Encyclopedia Astronautica
Shuttle LRB



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Shuttle - LRB
Shuttle - LRB boosters side
Credit: © Mark Wade
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Shuttle - LRB 2 view
Shuttle - LRB boosters 2 view
Credit: © Mark Wade
American winged orbital launch vehicle. Shuttle with Liquid Rocket Boosters in place of Solid Rocket Boosters.

Development Cost $: 1,629.000 million in 1985 dollars.

Stage Data - Shuttle LRB

  • Stage 0. 2 x Shuttle LRB. Gross Mass: 350,000 kg (770,000 lb). Empty Mass: 52,000 kg (114,000 lb). Thrust (vac): 10,318.106 kN (2,319,603 lbf). Isp: 435 sec. Burn time: 121 sec. Isp(sl): 330 sec. Diameter: 5.50 m (18.00 ft). Span: 5.50 m (18.00 ft). Length: 45.54 m (149.40 ft). Propellants: Lox/LH2. No Engines: 4. Engine: STME. Other designations: Liquid Rocket Booster. Status: Study 1984.
  • Stage 1. 1 x Shuttle Tank. Gross Mass: 750,975 kg (1,655,616 lb). Empty Mass: 29,930 kg (65,980 lb). Thrust (vac): 0.0000 N ( lbf). Isp: 455 sec. Burn time: 480 sec. Isp(sl): 363 sec. Diameter: 8.40 m (27.50 ft). Span: 8.70 m (28.50 ft). Length: 46.88 m (153.80 ft). Propellants: Lox/LH2. No Engines: 0. Engine: None. Other designations: External Tank. Status: Out of production.
  • Stage 2. 1 x 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.
  • Stage 3. 1 x Shuttle Orbiter OMS. Gross Mass: 25,200 kg (55,500 lb). Empty Mass: 3,600 kg (7,900 lb). Thrust (vac): 53.377 kN (12,000 lbf). Isp: 316 sec. Burn time: 1,250 sec. Isp(sl): 0.0000 sec. Diameter: 4.90 m (16.00 ft). Span: 23.79 m (78.05 ft). Length: 37.24 m (122.17 ft). Propellants: N2O4/MMH. No Engines: 2. Engine: OME. Other designations: Orbital Maneuvering System Pods. Status: In Production. Comments: Two pods, mounted each side of vertical stabilizer, provide propulsion for orbit insertion, maneuver, and de-orbit.

Status: Study 1984.
Gross mass: 1,575,493 kg (3,473,367 lb).
Height: 56.00 m (183.00 ft).
Diameter: 8.70 m (28.50 ft).
Thrust: 21,107.40 kN (4,745,132 lbf).

More... - Chronology...


Associated Countries
Associated Engines
  • None Indicates that the stage shown is a propellant tank. The engine on another stage is drawing propellants from this tank. Performance shown is for that of the engine on the other stage. First flight 1964. More...
  • OME Aerojet N2O4/MMH rocket engine. 26.7 kN. Study 1972. Isp=316s. Engine used in Shuttle Orbiter Orbital Maneuvering System pods, for orbit insertion, maneuvering, and re-entry initiation. First flight 1981. More...
  • SSME Rocketdyne lox/lh2 rocket engine. 2278 kN. In production. Isp=453s. Space Shuttle Main Engines; only high-pressure closed-cycle reusable cryogenic rocket engine ever flown. . Three mounted in the base of the American space shuttle. First flight 1981. More...
  • STME Rocketdyne lox/lh2 rocket engine. 2890 kN. Cancelled 1984. Isp=430s. Space Transportation Main Engine. Rocketdyne was teamed with Aerojet and Pratt & Whitney on the STME, which was to have powered the next generation of large launch vehicles. More...

See also
  • Shuttle The manned reusable space system which was designed to slash the cost of space transport and replace all expendable launch vehicles. It did neither, but did keep NASA in the manned space flight business for 30 years. More...
  • Winged In the beginning, nobody (except Jules Verne) thought anybody would be travelling to space and back in ballistic cannon balls. The only proper way for a space voyager to return to earth was at the controls of a real winged airplane. More...

Associated Manufacturers and Agencies
  • NASA American agency overseeing development of rockets and spacecraft. National Aeronautics and Space Administration, USA, USA. More...

Associated Stages
  • Shuttle Tank Lox/LH2 propellant rocket drop tank. Loaded/empty mass 750,975/29,930 kg. Vacuum specific impulse 455 seconds. Original version. More...
  • Shuttle LRB Lox/LH2 propellant rocket stage. Loaded/empty mass 350,000/52,000 kg. Thrust 10,318.11 kN. Vacuum specific impulse 435 seconds. More...
  • Shuttle Orbiter Lox/LH2 propellant rocket stage. Loaded/empty mass 99,318/99,117 kg. Thrust 6,834.30 kN. Vacuum specific impulse 455 seconds. More...
  • Shuttle Orbiter OMS N2O4/MMH propellant rocket stage. Loaded/empty mass 25,200/3,600 kg. Thrust 53.38 kN. Vacuum specific impulse 316 seconds. Two pods, mounted each side of vertical stabilizer, provide propulsion for orbit insertion, maneuver, and de-orbit. More...

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