Control law design for flexible aircraft with coupled flight and structural dynamics is currently a challenge. If not correctly addressed during control law design, the aeroservoelastic coupling can negatively affect the lateral-directional stability of the aircraft. In this context, this paper describes a methodology for the design of a stability augmentation system for the Instituto Tecnológico de Aeronáutica X-HALE flexible aircraft and proposes a performance index for numerical optimization of the closed-loop feedback gains. Comparisons between open-loop and closed-loop numerical simulation results show how the proposed control system attenuates the Dutch-roll response. An aeroservoelastic analysis is made in which it its demonstrated that the control system has small but beneficial effects on aeroelastic stability. Finally, experimental data obtained via flight tests with the real aircraft demonstrate the effectiveness of the control system in practice.

具有耦合飞行和结构动力学的柔性飞机的控制律设计目前是一个挑战。如果在控制律设计过程中没有正确解决，气动伺服弹性耦合会对飞机的横向稳定性产生负面影响。在此背景下，本文描述了一种为 Instituto Tecnológico de Aeronáutica X-HALE 柔性飞机设计增稳系统的方法，并提出了闭环反馈增益数值优化的性能指标。开环和闭环数值模拟结果之间的比较显示了所提出的控制系统如何衰减荷兰滚响应。进行了气动伺服弹性分析，其中证明了控制系统对气动弹性稳定性的影响很小但有益。最后，