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N1 1969
Part of N1 Family
N1-L3 - 1964
N1-L3 - 1964
N1-L3 as per advanced project, 1964
Russian heavy-lift orbital launch vehicle. The N1 launch vehicle, developed by Russia in the 1960's, was to be the Soviet Union's counterpart to the Saturn V. The largest of a family of launch vehicles that were to replace the ICBM-derived launchers then in use, the N series was to launch Soviet cosmonauts to the moon, Mars, and huge space stations into orbit. In comparison to Saturn, the project was started late, starved of funds and priority, and dogged by political and technical struggles between the chief designers Korolev, Glushko, and Chelomei. The end result was four launch failures and cancellation of the project five years after Apollo landed on the moon. Not only did a Soviet cosmonaut never land on the moon, but the Soviet Union even denied that the huge project ever existed.

AKA: 11A52; G-1; N-1; N-1 11A52; SL-15. Status: Retired 1972. Payload: 70,000 kg (154,000 lb). Thrust: 43,000.00 kN (9,666,000 lbf). Gross mass: 2,735,000 kg (6,029,000 lb). Height: 105.00 m (344.00 ft). Diameter: 17.00 m (55.00 ft). Apogee: 225 km (139 mi).

Data is for the N1 launch vehicle as flown. These test vehicles did not exceed 2735 metric tons liftoff mass and 70 metric ton earth orbit payload capability. Four flight tests, all failures.

Stage Data - N1

  • Stage 1. 1 x 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: Out of Production. Comments: 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 2. 1 x 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. Diameter: 6.80 m (22.30 ft). Span: 9.80 m (32.10 ft). Length: 20.50 m (67.20 ft). Propellants: Lox/Kerosene. No Engines: 8. Engine: NK-15V. Status: Out of Production. Comments: 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.
  • Stage 3. 1 x N1 Block V. Gross Mass: 188,700 kg (416,000 lb). Empty Mass: 13,700 kg (30,200 lb). Thrust (vac): 1,608.000 kN (361,492 lbf). Isp: 353 sec. Burn time: 370 sec. Diameter: 4.80 m (15.70 ft). Span: 6.40 m (20.90 ft). Length: 14.10 m (46.20 ft). Propellants: Lox/Kerosene. No Engines: 4. Engine: NK-21. Status: Out of Production.
  • Stage 4. 1 x N1 Block G. Gross Mass: 61,800 kg (136,200 lb). Empty Mass: 6,000 kg (13,200 lb). Thrust (vac): 445.996 kN (100,264 lbf). Isp: 353 sec. Burn time: 443 sec. Diameter: 4.40 m (14.40 ft). Span: 4.40 m (14.40 ft). Length: 9.10 m (29.80 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: NK-19. Status: Out of Production. Comments: Empty mass estimated.
  • Stage 5. 1 x N1 Block D. Gross Mass: 18,200 kg (40,100 lb). Empty Mass: 3,500 kg (7,700 lb). Thrust (vac): 83.300 kN (18,727 lbf). Isp: 349 sec. Burn time: 600 sec. Isp(sl): 0.0000 sec. Diameter: 2.90 m (9.50 ft). Span: 2.90 m (9.50 ft). Length: 5.70 m (18.70 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-58. Status: Out of Production. Comments: Block D adapted as lunar crasher stage.

Family: heavy-lift, orbital launch vehicle. Country: Russia. Engines: NK-19, NK-15V, NK-21, 8D415K, NK-15, RD-54, RD-58. Spacecraft: MPK, TMK-E, TMK-1, Vostok, OS, L1-1960, L4-1960, TKS Heavy Space Station, OS-1962, OP, OS-1 (1965), DLB Module, L3-1963, L4-1963, L5-1963, Global Communications Satellite Using Nuclear Power, Mavr, L3, KK, Soyuz 7K-OK, OS-1 (1969), Soyuz 7K-L1, L5-1967, L3M-1970, DLB Lunar Base, Mars 5NM, Luna Ye-8, Soyuz 7K-L1A, Luna Ye-8-5, MKBS, MEK, OS-1 Lunar, LK, Soyuz 7K-LOK, DLB Lunokhod 1, DLB Lunokhod 2, DLB Lunokhod 3, L3M-1972. Projects: Lunar L3. Launch Sites: Baikonur, Baikonur LC110R, Baikonur LC110L. Stages: N1 Block G, N1 Block V, N1 Block B, N1 Block A, N1 Block D. Agency: Korolev bureau. Bibliography: 123, 125, 164, 165, 168, 2, 21, 23, 283, 288, 32, 367, 376, 474, 51, 57, 69, 70, 72, 75, 77, 84, 89, 96.



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