Encyclopedia Astronautica
IHLLV


American orbital launch vehicle. Same concept as Shuttle C. Shuttle orbiter replaced by recoverable pod with shuttle main engines and payload cannister. Quick way for US to obtain heavy payload capability and reduce shuttle cost per kg to orbit by 3 X.

LEO Payload: 77,000 kg (169,000 lb) to a 400 km orbit at 28.00 degrees in 1985 dollars. Flyaway Unit Cost $: 84.970 million.

Stage Data - IHLLV

  • Stage 0. 2 x Shuttle SRB. Gross Mass: 589,670 kg (1,299,990 lb). Empty Mass: 86,183 kg (190,000 lb). Thrust (vac): 11,519.999 kN (2,589,799 lbf). Isp: 269 sec. Burn time: 124 sec. Isp(sl): 237 sec. Diameter: 3.71 m (12.17 ft). Span: 5.10 m (16.70 ft). Length: 38.47 m (126.21 ft). Propellants: Solid. No Engines: 1. Engine: SRB. Other designations: Solid Rocket Booster. Status: In Production.
  • Stage 1. 1 x Shuttle C. Gross Mass: 36,360 kg (80,160 lb). Empty Mass: 34,380 kg (75,790 lb). Thrust (vac): 6,834.303 kN (1,536,412 lbf). Isp: 313 sec. Burn time: 120 sec. Isp(sl): 0.0000 sec. Diameter: 6.30 m (20.60 ft). Span: 6.30 m (20.60 ft). Length: 21.00 m (68.00 ft). Propellants: N2O4/MMH. No Engines: 2. Engine: OME. Other designations: IHLLV; Interim Heavy Lift Launch Vehicle. Status: Study 1980.
  • Stage 2. 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.

AKA: Interim Heavy Lift Launch Vehicle.
Status: Study 1980.
Gross mass: 1,966,675 kg (4,335,776 lb).
Payload: 77,000 kg (169,000 lb).
Height: 56.00 m (183.00 ft).
Diameter: 8.70 m (28.50 ft).
Thrust: 20,299.20 kN (4,563,442 lbf).
Apogee: 400 km (240 mi).

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...
  • SRB Thiokol solid rocket engine. 11,520 kN. Isp=269s. Segmented solid rocket boosters for the compromised space shuttle design. Field joint design led to Challenger shuttle disaster. Production 1981-1985, after which superseded by RSRM's. 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 C N2O4/MMH propellant rocket stage. Loaded/empty mass 36,360/34,380 kg. Thrust 6,834.30 kN. Vacuum specific impulse 313 seconds. More...
  • Shuttle SRB Solid propellant rocket stage. Loaded/empty mass 589,670/86,183 kg. Thrust 11,520.00 kN. Vacuum specific impulse 269 seconds. Original configuration. More...
  • Shuttle Tank Lox/LH2 propellant rocket drop tank. Loaded/empty mass 750,975/29,930 kg. Vacuum specific impulse 455 seconds. Original version. More...

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