N1 (rocket)

The N1/L3 (from Ракета-носитель Raketa-nositel', "Carrier Rocket"; Cyrillic: Н1) was a super heavy-lift launch vehicle intended to deliver payloads beyond low Earth orbit. The N1 was the Soviet counterpart to the US Saturn V and was intended to enable crewed travel to the Moon and beyond, with studies beginning as early as 1959. Its first stage, Block A, was the most powerful rocket stage ever flown for over 50 years, generating 45.4 MN of thrust. However, each of the four attempts to launch an N1 failed in flight, with the second attempt resulting in the vehicle crashing back onto its launch pad shortly after liftoff. Adverse characteristics of the large cluster of thirty engines and its complex fuel and oxidizer feeder systems were not revealed earlier in development because static test firings had not been conducted.

N1/L3
Mockup at the Baikonur Cosmodrome in late 1967
FunctionCrewed lunar launch vehicle/Super heavy-lift launch vehicle
ManufacturerOKB-1
Country of originUSSR
Size
Height105.3 meters (345 ft)
Diameter17.0 meters (55.8 ft)
Mass2,750 tonnes (6,060,000 lb)
Stages5
Capacity
Payload to LEO
Mass95 t (209,000 lb)
Payload to TLI
Mass23.5 t (52,000 lb)
Launch history
StatusCancelled
Launch sitesLC-110, Baikonur
Total launches4
Success(es)0
Failure(s)4
First flight21 February 1969
Last flight23 November 1972
First stage – Block A
Diameter17.0 m (55.8 ft)
Powered by30 NK-15
Maximum thrust45,400 kN (10,200,000 lbf)
Specific impulse330 seconds (3.2 km/s)
Burn time125 s
PropellantRP-1/LOX
Second stage – Block B
Powered by8 NK-15V
Maximum thrust14,040 kN (3,160,000 lbf)
Specific impulse346 seconds (3.39 km/s)
Burn time120 s
PropellantRP-1/LOX
Third stage – Block V
Powered by4 NK-21
Maximum thrust1,610 kN (360,000 lbf)
Specific impulse353 seconds (3.46 km/s)
Burn time370 s
PropellantRP-1/LOX
Fourth stage (N1/L3) – Block G (Earth departure)
Powered by1 NK-19
Maximum thrust446 kN (100,000 lbf)
Specific impulse353 seconds (3.46 km/s)
Burn time443 s
PropellantRP-1/LOX
Fifth stage (N1/L3) – Block D (Lunar descent assist)
Powered by1 RD-58
Maximum thrust83.36 kN (18,740 lbf)
Specific impulse349 seconds (3.42 km/s)
Burn time600 s
PropellantRP-1/LOX

The N1-L3 version was designed to compete with the United States Apollo program to land a person on the Moon, using a similar lunar orbit rendezvous method. The basic N1 launch vehicle had three stages, which were to carry the L3 lunar payload into low Earth orbit with two cosmonauts. The L3 contained one stage for trans-lunar injection; another stage used for mid-course corrections, lunar orbit insertion, and the first part of the descent to the lunar surface; a single-pilot LK Lander spacecraft; and a two-pilot Soyuz 7K-LOK lunar orbital spacecraft for return to Earth.

The N1-L3 started development in October 1965, almost four years after the Saturn V, during which it was underfunded and rushed. The project was badly derailed by the death of its chief designer Sergei Korolev in 1966. The N1 program was suspended in 1974, and officially canceled in 1976. All details of the Soviet crewed lunar programs were kept secret until the USSR was nearing collapse in 1989.

This article is issued from Wikipedia. The text is licensed under Creative Commons - Attribution - Sharealike. Additional terms may apply for the media files.