Adaptive flight control system for flight safety improvement in reentry and other high-velocity vehicles

Ефремов, А. В.; Efremov, E.V.; Tiaglik, Mikhail; Irgaleev, I. Kh.; Shcherbakov, A.I.; Mbikayi, Zoe

doi:10.1016/j.actaastro.2022.10.056

Cited by 11 publications

(3 citation statements)

References 29 publications

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“…Bringing the control law (19) and (24) into (19) and (21), respectively, the dynamics of attitude and angular rate takes the form:…”

Section: Analysis Of Dynamic Inversion Controllermentioning

confidence: 99%

“…On the other hand, for some conventional nonlinear control methods, the design process of the controller is cumbersome, especially when the model complexity is increasing. In addition, model uncertainties and measurement errors may also seriously affect the control accuracy [19]. Compared to other control methods, adaptive control is relatively model-free and its addition can compensate for the effects of possible faults or unexpected uncertainties and achieve a substantial improvement in performance; however, it is difficult for conventional adaptive control methods to achieve the trade-off between control performance and robustness [20][21][22].…”

Section: Introductionmentioning

confidence: 99%

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L1 Adaptive Control Based on Dynamic Inversion for Morphing Aircraft

Cheng,

Li,

Yuan

et al. 2023

Aerospace

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Morphing aircraft are able to keep optimal performance in diverse flight conditions. However, the change in geometry always leads to challenges in the design of flight controllers. In this paper, a new method for designing a flight controller for variable-sweep morphing aircraft is presented—dynamic inversion combined with L1 adaptive control. Firstly, the dynamics of the vehicle is analyzed and a six degrees of freedom (6DOF) nonlinear dynamics model based on multibody dynamics theory is established. Secondly, nonlinear dynamic inversion (NDI) and incremental nonlinear dynamic inversion (INDI) are then employed to realize decoupling control. Thirdly, linear quadratic regulator (LQR) technique and L1 adaptive control are adopted to design the adaptive controller in order to improve robustness to uncertainties and ensure the control accuracy. Finally, extensive simulation experiments are performed, wherein the demonstrated results indicate that the proposed method overcomes the drawbacks of conventional methods and realizes an improvement in control performance.

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“…Bringing the control law (19) and (24) into (19) and (21), respectively, the dynamics of attitude and angular rate takes the form:…”

Section: Analysis Of Dynamic Inversion Controllermentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

L1 Adaptive Control Based on Dynamic Inversion for Morphing Aircraft

Cheng,

Li,

Yuan

et al. 2023

Aerospace

View full text Add to dashboard Cite

show abstract

“…Fig.12. Scheme with Pilot in the loop.The following set of experiments were carried out on the nonlinear model developed recently in the process of research carried out within the Program for the Development of the World-Class Research Center "Supersonic" in 2020-2025 [10]. First experiment was conducted for tracking task via PI controller Second experiment was conducted with the INDI controller Third experiment was conducted when half of the section of stabilizer stopped working for PI Controller Fourth experiment was conducted when half of the section of stabilizer stopped working for INDI controller…”

mentioning

confidence: 99%

Synthesis of Control Law Based on Nonlinear Dynamic Inversion for Supersonic Aircraft in Presence of Noise and Uncertainties

Gaurav,

Sekou,

2023

E3S Web Conf.

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In this paper, the approach for synthesis of control law based on nonlinear dynamic inversion (NDI) via feedback linearization combined with Proportional–integral–derivative (PID) controller in outer loop to control supersonic aircraft in its most challenging flight task, i.e., landing in the presence of uncertainty in knowledge of model, measurement noise is developed. The results obtained demonstrate higher control accuracy, lower pilot workload compared to PI in tracking task of pitch angle of a supersonic passenger aircraft in presence of uncertainties, noise and in case of control surface faults.

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