Martin Marietta Spacemaster

From Wikipedia, the free encyclopedia
Jump to: navigation, search
Spacemaster
Function Manned Re-usable orbital launch vehicle
Manufacturer Martin Marietta
Country of origin United States
Size
Height 128 m (419 ft)
Diameter 8.0 m (26.2 ft)
Mass 3,500,000 lb (1,590,000 kg)
Stages 2
Capacity
Payload to LEO 50,000 lb (22,700 kg)
Launch history
Status Cancelled
Launch sites LC-39 Kennedy Space Center
Total launches 0
First stage
Engines 14 Rocketdyne SSME
Thrust 28,080 kN (6,313,000 lbf)
Burn time 155 seconds
Fuel LH2/LOX
Second stage
Engines 2 Rocketdyne SSME
Thrust 4,549 kN (1,022,700 lbf)
Burn time 276 seconds
Fuel LH2/LOX

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).

See also[edit]

References[edit]

External links[edit]