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New information is presented on conceptual designs of bioregenerative life support systems, with subsystems defined, sizes estimated, and configurations developed.1 Components are sized by comparison with design data from Spacelab, the space station, commercial practice, and research on new technologies. Designs were developed on a Microstation CAD system, importing existing models such as space station modules where available. Layouts consider component mass and power as well as connections and access requirements. In addition, current efforts in the NASA CELSS Breadboard Facility (CBF) at Kennedy Space Center are described, which may validate some of these design concepts. Design optimization for the next-generation Breadboard Facility is discussed.

Work defining advanced life support (ALS) technologies and evaluating their applicability to various long-duration missions has continued. Time-dependent and time-invariant costs have been estimated for a variety of life support technology options, including International Space Station (ISS) environmental control and life support systems (ECLSS) technologies and improved options under development by the ALS Project. These advanced options include physicochemical (PC) and bioregenerative (BIO) technologies, and may in the future include in-situ-resource utilization (ISRU) in an attempt to reduce both logistics costs and dependence on supply from Earth. PC and bioregenerative technologies both provide possibilities for reducing mission equivalent system mass (ESM). PC technologies are most advantageous for missions of up to several years in length, while bioregenerative options are most appropriate for longer missions. ISRU can be synergistic with both PC and bioregenerative options.

Equivalent System Mass (ESM) is the basis of the Advanced Life Support Research and Technology Development metric for measurement of progress of the Advanced Life Support (ALS) Project under the Advanced Human Support Technology (AHST) Program. ESM may be used to evaluate a system or technology based upon its mass, volume, power, cooling and manpower requirements. The ESM metric as defined in the ALS Research and Technology Development Metric Baseline is International Space Station (ISS) technology ESM divided by the ALS technology ESM for a specified mission. This paper discusses various theoretical and practical issues behind application of ESM to systems as well as to individual technologies. Difficulties that might be encountered by researchers in application of the metric are addressed. It is crucial that ALS researchers be proficient in assessing technologies and/or systems of interest with ESM, to minimize the chance of misapplication of the approach.