Accession Number : ADA306591

Title :   Panel Flutter Studies of Boost-Vehicle Full-Scale Flight Insulation Panels.

Descriptive Note : Technical memo,

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CEN TER

Personal Author(s) : Nacht, Michael L. ; Greene, Richard L.

PDF Url : ADA306591

Report Date : 1966

Pagination or Media Count : 17

Abstract : Two full-scale quarter-segment Centaur flight insulation panels were tested in the Lewis 10- by 10-foot supersonic wind tunnel over a Mach number range of 2.0 to 3. 5 at a 0 deg angle of attack. The test objective was to determine the ability of the panels to resist flutter under conditions simulating the flight environment. Mach number, dynamic pressure, and panel tension were the primary test variables, and liquid nitrogen was employed to produce cryogenic temperatures on the underside of the panels. Analytical comparison of panel characteristics with a conservative flutter criteria which neglected the stiffness of the supporting tank indicated that panel resistance to flutter was questionable. Examination of strain-gage output used to detect panel movement during the tunnel tests revealed that no flutter was experienced by the panels at any of the test conditions.

Descriptors :   *LAUNCH VEHICLES, STRAIN GAGES, MACH NUMBER, EPOXY RESINS, FLIGHT SIMULATION, AERODYNAMIC HEATING, SEALING COMPOUNDS, ADHESIVES, SUPERSONIC WIND TUNNELS, FLUTTER, THERMAL INSULATION, CRYOGENIC PROPELLANTS.

Subject Categories : Unmanned Spacecraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE