Robust Modal Damping Control for Active Flutter Suppression

Theis, Julian; Pfifer, Harald; Seiler, Peter

doi:10.2514/1.g004846

Cited by 29 publications

(9 citation statements)

References 48 publications

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“…The weighting scheme differentiates between frequency dependent weights denoted by 𝑊 and constant scaling factors denoted by 𝑉. It is taken from [21]. The weight function 𝑊 𝑒 enforces the frequency requirements on the sensitivity function, i.e.…”

Section: Enhanced Roll Attitude Flight Control System Designmentioning

confidence: 99%

Attitude Control for High Altitude Long Endurance Aircraft Considering Structural Load Limits

Weiser

Schulz

Voß

et al. 2023

AIAA SCITECH 2023 Forum

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This paper presents the design of a flight control system (FCS) for the lateral axis of a very flexible High Altitude Long Endurance (HALE) aircraft. To ensure that the HALE aircraft stays within its defined flight envelope, the FCS design incorporates roll attitude tracking requirements in the form of a coordinated turn and disturbance rejection requirements in the form of adequate discrete gust and continuous turbulence mitigation. The HALE aircraft itself is prone to aeroelastic effects. The paper shows via an aeroelastic load analysis, that a FCS not explicitly considering loads in its design is insufficient, as peak loads in the fuselage torsion and vertical tail bending moment are increased. As a response to these findings, a design approach for lateral FCS is proposed, which allows to weight the structural loads at the vertical tail root against the maximum roll attitude during the gust encounter. The benefit of this control design may result either in a potential decrease in structural weight or strength margins of the fuselage. Finally, the resulting lateral axis FCS design is validated in non-linear simulations of lateral gust encounters and the reduction of maximum loads on the vertical tail during worst case gusts is shown.

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Section: Enhanced Roll Attitude Flight Control System Designmentioning

confidence: 99%

Attitude Control for High Altitude Long Endurance Aircraft Considering Structural Load Limits

Weiser

Schulz

Voß

et al. 2023

AIAA SCITECH 2023 Forum

View full text Add to dashboard Cite

show abstract

“…The weighting scheme differentiates between frequency dependent weights denoted by W and constant scaling factors denoted by V . It is taken from [5]. The weight function W e enforces the frequency requirements on the sensitivity function, i.e.…”

Section: A Mixed Sensitivity Controller Synthesismentioning

confidence: 99%

Robust Path-following Control with Anti-Windup for HALE Aircraft

Weiser

Ossmann

Pfifer

2022

2022 30th Mediterranean Conference on Control and Automation (MED)

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In this paper, a robust path-tracking controller for a High Altitude Long Endurance (HALE) aircraft is presented. The main control paradigm for operating a HALE aircraft consists of a basic path following control, i.e. tracking a reference flight path and airspeed while dealing with very limited thrust. The priority lies in keeping airspeed inside the small flight envelope of HALE aircraft even during saturated thrust. For the basic path following objective, a mixed sensitivity approach is proposed which can easily deal with decoupled tracking and robustness requirements. To deal with saturated control inputs, an anti-windup scheme is incorporated in the control design. A novel observer-based mixed sensitivity design is used which allows directly using classical anti-windup methods based on back-calculation. The control design is verified in nonlinear simulation and compared to a classical total energy control based controller.

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“…Unless otherwise specified, we will consider as output only the first bending mode of the wing (n y =1), since this is usually the one associated with dynamic instabilities and large deformations, and thus it is of particular interest for active control tasks [48,49]. The flight speed will be considered as the time-varying parameter (n ρ =1).…”

Section: Summary Of the Wing's Fsi Modelmentioning

confidence: 99%

The Balanced Mode Decomposition Algorithm for Data-Driven LPV Low-Order Models of Aeroservoelastic Systems

Iannelli¹,

Fasel²,

Smith³

2021

Preprint

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A novel approach to reduced-order modeling of high-dimensional time varying systems, such as those encountered in aeroservoelasticity, is proposed. It leverages the formalism of the Dynamic Mode Decomposition technique together with the concept of balanced realization. It is assumed that the only information available on the system comes from input, state, and output trajectories generated by numerical simulations or recorded and estimated during experiments, thus the approach is fully data-driven. The goal is to obtain an input-output low dimensional linear model which approximates the system across its operat-

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Robust Modal Damping Control for Active Flutter Suppression

Cited by 29 publications

References 48 publications

Attitude Control for High Altitude Long Endurance Aircraft Considering Structural Load Limits

Attitude Control for High Altitude Long Endurance Aircraft Considering Structural Load Limits

Robust Path-following Control with Anti-Windup for HALE Aircraft

The Balanced Mode Decomposition Algorithm for Data-Driven LPV Low-Order Models of Aeroservoelastic Systems

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