NDLI: Design and fabrication of a stringer stiffened discrete-tube actively cooled panel for a hypersonic aircraft

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Design and fabrication of a stringer stiffened discrete-tube actively cooled panel for a hypersonic aircraft

Content Provider	NASA Technical Reports Server (NTRS)
Author	Halenbrook, R. G. Anthony, F. M.
Copyright Year	1981
Description	A 0.61 x 1.22 m (2 x 4 ft) test panel was fabricated and delivered to the Langley Research Center for assessment of the thermal and structural features of the optimized panel design. The panel concept incorporated an aluminum alloy surface panel actively cooled by a network of discrete, parallel, redundant, counterflow passage interconnected with appropriate manifolding, and assembled by adhesive bonding. The cooled skin was stiffened with a mechanically fastened conventional substructure of stringers and frames. A 40 water/60 glycol solution was the coolant. Low pressure leak testing, radiography, holography and infrared scanning were applied at various stages of fabrication to assess integrity and uniformity. By nondestructively inspecting selected specimens which were subsequently tested to destruction, it was possible to refine inspection standards as applied to this cooled panel design.
File Size	7356416
Page Count	90
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19810010957
Archival Resource Key	ark:/13960/t7bs3mf3m
Language	English
Publisher Date	1981-02-01
Access Restriction	Open
Subject Keyword	Structural Mechanics Panels Temperature Distribution Cooling Structural Stability Counterflow Aluminum Alloys Structural Design Criteria Redundant Components Adhesive Bonding Hypersonic Aircraft Aircraft Structures Stringers Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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