Vacuum leakage tests of a simulated lightweight spacecraft air lock
Otto F. Trout (Jr.), United States. National Aeronautics and Space Administration, Langley Research Center
National Aeronautics and Space Administration, 1970 - Technology & Engineering - 45 pages
A lightweight simulated spacecraft air-lock structure was tested under high vacuum to evaluate structural sealing problems and to determine leakage rates. Three different types of hatch configurations and three different seal configurations were tested for a temperature range of from -40° F (-40° C) to 200' F (930 C). Leakage rates of less than 1 x cc/sec or less than 10 (to the power of negative 4) cc/day of helium (standard temperature and pressure) were attained for each hatch.
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50 cycles air lock mounted air-lock structure aluminum atmosphere Average temperature cc/day of helium cc/sec after 50 closed position Closed Room constructed of 2014-T6 contoured hatch cooling tests cycles of hatch cylindrical section cylindrical shell elastomer expander rings Figure 12 Figure 25 function hatch and frame hatch and hatch hatch configurations hatch frame hatch pressure loaded heating tests honeycomb core illustrated in figure inch inflatable seal interior isolation blanket Langley Research Center latching mechanism leakage measurements leakage rate LEAKAGE TESTS lightweight simulated spacecraft liquid nitrogen lubricant Maximum leakage maximum measured leakage molded seal molybdenum disilicide NASA open position Open Room Otto F outgassing presented in reference presents the leakage pressure-equalization valve rate of hatch reported in reference seal on hatch seals test chamber section was mounted shown in figure SPACECRAFT AIR LOCK structural deflections structural loading structural sealing problems Temperature Tests tests on hatch thermocouples ture unseating vacuum seals test