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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Inducing losses in the vortex chamber of vortex valves and vortex amplifiers resolves the problem of unstable operation caused by a sufficiently large positive feedback. Induced losses also reduce pressure gain and throttling range of vortex pressure amplifier.
Multiple orifice fluid flow control valve to provide different flow patterns
Solenoid two-step valve for bipropellant flow rate control to rocket engine
Design and testing of squib-actuated valve
Vacuum jacketed components on launch umbilical tower service arms at Launch Complex 39 - vacuum seal valves
High-temperature, high-pressure spherical segment valve
Gas valve operated by thermally expanding and contracting device
Actuator using compressed gas as driving force to control valve handling large liquid flows
Study, design, fabrication, and evaluation of thermally actuated valves for spacecraft instrumentation requiring small zero leakage
High pressure four-way valve with O ring adapted to pass across inlet port
Advanced mechanical valves and controls for liquid propellant rocket engines for space flights up to ten years
Research and developments in advanced spacecraft valve technology
Antiflutter check valve for use with high pressure fluid flow
Fluidic vortex valve to modulate solid propellant generated hot gas flow
NERVA engine chamber pressure control, investigating replacement of TPCV with fluidic vortex valve