Abstract
This paper presents distributed load aircraft design concepts that have as a major goal the significant increase in payload from reduction of the bending moments that are responsible for a large percentage of the structural weight. The judicious use of advanced technology, including composite structure and digital control of active control surfaces for gust alleviation, flutter suppression, and maneuver load control, all contribute to reductions in bending moments to achieve significantly lower structural weight fractions. The results show significant potential improvements in energy conservation and operating economics when compared to today's aircraft.
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