Disturbance observer based dynamic inversion control for a wind tunnel free-flying test of a blended-wing-body aircraft

Chen, Zhirun; Sun, Chaoyi; Cen, Fei; Nie, Bowen; Li, Qing

doi:10.1109/cac48633.2019.8996867

Cited by 2 publications

(10 citation statements)

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“…The flight dynamics of the tailless aircraft model on the rig are modeled as a three degree-of-freedom (3-DOF) angular motion, which has been developed in ref. [32,36,37]. In modeling of this motion, a set of assumptions are made including: the rigid-body aircraft model, the symmetrical distribution of aircraft mass about the xz plane, the negligible aerodynamic interference induced by the rig and the limited dynamic influence of rig friction and support misalignment.…”

Section: Mathematical Modelingmentioning

confidence: 99%

“…and moment C l C m C n T coefficients can be approximated and formulated as the following form [32,37]:…”

Section: Mathematical Modelingmentioning

confidence: 99%

“…The α and µ responses are recovered close to that of the nominal case, except that the overshoots and damping deteriorate marginally, and the coupling influence of µ maneuver to α and β increases slightly. It is the disturbance observers of Equations (32) and (48) that estimate the aerodynamic biases and the CG mismatch as a set of lumped disturbances, respectively, as shown in Figure 8d. Additionally, then, the estimated lumped disturbances are substituted into Equation 33for dynamic inversion compensation.…”

Section: Comparison Of the Robust Performancementioning

confidence: 99%

“…Such an outcome was in agreement with the prospective effect of the disturbance observer. On one hand, the NDI-DO and the NDI-AW controllers estimated the lumped disturbances using Equations (32) and (48), respectively, which were then compensated using the inner-loop dynamic inversion controller of Equation (33). As a result, the influence of the lumped disturbances to the closed-loop system was mostly rejected by the disturbance observer augmented controllers.…”

Section: Investigation Of the Anti-windup Performancementioning

confidence: 99%

“…Though a primitive NDI-DO controller has been designed for a tailless aircraft and numerically validated in ref. [32], experimental implementation and flight validation are to be carried out.…”

Section: Introductionmentioning

confidence: 99%

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Design and Validation of Disturbance Rejection Dynamic Inverse Control for a Tailless Aircraft in Wind Tunnel

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This paper focuses on the design of a disturbance rejection controller for a tailless aircraft based on the technique of nonlinear dynamic inversion (NDI). The tailless aircraft model mounted on a three degree-of-freedom (3-DOF) dynamic rig in the wind tunnel is modeled as a nonlinear affine system subject to mismatched disturbances. First of all, a baseline NDI attitude controller is designed for sufficient stability and good reference tracking performance of the nominal system. Then, a nonlinear disturbance observer (NDO) is supplemented to the baseline NDI controller to estimate the lumped disturbances for compensation, including unmodeled dynamics, parameter uncertainties, and external disturbances. Mathematical analysis demonstrates the convergence of the employed NDO and the resulting closed-loop system. Furthermore, an anti-windup modification is applied to the NDO for control performance preserving in the presence of actuator saturation. Subsequently, the designed control schemes are preliminarily validated and compared via simulations. The baseline NDI controller demonstrates satisfactory attitude tracking performance in the case of nominal simulation; the NDO augmented NDI controller presents significantly improved ability of disturbance rejection when compared with the baseline NDI controller in the case of robust simulation; the anti-windup modified scheme, rather than the baseline NDI controller nor the NDO augmented NDI controller, can preserve the closed-loop performance in the case of actuator saturation. Finally, the baseline NDI scheme and the NDO augmented NDI scheme are implemented and further validated in the wind tunnel flight tests, which demonstrate that the experimental results are in good agreement with that of the simulations.

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Section: Mathematical Modelingmentioning

confidence: 99%

“…and moment C l C m C n T coefficients can be approximated and formulated as the following form [32,37]:…”

Section: Mathematical Modelingmentioning

confidence: 99%

Section: Comparison Of the Robust Performancementioning

confidence: 99%

Section: Investigation Of the Anti-windup Performancementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Design and Validation of Disturbance Rejection Dynamic Inverse Control for a Tailless Aircraft in Wind Tunnel

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Aircraft Modeling and Simulation

2022

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Cover image courtesy of Ruxandra Mihaela Botez © 2022 by the authors. Articles in this book are Open Access and distributed under the Creative Commons Attribution (CC BY) license, which allows users to download, copy and build upon published articles, as long as the author and publisher are properly credited, which ensures maximum dissemination and a wider impact of our publications.The book as a whole is distributed by MDPI under the terms and conditions of the Creative Commons license CC BY-NC-ND.

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Disturbance observer based dynamic inversion control for a wind tunnel free-flying test of a blended-wing-body aircraft

Cited by 2 publications

References 10 publications

Design and Validation of Disturbance Rejection Dynamic Inverse Control for a Tailless Aircraft in Wind Tunnel

Design and Validation of Disturbance Rejection Dynamic Inverse Control for a Tailless Aircraft in Wind Tunnel

Aircraft Modeling and Simulation

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