The use of cryogenic propellants is prioritized for powering Mars lander propulsion systems. To provide thermal protection for these cryogenic propellants, a combination of multilayer insulation (MLI) and foam is commonly employed. However, during the Mars lander ascent, space travel, and reentry, unique phenomena such as transient venting and suction of gas occur within the MLI, significantly compromising its insulation performance. In the current study, an experimental platform was developed to investigate the discharge and suction of rarefied gas in MLI microchannels. Based on the perforation MLI results, the residual gas pressure in the innermost layer reaches below 10 Pa after over 100 h of evacuation. Baked MLI exhibits favorable discharge gas performance, with an average pressure value (the sum of the interstitial pressure in MLI divided by the total number of layers) 30.85% lower than that of the original MLI. Evacuation rates are improved by 11.87% when the MLI is flushed with nitrogen (N2). The baking condition does not significantly affect suction gas properties. The thermal conductivity of residual helium (He) is much higher than that of air and N2. These findings offer valuable insights for the design of cryogenic propellant tanks, aiding in optimizing their insulation performance.
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