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): 30º
- 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):90º
- Isp (vac):227s
- Thrust (per Nozzle):2500 lbs / 11 kN
- Burn Time:20s
- Jettison Motor
- No. of Nozzles:4
- Nozzle Cant Angle (to CL): 35º
- 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
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Orion American manned spacecraft. In development. NASA's Crew Excursion Vehicle for the 21st Century More...
See also
Associated Propellants
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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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