Artificial meteor ablation studies - Iron oxides
Artificial meteor ablation studies of natural minerals composed of magnetite and hematite
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Artificial meteor ablation studies of natural minerals composed of magnetite and hematite
Light weight, low cost, ablative thermal protection system for space shuttles
Design of low cost ablator leading edge for space shuttle thermal protection system
Development and testing of ablative rocket engine with selected 7.62 cm /3.0 in./ diameter throat inserts, and testing of zirconia reinforced with tungsten-rhenium wire for throat insert material
Numerical method of unsteady adjustment for calculating inviscid flow fields about convex and concave shapes on atmospheric entry with ablation
Low cost replaceable ablative heat shield panels for space shuttles
Evaluation of selected low-cost ablative materials for large solid rocket engine nozzle design
Ablative response of silica phenolic to simulated liquid propellant rocket engine operating conditions
Computer program for analyzing transient response of ablating axisymmetric bodies including effects of shape change
Analysis of reacting flow of pyrolysis products through char layer of low density, nylon phenolic resin, charring ablators and porous graphite
Ablative heat shield char layer, examining reacting nonequilibrium pyrolysis gas flow
Ablative materials performance in high radiative heat flux environments produced by CW carbon dioxide laser
Thoria dispersed Ni-Cr alloy hypersonic entry ablation model, accounting for Cr oxidation
Artificial meteors ablation and luminosity measurements, using ballistic range shadowgraph and radiometric equipment for velocity history, shock wave formation and mass loss process
Cone roll dynamics-ablation patterns coupling in hypersonic wind tunnels
Epoxy novolac resin-cured alicyclic anhydride amine-catalyzed ablative polymers molecular structure from computer correlation of analytical data
Ablative polymers synthesis from formaldehyde, phenols and ethers reaction products, discussing char yield, thermally stable fillers incorporation and thermogravimetric analysis
Graphite ablation under high temperatures for large outer planets entry probes, correlating mass loss rates with surface temperatures and specimen nose cone radii