Vacuum Leakage Tests of a Simulated Lightweight Spacecraft Air LockA 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. |
Common terms and phrases
50 cycles air lock mounted air-lock structure air-lock system Aluminum honeycomb atmosphere Average temperature butyl O-ring Cam roller cc/sec after 50 cc/sec Leakage rate closed position Closed Room constructed of 2014-T6 cooling hatch cooling tests Cross-sectional diagram cycles of hatch cylindrical section deflection plate elastomer expander rings Figure 12 Figure 17 Figure 28 function hatch and frame hatch and hatch hatch configurations hatch frame heating hatch heating tests honeycomb core inch inflatable seal insulating cover interior isolation blanket Langley Research Center Latching handle latching mechanism leakage measurements LEAKAGE TESTS liquid nitrogen maximum measured leakage meter molded seal molybdenum disilicide N/m² NASA O-ring seal open position Open Room outgassing presents the leakage pressure-equalization valve Push-pull actuation lever rate of hatch Retainer lip seal on hatch seals test chamber section was mounted shown in figure SPACECRAFT AIR LOCK structural deflections structural loading structural sealing problems Temperature Tests thermocouples unseating vacuum seals test