• Capability for long duration space environment soaking of engine module of complete launch vehicle prior to engine start
• Capable of 5 torr engine exhaust duct pressure throughout engine firings while maintaining high altitude soaking conditions
• Can duplicate multiple ignition sequence to accurately simulate actual space flight operation
• Successful history of more than 100 hot firings of RL10 engines during Centaur development, 80 firings of current RL10B-2 engine for Delta-3 development, and 12 firings of the Delta 3 Upper Stage

Vacuum Chamber
• 35 ft in diameter by 55 ft tall, vertical stainless steel chamber

Vacuum Range
• 10^-7 torr long duration vaccum capability (Local atmospheric pressure to 200 statute miles altitude)

Thrust Capability
• Up to 400,000lb of thrust

Thermal Conditioning
Vacuum chamber surfaces are lined with a liquid nitrogen cold wall, capable of maintaining -320 °F. A quartz infrared heating system can be programmed to radiate a sinusoidal distribution, simulating rotational solar heating.

Chamber Access
• 27-ft-diameter top hatch for equipment loading, two 6.5-ft personnel entry doors.

Spray Chamber
• 67 ft in diameter by 118 ft deep, located immmediately below the vacuum chamber; 1.75 million gallons of chilled water for cooling exhaust gases; deluge system with 11000 hp (240000 gallons per minute) pumping capacity.

Supply Systems
• Liquid hydrogen, liquid oxygen, liquid nitrogen; gaseous nitrogen and helium, and other storable fuels/gases

Altitude Exhaust Systems
• Two, three-stage steam-operated ejector systems provide the exhaust capability. • The system can provide a launch ascent pressure profile and maintain altitude exhaust condition during engine firing for up to 90000 ft altitude

Test Control
Control room located 2600 ft from the test site.