Add to ORKGHigh temperature materials were surveyed, and Inconel 617 and titanium were selected for application to a honeycomb TPS configuration designed to withstand 2000 F. The configuration was analyzed both thermally and structurally. Component and full-sized panels were fabricated and tested to obtain data for comparison with analysis. Results verified the panel design. Twenty five panels were delivered to NASA Langley Research Center for additional evaluation
The 'Development of Sensors for Ceramics Components in Advanced Propulsion Systems' program was divi...
Design concepts are developed and evaluated for a cooled structures assembly for the Scramjet engine...
This report covers a portion of an ongoing investigation of the durability of composites for the Hig...
The results of a thermal-structural test program to verify the performance of a metallic/radiative T...
Foil enclosure configurations of 10 variations were fabricated and evaluated. A discussion of the th...
The second task of a study with the overall objective of providing a conceptual definition of the Te...
Structural design of spacecraft subjected to thermal sterilization prior to planetary landin
Thermophysical property measurements were made under transient heating conditions on several materia...
Fabrication of three flat plate sections for silicon-germanium solar thermoelectric generato
Prototype erectable communications satellite of spherical design using plastic memory effec
The Titanium Multi-wall Thermal Protection System (TIPS) panel was re-designed to incorporate Ti-6-2...
A 0.61 x 1.22 m (2 x 4 ft) test panel was fabricated and delivered to the Langley Research Center fo...
Passive temperature control coatings for Apollo spacecraft ablative thermal protection syste
These proceedings describe the application of LDEF data to spacecraft and payload design, and emphas...
Aluminum brazed titanium (ABTi) structures were evaluated during prolonged exposure to extreme envir...
The 'Development of Sensors for Ceramics Components in Advanced Propulsion Systems' program was divi...
Design concepts are developed and evaluated for a cooled structures assembly for the Scramjet engine...
This report covers a portion of an ongoing investigation of the durability of composites for the Hig...
The results of a thermal-structural test program to verify the performance of a metallic/radiative T...
Foil enclosure configurations of 10 variations were fabricated and evaluated. A discussion of the th...
The second task of a study with the overall objective of providing a conceptual definition of the Te...
Structural design of spacecraft subjected to thermal sterilization prior to planetary landin
Thermophysical property measurements were made under transient heating conditions on several materia...
Fabrication of three flat plate sections for silicon-germanium solar thermoelectric generato
Prototype erectable communications satellite of spherical design using plastic memory effec
The Titanium Multi-wall Thermal Protection System (TIPS) panel was re-designed to incorporate Ti-6-2...
A 0.61 x 1.22 m (2 x 4 ft) test panel was fabricated and delivered to the Langley Research Center fo...
Passive temperature control coatings for Apollo spacecraft ablative thermal protection syste
These proceedings describe the application of LDEF data to spacecraft and payload design, and emphas...
Aluminum brazed titanium (ABTi) structures were evaluated during prolonged exposure to extreme envir...
The 'Development of Sensors for Ceramics Components in Advanced Propulsion Systems' program was divi...
Design concepts are developed and evaluated for a cooled structures assembly for the Scramjet engine...
This report covers a portion of an ongoing investigation of the durability of composites for the Hig...