Unified Theory for the Dynamics and Control of Maneuvering Flexible Aircraft

Meirovitch, L.; Tuzcu, Ilhan

doi:10.2514/1.1489

Cited by 112 publications

(107 citation statements)

References 10 publications

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“…25 and L g =0.5, are presented in Figs. [17][18][19][20][21][22]. Note that in the absence of GLA the aircraft experienced control surface saturation, and the controller failed to stabilize the plant when it was flying through a discrete gust with L g =0.5.…”

Section: B Simulation Resultsmentioning

confidence: 99%

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Model-Predictive Gust Load Alleviation Controller for a Highly Flexible Aircraft

Haghighat

Liu

Martins

2012

Journal of Guidance, Control, and Dynamics

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In this paper, a gust load alleviation system based on model-predictive control is developed for a very flexible aircraft. Two main contributions presented in this work are as follows. First, a unified dynamics framework is developed to represent the full six-degrees-of-freedom rigid body along with the structural dynamics. This allows for an integrated control design to account for maneuverability (flying qualities) and aeroelasticity simultaneously, leading to a new and improved configuration for a very flexible aircraft. Second, an improved model-predictive control formulation is proposed for stabilization and gust load alleviation. The performance of the model-predictive control is further improved by introducing an additional feedback loop to increase the prediction accuracy. To demonstrate the effectiveness of the proposed approach, the integrated formulation is compared with existing approaches. Further, the load alleviation performance is evaluated for various discrete and continuous gusts.

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Section: B Simulation Resultsmentioning

confidence: 99%

“…Some of their assumptions, including the application of aerodynamic strip theory and small structural deflections, make this approach less appropriate for modeling highly flexible aircraft. More rigorous formulations using a body-fixed axis system have also been developed [20,21,22,23,24,25].…”

Section: Aeroservoelastic Formulationmentioning

confidence: 99%

Model-Predictive Gust Load Alleviation Controller for a Highly Flexible Aircraft

Haghighat

Liu

Martins

2012

Journal of Guidance, Control, and Dynamics

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“…Their aerodynamic model, however, assumed a steady flow, and their frame of reference consisted of the so-called mean axes which are hard to locate in a practical situation. Meirovitch and Tuzcu [11] extended their model in several ways: they used a more intuitive reference frame (the conventional body axes) and a more accurate Theodorsen's unsteady aerodynamics theory for computing the forces and moments [12]. Recently, Nguyen and Tuzcu [13] presented a dynamic model for a fully flexible aircraft.…”

Section: A Literature Reviewmentioning

confidence: 99%

Dynamics and Performance of Tailless Micro Aerial Vehicle with Flexible Articulated Wings

et al. 2012

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The purpose of this paper is to analyze and discuss the performance and stability of a tailless micro aerial vehicle with flexible articulated wings. The dihedral angles can be varied symmetrically on both wings to control the aircraft speed independently of the angle of attack and flight-path angle, while an asymmetric dihedral setting can be used to control yaw in the absence of a vertical tail. A nonlinear aeroelastic model is derived, and it is used to study the steadystate performance and flight stability of the micro aerial vehicle. The concept of the effective dihedral is introduced, which allows for a unified treatment of rigid and flexible wing aircraft. It also identifies the amount of elasticity that is necessary to obtain tangible performance benefits over a rigid wing. The feasibility of using axial tension to stiffen the wing is discussed, and, at least in the context of a linear model, it is shown that adding axial tension is effective but undesirable. The turning performance of an micro aerial vehicle with flexible wings is compared to an otherwise identical micro aerial vehicle with rigid wings. The wing dihedral alone can be varied asymmetrically to perform rapid turns and regulate sideslip. The maximum attainable turn rate for a given elevator setting, however, does not increase unless antisymmetric wing twisting is employed.

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“…At last, we aim to investigate this coupling effect of the nonlinear gyroscopic forces on the elastic deformations to assess the mean-axes approximation. The application in mind is for the nonlinear flight dynamics of flexible aircraft [29] and the methodology has been integrated into the framework for Simulation of High-Aspect Ratio Planes (SHARP) [30]. Our starting point will be a geometrically-exact formulation of the beam dynamics, using a displacement-based approach [24,28].…”

Section: Introductionmentioning

confidence: 99%

Consistent structural linearisation in flexible-body dynamics with large rigid-body motion

Hesse

Palacios

2012

Computers & Structures

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A consistent linearisation, using perturbation methods, is obtained for the structural degrees of freedom of flexible slender bodies with large rigid-body motions. The resulting system preserves all couplings between rigid and elastic motions and can be projected onto a few vibration modes of a reference configuration. This gives equations of motion with cubic terms in the rigid-body degrees of freedom and constant coefficients which can be pre-computed prior to the time-marching simulation. Numerical results are presented to illustrate the approach and to show its advantages with respect to mean-axes approximations.

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Unified Theory for the Dynamics and Control of Maneuvering Flexible Aircraft

Cited by 112 publications

References 10 publications

Model-Predictive Gust Load Alleviation Controller for a Highly Flexible Aircraft

Model-Predictive Gust Load Alleviation Controller for a Highly Flexible Aircraft

Dynamics and Performance of Tailless Micro Aerial Vehicle with Flexible Articulated Wings

Consistent structural linearisation in flexible-body dynamics with large rigid-body motion

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