Liquid Behavior through a Capillary Microchannel Contactor in a Reduced Gravity Aircraft

A reliable, efficient, cost-effective carbon dioxide (CO2) removal and dehumidification system is needed for deep space exploration. Current CO2 removal technology on the International Space Station (ISS) utilizes solid zeolite media that is prone to dusting, requires high regeneration temperatures, frequent maintenance, and has a fixed low absorption capacity. NASA has begun investigating an alternative approach using liquid sorbents. Liquid sorbents have a favorable capacity, four times greater than current solid zeolites, low regeneration temperature, and require fewer unreliable moving mechanical parts than solid based systems. Knowledge of liquid morphology in microgravity however is limited and currently under investigation. This paper presents the study and findings of an experiment conducted on NASA’s C-9 reduced gravity aircraft examining viscous liquid behavior in a capillary driven 3D printed microchannel reactor through a closed loop system.