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Fully fueled, the Saturn V weighed 6.5 million pounds (2,900,000 kg) [3] and had a low Earth orbit (LEO) payload capacity originally estimated at 261,000 pounds (118,000 kg), but was designed to send at least 90,000 pounds (41,000 kg) to the Moon. [47]
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 American Saturn MLV family of rockets was proposed in 1965 by NASA as successors to the Saturn V rocket. [64] 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 [65] Nova was cancelled in 1964 and had reusable ...
Thrust-to-weight ratio is a dimensionless ratio of thrust to weight of a rocket, ... 2,000 kg (4,400 lb) 35.2 7,900 ... (Saturn V first stage) [28] 8,391 kg (18,499 lb)
Launch mass (kg) Power system Generated power (W) Recovery method First spaceflight § Last spaceflight Flights § SpaceShipOne USA: Scaled Composites: 112 km X Prize: White Knight Hybrid Motor: 1: 8.53 8.05 3,600 Batteries Runway landing 2004: 2004: 3 [note 22] X-15 USA: North American Aviation: 108 km altitude: B-52 Ammonia-LOX: 1: 15.45 6.8 ...
Vehicle Liftoff Mass Payload Mass to LEO Mass ratio Payload fraction Falcon 9 Block 5: 549,054 kg + 22,800 kg 22,800 kg 25.1 3.99% Proton-M: 705,000 kg + 23,000 kg
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)
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.