Adaptive Feedforward Control Design for Gust Loads Alleviation of Highly Flexible Aircraft

Wang, Y.; Li, F.; Ronch, Andrea Da

doi:10.2514/6.2015-2243

Cited by 18 publications

(6 citation statements)

References 16 publications

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“…The last objective assesses the effects of the proposed controller for GLA. It is worth noting that a follow-up study conducted flight tests on a high-altitude, longendurance unmanned air vehicle with a wing span of 24 m [19]. The paper continues with a description of the aeroelastic testbed in Section 2.…”

Section: Aeroelastic Modelmentioning

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: Aeroelastic Modelmentioning

confidence: 99%

Adaptive Feedforward Control for Gust-Induced Aeroelastic Vibrations

2018

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“…While some parameters causing these variations are known, it is difficult to precisely model their effect on the various aeroelastic modes that compose the system. The main approach to deal with this important issue in GLA is to define adaptive control laws, generally relying on finite-impulse response controllers [9][10][11][30][31][32], that can adapt in real-time to the current system thanks to the sensors' measurements. This technique is promising but requires an on-line optimization process that can be computationally intensive and does not lead to strong guarantees of stability and performance.…”

Section: Introductionmentioning

confidence: 99%

Robust Gust Load Alleviation at Different Flight Points and Mass configurations

Fournier

Massioni

Pham

et al. 2022

AIAA SCITECH 2022 Forum

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This work studies the gust load alleviation of a flexible aircraft equipped with a lidar sensor that measures the wind velocity ahead of the aircraft. The focus is put on the aeroelastic dynamics uncertainties due to the evolution of the velocity and the altitude during a flight, and to the variations of the aircraft mass configuration. A robust control approach is adopted in order to minimize the aircraft loads due to the wind in presence of such uncertainties with low-order controllers that satisfy the constraints imposed by the system's limitations and the implementability considerations. This is achieved through structured mixed H 2 /H ∞ synthesis with multiple models. The load alleviation capability of controllers of various orders, using a variable number of control surfaces, is assessed through the computation of the maximum loads obtained in various conditions of velocity, altitude and mass configurations.

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“…Flight-test measurements showed that the designed Lidar system was potential for future implementation in a real-time feedforward flight control system. The work of [35][36][37] investigated the gust load alleviation (GLA) problem using Lidar preview measurements of the incoming gust, based on model predictive control, gain-scheduled linear parametervarying control and adaptive feedforward control, respectively. Their simulation results showed that the wing root bending moments and the average vertical acceleration were largely reduced, indicating better load alleviation performance and disturbance rejection performance.…”

Section: Introductionmentioning

confidence: 99%