STS Credit - NASA

Redesign of the shuttle with reliability in mind after the Challenger disaster reduced maximum payload to low earth orbit from 27,850 kg to 24,400 kg. When the decision was made to move the International Space Station to a high-inclination 51.6 degree orbit, net payload to the more challenging orbit dropped to unacceptable limits. The situation was improved by introduction of the Super Lightweight External Tank, which used 2195 Aluminium-Lithium alloy as the main structural material in place of the 2219 aluminium alloy of the original design. This saved 3,500 kg in empty mass, increasing shuttle payload by the same amount. The tank was first used on STS-91 in June 1998.

Manufacturer: NASA. LEO Payload: 27,500 kg (60,600 lb). to: 204 km Orbit. at: 28.50 degrees. Payload: 16,050 kg (35,380 lb). to a: space station orbit, 407 km, 51.6 deg inclination trajectory. Liftoff Thrust: 28,190.000 kN (6,337,360 lbf). Total Mass: 2,040,000 kg (4,490,000 lb). Core Diameter: 8.70 m (28.50 ft). Total Length: 56.00 m (183.00 ft).

• Stage Number: 0. 2 x Stage: Shuttle RSRM. Gross Mass: 590,000 kg (1,300,000 lb). Empty Mass: 88,000 kg (194,000 lb). Thrust (vac): 11,519.999 kN (2,589,799 lbf). Isp: 267 sec. Burn time: 123 sec. Isp(sl): 235 sec. Diameter: 3.77 m (12.36 ft). Span: 5.10 m (16.70 ft). Length: 45.46 m (149.14 ft). Propellants: Solid. No Engines: 1. Engine: RSRM. Other designations: Redesigned Solid Rocket Motor. Status: Study 1996. After the Challenger disaster the redesigned solid rocket motors had a slight reduction in performance due to reliability improvements.

• Stage Number: 1. 1 x Stage: Shuttle Super Lightweight Tank. Gross Mass: 748,000 kg (1,649,000 lb). Empty Mass: 27,000 kg (59,000 lb). Isp: 453 sec. Burn time: 522 sec. Isp(sl): 361 sec. Diameter: 8.40 m (27.50 ft). Span: 8.70 m (28.50 ft). Length: 47.00 m (154.00 ft). Propellants: Lox/LH2. No Engines: 0. Engine: None. Other designations: Super Lightweight External Tank. Status: In production. The Super Lightweight Tank used 2195 Aluminium-Lithium alloy as the main structural material in place of the 2219 aluminium alloy of the original design. This saved 3,500 kg in empty mass, increasing shuttle payload by the same amount. This change was made in anticipation of Shuttle-Mir and Shuttle-ISS flights to high inclination 51.6 degree orbits. The tank was first used on STS-91 in June 1998.

• Stage Number: 2. 1 x Stage: Shuttle Orbiter. Gross Mass: 99,318 kg (218,958 lb). Empty Mass: 99,117 kg (218,515 lb). Thrust (vac): 6,834.303 kN (1,536,412 lbf). Isp: 455 sec. Burn time: 480 sec. Isp(sl): 363 sec. Diameter: 4.90 m (16.00 ft). Span: 23.79 m (78.05 ft). Length: 37.24 m (122.17 ft). Propellants: Lox/LH2. No Engines: 3. Engine: SSME. Other designations: Shuttle; STS (Space Transportation System). Status: In production.

• Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition). ISBN: 1563473534. Superseded by the later editions. More at amazon.com...

• Jenkins, Dennis R,, Space Shuttle: The History of the National Space Transportation System : The First 100 Missions, Third edition, Voyageur Press, 2001. ISBN: 0963397451. Excellent - the most comprehensive account of the design, development, and flights of the space shuttle.Takes the reader from the maze of designs during the first shuttle competition to future plans. More at amazon.com...

• Isakowitz, Steven J, Hopkins, Joshua B, and Hopkins, Joseph P, International Reference to Space Launch Systems, AIAA, Washington DC, 2004. ISBN: 156347591X. The best reference on launch vehicles ever produced. More at amazon.com...