High temperature reflectance measurements with the paraboloid reflectometer.
High temperature directional reflectance measurements of ablative materials as function of sample temperature using paraboloid reflectometer
Bevans, J. T.↗
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Further studies of the coupled chemically reacting boundary layer and charring ablator. Part 1 - Summary Final report
Computer program development for charring ablative materials, chemically reacting laminar boundary layers, and turbulent boundary layer initiation
Anderson, L. W.↗
A study of the potential benefits of using lower-density ablators for protecting manned lifting-body entry vehicles
Investigation of low density ablative materials for heat shields on reentry vehicles
Moss, J. N.↗
Determination of the density and chemical profiles of government-furnished charred elastomeric ablator models
Chemical analysis of ablative materials
Source record↗
High-temperature reflectance measurements with the paraboloid reflectometer.
High temperature directional reflectance measurements of ablative materials as function of sample temperature using paraboloid reflectometer
Bevans, J. T.↗
Evaluation of a polyurethane foam for ablative protection at low heating rates.
Low density polyurethane foam with and without honeycomb as ablative material for reentry vehicles, discussing oxidation resistance
Parker, J. A.↗
Comparison of the performance of a charring ablator under transient and constant combined convective and radiative heating.
Charring phenolic nylon ablator material pyrolysis and surface recession for cyclic and constant combined convective and radiative heating
Lundell, J. H.↗
Ablative thermal protection at low heating rates.
Ablative materials thermal protection characteristics at low heating rates evaluated by convective heating tests, stressing polyurethane foam composite
Goldstein, H. E.↗
Development of low cost ablative nozzles for solid propellant rocket motors, volume 1 Final report
Evaluating low cost ablative materials for use in large solid propellant rocket motors
Laramee, R. C.↗
Comparison of Methods for Determining the Composition of Pyrolysis Products from the Degradation of Ablative Composites. Status report.
Determining composition of pyrolysis products from degradation of ablative materials
April, G. C.↗
Ablative thermal protection at low heating rates
Ablative materials for thermal protection at low convective heating rates, comparing foam and state-of-art materials performance
Goldstein, H. E.↗
Ablation in a radiative environment
Radiative heating rates and gas environments effects on ablative material performance from tests at arc image facility
Baker, E. J., Jr.↗
Method for molding compounds Patent
Vacuum method for molding thermosetting compounds used as ablative materials
Heier, W. C.↗
Ablative resin Patent
Ablative resins used for retarding regression in ablative material
Burns, E. A.↗
Development of low cost ablative nozzles for large solid propellant rocket motors
Evaluation of selected low-cost ablative materials for large solid rocket engine nozzle design
Sohl, J. D.↗
Application of Ablation to a High Chamber Pressure Rocket Engine
Ablation cooling in rocket engine with combustion chamber liner and nozzle constructed of silica phenolic ablative material
Brecheisen, A. W.↗
Chemical modification of poly(p-phenylene) for use in ablative compositions
Development of ablative materials based on modification of polyphenylene compounds is discussed. Chemical and physical properties are analyzed for application as heat resistant materials. Synthesis of linear polyphenylenes is described. Effects of exposure to oxyacetylene flame and composition of resultant char layer are presented.
Parker, J. A.↗
Effective specific impulse of external nuclear pulse propulsion systems
An investigation of a simple self-similar flow model for an external nuclear pulse propulsion system indicates that to achieve the high effective specific impulse of such a system three principal factors are required. The are (1) attaining pulses of optimum energy, (2) attaining good propellant collimation, and (3) using an ablative material for the pusher surface which has high absorptivity for radiant energy at the propellant stagnation temperature.
Reynolds, T. W.↗