N1FV-III

Then N-IFV-III would add the Block V-III cryogenic third stage to the first and second stages of the N-IF.

Manufacturer: Korolev. LEO Payload: 125,000 kg (275,000 lb). to: 220 km Orbit. at: 51.60 degrees. Liftoff Thrust: 51,500.000 kN (11,577,600 lbf). Total Mass: 3,000,000 kg (6,600,000 lb). Core Diameter: 17.00 m (55.00 ft). Total Length: 125.00 m (410.00 ft).

• Stage Number: 1. 1 x Stage: N1F 1965 - A. Gross Mass: 1,940,000 kg (4,270,000 lb). Empty Mass: 200,000 kg (440,000 lb). Thrust (vac): 57,560.000 kN (12,940,000 lbf). Isp: 331 sec. Burn time: 100 sec. Isp(sl): 296 sec. Diameter: 10.00 m (32.00 ft). Span: 17.00 m (55.00 ft). Length: 30.00 m (98.00 ft). Propellants: Lox/Kerosene. No Engines: 30. Engine: 11D51F. Status: Study 1965. As per N1 improvement study, 1965. Block A engine thrust increased but little additional propellant.

• Stage Number: 2. 1 x Stage: N1F 1965 - B. Gross Mass: 590,000 kg (1,300,000 lb). Empty Mass: 60,000 kg (132,000 lb). Thrust (vac): 15,600.000 kN (3,507,000 lbf). Isp: 346 sec. Burn time: 115 sec. Diameter: 6.80 m (22.30 ft). Span: 9.80 m (32.10 ft). Length: 26.00 m (85.00 ft). Propellants: Lox/Kerosene. No Engines: 8. Engine: 11D52F. Status: Study 1965. As per N1 improvement study, 1965. Engine thrust increased from 150 t each to 200 t and stretched propellant tanks.

• Stage Number: 3. 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.

1967 October 10 - Launch Vehicle: N-IFV-III, N1F Sr.

• Lunar Soviet Nation: USSR. Program: Lunar L1, Lunar L3. Spacecraft: L5-1967. The meeting is headed by Afanasyev. The first N1 will have a payload of only 76 tonnes, versus the 95 tonnes required for the L3 lunar landing complex. In order to land two cosmonauts on the moon, as the Americans are planning, a 105 tonne low earth orbit payload would be needed. This would require new engines in the first and second stages. Kuznetsov says that his 153 tonne engine could be uprated to 170 tonnes without any basic changes. Lox/LH2 engines would be needed for the upper stages. Keldysh questions the safety of the current plan of landing only one cosmonaut on the moon. Mishin replies that putting two cosmonauts on the moon simply is not possible with the N1. Chelomei raises a question - How is it possible that the Americans have built he Saturn V, which can put 130 tonnes in low earth orbit, in order to land two men on the moon, and Mishin says he can do the same mission with 105 tonnes? Mishin claims that this is due to the lighter design and construction of the L3. The following decisions are made:
  • The first Soviet flight to he moon will use the current plan - one N1 launch, one cosmonaut on the moon.
  • Special measures must be taken to ensure the safety of that single cosmonaut
  • A new N1 model is to be developed to land the new L5 spacecraft (which will be able to handle 4 to 5 crew, 1.5 to 2.0 tonnes of scientific equipment, and spend three months on the lunar surface). This is to be ready two to three years after the first landing.
  • The Academy of Sciences, the Ministry of Defence, and MOM are to develop a program of military and scientific experiments to be carried aboard the L3
  • The next meeting of the lunar soviet will be in November/December 1967
  References: 376.

• Vetrov, G S, S. P. Korolev i evo delo, Nauka, Moscow, 1998. ISBN: 5020036846. The collected papers of Soviet Chief Designer Korolev. A tremendous source of new information and insight on the Soviet space program. Russian language. More at amazon.com...