Neural network adaptive control of wing-rock motion of aircraft model mounted on three-degree-of-freedom dynamic rig in wind tunnel

Ignatyev, Dmitry

doi:10.1051/eucass/201810073

Cited by 3 publications

(3 citation statements)

References 16 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In this section, the MRAC controller [22,23,27,32] stabilizing the wind-tunnel model in the entire available incidence range is discussed. The proportional control law δ prop [Eq.…”

Section: B Neural Network Adaptive Controlmentioning

confidence: 99%

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

Ignatyev¹,

Sidoryuk²,

Kolinko³

et al. 2017

Journal of Aircraft

View full text Add to dashboard Cite

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

show abstract

“…In this section, the MRAC controller [22,23,27,32] stabilizing the wind-tunnel model in the entire available incidence range is discussed. The proportional control law δ prop [Eq.…”

Section: B Neural Network Adaptive Controlmentioning

confidence: 99%

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

Ignatyev¹,

Sidoryuk²,

Kolinko³

et al. 2017

Journal of Aircraft

View full text Add to dashboard Cite

show abstract

“…The Russian Central Aerodynamics Research Institute has developed a back-supported VFT support mechanism with three degrees of freedom and performed research on issues such as high angle of attack stall/deviation [12] and flight control law algorithm verification [13].…”

Section: Introductionmentioning

confidence: 99%

Underconstrained Cable-Driven Parallel Suspension System of Virtual Flight Test Model in Wind Tunnel

Wu¹,

Zeng²,

Liu³

et al. 2023

Computer Modeling in Engineering &Amp; Sciences

View full text Add to dashboard Cite

An underconstrained cable-driven parallel robot (CDPR) suspension system was designed for a virtual flight testing (VFT) model. This mechanism includes two identical upper and lower kinematic chains, each of which comprises a cylindrical pair, rotating pair, and cable parallelogram. The model is pulled via two cables at the top and bottom and fixed by a yaw turntable, which can realize free coupling and decoupling with three rotational degrees of freedom of the model. First, the underconstrained CDPR suspension system of the VFT model was designed according to the mechanics theory, the degrees of freedom were verified, and the support platform was optimized to realize the coincidence between the model's center of mass and the rotation center of the mechanism during the motion to ensure the stability of the support system. Finally, kinematic and dynamical modeling of the underconstrained CDPR suspension system was conducted; the system stiffness and stability criteria were deduced. Thus, the modeling of an underconstrained, reconfigurable, passively driven CDPR was understood comprehensively. Furthermore, dynamic simulations and experiments were used to verify that the proposed system meets the support requirements of the wind tunnel-based VFT model. This study serves as the foundation for subsequent wind tunnel test research on identifying the aerodynamic parameters of aircraft models, and also provides new avenues for the development of novel support methods for the wind tunnel test model.

show abstract

“…Wing rock motion is not acceptable from the operational and safety point of view. The problem is a concern to a pilot because it may have an adverse effect on aircraft manoeuvrability during landing approach or during a dogfight in a combat situation and it may lead to its crash (Ignatyev, 2018). The severity of wing rock may degrade the performance of weapon aiming control and accuracy.…”

Section: Introductionmentioning

confidence: 99%

Finite-Time Control of Wing-Rock Motion for Delta Wing Aircraft Based on Whale-Optimization Algorithm

Al-Qassar

Al-Obaidi

Hasan

et al. 2021

Indonesian J. Sci. Technol

View full text Add to dashboard Cite

The rise of wing-rock motion in delta-wing aircraft has an adverse effect on the manoeuvrability of aircraft and it may result in its crash. This study presents a finite-time control design to tackle the dynamic motion due to the Wing-Rock effect in delta-wing aircraft. The control design is developed based on the methodology of Super Twisting Sliding Mode Control (STSMC). The Lyapunov stability analysis has been pursued to ensure asymptotic convergence of errors and to determine the finite time. The design of STSMC leads to the appearance of design parameters, which have a direct impact on the dynamic performance of the controlled system. To avoid the conventional tuning of these parameters and to have an optimal performance of the proposed controller, a modern optimization technique has been proposed based on Wale Optimization Algorithm. A comparison study between optimal and non-optimal finite-time super twisting sliding mode controllers has been established and their effectiveness has been verified via numerical simulation using MATLAB programming format.

show abstract

Neural network adaptive control of wing-rock motion of aircraft model mounted on three-degree-of-freedom dynamic rig in wind tunnel

Cited by 3 publications

References 16 publications

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

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

Underconstrained Cable-Driven Parallel Suspension System of Virtual Flight Test Model in Wind Tunnel

Finite-Time Control of Wing-Rock Motion for Delta Wing Aircraft Based on Whale-Optimization Algorithm

Contact Info

Product

Resources

About