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Orion LAS

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Orion LAS Credit: NASA

Status: In development 2016. Thrust: 2,253.00 kN (506,494 lbf). Gross mass: 6,176 kg (13,615 lb). Unfuelled mass: 3,696 kg (8,148 lb). Specific impulse: 250 s. Height: 11.60 m (38.00 ft). Diameter: 0.40 m (1.31 ft).

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

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