N-IFV-II, III of 1965
N-IFV-II, III of 1965
Russian heavy-lift orbital launch vehicle. N-IFV-II, III would use only the first stage from the N-1F, and use new cryogenic second and third stages. This cryogenic second stage seems not to have been pursued beyond the study phase.
LEO Payload: 150,000 kg (330,000 lb) to a 220 km orbit at 51.60 degrees.
Status: Study 1965.
More... - Chronology...
Gross mass: 3,250,000 kg (7,160,000 lb).
Payload: 150,000 kg (330,000 lb).
Height: 145.00 m (475.00 ft).
Diameter: 17.00 m (55.00 ft).
Thrust: 51,500.00 kN (11,577,600 lbf).
Apogee: 220 km (130 mi).
11D51F Kuznetsov Lox/Kerosene rocket engine. 1918 kN. N1F 1965 - A. Study 1965. As described in N1 improvement study, 1965. Block A engine thrust increased. Isp=331s. More...
NK-15VM Kuznetsov lox/lh2 rocket engine. 1960 kN. N-1 stage 2 (block B) replacement. Design 1972. Derivative of NK-15 with kerosene replaced by hydrogen. Canceled before hot-tests. More...
RD-57 Lyulka lox/lh2 rocket engine. 392 kN. N1 Block S (N-1M). Study 1965. One to have been used in N1 Block S. In fixed chamber version, 3 to 6 to have been used in N1 Block V-III. Engine system includes roll control thruster with 1.29 kN thrust. Isp=456s. More...
N1 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. More...
Associated Manufacturers and Agencies
Korolev Russian manufacturer of rockets, spacecraft, and rocket engines. Korolev Design Bureau, Kaliningrad, Russia. More...
N1 Block V-II Lox/LH2 propellant rocket stage. Loaded/empty mass 805,000/115,000 kg. Thrust 7,840.00 kN. Vacuum specific impulse 440 seconds. N1 improvement study, 1965. Lox/LH2 replacement for Block B second stage. More...
N1 Block V-III Lox/LH2 propellant rocket stage. Loaded/empty mass 325,000/35,000 kg. Thrust 2,350.00 kN. Vacuum specific impulse 440 seconds. 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. More...
N1F 1965 - A Lox/Kerosene propellant rocket stage. Loaded/empty mass 1,940,000/200,000 kg. Thrust 57,560.00 kN. Vacuum specific impulse 331 seconds. As per N1 improvement study, 1965. Block A engine thrust increased but little additional propellant. More...
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