Model: Spacemaster.

Spacemaster Credit - NASA

Winged orbital launch vehicle. Family:

Martin-Marrietta shuttle Phase A design. X-24B type lifting body orbiter with unique catamaran-configuration booster.

Martin Marietta’s unsolicited company-funded shuttle proposal was named "Spacemaster". It was designed for carrying 11,340-22,680 kilogram payloads in the same 4.57 * 18.3-meter cargo envelope as the other Phase A shuttle proposals. Martin’s twin-body booster would have reduced the overall length of the mated vehicle and would also have been compatible with different orbiters or rocket stages between bodies. The booster rocket engines are on the aft end of each body. Since the orbiter would be nested during ascent, Martin Marietta predicted that the centre of gravity shift from lift-off to staging would be relatively small. The nested orbiter design would also have reduced booster rocket engine gimbal angles, ascent drag and vehicle angle of attack. The booster landing jet motors were installed in the forward wing to achieve a good centre-of-gravity location.

Manufacturer: Martin. Liftoff Thrust: 24,905.800 kN (5,599,046 lbf). Total Mass: 1,587,302 kg (3,499,401 lb). Core Diameter: 8.00 m (26.20 ft). Total Length: 128.00 m (419.00 ft).

• Stage1: 1 x Spacemaster-1. Gross Mass: 1,224,490 kg (2,699,530 lb). Empty Mass: 203,342 kg (448,292 lb). Motor: 14 x SSME Study. Thrust (vac): 28,082.538 kN (6,313,206 lbf). Isp: 442 sec. Burn time: 155 sec. Length: 57.93 m (190.05 ft). Diameter: 8.00 m (26.20 ft). Propellants: Lox/LH2.

• Stage2: 1 x Spacemaster-2. Gross Mass: 362,812 kg (799,863 lb). Empty Mass: 80,000 kg (176,000 lb). Motor: 2 x SSME Study. Thrust (vac): 4,549.049 kN (1,022,667 lbf). Isp: 459 sec. Burn time: 276 sec. Length: 48.78 m (160.03 ft). Diameter: 6.71 m (22.01 ft). Propellants: Lox/LH2.

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Media Gallery for Spacemaster

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	Spacemaster		sts69sm2.jpg 306 x 508 42.2 kb Credit: NASA