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Z-2 Architecture Description and Requirements Verification Results

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ICES_2016_301.pdf (989.3Kb)
Datum
2016-07-10
Autor
Graziosi, David
Jones, Robert
Ferl, Jinny
Scarborough, Steve
Hewes, Linda
Ross, Amy
Rhodes, Richard
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Zusammenfassung
The Z-2 Prototype Planetary Extravehicular Space Suit Assembly is a continuation of NASA’s Z series of spacesuits. The Z-2 is another step in NASA’s technology development roadmap leading to human exploration of the Martian surface. The suit was designed for maximum mobility at 8.3 psid, reduced mass, and to have high fidelity life support interfaces. The Z-2 suit architecture is an evolution of previous EVA suits, namely the ISS EMU, Mark III, Rear Entry I-Suit and Z-1 spacesuits. The suit is a hybrid hard and soft multi-bearing, rear entry spacesuit. The hard upper torso (HUT) is an all-composite structure and includes a 2-bearing rolling convolute shoulder with Z-1 Style lower arms and an elliptical hemispherical helmet. The lower torso includes a telescopic waist sizing system, waist bearing, rolling convolute waist joint, hard brief, 2 bearing soft hip thigh, Z-1 style legs, and walking boots with ankle bearings. The Z-2 Requirements Verification Plan includes the verification of more than 200 individual requirements. The verification methods include test, analysis, inspection, demonstration or a combination of methods. Examples of unmanned requirements include suit leakage, proof pressure testing, mass, man-loads, sizing adjustment ranges, internal and external interfaces such as in-suit drink bag, purge valve, and donning stand. Examples of manned requirements include verification of anthropometric range, suit self-don/doff, secondary suit exit method, donning stand self-ingress/egress and manned mobility covering eight functional tasks. The eight functional tasks include kneeling with object pick-up, standing toe touch, cross-body reach, walking, reach to the SIP and helmet visor. This paper will provide an overview of the Z-2 design. Z-2 requirements verification testing was performed with NASA at the ILC Houston test facility. This paper will also discuss pre-delivery manned and unmanned test results as well as analysis performed in support of requirements verification.
Citable Link
http://hdl.handle.net/2346/67653
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