Encyclopedia Astronautica
Orion LAS



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Orion LAS
Credit: NASA
American manned spacecraft module. Orion launch abort system; consists of launch escape tower, adapter cone, and boost protective cover. Provides emergency crew escape during early boost phase of ascent to orbit.

Engine layout follows Soviet Soyuz/TKS design practice as opposed to earlier US Mercury/Apollo designs.

Configuration Summary:

  • Abort Motor
    • No. of Nozzles:4
    • Nozzle Cant Angle (to CL): 30
    • Isp (sea level):250s
    • Thrust (Total in Vehicle Axis):506,408 lbs / 2253 kN
    • Burn Time:2.0s
    • T/W:15:1
  • Attitude Control Motor
    • No. of Nozzles:8
    • Nozzle Cant Angle (to CL):90
    • Isp (vac):227s
    • Thrust (per Nozzle):2500 lbs / 11 kN
    • Burn Time:20s
  • Jettison Motor
    • No. of Nozzles:4
    • Nozzle Cant Angle (to CL): 35
    • Isp (vac.):221s
    • Thrust (per Nozzle):9668 lbs / 43 kN
    • Burn Time:1.5 s

Characteristics

RCS Coarse No x Thrust: 8 x 11 kN. RCS specific imulse: 227 sec.

Gross mass: 6,176 kg (13,615 lb).
Unfuelled mass: 3,696 kg (8,148 lb).
Height: 11.60 m (38.00 ft).
Diameter: 0.40 m (1.31 ft).
Thrust: 2,253.00 kN (506,494 lbf).
Specific impulse: 250 s.

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Associated Countries
Associated Spacecraft
  • Orion American manned spacecraft. In development. NASA's Crew Excursion Vehicle for the 21st Century More...

See also
Associated Propellants
  • Solid Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. More...

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