Encyclopedia Astronautica

NLS - Martin
NLS - Martin Marrietta 'stage-and-a-half' design
Credit: Lockheed Martin
American heavy-lift orbital launch vehicle. NLS Heavy Lift Version. Lower cost expendable launch vehicle studied by NASA/USAF in late 1980's.

in: 1985 dollars. Flyaway Unit Cost $: 59.000 million.

Stage Data - NLS HLV

  • Stage 1. 1 x NLS HLV. Gross Mass: 833,732 kg (1,838,064 lb). Empty Mass: 62,757 kg (138,355 lb). Thrust (vac): 14,310.000 kN (3,217,010 lbf). Isp: 425 sec. Burn time: 221 sec. Isp(sl): 350 sec. Diameter: 8.70 m (28.50 ft). Span: 8.70 m (28.50 ft). Length: 52.00 m (170.00 ft). Propellants: Lox/LH2. No Engines: 4. Engine: STME. Other designations: National Launch System. Status: Study 1991.

AKA: National Launch System; New Launch System.
Status: Study 1991.
Gross mass: 833,732 kg (1,838,064 lb).
Height: 62.00 m (203.00 ft).
Diameter: 8.70 m (28.50 ft).
Thrust: 11,791.00 kN (2,650,722 lbf).

More... - Chronology...

Associated Countries
Associated Engines
  • 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
  • NLS New (or National) Launch System (NLS) joint NASA/USAF studies began in 1989, following the demise of the ALS. They proposed development of a family of launch vehicles using a new STME engine to replace the existing ‘high cost' boosters derived from 1950's missile designs. The $12 billion nonrecurring cost was nearly that estimated for ALS, and this cost could not be recouped at projected launch rates. NLS was terminated in 1991. More...

Associated Stages
  • NLS HLV Lox/LH2 propellant rocket stage. Loaded/empty mass 833,732/62,757 kg. Thrust 14,310.00 kN. Vacuum specific impulse 425 seconds. More...

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