Nonlinear H Method for Control of Wing Rock Motions

Shue, Shyh-Pyng; Agarwal, Ramesh K.; Shi, Peng

doi:10.2514/2.4487

Cited by 25 publications

(16 citation statements)

References 34 publications

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“…At meantime, some other researchers tried nonlinear control strategies like Shue and Agarwal [20] who introduced a nonlinear H ∞ method for the control of wing rock motions. In [21], Abdulwahab and Hongquan achieved limit cycle prevention by adding a certain control function to the nonlinear dynamics of the wing-rock model; Zribi, et al [22] introduced a state transformation such that the transformed dynamic model is in a form which is suitable for a variety of control designs.…”

Section: Introductionmentioning

confidence: 99%

Linear Adaptive Fault Tolerant Control against Aircraft Actuator Failures for Wing Rock Suppression

Benchaita¹,

Ladaci²

2020

Int J Robot Eng

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In this paper we consider the problem of the suppression of wing rock phenomenon in presence of actuator faults. The main aim of this work is the application of a linear adaptive actuator failure compensation control scheme for wing rock motion of a slender delta wing. First, the analytical nonlinear model that characterizes the phenomenon of wing rock is given, and its behavior for different angles of attack is presented. Then, an adaptive actuator failure compensation redundant control design is proposed, and applied for a rolling motion regulation in the presence of actuator faults. Finally, numerical simulations are conducted to show the effectiveness of the control scheme for wing rock suppression for different actuator failures scenarios.

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Section: Introductionmentioning

confidence: 99%

Linear Adaptive Fault Tolerant Control against Aircraft Actuator Failures for Wing Rock Suppression

Benchaita¹,

Ladaci²

2020

Int J Robot Eng

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“…In general the system in (19) can be written asẇ = f (w, t) where vector w = [e 1 z 1 ] T . Defining the virtual displacement for this system by δw, we get the following; (20) For transformed system, the Jacobian matrix J is defined as…”

Section: Controller Design For the System Without Uncertaintymentioning

confidence: 99%

“…Perfect ink@ee.iitd.ac.in rock mechanism in combat aircraft applications is still to be established. Several control strategies are being proposed to tackle this problem and some of them can be found in [15]- [19] and the references there in. In recent years, neural network based techniques have presented an alternative design methodology for identifying and control of dynamic systems [20]- [22].…”

Section: Introductionmentioning

confidence: 99%

Adaptive control of wing rock system in uncertain environment using contraction theory

Sharma

Kar

2008

2008 American Control Conference

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Contraction theory is used to study stability based on differential and incremental behaviour of trajectories of a system with respect to each other. Application of contraction theory provides a platform to analyze the exponential stability of nonlinear systems. This paper considers the design of a control law for wing rock system using contraction theory principles. An adaptive control design approach based on contraction theory is proposed for controlling the dynamics of such systems for the cases with and without uncertainty in parameters. An adaptive control law along with parameter updation law is derived for uncertain wing rock system to achieve convergence of trajectories of actual system to that of desired system. The analysis made in the paper leads to quite simple results avoiding complexities involved with Lyapunov method. Finally numerical simulations are presented to justify the effectiveness of the proposed controller.

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“…A set of techniques for wing rock control have been proposed previously, namely, using linear parameter-varying controllers [20], nonlinear H ∞ method [21], adaptive control methods [22][23][24], etc. At the same time, when applied to a real system, the control algorithms can fail to ensure stability, and the validation stage could be considered as a very important part of the control design.…”

Section: Introductionmentioning

confidence: 99%

Dynamic Rig for Validation of Control Algorithms at High Angles of Attack

Ignatyev¹,

Sidoryuk²,

Kolinko³

et al. 2017

Journal of Aircraft

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The dynamics of a modern aircraft at high angles of attack is complicated, with hazardous phenomena such as wing rock, stall, and spin. The paper presents a technique for cost-effective and safe studying of conventional and critical flight regimes and control validation using an autonomous scaled aircraft model mounted in a three-degree-offreedom gimbal in a wind tunnel. The similarity of the dynamics at high angles of attack of the wind-tunnel model and the free-flying model is demonstrated. To suppress the wing rock and to prevent the stall, two control laws are designed using linear matrix inequalities and model reference adaptive control techniques. The controllers are tested in a semifree flight of the autonomous scaled model in the wind tunnel. Wing rock suppression and stall and spin prevention are demonstrated.C nΔδ e = ∂C n ∂Δδ e C nδ a = ∂C n ∂δ a C l ; C m ; C n = roll, pitch, and yaw moment coefficients C l0 ; C m0 ; C n0 = static values of roll, pitch, and yaw moment coefficients C mq = ∂C m ∂q c∕2V c = mean aerodynamic chord g = acceleration due to gravity I = matrix of moment of inertia I xx = moment of inertia in roll Iyy = moment of inertia in pitch I zz = moment of inertia in yaw k 1;2θ ; k 1;2ϕ ; k 1;2ψ = friction coefficients M a ; M g ; M f = aerodynamic, gravity, and gimbal friction moments p, q, r = roll, pitch, and yaw rates Q fθ ; Q fϕ ; Q fψ = components of friction moment S = reference wing area V = velocity α, β = angles of attack and sideslip δ = vector of control effectors ΔC lδ r ; ΔC nδ r = increment of roll and yaw moment coefficients due to rudder deflection Δx c:g: ; Δz c:g:= misalignment of the center of mass with respect to the center of gimbals δ e ; Δδ e ; δ a ; δ r = mean stabilator, differential stabilator, aileron, and rudder deflections ϕ; θ; ψ = rotational angles in gimbals in roll, pitch, and yaw

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Nonlinear H Method for Control of Wing Rock Motions

Cited by 25 publications

References 34 publications

Linear Adaptive Fault Tolerant Control against Aircraft Actuator Failures for Wing Rock Suppression

Linear Adaptive Fault Tolerant Control against Aircraft Actuator Failures for Wing Rock Suppression

Adaptive control of wing rock system in uncertain environment using contraction theory

Dynamic Rig for Validation of Control Algorithms at High Angles of Attack

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