Development of Frontal Section for Super-Orbital, Lifting, Re-Entry Vehicle, Volume III: Asset Nose Cap
Report Number: FDL TDR 64-59 Volume 3
Author(s): Licciardello, M. R.
Corporate Author(s): International Harvester Company
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1964-05-29
Pages: 177
Contract: AF 33(616)-8497
DoD Project: 1368
DoD Task: 136804
Identifier: AD0442591
Abstract:
A tungsten-thoria composite structure was selected for use on the nose cap of the ASSET glide reentry vehicle. The design, fabrication, and qualification ground tests for that nose cap are presented. The maximum stagnation point hot wall flux was 206 Btu/sq ft. sec, resulting in a maximum thoria surface temperature of 4150 F and a maximum temperature of the tungsten structure of 3300 F. Based on measured thermal properties of thoria, a composite design was developed, weighing a total of 12.8 pounds. A test nose cap survived a static pressure load test to 320 pounds; acoustic vibration to 155 db; and a combined temperature/vibration test of 10 g at 2000 F and 3 g at 4100 F. Other nose caps were tested successfully in a plasma arc tunnel at surface temperatures to 5000 F.
Provenance: Lockheed Martin Missiles & Fire Control
Author(s): Licciardello, M. R.
Corporate Author(s): International Harvester Company
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1964-05-29
Pages: 177
Contract: AF 33(616)-8497
DoD Project: 1368
DoD Task: 136804
Identifier: AD0442591
Abstract:
A tungsten-thoria composite structure was selected for use on the nose cap of the ASSET glide reentry vehicle. The design, fabrication, and qualification ground tests for that nose cap are presented. The maximum stagnation point hot wall flux was 206 Btu/sq ft. sec, resulting in a maximum thoria surface temperature of 4150 F and a maximum temperature of the tungsten structure of 3300 F. Based on measured thermal properties of thoria, a composite design was developed, weighing a total of 12.8 pounds. A test nose cap survived a static pressure load test to 320 pounds; acoustic vibration to 155 db; and a combined temperature/vibration test of 10 g at 2000 F and 3 g at 4100 F. Other nose caps were tested successfully in a plasma arc tunnel at surface temperatures to 5000 F.
Provenance: Lockheed Martin Missiles & Fire Control