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

By: Administration (Nasa), National Aeronaut

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. Ko, William L. Armstrong Flight Research Center NASA/TP-2005-212862, H-2572 WU 761-90-00-SE-65 AIR LAUNCHING; B-52 AIRCRAFT; STRESS ANALYSIS; STRUCTURAL DESIGN; STRUCTURAL FAILURE; CRITICAL LOADING; FINITE ELEMENT METHOD; PYLONS; PEGASUS AIR-LAUNCHED BOOSTER; X-37 VEHICLE; SHEAR STRESS

• Format: Paperback
• Language: English
• ISBN: B08F6CG98S
• ISBN13: 9798672733258
• Release Date: January 1
• Publisher: Independently Published
• Length: 40 Pages
• Weight: 0.26 lbs.
• Dimensions: 0.1" x 8.5" x 11.0"