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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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Zirconium oxide coating enables the determination of hot gas flow patterns on liquid rocket injector face and baffle surfaces to indicate modifications that will increase performance and improve combustion stability. The coating withstands combustion temperatures and due to the coarse surface and coloring of the coating, shows the hot gas patterns.
Exposure of assembled and fueled bipropellant liquid rocket propulsion system to ethylene oxide and heat sterilization environments
Static and dynamic behavior of space storable, cryogenic liquid rocket propellants in low gravity and transient situations
Thrust chamber tests on storable liquid rocket propellant
Liquid rocket propellant droplet burning rate and lifetimes in combustion chamber
Resin systems for matrix material in ablative composite for liquid rocket combustion chambers using fluorine-containing propellants
Compatibility tests for spacecraft construction materials by specimen encapsulation with liquid rocket propellants
Compatibility during long term storage of liquid rocket propellants with spacecraft propulsion system materials
Slosh damping method for liquid rocket propellant tanks
Mechanical and nonmechanical controls for earth and space storable propellants for liquid rocket propulsion
High temperature spark plug for igniting liquid rocket propellants
Predicting performance of tandem row pump inducers for conventional and recoverable liquid rocket engines
Liquid rocket engine injector elements design criteria, using noncircular orifice geometry to predict efficiency
S-IVB liquid rocket engine and propellant feed systems restart chilldown in orbital operations
Combustion instability in liquid rocket engines
Electronic recording system for spatial mass distribution of liquid rocket propellant droplets or vapors ejected from high velocity nozzles
S-IVB liquid rocket engine and propellant feed systems restart chilldown in orbital operations
Monograph was published which summarizes and systematically orders large body of successful techniques and practices developed for design of liquid rocket engine turbopump bearings. Document was written to organize and present significant experience and knowledge accumulated by NASA in development and operational programs.