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The second generation International Space Station (ISS) Total Organic Carbon Analyzer's (TOCA) function is to monitor concentrations of Total Organic Carbon (TOC) in ISS water samples. TOC is one measurement that provides a general indication of overall water quality by indicating the potential presence of hazardous chemicals. The data generated from the TOCA is used as a hazard control to assess the quality of the reclaimed and stored water supplies on-orbit and their suitability for crew consumption. This paper details the unique ISS Program requirements, the design of the ISS TOCA, and a brief description of the on-orbit concept-of-operations. The TOCA schematic will be discussed in detail along with specific information regarding key components.

A concentrated development effort was begun at NASA Johnson Space Center to create an advanced Portable Life Support System (PLSS) packaging concept. Ease of maintenance, technological flexibility, low weight, and minimal volume are targeted in the design of future micro-gravity and planetary PLSS configurations. Three main design concepts emerged from conceptual design techniques and were carried forth into detailed design, then full scale mock-up creation. “Foam”, “Motherboard”, and “LEGO™” packaging design concepts are described in detail. Results of the evaluation process targeted maintenance, robustness, mass properties, and flexibility as key aspects to a new PLSS packaging configuration. The various design tools used to evolve concepts into high fidelity mock ups revealed that no single tool was all encompassing, several combinations were complimentary, the devil is in the details, and, despite efforts, many lessons were learned only after working with hardware.

In this investigation, analytical models were developed to predict the performance characteristics of axisymmetric single jet ejector. The ejector is divided into four parts, jet, mixer, nozzle, and diffuser. Basic flow equations were combined to calculate end to end flow characteristics for each of the four ejector components. Different jets and mixer combination were tested using three jet and three mixers. Characteristics curves have been drawn to predict flow characteristics of the ejector. Different configuration of jet and mixer incorporated different loss coefficient. Hence to get correct flow characteristics of the ejector right loss coefficient should be used.

A high degree of in-flight availability of an Extravehicular Mobility Unit (EMU) must be assured to allow Extravehicular Activity (EVA) to become a routine operation, to minimize life cycle costs, and to support long duration missions. The ability to maintain an Advanced EMU and other equipment in flight will be of primary importance in achieving these high availability requirements while minimizing onboard spares quantities and resupply costs. This paper presents an analytical assessment of the advantages of in-flight maintainability in providing continued EMU availability for space-based operations by use of modular assemblies and components.

The Space Station Extravehicular Activity (EVA) Test Bed program at the Johnson Space Center (JSC) is addressed. A summary of the current testing activities are discussed as well as the test bed goals and future plans to support the Space Station Extravehicular Activity System (EVAS) development program.