N1F - 1974

The N1F would have been the definitive flight version of the N1, incorporating all changes resulting from the four flight tests of the vehicle, including the new Kuznetsov engines and 10% greater liftoff mass by using superchilled propellants in all stages. N1 8L would have been the first N1F configuration flight, with launch planned in the third quarter of 1975 at the time the project was cancelled.

Manufacturer: Korolev. LEO Payload: 105,000 kg (231,000 lb). to: 220 km Orbit. at: 51.60 degrees. Associated Spacecraft: L3M-1972. Liftoff Thrust: 44,400.000 kN (9,981,500 lbf). Total Mass: 3,025,000 kg (6,668,000 lb). Core Diameter: 17.00 m (55.00 ft). Total Length: 105.00 m (344.00 ft).

• Stage Number: 1. 1 x Stage: N1F Block A. Gross Mass: 2,070,000 kg (4,560,000 lb). Empty Mass: 126,230 kg (278,280 lb). Thrust (vac): 49,675.500 kN (11,167,497 lbf). Isp: 331 sec. Burn time: 125 sec. Isp(sl): 297 sec. Diameter: 10.00 m (32.00 ft). Span: 15.60 m (51.10 ft). Length: 30.00 m (98.00 ft). Propellants: Lox/Kerosene. No Engines: 30. Engine: NK-33. Status: Development ended 1971. Includes 14,000 kg for Stage 1-2 interstage.

• Stage Number: 2. 1 x Stage: N1F Block B. Gross Mass: 620,000 kg (1,360,000 lb). Empty Mass: 55,700 kg (122,700 lb). Thrust (vac): 14,040.004 kN (3,156,318 lbf). Isp: 346 sec. Burn time: 120 sec. Diameter: 6.80 m (22.30 ft). Span: 9.80 m (32.10 ft). Length: 20.00 m (65.00 ft). Propellants: Lox/Kerosene. No Engines: 8. Engine: NK-43. Status: Development ended 1971. Includes 3,500 kg for Stage 2-3 interstage.

• Stage Number: 3. 1 x Stage: N1F Block V. Gross Mass: 210,000 kg (460,000 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: 6.80 m (22.30 ft). Length: 12.00 m (39.00 ft). Propellants: Lox/Kerosene. No Engines: 4. Engine: NK-39. Status: Development ended 1971.

• Stage Number: 4. 1 x Stage: 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: Development ended 1974. Empty mass estimated.

• Stage Number: 5. 1 x Stage: 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 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: Development ended 1974. Block D adapted as lunar crasher stage

1970 June - Launch Vehicle: N1F.

• Development of engines for N1F authorised Nation: USSR. Spacecraft: L3M-1970. Full go-ahead to develop a liquid hydrogen/liquid oxygen high energy upper stage for the N1F. The multi-engine Block Sr would have a propellant mass of 66.4 tonnes. In July Kuznetsov was given authorisation to design substantially improved versions of the N1 lower stage rocket engines. The N1 that would utilise these engines was designated the N1F and would have a payload to a 225 km orbit of 105,000 kg.

• N1-L3M moon landing draft project work authorised. Nation: USSR. Spacecraft: L3M-1972. Military-Industrial Commission (VPK) Decree 'On approval of work on the draft project for the N1-L3M two-launch lunar landing proposal' was issued. References: 474.

• MOK technical proposal authorised. Nation: USSR. Spacecraft: MKBS. Decree 'On work on the technical proposal for the creation of the MOK' was issued. References: 474.

• N1-L3M development authorised. Nation: USSR. Spacecraft: L3M-1972. Council of Chief Designers Decree 'On approval of the N1-L3M proposal' was issued. References: 474.

• N1-L3 program is cancelled Nation: USSR. Program: Lunar L3. Class: Manned. The N1 program was cancelled before the next test flight. Mishin was removed as head of NPO Energia. Kozlov is first asked to replace him, but he prefers to stay in Samara. Glushko is appointed as the second choice. Two fully assembled (serial numbers 8L and 9L), and four partially assembled rockets were available at time of cancellation. These would have been the first to use the new modernized series NK-33/NK-39 engines. 8L was planned for launch in the fourth quarter of 1974. Confidence was high that, based on the massive telemetry received on the 7L flight, that all problems would have been rectified. A total of 3.6 billion rubles was spent on the N1-L3 program, of which 2.4 billion rubles went into N1 development. Those on the project felt that they were within months of finally providing the Soviet Union with a heavy-lift booster. Instead the work was discarded, and Glushko began design of the RLA/Vulkan with entirely new configuration and engines.References: 23, 69.

• N1 launches suspended. Nation: USSR. Spacecraft: L3M-1972. Ministry of Defence Decree 'On suspension of further launches of the N1' was issued. References: 474.

• N1-L3 work suspended. Nation: USSR. Spacecraft: Soyuz 7K-OK, LK, L3M-1972. TsKBEM Decree 'On suspension of work on the N1 -L3' was issued. References: 474.

• Energia; Buran; Mir; Luch; Potok approved; N1 formally cancelled. Nation: USSR. Spacecraft: Buran, Mir, Mir-2, Gamma, Potok, Luch. Central Committee of the Communist Party and Council of Soviet Ministers Decree 'On work on Energia-Buran, DOS-7K nos. 7 and 8, Gamma. Geyzer (Potok), and Altair (Luch) and cancellation of the N1' was issued. The design of an improved model of the Salyut DOS-17K space station was authorised as part of the third generation of Soviet space systems in a decree. At that time it was planned that the two stations (DOS-7 and DOS-8) would be equipped with two docking ports at either end of the station and an additional two ports at the sides of the forward small diameter compartment. Luch and Potok were elements of the second generation global command and control system (GKKRS) deployed in the first half of the 1980's. Luch satellites, analogous to the US TDRS, provided communications service to the Mir space station, Buran space shuttle, Soyuz-TM spacecraft, military satellites, and the TsUPK ground control center. They also served to provide mobile fleet communications for the Soviet Navy.Additional Details: Energia; Buran; Mir; Luch; Potok approved; N1 formally cancelled.(22882). References: 474.

• Przybilski, Olaf, and Wotzlaw, Stefan, N-1 Herkules - Entwicklung und Absturz einer Traegerrakete, Schriftenreihe der Deutschen Raumfahrtausstellung e.V., 1996. Best account of the development of the N-1 rocket and the Soviet lunar program. In German.