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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 ...
Launch mass (kg) Power system Recovery method Payload (kg) ‡ ... Saturn IB Saturn V: 3: 8.5: 3.91: ... 1 (2) Orion USA: Lockheed Martin ...
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.
The LEO orbital payload of the Saturn V which launched Skylab was 147,363 kg. Of this about 36,500 kg was the non-functional dry mass of the SII 2nd stage. Total orbital mass of the Skylab workshop was about 88,474 kg. Various other sources state the Saturn V LEO payload as 118,000 kg . So there are various ways to define payload: total ...
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 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 ...
The rocket was 36 feet (11 m) tall and weighed 1,648 pounds (748 kg). [1] On Saturday April 25, 2009 Eves launched the 1/10 scale replica of the Saturn V rocket 4,441 feet (1,354 m) into the air, and successfully recovered it. [ 2 ]
The S-II (pronounced "S-two") was the second stage of the Saturn V rocket. It was built by North American Aviation. Using liquid hydrogen (LH2) and liquid oxygen (LOX) it had five J-2 engines in a quincunx pattern. The second stage accelerated the Saturn V through the upper atmosphere with 1,000,000 pounds-force (4.4 MN) of thrust.