Add to ORKGThe thermal performance of shadow shields, and their support struts, for the thermal protection of cryogenic propellants in a simulated deep-space environment was investigated analytically and experimentally. Very low overall heat-transfer rates were obtained when highly reflective aluminized Mylar shadow shields were used. The thermal interactions between the shields and support struts were investigated with fair to good agreement between the analysis and experimental data. The exterior surface of both fiberglass and titanium struts was coated to reduce the heat input into the test tank. The vacuum level inside the test facility strongly influenced the heat-transfer rates
Design criteria and fabrication techniques for regeneratively cooled rocket thrust chamber
Heat and mass transfer, thermodynamics, fluid mechanics, and energy conversion studies for space fli...
An apparatus is described which can deliver uniform heat flux densities of up to 80 W/sq cm over an ...
Design concepts are developed and evaluated for a cooled structures assembly for the Scramjet engine...
Teflon and high density phenolic-nylon models evaluated at various enthalpies and heating rates unde...
A study performed to continue development of computational techniques for the Space Shuttle Thermal ...
The results of a thermal-structural test program to verify the performance of a metallic/radiative T...
During this reporting period, theoretical work on the secondary atomization process was continued an...
Low thrust chemical propulsion systems were sized for transfer of large space systems from LEO to GE...
Design and fabrication of sterilization container and model probe assembly for Mars landing capsul
High temperature materials were surveyed, and Inconel 617 and titanium were selected for application...
Determining discrepancy between theoretically calculated thermoconductivity of high temperature nitr...
This project was aimed at determining thermal conductivity, specific heat and thermal expansion of a...
Foil enclosure configurations of 10 variations were fabricated and evaluated. A discussion of the th...
Passive temperature control coatings for Apollo spacecraft ablative thermal protection syste
Design criteria and fabrication techniques for regeneratively cooled rocket thrust chamber
Heat and mass transfer, thermodynamics, fluid mechanics, and energy conversion studies for space fli...
An apparatus is described which can deliver uniform heat flux densities of up to 80 W/sq cm over an ...
Design concepts are developed and evaluated for a cooled structures assembly for the Scramjet engine...
Teflon and high density phenolic-nylon models evaluated at various enthalpies and heating rates unde...
A study performed to continue development of computational techniques for the Space Shuttle Thermal ...
The results of a thermal-structural test program to verify the performance of a metallic/radiative T...
During this reporting period, theoretical work on the secondary atomization process was continued an...
Low thrust chemical propulsion systems were sized for transfer of large space systems from LEO to GE...
Design and fabrication of sterilization container and model probe assembly for Mars landing capsul
High temperature materials were surveyed, and Inconel 617 and titanium were selected for application...
Determining discrepancy between theoretically calculated thermoconductivity of high temperature nitr...
This project was aimed at determining thermal conductivity, specific heat and thermal expansion of a...
Foil enclosure configurations of 10 variations were fabricated and evaluated. A discussion of the th...
Passive temperature control coatings for Apollo spacecraft ablative thermal protection syste
Design criteria and fabrication techniques for regeneratively cooled rocket thrust chamber
Heat and mass transfer, thermodynamics, fluid mechanics, and energy conversion studies for space fli...
An apparatus is described which can deliver uniform heat flux densities of up to 80 W/sq cm over an ...