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If all three stages were to explode simultaneously on the launch pad, an unlikely event, the Saturn V had a total explosive yield of 543 tons of TNT or 0.543 kilotons (2,271,912,000,000 J or 155,143 lbs of weight loss), which is 0.222 kt for the first stage, 0.263 kt for the second stage and 0.068 kt for the third stage. [76]
The American Saturn MLV family of rockets was proposed in 1965 by NASA as successors to the Saturn V rocket. [69] It would have been able to carry up to 160,880 kg (354,680 lb) to low Earth orbit. The Nova designs were also studied by NASA before the agency chose the Saturn V in the early 1960s [ 70 ] Nova was cancelled in 1964 and had reusable ...
Engine Origin Designer Vehicle Status Use Propellant Power cycle Specific impulse (s) [a] Thrust (N) [a] Chamber pressure (bar) Mass (kg) Thrust: weight ratio [b] Oxidiser: fuel ratio
The S-IC (pronounced S-one-C [3] [4]) was the first stage of the American Saturn V rocket. The S-IC stage was manufactured by the Boeing Company. Like the first stages of most rockets, more than 90% of the mass at launch was propellant, in this case RP-1 rocket fuel and liquid oxygen (LOX) oxidizer.
The first US medium-lift vehicle was a purpose-built orbital launch vehicle, the Saturn I. Saturn I first launched in 1961, and the Saturn family would eventually grow into the heavy-lift Saturn IB and the super-heavy lift Saturn V. ICBM-derived launch vehicles for the US include the Atlas, Titan, and Delta families.
A Saturn V rocket, one of the most powerful operational launch vehicles to date. This article compares different orbital launcher families (launchers which are significantly different from other members of the same 'family' have separate entries).
Ares V would have had a maximum lift capacity of about 188 metric tons (414,000 lb) to low Earth orbit (LEO), compared to the Space Shuttle's capacity of 24.4 metric tons (54,000 lb), and the Saturn V's 118 metric tons (260,000 lb). The Ares V would have carried about 71 metric tons (157,000 lb) to the Moon, versus the Saturn V's 45 metric tons ...
The J-2, commonly known as Rocketdyne J-2, was a liquid-fuel cryogenic rocket engine used on NASA's Saturn IB and Saturn V launch vehicles. Built in the United States by Rocketdyne, the J-2 burned cryogenic liquid hydrogen (LH 2) and liquid oxygen (LOX) propellants, with each engine producing 1,033.1 kN (232,250 lb f) of thrust in vacuum.