Ablation tests were performed on the insulation material used in the Pioneer F radioisotope thermoelectric generator (RTG) in the Ames Arc-Heated Planetary-Gas Wind Tunnel. Test results indicate that the material, trade name Min-K 1301, should experience little ablation for heat transfer rates below 40 BTU/sq ft-sec. If the current design were to be changed so that the various pieces of Min-K were fastened or interlocked together the total amount of heat delivered to the RTG heat source during an earth orbital decay reentry would be reduced by at least 22.7%
Reusable launch vehicle stages encounter large heat fluxes during their mission, especially during r...
Abstract (Topic: Thermoelastic design, heat shield, reentry spacecraft) For future space transportat...
Hypersonic spacecraft reentering the earth's atmosphere encounter extreme heat due to atmospheric fr...
Results of a study on thermal stress problems in an amorphous graphite heat shield that is part of t...
A comprehensive, generalized two-dimensional RTG analysis computer program was developed. This prog...
Entering a planetary atmosphere is one of the most claim missions as the space probe faces a loss of...
A spacecraft's thermal protection system (TPS) is required to survive the harsh environment experien...
System alerts personnel of hazards which may develop while they are performing tests on radioisotope...
Results are presented of a two year program to evaluate packaged thermal insulations for use under a...
During all phases of a spacecraft's mission, a Thermal Protection System (TPS) is needed to protect ...
Reentry shielding ablation measured by imbedded radioactive isotopes with radiation decto
A critical problem in the design of Thermal Protection Systems (TPS) for planetary probes and re-ent...
High temperature insulation materials for use under radiative thermal protection systems of shuttle ...
Ablative heat shield materials for Mars atmosphere entry evaluated for RF transmission loss and flex...
Radioactive isotope technique for heat shield ablation measurement during reentr
Reusable launch vehicle stages encounter large heat fluxes during their mission, especially during r...
Abstract (Topic: Thermoelastic design, heat shield, reentry spacecraft) For future space transportat...
Hypersonic spacecraft reentering the earth's atmosphere encounter extreme heat due to atmospheric fr...
Results of a study on thermal stress problems in an amorphous graphite heat shield that is part of t...
A comprehensive, generalized two-dimensional RTG analysis computer program was developed. This prog...
Entering a planetary atmosphere is one of the most claim missions as the space probe faces a loss of...
A spacecraft's thermal protection system (TPS) is required to survive the harsh environment experien...
System alerts personnel of hazards which may develop while they are performing tests on radioisotope...
Results are presented of a two year program to evaluate packaged thermal insulations for use under a...
During all phases of a spacecraft's mission, a Thermal Protection System (TPS) is needed to protect ...
Reentry shielding ablation measured by imbedded radioactive isotopes with radiation decto
A critical problem in the design of Thermal Protection Systems (TPS) for planetary probes and re-ent...
High temperature insulation materials for use under radiative thermal protection systems of shuttle ...
Ablative heat shield materials for Mars atmosphere entry evaluated for RF transmission loss and flex...
Radioactive isotope technique for heat shield ablation measurement during reentr
Reusable launch vehicle stages encounter large heat fluxes during their mission, especially during r...
Abstract (Topic: Thermoelastic design, heat shield, reentry spacecraft) For future space transportat...
Hypersonic spacecraft reentering the earth's atmosphere encounter extreme heat due to atmospheric fr...