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Summary of a study to determine low-velocity impact damage and residual tension strength for a thick graphite/epoxy motor case
U.S. Government
Paperback. Books LLC, Reference Series 2011-10-02.
ISBN 9781234302405
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Förlagets beskrivning
Original publisher: Hampton, Va. : National Aeronautics and Space Administration, Langley Research Center, [1990] OCLC Number: (OCoLC)25060179 Subject: Space shuttles -- Propulsion systems -- Materials -- Impact testing. Excerpt: ... the averageandoccursat the center. But, the contact pressuretendsto beunbounded a flat end. This unbounded pressure gives rise to unbounded near the edgeof a rod with stresses that cause a punch type behavior. Residual Tension Strength The stresses for first-ligament failure are critical because they are either less than or equal to those for remaining-ligament failure. Thus, only the analysis of stresses for first-ligament failure will be reviewed. The impact damage was represented as a semi-elliptical surface crack_ and the stress for failure of the first ligament was calculated using surface crack analysis [ 4-7 ]. The crack was assumed to be in a plane normal to the hoop direction. The depth of the equivalent crack a was calculated with stresses from Love's solution and the maximum shear stress criterion with ru = 228 MPa ( 33 ksi ) and no = 4.52 GPa ( 656 ksi ). The length of the equivalent crack 2c was assumed to be two times the depth ( semi circular ). At failure, the critical stress intensity factor [ 16 ] or fracture toughness Kq is given by Kq = Sxf ( r f ( alh, alc, clW, ¢ ) a / Q ) 1 / 2 ( 10 ) Sxf where is the laminate stress for failure of the first ligament, Q is the shape function, and f ( a / h, a / c, c / W, ¢ ) is the correction factor for finite thickness h and width W. The parametric angle ¢ was taken as 0 * or 90 ", whichever gave the largest value of the correction factor. The fracture toughness Kq of the laminate was calculated using the elastic constants, the failing strain of the fibers, and a general fracture toughness parameter [ 4---6 ]. For a crack whose plane is normal to the 0 ° direction of the cylinder, the result was Kq = 0.949 GPa mqrm--_ ( 27.3 ksiC '-ff? ). For shallow surface cracks or impac
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Summary of a study to determine low-velocity impact damage and residual tension strength for a thick graphite/epoxy motor case
Bokrecensioner » Summary of a study to determine low-velocity impact damage and residual tension strength for a thick graphite/epoxy motor case
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