Abstract
TCOM aerostats have been analyzed to investigate the stresses, deflections, and potential for buckling of the hull, empennage, and suspension system under various configurations and loading conditions. The finiteelement structural analysis shows the material strength requirements, minimum pressure differential requirements, and areas where material can be optimized in strength and weight. Graphic output from the analysis shows the deformed shapes and the stress distributions. The results of the analysis show the hull material and internal pressures used to optimum. The empennage can use lower strength materials for weight reduction.
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