Development of a Prototype Fan for Future Space Suit Applications

Paul, Heather L.; Converse, David; Dionne, Steve; Moser, Jeff

doi:10.2514/6.2010-6132

Cited by 2 publications

(2 citation statements)

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“…5 Measurements about the fan yield an estimated 1.4 W aerodynamic power imparted to the gas stream and the transference of 3.3 W of heat to the gas stream. In theory, the fan motor power should be balanced by imparted aerodynamic power and heat acquisition if the fan is perfectly insulated.…”

Section: An In-depth Look At the Steady-state Test Point 5r800mentioning

confidence: 99%

“…6) was designed by Hamilton Sundstrand (Windsor Locks, CT ) as part of a JSC technology development effort. 5 Two nearly identical units were built by Hamilton Sundstrand with the serial number 1 unit used in PLSS 1.0 testing. Fan performance requirements were to produce 672 Pa delta-pressure ( P) at 133 Lpm flow, 20°C (68°F) inlet oxygen, and 29.65 kPa Ventilation Subsystem loop absolute pressure while consuming no more than 14 W of total electrical power.…”

Section: Ventilation Subsystemmentioning

confidence: 99%

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Space Suit Portable Life Support System Test Bed (PLSS 1.0) Development and Testing

Watts

Campbell

Vogel

et al. 2012

42nd International Conference on Environmental Systems

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A multi-year effort has been carried out at NASA Johnson Space Center to develop an advanced extravehicular activity (EVA) Portable Life Support System (PLSS) design intended to further the current state of the art by increasing operational flexibility, reducing consumables, and increasing robustness. Previous efforts have focused on modeling and analyzing the advanced PLSS architecture, as well as developing key enabling technologies. Like the current International Space Station Extravehicular Mobility Unit PLSS, the advanced PLSS comprises three subsystems required to sustain the crew during EVA, including the Thermal, Ventilation, and Oxygen Subsystems. This effort has culminated in the construction and operation of PLSS 1.0, a test bed that simulates full functionality of the advanced PLSS design. PLSS 1.0 integrates commercial off-the-shelf hardware with prototype technology development components, including the primary and secondary oxygen regulators, Ventilation Subsystem fan, Rapid Cycle Amine swingbed carbon dioxide and water vapor removal device, and Spacesuit Water Membrane Evaporator heat rejection device. The overall PLSS 1.0 test objective was to demonstrate the capability of the Advanced PLSS to provide key life support functions including suit pressure regulation, carbon dioxide and water vapor removal, thermal control, and contingency purge operations. Supplying oxygen was not one of the specific life support functions because the PLSS 1.0 test was not oxygen rated. Nitrogen was used for the working gas. Additional test objectives were to confirm PLSS technology development components performance within an integrated test bed, indentify unexpected system-level interactions, and map the PLSS 1.0 performance with respect to key variables such as crewmember metabolic rate and suit pressure. Successful PLSS 1.0 testing completed 168 test points over 44 days of testing and produced a large database of test results that characterize system-level and component performance. With the exception of several minor anomalies, the PLSS 1.0 test rig performed as expected; furthermore, many system responses trended in accordance with pre-test predictions. Nomenclature BPV= backpressure valve Btu = British thermal unit CO 2 = carbon dioxide COTS = commercial off-the-shelf DACS = data acquisition and control system

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Section: An In-depth Look At the Steady-state Test Point 5r800mentioning

confidence: 99%

Section: Ventilation Subsystemmentioning

confidence: 99%