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The satellite designs also required that the Space Shuttle have a 4.6 by 18 m (15 by 60 ft) payload bay. NASA evaluated the F-1 and J-2 engines from the Saturn rockets, and determined that they were insufficient for the requirements of the Space Shuttle; in July 1971, it issued a contract to Rocketdyne to begin development on the RS-25 engine.
It would have had a larger payload bay with an additional 15 feet (4.6 m) in length giving it a payload capacity of 75 feet (23 m) and expected to carry payloads of up to 100,000 lb (45,000 kg). A new wing root and carry-through structure were designed to handle the additional weight at landing, keeping the outboard section of the original ...
For example, NASA planned a 40-by-15-foot (12.2 by 4.6 m) cargo bay, but NRO specified a 60-by-15-foot (18.3 by 4.6 m) bay because it expected future intelligence satellites to become larger. When Faget again proposed a 12 ft (3.7 m) wide payload bay, the military almost immediately insisted on retaining the 15 ft (4.6 m) width. [ 3 ]
Spacecraft Origin Manufacturer Range Launch system Crew size Length (m) Diameter (m) Launch mass (kg) Power system Recovery method Payload (kg) ‡
Soviet / Russian space station: LEO: Deorbited 2001: 1986–2001 Space Shuttle Atlantis STS-117: 122,683 kg (270,470 lb) Heaviest flight of the Space Shuttle with S3/S4 truss. LEO: Retired: 1985–2011 Space Shuttle Columbia STS-93: 122,534 kg (270,141 lb) Chandra X-ray Observatory, launch: LEO: Lost: 1981–2003 Space Shuttle Atlantis STS-115: ...
The Orbital Maneuvering System (OMS) is a system of hypergolic liquid-propellant rocket engines used on the Space Shuttle and the Orion spacecraft.Designed and manufactured in the United States by Aerojet, [1] the system allowed the orbiter to perform various orbital maneuvers according to requirements of each mission profile: orbital injection after main engine cutoff, orbital corrections ...
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About the size of a McDonnell Douglas DC-9, [2] the Space Shuttle orbiter resembled an airplane in its design, with a standard-looking fuselage and two double delta wings, both swept wings at an angle of 81 degrees at their inner leading edges and 45 degrees at their outer leading edges.