Development of Frontal Section for Super-Orbital, Lifting, Re-Entry Vehicle, Volume II: Materials and Composite Structure Development
Report Number: FDL TDR 64-59 Volume 2
Author(s): Licciardello, M. R., Ohnysty, B., Stetson, A. R.
Corporate Author(s): International Harvester Company
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1964-05-29
Pages: 248
Contract: AF 33(616)-8497
DoD Project: 1368
DoD Task: 136804
Identifier: AD0442590
Abstract:
Development of a tungsten/thoria composite structure suitable for use on super-orbital, lifting, re-entry vehicle nose caps is presented. Tungsten was chosen as the structural material, based on extensive testing of oxidation behavior, compatibility, and mechanical properties. Thorium oxide was selected as the thermal protection system, based on high melting point, good compatibility, and high emittance at high temperature. In addition, thoria was found to sublime rather than melt at high temperature with pressures less than 0.75 atmosphere. This factor was used to allow exposure to high heat pulses of short duration. Extensive materials data are presented on measurement of emittance, expansion coefficient, thermal conductivity, oxidation resistance, and compatibility of thoria, hafnia, and zirconia. Some data on selected carbides are also included. Thoria, chemically bonded with thorium nitrate, was selected as the coating. The coating exhibited shrinkage of less than 1 percent after exposure to 5200 F for 5 minutes.
Provenance: Lockheed Martin Missiles & Fire Control
Author(s): Licciardello, M. R., Ohnysty, B., Stetson, A. R.
Corporate Author(s): International Harvester Company
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1964-05-29
Pages: 248
Contract: AF 33(616)-8497
DoD Project: 1368
DoD Task: 136804
Identifier: AD0442590
Abstract:
Development of a tungsten/thoria composite structure suitable for use on super-orbital, lifting, re-entry vehicle nose caps is presented. Tungsten was chosen as the structural material, based on extensive testing of oxidation behavior, compatibility, and mechanical properties. Thorium oxide was selected as the thermal protection system, based on high melting point, good compatibility, and high emittance at high temperature. In addition, thoria was found to sublime rather than melt at high temperature with pressures less than 0.75 atmosphere. This factor was used to allow exposure to high heat pulses of short duration. Extensive materials data are presented on measurement of emittance, expansion coefficient, thermal conductivity, oxidation resistance, and compatibility of thoria, hafnia, and zirconia. Some data on selected carbides are also included. Thoria, chemically bonded with thorium nitrate, was selected as the coating. The coating exhibited shrinkage of less than 1 percent after exposure to 5200 F for 5 minutes.
Provenance: Lockheed Martin Missiles & Fire Control