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Title
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Development of Frontal Section for Super-Orbital, Lifting, Re-Entry Vehicle, Volume III: Asset Nose Cap
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Date
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1964
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Index Abstract
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Coming Soon
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Photo Quality
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Complete
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Report Number
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FDL TDR 64-59 Volume 3
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Creator
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Licciardello, M. R.
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Corporate Author
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International Harvester Company
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Laboratory
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Air Force Flight Dynamics Laboratory
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Date Issued
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1964-05-29
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Extent
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177
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Identifier
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AD0442591
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Access Rights
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DDC release to OTS not authorized
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Distribution Classification
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1
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Contract
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AF 33(616)-8497
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DoD Project
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1368
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DoD Task
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136804
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DTIC Record Exists
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No
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Distribution Change Authority Correspondence
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AFFDL LTR
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Abstract
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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.
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Report Availability
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Full text available
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Provenance
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Lockheed Martin Missiles & Fire Control
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Type
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report
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Format
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1 online resource
FDLTDR64-059volume03.pdf