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：本文提出了针对超柔性飞机阵风载荷缓解的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，该模型通过耦合流固飞行动力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，并在完整非线性模型上得到验证。控制架构采用后缘襟翼偏转作为执行机构，翼尖位移作为性能输出，并引入输入整形权重函数Kc来调节结构载荷缓解与刚体轨迹偏差之间的权衡。本文给出了类"全球鹰"无人机和超柔性飞翼构型的仿真结果。该方法表明，基于低阶ROM设计的H∞控制器应用于高维非线性气动弹性系统时，能够鲁棒地缓解阵风载荷。