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This paper is concerned with a series of three important problems on reliability where complete solutions are still unavailable. These problems have all been researched and approximate solutions are outlined. The three areas of interest are 1. The government requirement of assurance of high reliability of complex items where the cost of sampling is extremely high. 2. Confidence intervals for a system in series where component data are available, and 3. Estimation of the parameters of the Weibull distribution when sampling terminates after the rth failure is observed in a sample of size n.

Mixed liquid/solid wastes, including feces, water processor effluents, and food waste, can be lyophilized (freeze-dried) to recover the water they contain and stabilize the solids that remain. Our previous research has demonstrated the potential benefits of using thermoelectric heat pumps to build a lyophilizer for processing waste in microgravity. These results were used to build a working prototype suitable for ground-based human testing. This paper describes the prototype design and presents results of functional and performance tests.

Predicting the aerodynamic performance of an aircraft in icing conditions is critical as failures in an aircraft’s ice protection system can compromise flight safety. Aerodynamic effects of icing have typically relied on RANS modeling, which usually struggles to predict stall behavior, including those induced by surface roughness. Encouraged by recent studies using LES that demonstrate the ability to predict stall characteristics on full aircraft with smooth wings at an affordable cost [1], this study seeks to apply this methodology to icing conditions. Measurements of lift, drag, and pitching moments of a NACA23012 airfoil under clean and iced conditions are collected at Re = 1.8M. Using laser scanned, detailed representations of the icing geometries, LES calculations are conducted to compare integrated loads against experimental measurements in both clean and iced conditions at various angles of attack through the onset of stall [2].

Development of a suitable EVA suit for use on Mars will be a significant technological challenge. A particular concern is the excessive weight of existing planetary spacesuit designs. Mars has approximately one-third of the Earth's gravitational pull. Therefore, heavy suits will significantly hamper effective EVA operations. A suit design investigated by research groups from Stanford University and U.C. Berkeley uses semi-permeable membranes as a passive thermal control system. This design replaces the bulky active thermal control systems in more traditional spacesuit designs by working with the natural thermal control mechanisms of the human body. This idea is only possible due to the unique Martian atmosphere and the normal way in which the human body regulates its own temperature via sensory feedback to the brain, sweat, and regulation of blood flow.