Robustness Analysis of a Stability Augmentation System of a Highly Flexible Aircraft

Rona, Felipe Carpentieri; Ramirez, Pedro J. González; Silvestre, Flávio J.; Cesnik, Carlos E. S.; Pang, Zi Yang

doi:10.2514/6.2018-0604

Cited by 2 publications

(3 citation statements)

References 10 publications

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“…All poles of the closed-loop system must be placed on the left-hand side of the complex plane. The control system must be able to ensure stability under a 25% uncertainty of sensor measurements and control actuation [19,38]. This information may be assessed via a robustness analysis using the small-gain theorem [39].…”

Section: Robustness and Stabilitymentioning

confidence: 99%

“…This information may be assessed via a robustness analysis using the small-gain theorem [39]. To evaluate the stability of the SAS with uncertainties, the singular value σ and the MΔ-structure techniques were used [38].…”

Section: Robustness and Stabilitymentioning

confidence: 99%

“…The optimization process of the gains included a robustness checking based in the small gain theorem [38]. The system was evaluated to be robust to the given uncertainty if the structured singular value for MΔ structure was smaller than one at all frequencies.…”

Section: A Inner Loopmentioning

confidence: 99%

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Loop-Separation Control for Very Flexible Aircraft

et al. 2020

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In this research, a loop-separation concept (LSC) is applied to a very flexible aircraft. Appealing features of this control architecture include decoupled control logic and the use of high-order models for controller design, thus not requiring model order reduction. The LSC consists of two control loops. The inner loop employs a linear quadratic regulator capable of stabilizing the aircraft while controlling the shape of the half-wings independently from each other by artificially stiffening the structure. Structural dynamics can potentially be used in the design of the inner-loop regulator. The outer-loop design is based on rigid-body outputs. The outer loops for tracking velocity, heading, sideslip angle, and altitude are designed using nonsmooth H ∞ optimization techniques. Numerical results show that structural feedback in the inner loop yields better regulation performance and reduced structural deformations. The autopilot is capable of attaining the commanded reference with low control energy while meeting the maneuver requirements and regulating the elastic deformations of the wing.

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Section: Robustness and Stabilitymentioning

confidence: 99%

Section: Robustness and Stabilitymentioning

confidence: 99%