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Description
Space shuttle Prometheus OV-120 USAF

Length: 122.17 ft (37.237 m)
Wingspan: 78.06 ft (23.79 m)
Height: 56.58 ft (17.25 m)
Empty weight: 172,000 lb (78,000 kg)[46]
Gross liftoff weight (Orbiter only): 240,000 lb (110,000 kg)
Maximum landing weight: 230,000 lb (100,000 kg)
Payload to Landing (Return Payload): 14,400 kg (32,000 lb)[1]
Maximum payload: 55,250 lb (25,060 kg)
Payload to LEO: 53,600 lb (24,310 kg)
Payload to LEO @ 51.6° inclination (ISS):
Payload to GTO: 8,390 lb (3,806 kg)
Payload to Polar Orbit: 28,000 lb (12,700 kg)
(Note launch payloads modified by External Tank (ET) choice (ET, LWT, or SLWT)
Payload bay dimensions: 15 by 59 ft (4.6 by 18 m)
Operational altitude: 100 to 520 nmi (190 to 960 km; 120 to 600 mi)
Speed: 7,743 m/s (27,870 km/h; 17,320 mph)
Crossrange: 1,085 nmi (2,009 km; 1,249 mi)
First Stage (SSME with external tank)
Main engines: Three Rocketdyne Block II SSMEs, each with a sea level thrust of 393,800 lbf (1.752 MN) at 104% power
Thrust (at liftoff, sea level, 104% power, all 3 engines): 1,181,400 lbf (5.255 MN)
Specific impulse: 455 s
Burn time: 480 s
Fuel: Liquid Oxygen/Liquid Hydrogen
Second Stage
Engines: 2 Orbital Maneuvering Engines
Thrust: 53.4 kN (12,000 lbf) combined total vacuum thrust
Specific impulse: 316 s
Burn time: 1250 s
Fuel: MMH/N2O4
Crew: Varies.

The earliest Shuttle flights had the minimum crew of two; many later missions a crew of five. By program end, typically seven people would fly: (commander, pilot, several mission specialists, and rarely a flight engineer). On two occasions, eight astronauts have flown (STS-61-A, STS-71). Eleven people could be accommodated in an emergency mission (see STS-3xx).

External tank specifications (for SLWT)

Length: 46.9 m (154 ft)
Diameter: 8.4 m (28 ft)
Propellant volume: 2,025 m3 (534,900 US gal)
Empty weight: 26,535 kg (58,500 lb)
Gross liftoff weight (for tank): 756,000 kg (1,670,000 lb)

Solid Rocket Booster specifications

Length: 45.46 m (149 ft)[47]
Diameter: 3.71 m (12.2 ft)[47]
Empty weight (per booster): 68,000 kg (150,000 lb)[47]
Gross liftoff weight (per booster): 571,000 kg (1,260,000 lb)[48]
Thrust (at liftoff, sea level, per booster): 12.5 MN (2,800,000 lbf)[29]
Specific impulse: 269 s
Burn time: 124 s

System Stack specifications

Height: 56 m (180 ft)
Gross liftoff weight: 2,000,000 kg (4,400,000 lb)
Total liftoff thrust: 30.16 MN (6,780,000 lbf)

Description
Space shuttle Prometheus OV-120 USAF

Length: 122.17 ft (37.237 m)
Wingspan: 78.06 ft (23.79 m)
Height: 56.58 ft (17.25 m)
Empty weight: 172,000 lb (78,000 kg)[46]
Gross liftoff weight (Orbiter only): 240,000 lb (110,000 kg)
Maximum landing weight: 230,000 lb (100,000 kg)
Payload to Landing (Return Payload): 14,400 kg (32,000 lb)[1]
Maximum payload: 55,250 lb (25,060 kg)
Payload to LEO: 53,600 lb (24,310 kg)
Payload to LEO @ 51.6° inclination (ISS):
Payload to GTO: 8,390 lb (3,806 kg)
Payload to Polar Orbit: 28,000 lb (12,700 kg)
(Note launch payloads modified by External Tank (ET) choice (ET, LWT, or SLWT)
Payload bay dimensions: 15 by 59 ft (4.6 by 18 m)
Operational altitude: 100 to 520 nmi (190 to 960 km; 120 to 600 mi)
Speed: 7,743 m/s (27,870 km/h; 17,320 mph)
Crossrange: 1,085 nmi (2,009 km; 1,249 mi)
First Stage (SSME with external tank)
Main engines: Three Rocketdyne Block II SSMEs, each with a sea level thrust of 393,800 lbf (1.752 MN) at 104% power
Thrust (at liftoff, sea level, 104% power, all 3 engines): 1,181,400 lbf (5.255 MN)
Specific impulse: 455 s
Burn time: 480 s
Fuel: Liquid Oxygen/Liquid Hydrogen
Second Stage
Engines: 2 Orbital Maneuvering Engines
Thrust: 53.4 kN (12,000 lbf) combined total vacuum thrust
Specific impulse: 316 s
Burn time: 1250 s
Fuel: MMH/N2O4
Crew: Varies.

The earliest Shuttle flights had the minimum crew of two; many later missions a crew of five. By program end, typically seven people would fly: (commander, pilot, several mission specialists, and rarely a flight engineer). On two occasions, eight astronauts have flown (STS-61-A, STS-71). Eleven people could be accommodated in an emergency mission (see STS-3xx).

External tank specifications (for SLWT)

Length: 46.9 m (154 ft)
Diameter: 8.4 m (28 ft)
Propellant volume: 2,025 m3 (534,900 US gal)
Empty weight: 26,535 kg (58,500 lb)
Gross liftoff weight (for tank): 756,000 kg (1,670,000 lb)

Solid Rocket Booster specifications

Length: 45.46 m (149 ft)[47]
Diameter: 3.71 m (12.2 ft)[47]
Empty weight (per booster): 68,000 kg (150,000 lb)[47]
Gross liftoff weight (per booster): 571,000 kg (1,260,000 lb)[48]
Thrust (at liftoff, sea level, per booster): 12.5 MN (2,800,000 lbf)[29]
Specific impulse: 269 s
Burn time: 124 s

System Stack specifications

Height: 56 m (180 ft)
Gross liftoff weight: 2,000,000 kg (4,400,000 lb)
Total liftoff thrust: 30.16 MN (6,780,000 lbf)