Active gust load alleviation system for flexible aircraft: Mixed feedforward/feedback approach

Alam, Mushfiqul; Hromčík, Martin; Haniš, Tomáš

doi:10.1016/j.ast.2014.12.020

Cited by 36 publications

(21 citation statements)

References 13 publications

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“…A similar strategy was extended to the multiple-input multiple-output case in [15]. Reference [16] investigated a hybrid strategy obtained by combining feedback and feedforward controls. It was found that the hybrid strategy significantly improved the reduction in wing bending moment when compared with the feedback strategy alone.…”

Section: Introductionmentioning

confidence: 99%

Adaptive Feedforward Control for Gust-Induced Aeroelastic Vibrations

2018

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This paper demonstrates the implementation of an adaptive feedforward controller to reduce structural vibrations on a wing typical section. The aeroelastic model includes a structural nonlinearity, which is modelled in a polynomial form. Aeroelastic vibrations are induced by several gusts and atmospheric turbulence, including the discrete “one-minus-cosine” and a notably good approximation in the time-domain to the von Kármán spectrum. The control strategy based on the adaptive feedforward controller has several advantages compared to the standard feedback controller. The controller gains, which are updated in real-time during the gust encounter, are found solving a minimization problem using the finite impulse responses as basis functions. To make progress with the application in aeroelasticity, a single-input single-output controller is designed measuring the wing torsional deformation. For both deterministic and random atmospheric shapes, the controller was found successful in alleviating the aeroelastic vibrations. The impact of the control action on the unmeasured structural modes was found minimal.

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Section: Introductionmentioning

confidence: 99%

Adaptive Feedforward Control for Gust-Induced Aeroelastic Vibrations

2018

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“…performances, see e.g. [1], [2], [3], [4], [5], [5], [6], [7], [8], [9], [10] 2 . However a few involving real wind tunnel tests, and, to the authors' best of knowledge, most of them refer to tests performed in the low speed regime [11], [12].…”

Section: Introductionmentioning

confidence: 99%

Gust Load Alleviation: Identification, Control, and Wind Tunnel Testing of a 2-D Aeroelastic Airfoil

Poussot-Vassal

Demourant

Lepage

et al. 2017

IEEE Trans. Contr. Syst. Technol.

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One important element in the progression of aircraft environmental impact reduction is to reduce their overall weight (without impacting other consumption-oriented performance index, such as drag). In addition to the numerous work conducted in material and structural engineering, from a control viewpoint, this challenge is strongly connected to the need of the development and assessment of dedicated load control strategies in response to gust disturbances. Indeed, the load factors due to gust are considered as a sizing criteria during the aircraft conception steps and require specific verification according to the certification process. To this end, a dedicated experimental research program based on Wind Tunnel (WT) campaigns has been carried out. More specifically, the paper contributions are twofold: (i) to identify the gust load effect using two different versatile frequency-domain techniques, namely the Loewner interpolation and a modified subspace approach, and (ii) to design and implement an active closed-loop control to alleviate the gust main effect. The entire procedure is validated in a wind tunnel setup , involving a gust generator device and a 2D aeroelastic airfoil, for varying configuration travelling from sub to transonic airflow and varying angles of attack, emphasizing the effectiveness and robustness of the overall approach.

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“…Using a reference signal, Wildschek et al [23,24] constructed a Single-Input Single-Output finite impulse response (FIR) feedforward controller to suppress the gust-induced vibrations of a transport airplane. Recently, a similar strategy was extended to the Multiple-Input Multiple-Output case [25]; however, the hybrid control concept [26], which combines feedback and feedforward controls, can be used to obtain improved performance.…”

Section: Introductionmentioning

confidence: 99%

Gust Load Alleviation on a Large Transport Airplane

Zhao

Yue

2016

Journal of Aircraft

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This study develops an active control technology to reduce the incremental dynamic loads of a large four-engine transport airplane flying through a gust field. The mathematical model of the proposed gust-alleviation system features composite structural motions (for example, rigid-body motions, elastic vibrations, and deflections of control surfaces) and unsteady aerodynamic forces induced by the structural motions and the gusts. A clear outline of the procedure is first provided to determine the aeroservoelastic equation of the system. Then, an adaptive feedforward controller that uses the preview information of the gust sensed by an onboard alpha probe is designed to operate the ailerons symmetrically to alleviate the wing-root bending moment induced by the gust. The rigid-body motions due to travelling gusts are also compensated for using symmetrical deflections of the elevators. To solve the problems of weight drift and weight bias that are commonly encountered in adaptive control, the circular leaky least meansquared algorithm is applied to update the weights of the adaptive controller. The simulation results show that a large transport airplane equipped with the proposed gust-alleviation system experiences a significantly lower wing-root bending moment in both stationary and nonstationary gusty environments.

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Active gust load alleviation system for flexible aircraft: Mixed feedforward/feedback approach

Cited by 36 publications

References 13 publications

Adaptive Feedforward Control for Gust-Induced Aeroelastic Vibrations

Adaptive Feedforward Control for Gust-Induced Aeroelastic Vibrations

Gust Load Alleviation: Identification, Control, and Wind Tunnel Testing of a 2-D Aeroelastic Airfoil

Gust Load Alleviation on a Large Transport Airplane

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