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The Saturn V reached 400 feet per second (120 m/s) at over 1 mile (1,600 m) in altitude. Much of the early portion of the flight was spent gaining altitude, with the required velocity coming later. The Saturn V broke the sound barrier at just over 1 minute at an altitude of between 3.45 and 4.6 miles (5.55 and 7.40 km). At this point, shock ...
During their two and a half minutes of operation, the five F-1s propelled the Saturn V vehicle to a height of 42 miles (222,000 ft; 68 km) and a speed of 6,164 mph (9,920 km/h). The combined flow rate of the five F-1s in the Saturn V was 3,357 US gal (12,710 L) [5] or 28,415 lb (12,890 kg) per second.
Saturn Static Test Stand; Saturn V Booster Test Stand; Saturn V S-IC Static Test Stand; S-IC Static Test Complex; Advanced Engine Test Facility B-2 Test Stand specifications: [16] Concrete: 12,000,000 lb (5,400,000 kg) Foundation depth: 12 m (40 ft) Four concrete foundation leg walls: 15 m (48 ft) thick and 44 m (144 ft) tall
The American Saturn MLV family of rockets was proposed in 1965 by NASA as successors to the Saturn V rocket. [71] 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 [ 72 ] Nova was cancelled in 1964 and had reusable ...
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 Saturn V dynamic test vehicle, designated SA-500D, is a prototype Saturn V rocket used by NASA to test the performance of the rocket when vibrated to simulate the shaking which subsequent rockets would experience during launch. It was the first full-scale Saturn V completed by the Marshall Space Flight Center (MSFC).
The Saturn V instrument unit is a ring-shaped structure fitted to the top of the Saturn V rocket's third stage and ... Weight at launch: ~4,400 lb (1996 kg)
Apollo 8, Saturn V with 810,700 litres of RP-1 and 1,311,100 liters of LOX in the S-IC first stage [1] RP-1 is a fuel in the first-stage boosters of the Electron, Soyuz, Zenit, Delta I-III, Atlas, Falcon, Antares, and Tronador II rockets. It also powered the first stages of the Energia, Titan I, Saturn I and IB, and Saturn V.