摘要: Structural oscillatory modes may noticeably affect the handling characteristics of aircraft. In very flexible aircraft, these structural oscillations may be of sufficiently low frequency to approach the frequency band of pilot com... 展开 Structural oscillatory modes may noticeably affect the handling characteristics of aircraft. In very flexible aircraft, these structural oscillations may be of sufficiently low frequency to approach the frequency band of pilot commands. In such cases, it becomes difficult to finely control the aircraft without exciting these aeroelastic interactions. Pilot-induced oscillations may result as the pilot responds to both motion in the aircraft's rigid body states and motion at the pilot station due to flexing of the aircraft structure. This paper proposes a model reference control architecture to compensate for these aeroelastic interactions, avoiding pilot-induced oscillations and improving tracking performance without inherently limiting the pilot's control authority. The nonlinear compensation seeks to make the combined controller-plant system exhibit a closed-loop response similar to that of an idealized system. In this case, the desired closed-loop dynamics should approach that of a rigid aircraft devoid of aeroelastic effects, and therefore immune to this class of pilot induced oscillations. This paper discusses the methods used to train the model reference controller and details results from a pair of case studies. Controllers are designed and applied to two aircraft models that can be driven to encounter aeroelastic pilot induced oscillations: one with spanwise wing bending modal oscillations and one with fuselage bending oscillations. Results show that the model reference control scheme reduces pilot-induced oscillation tendencies throughout the tested maneuvering envelopes and improves closed-loop tracking performance in both cases. 收起