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Saturn V and N-1 Super Booster

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Description

Name: Saturn V

Country of Origin: United States of America (USA)

Function Crewed LEO and Lunar launch vehicle
Manufacturer Boeing (S-IC)
North American (S-II)
Douglas (S-IVB)

Size
Height 363.0 feet (110.6 m)
Diameter 33.0 feet (10.1 m)
Mass 6,200,000 pounds (2,800,000 kg)[1]
Stages 3

Capacity
Payload to LEO 260,000 pounds (120,000 kg)[1]
Payload to
TLI (100,000 pounds (45,000 kg))
Associated rockets
Family Saturn
Derivatives Saturn INT-21
Comparable N1 rocket

Launch history
Status Decommissioned
Launch sites LC-39, Kennedy Space Center
Total launches 13 (including INT-21)[2]
Successes 11
Failures 0
Partial failures 1 (Apollo 6))
First flight November 9, 1967 (SA-501)
Last flight December 6, 1972
(May 14, 1973 - INT-21)[2]

First Stage - S-IC
Length 138.0 feet (42.1 m)
Diameter 33.0 feet (10.1 m)
Empty mass 288,000 pounds (131,000 kg)
Gross mass 5,000,000 pounds (2,300,000 kg)
Engines 5 Rocketdyne F-1
Thrust 7,648,000 pounds-force (34,020,000 N)
Specific impulse 263 sec (2580 N-s/kg)
Burn time 150 seconds
Fuel RP-1/LOX

Second Stage - S-II
Length 81.5 feet (24.8 m)
Diameter 33.0 feet (10.1 m)
Empty mass 80,000 pounds (36,000 kg)
Gross mass 1,060,000 pounds (480,000 kg)
Engines 5 Rocketdyne J-2
Thrust 1,000,000 pounds-force (4,400,000 N)
Specific impulse 421 sec (4130 N-s/kg)
Burn time 360 seconds
Fuel LH2/LOX

Third Stage - S-IVB
Length 61.6 feet (18.8 m)
Diameter 21.7 feet (6.6 m)
Empty mass 23,000 pounds (10,000 kg)[citation needed]
Gross mass 266,400 pounds (120,800 kg)
Engines 1 Rocketdyne J-2
Thrust 225,000 pounds-force (1,000,000 N)
Specific impulse 421 sec (4130 N-s/kg)
Burn time 165 + 335 seconds
(2 burns)
Fuel LH2/LOX

Name: N-1 Super Booster

Country of Origin: Union of Soviet Socialist Republics (USSR)

Function Manned lunar carrier rocket
Manufacturer OKB-1
Size
Height 105 metres (344 ft)
Diameter 17.0 metres (55.8 ft)
Mass 2,735,000 kilograms (6,030,000 lb)
Stages 5
Capacity
Payload to
LEO 90,000 kg (200,000 lb)
Payload to
TLI 23,500 kg (52,000 lb)

Launch history
Status Retired
Launch sites LC-110, Baikonur
Total launches 4
Successes 0
Failures 4
First flight 21 February 1969
Last flight 23 November 1972

First Stage - Block A
Diameter 17.0 m (55.8 ft)
Engines 30 NK-15
Thrust 50,300 kN (11,300,000 lbf)
Specific impulse 3.24 kN·s/kg (330 s)
Burn time 125 s
Fuel RP-1/LOX

Second Stage - Block B
Engines 8 NK-15V
Thrust 14,040 kN (3,160,000 lbf)
Specific impulse 3.39 kN·s/kg (346 s)
Burn time 120 s
Fuel RP-1/LOX

Third Stage - Block V
Engines 4 NK-21
Thrust 1,610 kilonewtons (360,000 lbf)
Specific impulse 3.46 kN·s/kg (353 s)
Burn time 370 seconds
Fuel RP-1/LOX

Fourth Stage (N1/L3) - Block G (Earth departure)
Engines 1 NK-19
Thrust 446.00 kN (100,260 lbf)
Specific impulse 3.46 kN·s/kg (353 s)
Burn time 443 s
Fuel RP-1/LOX
Image size
1909x3527px 1.05 MB
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Comments22
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The N1, if corrected to work, would have been a real super.
Comparable in size to the Saturn but with a higher thrust to weight ratio and higher specific impulse first stage engines.
And so they had to loft more fuel, paying in payload.
If launched from Florida the N1 would have had better payload to LEO than the Saturn V.
Rotating earth gives a bigger speed bonus to those launching from nearer the equator.
N1 was stuck launching from Baikonur.

Times have changed and now the USSA is stuck buying engines from the "former" (thanks a lot Putin) CCCP.