Active disturbance rejection controller design for alleviation of gust-induced aeroelastic responses

Yue, Chengyu; Zhao, Yonghui

doi:10.1016/j.ast.2023.108116

Cited by 5 publications

(2 citation statements)

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“…The output vector y p can be sensor readings, such as displacement, velocity, and acceleration responses at the specified finite element nodes, as well as the virtual load outputs, such as wing-root shear force, bending, and torsional moments. Equations (7) and (9) constitute the final open-loop aeroelastic equations of motion excited by control surface deflections and atmospheric gust. The purpose of GLA is to seek a control law that drives the control surfaces to deflect appropriately, thereby generating additional aerodynamic forces to minimize the outputs of the system.…”

Section: State-space Open-loop Aeroservoelastic Equationsmentioning

confidence: 99%

“…Typical control design uses the empirical tuning-based PID method [7] and the state-space and linear model-based LQG method [8]. As a new feedback-based control strategy, Yue and Zhao [9] first employed the equivalent input disturbance (EID) method to alleviate the gust loads of a folding wing model. The advantage of feedback control lies in the robustness towards the uncertainties in the controlled object.…”

Section: Introductionmentioning

confidence: 99%

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Adaptive Feed-Forward Control for Gust Load Alleviation on a Flying-Wing Model Using Multiple Control Surfaces

Zhang,

Zhao

2023

Aerospace

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Based on measured gust information, a multi-input multi-output (MIMO) adaptive feed-forward control scheme for gust load alleviation (GLA) on a semi-span flying-wing aircraft using multiple control surfaces is proposed. In order to remedy weight drift and biased estimation problems that are commonly encountered in adaptive control, the circular leaky LMS (CLLMS) algorithm is employed, which utilizes gust measurement information, filtered reference signals, and error signals to update controller parameters online. The results demonstrate that good load reductions are achieved in both continuous and discrete gust environments. For instance, the designed GLA control system leads to an 80.72% reduction in the root-mean-square (RMS) values of wing-root bending moment in the Dryden gust environment and a 77.59% reduction of its maximum value in the 1-cos discrete gust condition. Based on the limited power of the actuator and the limited authority for control surface deflections when integrating GLA into the flight control system, a weight-updating algorithm with deflection angle and rate constraints on control surfaces is proposed. The simulation results show that the strict constraints on control surface deflections will degrade the GLA performance. Finally, the influence of the partial jamming fault of actuators on GLA performance is studied. It is found that good GLA performance can be preserved despite the degraded performance during the initial stage of the actuator jamming fault. This is due to the robustness brought about by multiple control surfaces and the adaptability of the control algorithm.

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Section: State-space Open-loop Aeroservoelastic Equationsmentioning

confidence: 99%