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AX-5 Space Suit Reliability Model
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English
Abstract
The AX-5 is an all metal Extra-vehicular (EVA) space suit currently under consideration for use on Space Station Freedom. A reliability model was developed based on the suit's unique design and on projected joint cycle requirements. Three AX-5 space suit component joints were cycled under simulated load conditions in accordance with NASA's advanced space suit evaluation plan. This paper will describe the reliability model developed, the results of the cycle testing, and an interpretation of the model and test results in terms of projected Mean Time Between Failure for the AX-5. A discussion of the maintenance implications and life cycle for the AX-5 based on this projection is also included.
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Citation
Reinhardt, A. and Magistad, J., "AX-5 Space Suit Reliability Model," SAE Technical Paper 901361, 1990, https://doi.org/10.4271/901361.Also In
References
- Vykukal, H.C. “Ames AX-5 Hard Space Suit Design, Analysis and Test Report,” Document No: PN-80-7104-519-11 Aerospace Human Factors Research Division, NASA Ames Research Center March 9 1987
- Van Horn, K. “Aluminum Vol II Design and Application,” 89 92 ASM 1968
- West, P. et. al. “Component Unmanned Bench Cycle Test Plan,” CTSD-SS-285 Johnson Space Center 1989
- Park, Eui H. Ram, Bala et. al. “Space Suit Inventory Model for a Space Station” Joint Research Interchange NCA2-15 NASA Ames Research Center North Carolina A&T University Sept 1986
- Vykukal, H.C. Component Hardware Demonstration Johnson Space Center April 1989