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Spacemaster
Function
Manned Re-usable orbital launch vehicle
Manufacturer
Martin Marietta
Country of origin
United States
Size
Height
128 m (420 ft)
Diameter
8.0 m (26.2 ft)
Mass
1,600,000 kg (3,500,000 lb)
Stages
2
Capacity
Payload to LEO
Mass
22,700 kg (50,000 lb)
Launch history
Status
Cancelled
Launch sites
LC-39 Kennedy Space Center
Total launches
0
First stage
Powered by
14 Rocketdyne SSME
Maximum thrust
28,080 kN (6,310,000 lbf)
Burn time
155 seconds
Propellant
LH2/LOX
Second stage
Powered by
2 Rocketdyne SSME
Maximum thrust
4,549 kN (1,023,000 lbf)
Burn time
276 seconds
Propellant
LH2/LOX
[edit on Wikidata]
The Martin Marietta Spacemaster was a proposed configuration for what became the Space Shuttle, which featured an X-24-derived orbiter, and an unusual "catamaran style" booster stage. During launch and ascent, the orbiter would be located in a recess in the booster. The booster's 14 engines would be located in clusters of seven, at the bottom of both halves of the booster. Unlike the final design for the Space Shuttle, the Spacemaster would lack an external tank, and the boosters would be joined, by means of connecting struts which would also serve as the mounting for the orbiter.
The concept was evaluated in 1967, but was rejected. Martin Marietta went on to produce the Space Shuttle external tank (ET) for the final STS Space Shuttle design (by Lockheed Martin after a merger with Lockheed).
A model of the Martin Marietta Spacemaster is in the collection of the Smithsonian National Air and Space Museum.[1]
^"Model, Space Shuttle, Martin Marietta Spacemaster Two-Stage Concept, 1:96". National Air and Space Museum. Retrieved 2018-08-19.
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