Aeroservoelastic design optimization of a flexible wing

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文件名称：Aeroservoelastic design optimization of a flexible wing
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更新时间：2022-02-27 02:32:34
flexible win 关于柔性机翼的建模优化，使用伺服单性建模方法。 In this paper a multidisciplinary design optimization framework is developed that integrates control system design with aerostructural design. The equations of motion are derived for a flexible air- craft and used to perform aeroservoelastic analysis. The objective of this framework is to go beyond the current limits of aircraft performance through simultaneous design optimization of aerodynamic shape, structural sizing and control system. The control system uses load alleviation to reduce the critical structural loads. Time-domain analysis of the aircraft performing an altitude change maneu- ver and encountering an atmospheric gust is included in the design process. The optimal trade-off between aerodynamics, structures and control system is found by maximizing the endurance sub- jected to stress and maneuverability constraints. Two cases — with and without load alleviation system — are considered. Due to the proposed MDO framework, the inclusion of load alleviation system in design leads to a significant increase in endurance performance.