Sheet Membrane Spacesuit Water Membrane Evaporator Design and Thermal Tests

Vogel, Matthew; Vonau, Walt; Trevino, Luis; Bue, Grant C.

doi:10.2514/6.2010-6039

Cited by 13 publications

(2 citation statements)

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“…The SWME also simplifies the PLSS schematic, as compared to the current EMU, because it has the ability to vent entrained gas from the water loop to the atmosphere, which eliminates the need for a separate gas separator. The current the state-of-the-art for thermal control is identified in Table 1 Extensive testing of the candidate SWME prototypes using porous Teflon® sheet membranes (SaM) 8 and porous polyester hollow fiber (HoFi) 9 membranes was performed at JSC in 2009 and 2010 in SWME vacuum chamber tests shown in Fig. 9.…”

Section: A Thermal Subsystemmentioning

confidence: 99%

Extravehicular Activity Technology Development Status and Forecast

Chullen

Westheimer

2011

41st International Conference on Environmental Systems

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The goal of NASA's current EVA technology effort is to further develop technologies that will be used to demonstrate a robust EVA system that has application for a variety of future missions including microgravity and surface EVA. Overall the objectives will be to reduce system mass, reduce consumables and maintenance, increase EVA hardware robustness and life, increase crew member efficiency and autonomy, and enable rapid vehicle egress and ingress. Over the past several years, NASA realized a tremendous increase in EVA system development as part of the Exploration Technology Development Program and the Constellation Program. The evident demand for efficient and reliable EVA technologies, particularly regenerable technologies was apparent under these former programs and will continue to be needed as future mission opportunities arise. The technological need for EVA in space has been realized over the last several decades by the Gemini, Apollo, Skylab, Space Shuttle, and the International Space Station (ISS) programs. EVAs were critical to the success of these programs. Now with the ISS extension to 2028 in conjunction with a current forecasted need of at least eight EVAs per year, the EVA hardware life and limited availability of the Extravehicular Mobility Units (EMUs) will eventually become a critical issue. The current EMU has successfully served EVA demands by performing critical operations to assemble the ISS and provide repairs of satellites such as the Hubble Space Telescope. However, as the life of ISS and the vision for future mission opportunities are realized, a new EVA systems capability will be needed and the current architectures and technoliges under development offer significant improvements over the current flight systems. In addition to ISS, potential mission applications include EVAs for missions to Near Earth Objects (NEO), Phobos, or future surface missions. Surface missions could include either exploration of the Moon or Mars. Providing an EVA capability for these types of missions enables in-space construction of complex vehicles or satellites, hands on exploration of new parts of our solar system, and engages the public through the inspiration of knowing that humans are exploring places that they have never been before. This paper offers insight into what is currently being developed and what the potential opportunities are in the forecast.

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Section: A Thermal Subsystemmentioning

confidence: 99%

Extravehicular Activity Technology Development Status and Forecast

Chullen

Westheimer

2011

41st International Conference on Environmental Systems

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“…3 Custom designs for Suit Water Membrane Evaporator (SWME) also showed excellent degassing characteristics with a tube-flow design, typical of their commercial counterparts. [4][5][6][7] Accordingly, a development project was undertaken to design, build, and test a venting gas trap specifically tailored for Orion's requirements that significantly reduce the size and volume compared with non-venting designs. Two shell-flow and one tube-flow design concepts were compared.…”

Section: Introductionmentioning

confidence: 99%

Design and Testing of a Shell-Flow Hollow-Fiber Venting Gas Trap

Bue

Cross

Hansen

et al. 2013

43rd International Conference on Environmental Systems

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A Venting Gas Trap (VGT) was designed, built, and tested at NASA Johnson Space Center to eliminate dissolved and free gas from the circulating coolant loop of the Orion Environmental Control Life Support System. The VGT was downselected from two different designs. The VGT has robust operation, and easily met all the Orion requirements, especially size and weight. The VGT has a novel design with the gas trap made of a five-layer spiral wrap of porous hydrophobic hollow fibers that form a cylindrically shaped curtain terminated by a dome-shaped distal plug. Circulating coolant flows into the center of the cylindrical curtain and flows between the hollow fibers, around the distal plug, and exits the VGT outlet. Free gas is forced by the coolant flow to the distal plug and brought into contact with hollow fibers. The proximal ends of the hollow fibers terminate in a venting chamber that allows for rapid venting of the free gas inclusion, but passively limits the external venting from the venting chamber through two small holes in the event of a long-duration decompression of the cabin. The VGT performance specifications were verified in a wide range of flow rates, bubble sizes, and inclusion volumes. Long-duration and integrated Orion human tests of the VGT are also planned for the coming year. Nomenclature

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A fuzzy coordination control of a water membrane evaporator cooling system for aerospace electronics

Xie

et al. 2021

Applied Thermal Engineering

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Sheet Membrane Spacesuit Water Membrane Evaporator Design and Thermal Tests

Cited by 13 publications

References 1 publication

Extravehicular Activity Technology Development Status and Forecast

Extravehicular Activity Technology Development Status and Forecast

Design and Testing of a Shell-Flow Hollow-Fiber Venting Gas Trap

A fuzzy coordination control of a water membrane evaporator cooling system for aerospace electronics

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