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Stress Analysis of B-52B and B-52H Air-Launching Systems Failure-Critical Structural Components

Author
Ko, William L.
Published
April 12, 2005.
Physical Description
1 electronic document
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
The operational life analysis of any airborne failure-critical structural component requires the stress-load equation, which relates the applied load to the maximum tangential tensile stress at the critical stress point. The failure-critical structural components identified are the B-52B Pegasus pylon adapter shackles, B-52B Pegasus pylon hooks, B-52H airplane pylon hooks, B-52H airplane front fittings, B-52H airplane rear pylon fitting, and the B-52H airplane pylon lower sway brace. Finite-element stress analysis was performed on the said structural components, and the critical stress point was located and the stress-load equation was established for each failure-critical structural component. The ultimate load, yield load, and proof load needed for operational life analysis were established for each failure-critical structural component.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 20050165092.
H-2572.
NASA/TP-2005-212862.
Terms of Use and Reproduction
No Copyright.
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