N1M 1974 Media Gallery

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 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.

Manufacturer: Korolev. Associated Spacecraft: L3M-1970. Liftoff Thrust: 43,295.500 kN (9,733,216 lbf). Total Mass: 2,348,000 kg (5,176,000 lb). Core Diameter: 10.00 m (32.00 ft). Total Length: 96.00 m (314.00 ft).

• Stage Number: 1. 1 x Stage: 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. 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). Propellants: Lox/Kerosene. No Engines: 30. Engine: NK-15. Status: Development ended 1971. 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.

• Stage Number: 2. 1 x Stage: N1 Block V-III. Gross Mass: 325,000 kg (716,000 lb). Empty Mass: 35,000 kg (77,000 lb). Thrust (vac): 2,350.000 kN (528,300 lbf). Isp: 440 sec. Burn time: 510 sec. Diameter: 8.00 m (26.20 ft). Span: 8.00 m (26.20 ft). Length: 27.00 m (88.00 ft). Propellants: Lox/LH2. No Engines: 6. Engine: RD-57. Status: Study 1965. N1 improvement study, 1965. Lox/LH2 replacement for Block V third stage. Pursued into 1966 and later, but later efforts concentrated on Block S, R, and SR cryogenic stages.

• Stage Number: 3. 1 x Stage: N1 Block S. Gross Mass: 58,000 kg (127,000 lb). Empty Mass: 8,000 kg (17,600 lb). Thrust (vac): 392.000 kN (88,125 lbf). Isp: 440 sec. Burn time: 540 sec. Diameter: 6.70 m (21.90 ft). Span: 6.70 m (21.90 ft). Length: 16.00 m (52.00 ft). Propellants: Lox/LH2. No Engines: 1. Engine: RD-57. Status: Development ended 1971. Designed 1965-1971 as replacement for N-1 Blok G. Cancelled in 1971 in favor of development of single stage, Block Sr.

• Stage Number: 4. 1 x Stage: N1 Block R. Gross Mass: 23,000 kg (50,000 lb). Empty Mass: 4,300 kg (9,400 lb). Thrust (vac): 73.500 kN (16,523 lbf). Isp: 440 sec. Burn time: 1,080 sec. Diameter: 4.10 m (13.40 ft). Span: 4.10 m (13.40 ft). Length: 8.70 m (28.50 ft). Propellants: Lox/LH2. No Engines: 1. Engine: RD-56. Status: Development ended 1971. Designed 1965-1971 as replacement for N-1 Blok D. Cancelled 1971 in favor of Blok Sr; revived and developed in 1974-1976. First static test Oct 12 1976. Two stages tested 1976-1977. Strangely never replaced Blok D on Proton.

1967 June 15 - Launch Vehicle: N1M.

• First test of liquid hydrogen/LOX engine for N1M Nation: USSR. Program: Lunar L3. 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. References: 21.

• N1 State Commission Nation: USSR. Program: Lunar L3. Spacecraft: LK, Soyuz 7K-L1A, Soyuz 7K-LOK, Aelita. Over two days a State Commission reviewed all of the conclusions of the N1 3L failure investigation and the readiness of N1 5L for flight. All of the fixes identified to remedy the 3L failure had been incorporated into 5L. It was felt that the behaviour of the systems in fire conditions were understood and appropriate measures had been taken. The wiring had been rerouted and insulated. Barmin wanted the system not to shut down any engines under any conditions during the first 15-20 seconds of flight, so that the booster would clear the pad and there would be no risk of the pad's destruction. But there was no time to develop such measures before the 5L launch; it could only be added in vehicle 6L.Additional Details: N1 State Commission(51176). References: 367.

• Go-ahead to develop LH2/LOX stage for N1M Nation: USSR. Program: Lunar L3. 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.References: 21.

• Semenov, Yu. P., S P Korolev Space Corporation Energia, RKK Energia, 1994. ISBN: 1896522815. Dual English/Russian language picture book of the history of the Energia Corporation. Many unique photos and drawings of Korolev's rockets and spacecraft. Republished by Apogee books in 2000. More at amazon.com...