Vacuum leakage tests of a simulated lightweight spacecraft air lock

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National Aeronautics and Space Administration, 1970 - Technology & Engineering - 45 pages
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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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