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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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Summary of industry survey and literature search of ignition spike phenomena in low thrust, hypergolic, liquid bipropellant rocket engines
Torodial ring welded to the vent stack outlet prevents static discharges which ignite combustible gases in a venting system. The ring inhibits the flow of current by removing the cause of turbulence characteristics of a sharply defined vent exit.
Ignition pressure transient in solid rocket motors, examining chamber filling interval, flame propagation, heat transfer correlation, burning area, etc
Elastomeric materials thermostability in simulated spacecraft environment tested to obtain ignition point values
Ignition kinetics of carbon monoxide-oxygen reaction
Additives effect on ignition delay and pressure of hypergolic hydrazine-nitrogen tetroxide propellant systems.
Mathematical analysis of flame propagation at high pressures over surface of igniting solid propellants and propellant ingredients in oxygen/inert atmospheres
Ignition kinetics of carbon monoxide-oxygen reaction
Design and test performance of igniter system for solid propellant applications technology satellite apogee rocket motor
Hypergolic ignition of polymeric fuels with oxygen
Initial air boundary layer effect on ignition of slot-injected gaseous hydrogen in supersonic airstream, discussing isotherm and streamline patterns
Switchless spark discharge system for improved minimum ignition energy measurements of premixed gaseous combustible mixture
Optimal determination of vehicle ignition and cut-off masses, discussing applications to Saturn S-4B Stage flight evaluation
Spectrographic method determines individual stainless steel components in molten bismuth-42 w/o tin eutectic to determine the solubility of Type 304 stainless steels. It utilizes the high sensitivity and precision of the spark-ignited, low-voltage ac-arc excitation of samples rendered homogeneous by dissolution.
Evaluation of ignition mechanisms for spacecraft materials in simulated spacecraft cabin atmospheres
Ignition mechanism of hydrazine-nitrogen dioxide hypergolic propellant system
Vacuum ignition characteristics of Flox-diborane and oxygen difluoride-diborane