An Adaptive Control Approach for a Flexible Hypersonic Glide Vehicle

Chen, Erkang; Jing, Wuxing; Gao, Changsheng; Zhang, Zhao

doi:10.1109/icmae.2018.8467711

Cited by 4 publications

(2 citation statements)

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“…26 Pourtakdust and Assadian 27 model the IMU vibrations effects, and find that IMU location in the aft portion of vehicle could lead to dynamic instability. Similarly, Chen et al 28 find that the bending vibration degrades the performance of rigid-body control system and the INS located in the aft portion of FHV could lead to instability. Hence, aeroservoelastic effect (especially servoelastic effect) must be taken into account in control system design for FHV.…”

Section: Introductionmentioning

confidence: 95%

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Moving-horizon-estimator-integrated adaptive hierarchical sliding mode control for flexible hypersonic vehicles considering aeroservoelastic effect

Chen¹,

Jing

Gao

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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In order to solve the attitude control problem of flexible hypersonic vehicles with consideration of aeroservoelastic effect, uncertainty and external disturbance, a novel moving-horizon-estimator-integrated adaptive hierarchical sliding mode control scheme is presented in this paper. First, the measurement model considering flexibility is established and the influence of aeroservoelastic effect on system stability is analyzed. Then moving horizon estimator is developed to reconstruct full state information from sensor measurements, while sliding mode disturbance observer and gain adaptation law is proposed to enhance the robustness and attenuate the chattering. Via combining moving horizon estimator, sliding mode disturbance observer, gain adaptation law and baseline hierarchical sliding mode controller, the moving-horizon-estimator-integrated adaptive hierarchical sliding mode control scheme that is able to achieve the control objective of both precise attitude control and active flexible vibration suppression is developed. Finally, Lyapunov theory is used to prove the stability of the proposed control scheme, and the numerical simulations are carried out, which further verify the effectiveness of the proposed control scheme against aeroservoelastic effect, uncertainty and external disturbance.

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Section: Introductionmentioning

confidence: 95%

“…Substituting equation (38) into equation (28), the recursive arrival cost update equation based on QR decomposition is obtained.…”

Section: Moving Horizon Estimator Designmentioning

confidence: 99%