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A set of physically based retrieval algorithms has been developed to derive from multispectral satellite imagery a variety of cloud properties that can be used to diagnose icing conditions when upper-level clouds are absent. The algorithms are being applied in near-real time to the Geostationary Operational Environmental Satellite (GOES) data over Florida, the Southern Great Plains, and the midwestern USA. The products are available in image and digital formats on the world-wide web. The analysis system is being upgraded to analyze GOES data over the CONUS. Validation, 24-hour processing, and operational issues are discussed.

A theoretically based algorithm to derive super-cooled liquid water (SLW) cloud macrophysical and microphysical properties is applied to operational satellite data and compared to pilot reports (PIREPS – from commercial and private aircraft) of icing and to in-situ measurements collected from a NASA icing research aircraft. The method has been shown to correctly identify the existence of SLW provided there are no higher-level ice crystal clouds (i.e. cirrus) above the SLW deck. The satellite-derived SLW cloud properties, particularly the cloud temperature, optical thickness or water path and water droplet size, show good qualitative correspondence with aircraft observations and icing intensity reports. Preliminary efforts to quantify the relationship between the satellite retrievals, PIREPS and aircraft measurements are reported here. The goal is to determine the extent to which the satellite-derived cloud parameters can be used to improve icing diagnoses and forecasts.

Future human expeditionary missions such as return to the Moon or initial Martian expeditions must deal with new mission modes, mission environmental diversity, and extended mission durations. Two recently emerging technology capabilities, Virtual Environment (VE)/Virtual Reality (VR) and Computer Aided Design (CAD)/Computer Aided Engineering (CAE)/Computer Aided Manufacturing (CAM) enhanced capability, when used in combination with a systems engineering focus on systems effectiveness and availability, can make the difference in supporting human expeditionary systems design, development, manufacturing, and operations (flight and surface). Mission durations for human permanent lunar operations and initial and follow-on Martian expeditions will require a significant focus on system effectiveness. The systems effectiveness availability component has subsets of reliability, maintainability, operability, spares number and location, transportation capability, and “others”.

NASA's Office of Exploration depends on both robotic and human exploration system capabilities to support a rich set of lunar and Mars mission options. Permanent operations on the lunar surface will demand high systems availability and low logistics. Mars human exploration missions require sustainable operations with no logistics except what has been forward deployed on earlier missions. This paper will discuss the top-level mission requirements and the systems engineering issues for life support systems which must be addressed to support viable human exploration missions for lunar and Mars applications.

NASA's Office of Space Science and Applications has recently completed its long-range strategic plan which describes a number of exciting space science missions into the early 21st century. In parallel, NASA's new Office of Exploration has begun defining in more detail the architectures of the Space Exploration Initiative (SEI) for returning to the Moon and going to Mars. Both the space science missions and the SEI missions are dependent upon power sources and energy storage with strong requirements for reliability, long life, ease of assembly, autonomy, and light weight. This paper reviews the currently planned space science and SEI missions and focuses upon the power requirements with a view toward guiding technology developers and power designers.

The Orbital Maneuvering Vehicle (OMV) systems' performance coupled with its canti-levered payload capability provides an excellent orbital test bed for short- and intermediate-duration life support subsystem and subscale system experimental investigations. As an experiment carrier or support vehicle, the OMV can remove the experiment or engineering test bed from the National Space Transportation System (NSTS) or Space Station environmental influences. This paper explores both the primary OMV capability to support short-term experiments as well as intermediate-duration evaluations of life support system.