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Estimating Critical Flaw Sizes in Welds of the New ARES I-X Space Vehicle for Its Successful Solo Flight Using Probabilistic Approaches

[+] Author Affiliations
Shantaram S. Pai

NASA Glenn Research Center, Cleveland, OH

Peter A. Hoge, B. M. Patel, Vinod K. Nagpal

N&R Engineering, Cleveland, OH

Paper No. GT2008-50626, pp. 1327-1334; 8 pages
doi:10.1115/GT2008-50626
From:
  • ASME Turbo Expo 2008: Power for Land, Sea, and Air
  • Volume 5: Structures and Dynamics, Parts A and B
  • Berlin, Germany, June 9–13, 2008
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4315-4 | eISBN: 0-7918-3824-2
  • Copyright © 2008 by ASME

abstract

The primary structure of the ARES I-X Upper Stage Simulator (USS) launch vehicle is constructed of welded mild steel plates. There is some concern over the possibility of structural failure due to welding flaws. It was considered critical to quantify the impact of uncertainties in residual stress, material porosity, applied loads, and material and crack growth properties on the reliability of the welds during its pre-flight and flight. A criterion — an existing maximum size crack at the weld toe must be smaller than the maximum allowable flaw size — was established to estimate the reliability of the welds. A spectrum of maximum allowable flaw sizes was developed for different possible combinations of all of the above listed variables by performing probabilistic crack growth analyses using the ANSYS finite element analysis code in conjunction with the NASGRO crack growth code.

Copyright © 2008 by ASME

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