use liquid oxygen/liquid hydrogen high energy cyrogenic propellants. It was designed to launch payloads in support of the LEK lunar expeditions (two cosmonauts on the surface), the Zvezda DLB (long-duration lunar base), and heavy unmanned satellites into geosynchronous and interplanetary trajectories. As originally conceived, the advanced propellants would be used in all upper stages. However due to delays in Kuznetsov development of a 200 tonne thrust Lox/LH2 engine, the final version used an N1 first stage, with a Block V-III second stage, and Blocks S and R third and fourth stages.

Liftoff Thrust: 4,414,910 kgf. Total Mass: 2,348,000 kg. Core Diameter: 10.0 m. Total Length: 96.0 m.

• Stage Number: 1. 1 x N1 Block A Gross Mass: 1,880,000 kg. Empty Mass: 130,000 kg. Thrust (vac): 5,130,000 kgf. Isp: 330 sec. Burn time: 125 sec. Isp(sl): 284 sec. Diameter: 10.3 m. Span: 16.9 m. Length: 30.1 m. Propellants: Lox/Kerosene No Engines: 30. NK-15

• Stage Number: 2. 1 x N1 Block V-III Gross Mass: 325,000 kg. Empty Mass: 35,000 kg. Thrust (vac): 240,000 kgf. Isp: 440 sec. Burn time: 510 sec. Diameter: 8.0 m. Span: 8.0 m. Length: 27.0 m. Propellants: Lox/LH2 No Engines: 6. RD-57

• Stage Number: 3. 1 x N1 Block S Gross Mass: 58,000 kg. Empty Mass: 8,000 kg. Thrust (vac): 40,000 kgf. Isp: 440 sec. Burn time: 540 sec. Diameter: 6.7 m. Span: 6.7 m. Length: 16.0 m. Propellants: Lox/LH2 No Engines: 1. RD-57

• Stage Number: 4. 1 x N1 Block R Gross Mass: 23,000 kg. Empty Mass: 4,300 kg. Thrust (vac): 7,500 kgf. Isp: 440 sec. Burn time: 1,080 sec. Diameter: 4.1 m. Span: 4.1 m. Length: 8.7 m. Propellants: Lox/LH2 No Engines: 1. RD-56

• First test of liquid hydrogen/LOX engine for N1M

  First test of the 11D56 in an iron stand version. First test of an engine with these propellants in USSR for use in a space launch vehicle.

• Go-ahead to develop LH2/LOX stage for N1M

  Decision made to proceed with development of the multi-engined stage Block Sr with a propellant mass of 66.4 tonnes. This single stage would be used in place of the previously-planned Blocks S and R to insert the modernized Lunar Expeditionary Complex (LEK) into low lunar orbit. It was also to be used to insert heavy spacecraft into geosynchronous orbit and on interplanetary trajectories.

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  N1 and N-1M - N1 and N-1M Dynamic test models Credit: © Mark Wade. 29,402 bytes. 205 x 476 pixels.

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• 89 - Semenov, Yu. P., S P Korolev Space Corporation Energia, RKK Energia, 1994.

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N1M cutaway Credit: © Mark Wade. 2,087 bytes. 75 x 386 pixels.

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