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Super-twisting sliding mode control for aircraft at high angle of attack based on finite-time extended state observer

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Abstract

This paper proposes a finite-time decoupling control strategy for aircraft with thrust vector at high angle of attack maneuver. Firstly, the nonlinear mathematical model of the aircraft is presented. Taking into account the insufficiency of the aerodynamic control surface, a thrust vector model with double nozzles is added. Subsequently, a three-channel decoupling control scheme based on finite-time extended state observer is employed to realize the high angle of attack maneuver. Strong coupling among different channels, aerodynamic uncertainties and other unmodeled dynamics are regarded as total disturbance and estimated by a finite-time extended state observer. Super-twisting (SWT) sliding mode control is utilized to obtain expected performance and finite-time stability. The daisy chain method is adopted to realize the control allocation. Finally, the numerical simulations are provided to demonstrate the effectiveness and robustness of the proposed methodology.

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Acknowledgements

This work was supported by the National Natural Science Foundation of China under Grant Nos. 61973175, 61573197, 61973172 and the Key Technologies R&D Program of Tianjin Grant No. 19JCZDJC32800. The authors thank the editors and the anonymous reviewers for their helpful comments and suggestions that allowed us to improve the paper.

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Authors and Affiliations

  1. College of Artificial Intelligence, Nankai University, Tianjin, 300350, China

    Junjie Liu, Mingwei Sun, Zengqiang Chen & Qinglin Sun

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  1. Junjie Liu
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  2. Mingwei Sun
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  3. Zengqiang Chen
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  4. Qinglin Sun
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Correspondence to Zengqiang Chen.

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Appendix: Nomenclature

Appendix: Nomenclature

Nomenclature

Interpretation

\(\alpha ,\beta \)

Angle of attack, sideslip angle

V

Flight speed

g

Gravitational acceleration

\(\mu \)

Bank angle about the velocity vector

\(\gamma \)

Flight path angle

\(\chi \)

Velocity heading angle

T

Total engine thrust

\(\bar{q}\)

Dynamic pressure

\(I_{xx},I_{yy},I_{zz}\)

Roll, pitch, yaw inertia moments

p, q, r

Components of angular velocity

\(x_E,y_E,z_E\)

Position coordinates

\(C_{x\_\mathrm{tot}}\)

Aerodynamic force coefficient in x axis

\(C_{y\_\mathrm{tot}}\)

Aerodynamic force coefficient in y axis

\(C_{z\_\mathrm{tot}}\)

Aerodynamic force coefficient in z axis

\(C_{l\_\mathrm{tot}}\)

Aerodynamic torque coefficient in x axis

\(C_{m\_\mathrm{tot}}\)

Aerodynamic torque coefficient in y axis

\(C_{n\_\mathrm{tot}}\)

Aerodynamic torque coefficient in z axis

\(T_x,T_y,T_z\)

Thrust components in three axes

l, m, n

Aerodynamic torque

\(l_T,m_T,n_T\)

Thrust vector torque

\(\delta _e,\delta _a,\delta _r\)

Aerodynamic surfaces deflection angles

\(\delta _x,\delta _y,\delta _z\)

Thrust vector deflection angles

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Liu, J., Sun, M., Chen, Z. et al. Super-twisting sliding mode control for aircraft at high angle of attack based on finite-time extended state observer. Nonlinear Dyn 99, 2785–2799 (2020). https://doi.org/10.1007/s11071-020-05481-1

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