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SCIENCE CHINA Information Sciences, Volume 63 , Issue 11 : 212203(2020) https://doi.org/10.1007/s11432-019-2682-y

Robust adaptive control of hypersonic flight vehicle with asymmetric AOA constraint

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  • ReceivedJun 2, 2019
  • AcceptedSep 27, 2019
  • PublishedAug 18, 2020

Abstract

This paper investigates the state-constrained controller design of a hypersonic flight vehicle (HFV) based on an asymmetric barrier Lyapunov function (ABLF). The robust adaptive back-stepping controller with integral terms is applied for the HFV longitudinal dynamics. Considering the asymmetric angle of attack (AOA) constraint caused by the unique structure and scramjet, the controller is modified by constructing an ABLF, where the asymmetric constraint on AOA tracking error is introduced. Combined with the constraint on virtual control, the AOA is restricted to a predefined asymmetric interval. The system stability and the AOA constraint are guaranteed via Lyapunov analysis. Simulation results verify that the AOA can be kept in the given asymmetric interval while the altitude reference signal is tracked.


Acknowledgment

This work was supported by National Natural Science Foundation of China (Grant Nos. 61622308, 61873206, 61933010), Open Research Project of the State Key Laboratory of Industrial Control Technology, Zhejiang University, China (Grant Nos. ICT1900312, ICT20037), Stable Supporting Fund of Science and Technology on Underwater Vehicle Technology (Grant No. SXJQR2018WDKT05), and Synergy Innovation Foundation of the University and Enterprise for Graduate Students in Northwestern Polytechnical University (Grant No. XQ201904).


Supplement

Appendix

Nomenclature


References

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  • Figure 1

    Control scheme.

  • Figure 2

    (Color online) System tracking. (a) Altitude tracking; (b) altitude tracking error; (c) velocity tracking; protectłinebreak (d) velocity tracking error.

  • Figure 3

    (Color online) AOA response. (a) AOA; (b) AOA tracking error.

  • Figure 6

    Response of the system states. (a) FPA; (b) pitch rate; (c) FPA tracking error; (d) pitch rate tracking error.

  • Table A1  

    Table A1Nomenclature

    Parameter DescriptionParameterDescription
    $C_D^{\alpha^i}$The $i$th order coefficient of $\alpha$ contribution to drag $q$ Pitch rate
    $C_L^{\alpha^i}$The $i$th order coefficient of $\alpha$ contribution to lift $\bar~q$ Dynamic pressure
    $C_L^{\delta_e}$Coefficient of $\delta_e$ contribution to lift $S$ Reference area
    $C_M^{\delta_e}$Coefficient of $\delta_e$ contribution to pitch moment $T$ Thrust
    $C_M^{\alpha^i}$Coefficient of $\alpha$ contribution to pitch moment $V$ Velocity
    $\bar~c$Mean aerodynamic chord $V_d$ Velocity reference signal
    $D$Drag $z_T$ Thrust to moment coupling coefficient
    $g$Acceleration due to gravity $\alpha$ Angle of attack
    $h$Altitude $\beta_i$ Thrust fit parameters
    $h_r$Altitude reference signal $\gamma$ Flight path angle
    $I_{yy}$ Moment of inertia $\delta_e$ Elevator deflection
    $L$Lift $\delta_i$ Positive coefficients of modification terms
    $M_{yy}$Pitch momentin adaptive laws
    $m$ Mass $\eta_i$ Positive adaption gains
    $p_{ij}$ Positive parameters of differentiators $\Phi$ Fuel equivalence ratio

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