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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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Quenching distances for flaming thin polymer films, and fire extinguisher using inert gas to reduce fire hazards in spacecraft cabin atmospheres
Chemical kinetic model for hydrocarbon fuels combustion and application to multidimensional finite difference mixing analyses in hypersonic engines and nozzles
Laser ignited combustion of 365 micron Zr droplets falling in ultrapure oxygen using spectroscopic and photographic techniques, discussing vapor phase transport phenomena
Propane annular combustor for use in miniature gas turbine engine for wind tunnels
Reaction heat for flameless combustion of double- base propellant using differential scanning calorimetry and thermogravimetric analysis, noting pressure effects
Combustion characteristics and safety factors for hydrogen diffusion flames in flare stack operations
Effect of fuel distribution and flame stabilization techniques on combustion stability limits for swirl-can combustor modules
Combustion properties of Teflon insulated wires in supercritical oxygen at normal and zero gravities
Numerical analysis of energy release rates during combustion caused by periodic flow field disturbances
Reaction heat for flameless combustion of double- base propellant using differential scanning calorimetry and thermogravimetric analysis, noting pressure effects
Photographic study of acceleration and pressure effects on Al agglomerates and combustion processes on solid propellant surface, describing pit growth by combustion model
A computer program was developed which performs an error analysis of a minimum-fuel, finite-thrust, transfer maneuver between two Keplerian orbits in the vicinity of Mars. The method of analysis is the Monte Carlo approach where each off-nominal initial orbit is targeted to the desired final orbit. The errors in the initial orbit are described by two covariance matrices of state deviations and tracking errors. The function of the program is to relate these errors to the resulting errors in the final orbit. The equations of motion for the transfer trajectory are those of a spacecraft maneuvering with constant thrust and mass-flow rate in the neighborhood of a single body. The thrust vector is allowed to rotate in a plane with a constant pitch rate. The transfer trajectory is characterized by six control parameters and the final orbit is defined, or partially defined, by the desired target parameters. The program is applicable to the deboost maneuver (hyperbola to ellipse), orbital trim maneuver (ellipse to ellipse), fly-by maneuver (hyperbola to hyperbola), escape maneuvers (ellipse to hyperbola), and deorbit maneuver.
The ignition of a combustible gas mixture by a hot cylinder under the effect of a gravity field for steady state conditions is examined. For this purpose a horizontal cylinder is considered with gravity as a parameter together with a finite chemical reacting flow generated by free convection with the additional effect of diffusion. Both mass transfer and zero mass transfer cases are considered. By defining an ignition criterion the surface temperature and species are obtained from the analysis as a function of the gravity field. It is supposed that at the point of ignition the heat evolved in the gas is sufficiently high to attain a sustained combustion without any energy from the hot cylinder.
Various space shuttle ascent configurations were tested in a trisonic wind tunnel to determine the aerodynamic characteristics. The ascent configuration consisted of a NASA/MSC 040 orbiter in combination with various HO centerline tank and booster geometries. The aerodynamic interference between components of the space shuttle and the effect on the orbiter aerodynamics was determined. The various aerodynamic configurations tested were: (1) centerline HO tanks T1 and T2, (2) centerline HO tank T3, and (3) centerline HO tank H4.