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The availability of real time, automated, and reliable atmosphere and water monitoring instrumentation within the timeframe of future manned lunar and Mars missions is vital to the success of the Space Exploration Initiative (SEI). For these missions, with durations measured in years, the environmental control and life support system (ECLSS) must be properly instrumented to assure the crew that the physical, chemical, and biological properties of the atmosphere and water are within ranges that are healthy and safe. The technology for measuring some properties, such as temperature and pressure, is currently available for most applications; however, there are a number of instrumentation functions required for future long duration missions that cannot be performed by current technology. Defining the areas where current instrumentation technology falls short of satisfying potential SEI requirements is a task of immediate importance.

The Space Station Environmental Control and Life Support System (ECLSS) test program at the Marshall Space Flight Center (MSFC) is addressed. The immediate goals and current activities of the test program are discussed. Also described are the Core Module Integration Facility (CMIF) and the initial ECLSS test configuration. Future plans for the ECLSS test program and the CMIF are summarized.

This paper describes the design and performance of the Astro Integrated Radiator System (IRS). The system was recently ground tested and proven successful in rejecting approximately 400 watts of heat. The radiator was constructed from an aluminum panel configured to form two orthogonal planes. Heat pipes were adhesively bonded and riveted to the radiator to isothermalize the surface. The IRS was subjected to a full thermal vacuum test to validate the thermal math model and to qualify the radiator for space flight. The thermal performance met prescribed temperature limits with margins at both extremes, and no mechanical failures occurred.

The space station environmental control and life support system (ECLSS) is divided into seven functional groups: temperature and humidity control (THC), atmosphere control and supply (ACS), atmosphere revitalization (AR), fire detection and suppression (FDS), water recovery and management (WRM), waste management (WM), and EVA support (ES). This paper addresses the distribution among the modules of the ECLSS subsystems within each of these groups, both in terms of physical and functional distribution. The module resource requirements and safety implications, particularly with regard to safe haven operations are discussed. The implications of subsystem sizing are also addressed. The major recommendation is to physically distribute, but functionally centralize the air revitalization and potable water reclamation systems, while sizing each of these subsystems to support a six person crew under emergency conditions.

With the advent of a long-life U.S. Space Station, the development of a regenerative Environmental Control and Life Support Systems (ECLSS) becomes essential in order avoid the severe logistics penalty associated with an expendable ECLSS. Currently, NASA/Marshall Space Flight Center (MSFC) and their prime contractors are evaluating competing regenerative ECLSS technologies using the Technology Demonstrator (Tech Demo) Program. The Tech Demo Program consists of two phases: (1) comparative test, and (2) 90-day manned systems test. The data derived from this test program, in conjunction with analytical assessments and other test data, will determine the prime technologies to pursue for the Space Station ECLSS. This paper details the Tech Demo program including the overall objectives, hardware requirements and major milestones as currently conceived by the MSFC.