This rocket test stand is designed to test “breadboard” rocket engine chambers, pre-burners, nozzles, and turbopumps. The test stand is unique in that these components can be tested without the necessity to run a full-up engine configuration to obtain data on an individual component.

The test stand has high and low pressure run tanks for liquid oxygen and liquid hydrogen along with an RP (kerosene) tank for testing Russian rocket engines.  The high pressure tanks are rated at 10,000 psi and are routinely pressurized to 9,000 psi to feed the pre-burner while testing the LOX and hydrogen turbopumps for space shuttle main engines. Gaseous hydrogen is produced by high pressure vaporizers and is stored at 12,000 psi. Similar storage is provided for high pressure nitrogen.  These gases are used for tank pressurization to force the propellants into the pre-burner.  Propellant flow rates of 19,000 gpm were achieved. 

EDF was a part of the design team that configured the test stands, designed the flow paths, designed the operator's console, and configured the data acquisition system.  EDF was also responsible for designing a major portion of the high response control system that controlled the operation of seventeen electro-hydraulic control valves, many of which operated at 7,000-9,000 psi along with numerous pneumatic and motorized valves.  The control system also contained a digital sequencer with one millisecond resolution, a high response test termination system, a real time computer model of the control system dynamics for pre-run checkout and numerous operational displays and control panels.  This control system was designed to simulate the four second acceleration rates that the turbopumps would experience when used on the Space Shuttle main engines.