NASA NTRS · 19660000522
Study of vortex valve for medium temperature solid propellants
Abstract
Fluid state vortex valve secondary injection control system shows considerable promise for future application to solid propellant rocket engine thrust vector control. The single axis injection system tested would be capable of providing secondary injection thrust vector control using 2000 deg F gas.
Keep this discovery
Explore connections, maps & timelines
Holt, W. D., Rivard, J. G.. 1966-12-01. Study of vortex valve for medium temperature solid propellants. https://ntrs.nasa.gov/citations/19660000522
Cite the original work for its findings. Save a collection to share your selection of sources.