Design and Experimental Validation of Gust Load Alleviation Systems based on Static Output Feedback

Ricci, Sergio; Toffol, Francesco; Marchetti, Luca; Gaspari, Alessandro De; Chardi, Jose V.; Riccobene, Luca; Fonte, Federico; Mantegazza, Paolo

doi:10.2514/6.2022-0441

Cited by 2 publications

(2 citation statements)

References 21 publications

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“…Because of the aforementioned iso-frequency scaling and the need to emulate a full-scale EMA solution for the actuating systems, during the various phases of the GLAMOUR project [30] and one of its extensions [53], the bandwidth of the actuators has always been maintained at 10 Hz. On the other hand, in order to follow the sampling rate guide lines listed in subsection II-F, the actual rate values for the actuators had to vary in relation to the sampling frequencies of the diverse gust controllers under test, as dictated by their designers.…”

Section: Sampling Frequencymentioning

confidence: 99%

Dual Loop PI^m PIⁿ Control for an Aileron Positioning

De Gaspari,

Mantegazza

2024

IEEE Access

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Aircraft control surfaces are subjected to uncertain design parameters and time-varying external disturbances related to aerodynamic loads. This paper presents a control formulation for their positioning based on a velocity/position dual loop, embedding an arbitrary order of integral actions determined through a simple linear design. The adoption of an appropriate high order integration aims to compensate for external disturbances, modeling uncertainties and the impact of some nonlinearities. Relevant design and implementation issues were also described, including windup mitigation and the use of an observer to compensate for out-of-band disturbances. After a numerical model validation comprising a Monte Carlo assessment of the combined uncertainties, the controller was verified experimentally. The test bench was made up of the aileron of a wind tunnel model, driven by an electric motor through a mildly tensioned timing belt transmission. The results of a significant test set are provided to demonstrate the effectiveness of such a controller against noteworthy design uncertainties, such as sliding friction, sensor failure, free play due to inadequate belt tension, and approximate design parameters.

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Section: Sampling Frequencymentioning

confidence: 99%

Dual Loop PI^m PIⁿ Control for an Aileron Positioning

De Gaspari,

Mantegazza

2024

IEEE Access

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“…For this test, an aero-servo-elastic 1:6 scaled wind tunnel half-model, representative of the TP90, was designed and built [50] and called WTT3. The half-model is vertically mounted, and the free body motion (plunge and pitch) is preserved thanks to a pivotsledge mechanism.…”

Section: Aero-servo-elastic Wind Tunnel Test (Wtt3)mentioning

confidence: 99%

Development of an Active Wingtip for Aeroelastic Control

Toffol

Ricci

2023

Aerospace

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This paper presents the design of an innovative wingtip device actively actuated to control the aeroelastic loads, with a focus on the gust load alleviation. It summarizes the work carried out in the Clean Sky 2 AIRGREEN2 project, where the device was developed from scratch and reached a relevant technology readiness level with the full-scale prototype manufacturing and testing, compulsory to obtain the permit to fly. This paper describes the overall design of the devices, covering the structure, the aero-servo-elasticity characteristics of the whole aircraft, the actuation system design, the scaled wind tunnel testing, and the full-scale structural qualification tests. The paper proves how the development of a new item involves several disciplines simultaneously, remarking on the importance of an integrated approach to the new generation aircraft design.

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Design and Experimental Validation of Gust Load Alleviation Systems based on Static Output Feedback

Abstract: Access to the published version may require subscription.When citing this work, cite the original published paper.

Cited by 2 publications

References 21 publications

Dual Loop PI^m PIⁿ Control for an Aileron Positioning

Dual Loop PI^m PIⁿ Control for an Aileron Positioning

Development of an Active Wingtip for Aeroelastic Control

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Design and Experimental Validation of Gust Load Alleviation Systems based on Static Output Feedback

Abstract: Access to the published version may require subscription.When citing this work, cite the original published paper.

Cited by 2 publications

References 21 publications

Dual Loop PIm PIn Control for an Aileron Positioning

Dual Loop PIm PIn Control for an Aileron Positioning

Development of an Active Wingtip for Aeroelastic Control

Contact Info

Product

Resources

About

Dual Loop PI^m PIⁿ Control for an Aileron Positioning

Dual Loop PI^m PIⁿ Control for an Aileron Positioning