Lower thrust structure S/N 0000001 static structural test evaluation report Page: 50 of 53
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was 41,170 psi, divided about equally between membrane and bending stresses.
Permanent strain recorded was 350 micro-inches/inch, which again is well within
the allowable permanent set. It should be noted that mismatch and distortion was
visible at this joint.
The stresses at the ftustrum-to-gimbal-housing weld joint (as
shown in Figure 23) consisted of both high membrane and bending stresses. At
location 119 a meridional stress of 39,400 psi was indicated with permanent set of
955 micro-inches/inch on the inner surface, On the other side of the weld joint,
at location 120, a meridional stress of 39,620 psi with a permanent set of 504
micro-inches/inch was shown indicating a reversal of stress. The resulting high
bending stresses were caused by the lap joint weld design, weld mismatch and
distortion. As noted in discussing other weld areas, the inelastic strain was
still within the allowable limit, even with the defects.
From Table 3 it can be deduced that the axial stresses of all
seven tubular members of the actuator supports were generally of the same magnitude.
The members connected to the frustrum from the actuator yoke were always maximum and q
of opposite sign compared to the other members. Load symmetry between actuator
supports was within the same order-of-magnitude as symmetry within the same support.
Maximum axial stress was 29,300 psi, which was tension stress on member C during
Case 7. At midspan, the bending was reasonably uniform, as shown in Table 4, On
support member C the bending stress was about 3,300 psi or 11% of the membrane
stress. In no case was there a greater combined stress. As the inelastic strain
was small (100 micro-inches/inch), the structural adequacy of the actuator
supports was proven.
2. Axial and Lateral Stiffness
LTS axial spring constants computed from deflection data in Table 6
are shown in Table 7 Load Cases 1 and 10 were used as only a single load was
applied. Overall value was shown to be between 1.8 to 1.9 x 10 lbs/in. Because
of complex multiple loading in the remainder of the Oases, Lateral LTS and actuator
support spring constants were not computed.
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Lower thrust structure S/N 0000001 static structural test evaluation report, report, April 1, 1965; Sacramento, California. (https://digital.library.unt.edu/ark:/67531/metadc1024652/m1/50/?rotate=270: accessed April 18, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.