EFFECT OF COMPOSITION ON COMBUSTION OF SOLID PROPELLANTS DURING A RAPID PRESSURE DECREASE
Effect of composition on combustion of solid propellants during a rapid pressure drop
SEARCH · Engineering Papers
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Effect of composition on combustion of solid propellants during a rapid pressure drop
Advanced high energy space storable propellant - oxygen bifluoride, diborane
Heated-hybrid generated gas pressurization system for liquid propellant transfer in rocket vehicles
Liquid dynamics in rocket propellant tanks
Aluminum additive in unstable combustion of solid rocket propellants - growth, evaporation and burning rates in flame zone
Study of cryogenic-propellant heating in the thermal environment of space
Propellant mass measurement in a rocket fuel tank at any time during zero gravity conditions
Engineering problems encountered in the development of propellant feed systems
Research on mechanism of ignition of solid rocket propellants
Injection mass flux distributions and resonant combustion effects on local heat transfer in liquid propellant rocket engine
Liquid propellant slosh control - design application of linearized theory
Equations for dynamic behavior of liquid propellants sloshing in mobile tanks of arbitrary shape
Capacitance sensors for measuring liquid propellant sloshing in space vehicle fuel tanks
Effect of absorptance/emittance ratio on storage of cryogenic propellants in deep space
Performance of composite solid propellant at simulated high altitudes
Large aluminum particle behavior in composite propellant combustion
Spontaneous ignition and reaction characteristics of hypergolic propellant pair in low pressure and temperature environment, specifically hydrazine fuel and nitrogen tetroxide atmosphere
Burning rate, grain geometries and propulsion parameters derived for solid propellant rocket engines