Applied Aviation Sciences
Presentation without Video
Conceptual designs for a space suit Personal Life Support Subsystem (PLSS) were developed and assessed to determine if upgrading the system using new, emerging, or projected technologies to fulfill basic functions would result in mass, volume, or performance improvements. Technologies were identified to satisfy each of the functions of the PLSS in three environments (zero-g, Lunar, and Martian) and in three time frames (2006, 2010, and 2020). The viability of candidate technologies was evaluated using evaluation criteria such as safety, technology readiness, and reliability. System concepts (schematics) were developed for combinations of time frame and environment by assigning specific technologies to each of four key functions of the PLSS -- oxygen supply, waste removal, thermal control, and power. The PLSS concepts were evaluated using the ExtraVehicular Activity System Sizing Analysis Tool, software created by NASA to analyze integrated system mass, volume, power and thermal loads. The assessment resulted in the Texas Engineering Experiment Station recommending to NASA an evolution path from the existing PLSS to a long duration, low mass PLSS suitable for Martian missions.
36th International Conference on Environmental Systems (ICES)
SAE paper 2006-01-2201
Number of Pages
Required Publisher’s Statement
This is a publication from SAE International.
Scholarly Commons Citation
Schuller, M., Kobrick, R., Lalk, T., Wiseman, L., Little, F., & et al. (2006). Innovative Schematic Concept Analysis for a Space Suit Portable Life Support Subsystem. , (). https://doi.org/10.4271/2006-01-2201
Dr. Kobrick was not affiliated with Embry-Riddle Aeronautical University at the time this paper was published.