H Infinity robust control synthesis for gust load alleviation of very flexible aircraft is presented. The controller is synthesised on a compact reduced-order model comprising 8 degrees of freedom for the UAV configuration and 9 for the flying-wing, obtained through nonlinear model order reduction of the coupled fluid-structure-flight dynamics system, and validated on the full nonlinear model. The control architecture employs trailing-edge flap deflection as the actuator and wing-tip displacement as the performance output, with an input-shaping weighting function Kc that governs the trade-off between structural load alleviation and rigid-body trajectory deviation. Results are presented for a Global Hawk-like UAV and a very flexible flying-wing configuration. The methodology demonstrates that H infinity controllers designed on low-order ROMs can robustly alleviate gust loads when applied to high-dimensional nonlinear aeroelastic systems.

翻译：本文提出了一种用于超柔性飞行器阵风载荷减缓的H∞鲁棒控制综合方法。控制器基于一个紧凑的降阶模型进行综合，该模型通过耦合的流体-结构-飞行动力学系统的非线性模型降阶获得，其中无人机构型包含8个自由度，飞翼构型包含9个自由度，并在全非线性模型上进行了验证。控制架构采用后缘襟翼偏转作为作动器，翼尖位移作为性能输出，并引入一个输入整形加权函数Kc，用以权衡结构载荷减缓与刚体轨迹偏差。研究结果针对类全球鹰无人机和一种超柔性飞翼构型进行了展示。该方法表明，基于低阶降阶模型设计的H∞控制器在应用于高维非线性气动弹性系统时，能够鲁棒地减缓阵风载荷。