发表机构
German Aerospace Center (DLR), Institute of Flight Systems（德国航空航天中心（DLR）飞行系统研究所）
机构由 AI 辅助整理，请以论文原文为准。AI 中文总结
针对尾缘变体飞行器，提出带自适应增广的控制分配框架，在不确定性下保证稳定，并优化机翼形状以实现椭圆升力分布，数值验证有效。
AI 中文摘要
本文针对尾缘变体飞行器提出了一种带自适应增广的控制分配框架，在利用可用变体自由度优化气动效率的同时，为不确定性下的稳定性提供保证。利用标称飞行器模型设计了一个基准控制器，以建立期望的闭环参考动态。对于气动方面，根据飞行状态优化机翼形状，以实现对应于最小诱导阻力的目标椭圆升力分布。自适应增广针对控制分配问题量身定制，以考虑不确定的系统动态，并使飞行器围绕参考动态稳定。所得稳定性条件被表述为分配问题中的硬约束，同时最小化与相应状态相关的气动最优机翼形状的偏差。数值结果表明，自适应增广补偿了匹配的不确定性，而控制分配则针对参考椭圆升力分布优化机翼形状。
英文摘要
This paper presents a control allocation framework with adaptive augmentation for a trailing edge morphing aircraft, providing stability guarantees under uncertainty while exploiting the available morphing degrees of freedom to optimize aerodynamic efficiency. A baseline controller is designed using the nominal aircraft model to establish the desired closed-loop reference dynamics. For the aerodynamics, the wing shape is optimized dependent on the flight state to achieve a target elliptical lift distribution corresponding to minimum induced drag. The adaptive augmentation is tailored to the control allocation problem to account for the uncertain system dynamics and stabilize the aircraft around the reference dynamics. The resulting stabilization condition is formulated as hard constraint in the allocation problem while minimizing deviations from the corresponding state-dependent aerodynamically optimal wing shape. Numerical results demonstrate that the adaptive augmentation compensates for matched uncertainties while the control allocation optimizes the wing shape with respect to the reference elliptical lift distribution.
CommentsSubmitted to American Control Conference (ACC) 2027
