Refine Your Search

Search Results

Viewing 1 to 5 of 5
Technical Paper

Demonstration of Super Cooled Ice as a Phase Change Material Heat Sink for Portable Life Support Systems

A phase change material (PCM) heat sink using super cooled ice as a non-toxic, non-flammable PCM is being developed for use in a portable life support system (PLSS). The latent heat of fusion for water is approximately 70% larger than most paraffin waxes, which can provide significant mass savings. Further mass reduction is accomplished by super cooling the ice significantly below its freezing temperature for additional sensible heat storage. Expansion and contraction of the water as it freezes and melts is accommodated with the use of flexible bag and foam materials. A demonstrator unit has been designed, built, and tested to demonstrate proof of concept. Both testing and modeling results are presented.
Technical Paper

Advanced Design Heat Pump/Radiator for EVA Suits

Absorption cooling using a lithium chloride/water heat pump can enable lightweight and effective thermal control for Extravehicular Activity (EVA) suits without venting water to the environment. The key components in the system are an absorber/radiator that rejects heat to space and a flexible evaporation cooling garment that absorbs heat from the crew member, This paper describes progress in the design, development, and testing of the absorber/radiator and evaporation cooling garment. New design concepts and fabrication approaches will significantly reduce the mass of the absorber/radiator. We have also identified materials and demonstrated fabrication approaches for production of a flexible evaporation cooling garment, Data from tests of the system's modular components have validated the design models and allowed predictions of the size and weight of a complete system.
Technical Paper

Development of a Contaminant Insensitive Sublimator

Sublimators have been used for heat rejection for a variety of space applications including the Apollo Lunar Module and the Extravehicular Mobility Unit (EMU). Sublimators are excellent candidates for heat rejection devices on future vehicles like the Crew Exploration Vehicle (CEV), the Lunar Surface Access Module (LSAM), and future spacesuits. One of the drawbacks of previous designs was sensitivity to contamination in the feedwater. Undissolved contaminants can be removed with filters, but dissolved contaminants would be left in the pores of the porous plates in which the feedwater freezes and sublimates. These contaminants build up and clog the relatively small pores (~3–6 μm), thereby blocking the flow of the feedwater, reducing the available area for freezing and sublimation, and degrading the performance of the sublimator. For the X-38 program, a new sublimator design was developed by NASA-JSC that is less sensitive to contaminants.
Technical Paper

Thermal Analysis of Lightweight Liquid Cooling Garments Using Highly Conductive Materials

This paper presents the analysis findings of a study reducing the overall mass of the lightweight liquid cooling garment (LCG). The LCG is a garment worn by crew to actively cool the body, for spacesuits and launch/entry suits. A mass reduction of 66% was desired for advanced missions. A thermal math model of the LCG was developed to predict its performance when various mass-reducing changes were implemented. Changes included varying the thermal conductivity and thickness of the garment or of the coolant tubes servicing the garment. A second model was developed to predict behavior of the suit when the cooling tubes were to be removed, and replaced with a highly-conducting (waterless) material. Findings are presented that show significant reductions in weight are theoretically possible by improving conductivity in the garment material.
Journal Article

Common Helmet Design for Launch, Entry, & Abort and EVA Activities – A Discussion on the Design and Selection Process of Helmets for Future Manned Flight

Effective helmet performance is a critical component to achieving safe and efficient missions along the entire timeline; from launch and entry events to operations in a micro-gravity environment to exploration of a planetary surface, the helmet system is the capstone of the pressurized space suit assembly. Each phase of a mission requires uncompromising protection in the form of a robust pressure vessel and adequate protection from impact, both interior and exterior, all while remaining relatively comfortable and providing excellent visual interaction with the environment. Historically there have been large voids between these critical characteristics with the primary focus concerning the pressure vessel first and impact protection and crew comfort second. ILC Dover, NASA-JSC, Gentex Corporation, and Hamilton Sundstrand formed an Integrated Product Team (IPT) and conducted a NASA funded study to research and evaluate new concepts in helmet design.