H/sub 2/ and H/sub /spl infin//-optimal gust load alleviation for a flexible aircraft

Aouf, Nabil; Boulet, Benoît; Botez, Ruxandra

doi:10.1109/acc.2000.879526

Cited by 32 publications

(35 citation statements)

References 3 publications

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“…Early efforts in aeroservoelasticity were based on flexible aircraft models consisting of traditional rigid-body equations and a series of second-order differential equations representing the structural modes [11,12]. Recently, more detailed mathematical formulations of flexible aircraft flight dynamics have been developed.…”

Section: Aeroservoelastic Formulationmentioning

confidence: 99%

“…Early efforts in aeroservoelasticity were based on flexible aircraft models consisting of rigid-body equations and a series of second-order differential equations representing the structural modes [11,12]. McLean and Prasad [11] used a linear quadratic optimal controller to reduce the wing bending moment of the C-5A Galaxy aircraft.…”

Section: Introductionmentioning

confidence: 99%

“…The simulation results showed that the application of the control system led to less oscillatory motion in the wing bending moment; this helps to reduce the accumulation of fatigue cycles in the aircraft wing. Aouf et al [12] employed optimal and robust control methods to perform GLA on a flexible variant of the B-52 aircraft. The controller took advantage of ailerons and horizontal canards to reduce the transient peak value of the structural loadings caused by stochastic gust excitation.…”

Section: Introductionmentioning

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: Aeroservoelastic Formulationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

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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“…Various sensors, effectors, 5 and control laws (LQG, 4 robust, 6 adaptive feedforward, 7 model predictive, 8 etc.…”

Section: Introductionmentioning

confidence: 99%

Gust Load Alleviation and Ride Quality Improvement with Incremental Nonlinear Dynamic Inversion

Wang

Kampen

Chu

2017

AIAA Atmospheric Flight Mechanics Conference

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In this paper, a non-cascaded control framework of Incremental Nonlinear Dynamic Inversion (INDI) is proposed to alleviate gust loads and improve ride quality using direct lift control. By feeding back linear and angular accelerations, the dependency of the control laws on model has been reduced, which enhances the robust performance of the system. Simulations of a quasi-rigid aircraft flying through various spatial turbulence and gust fields demonstrate the feasibility of the proposed INDI gust load alleviation (GLA) controller. Furthermore, a cascaded automatic flight control system is designed based on the INDI GLA control law. Desired tracking performance and load alleviation can be achieved simultaneously. Additionally, a comparison with LQR/LQG control is presented from the perspective of GLA performance, command tracking, and robustness.

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“…Several methods were investigated with the aim to generate of the LFT parametric models ([10]- [13]). LFT is based primarily on the number of different types of uncertainties that are incorporated in the aircraft dynamic model.…”

Section: Introductionmentioning

confidence: 99%

Cessna Citation X Business Aircraft Eigenvalue Stability– Part 1: a New GUI for the LFRs Generation

Boughari¹,

Mihaela²,

Theel³

et al. 2017

INCAS BULLETIN

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The aim of "Robustness Analysis" is to assess aircraft stability in the presence of all admissible uncertainties. Models that are able to describe the aircraft dynamics by taking into account all uncertainties over a region inside the flight envelope have therefore been developed, using Linear Fractional Representation (LFR). In this paper Part 1 a friendly Graphical User Interface is developed to facilitate the generation of Linear Fractional Representation uncertainty models for the

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H/sub 2/ and H/sub /spl infin//-optimal gust load alleviation for a flexible aircraft

Cited by 32 publications

References 3 publications

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

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

Gust Load Alleviation and Ride Quality Improvement with Incremental Nonlinear Dynamic Inversion

Cessna Citation X Business Aircraft Eigenvalue Stability– Part 1: a New GUI for the LFRs Generation

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