NASA LogoNTRSNTRS - NASA Technical Reports ServerSearchmore_vertCollectionsAboutNewsHelpLogin Back to ResultsAmes Research Center Shear Tests of SLA-561V Heat Shield Material for Mars-PathfinderThis report describes the results of arc-jet testing at Ames Research Center on behalf of Jet Propulsion Laboratory (JPL) for the development of the Mars-Pathfinder heat shield. The current test series evaluated the performance of the ablating SLA-561V heat shield material under shear conditions. In addition, the effectiveness of several methods of repairing damage to the heat shield were evaluated. A total of 26 tests were performed in March 1994 in the 2 in. X 9 in. arc-heated turbulent Duct Facility, including runs to calibrate the facility to obtain the desired shear stress conditions. A total of eleven models were tested. Three different conditions of shear and heating were used. The non-ablating surface shear stresses and the corresponding, approximate, non-ablating surface heating rates were as follows: Condition 1, 170 N/m(exp 2) and 22 W/cm(exp 2); Condition 2, 240 N/m(exp 2) and 40 W/cm(exp 2); Condition 3, 390 N/m(exp 2) and 51 W/cm(exp 2). The peak shear stress encountered in flight is represented approximately by Condition 1; however, the heating rate was much less than the peak flight value. The peak heating rate that was available in the facility (at Condition 3) was about 30 percent less than the maximum value encountered during flight. Seven standard ablation models were tested, of which three models were instrumented with thermocouples to obtain in-depth temperature profiles and temperature contours. An additional four models contained a variety of repair plugs, gaps, and seams. These models were used to evaluated different repair materials and techniques, and the effect of gaps and construction seams. Mass loss and surface recession measurements were made on all models. The models were visually inspected and photographed before and after each test. The SLA-561 V performed well; even at test Condition 3, the char remained intact. Most of the resins used for repairs and gap fillers performed poorly. However, repair plugs made of SLA-561V performed well. Approximately 70 percent of the thermocouples yielded good data.Document ID19960049758Acquisition SourceAmes Research CenterDocument TypeTechnical Memorandum (TM)AuthorsTauber, Michael*(Thermoscience Inst. Moffett Field, CA United States)*Tran, Huy*(NASA Ames Research Center Moffett Field, CA United States)*Henline, William*(NASA Ames Research Center Moffett Field, CA United States)*Cartledge, Alan*(NASA Ames Research Center Moffett Field, CA United States)*Hui, Frank*(NASA Ames Research Center Moffett Field, CA United States)*Tran, Duoc*(Thermoscience Inst. Moffett Field, CA United States)*Zimmerman, Norm*(Thermoscience Inst. Moffett Field, CA United States)*Date AcquiredSeptember 6, 2013Publication DateSeptember 1, 1996Subject CategoryAircraft Design, Testing And PerformanceReport/Patent NumberNAS 1.26:110402A-961865NASA-TM-110402Accession Number96N34006Funding Number(s)PROJECT: RTOP 232-01-04Distribution LimitsPublicCopyrightWork of the US Gov. Public Use Permitted.Available DownloadsNameType19960049758.pdfSTIcloud_downloadcontent_copyvisibilityRelated RecordsThere are no records associated with this record.visibility_offNo Preview Available
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