Aerodynamic/reaction-jet compound control of hypersonic reentry vehicle using sliding mode control and neural learning

Learning observer-based fault-tolerant tracking control for hypersonic vehicle with actuator faults

“…Uncertain model with disturbance and actuator faults. The reentry attitude dynamics of hypersonic vehicle with parameter uncertainty and external disturbance can be described as [6] (…”

“…In the reported literatures, various control methods have been investigated to raise the robust performance and tracking precision of the hypersonic vehicle control system, which involved but not limited to backstepping control strategy [3] [4], sliding mode control [5] [6], adaptive fuzzy control [7][8] [9], neural network-based control [10], adaptive compound control [11] [12], fixed-time control [13] [14], eventtriggered control [15], and prescribed performance control [16]. It is worth noting that fault-tolerant control (FTC) schemes play a great role in system stability when the redundant nonlinear systems experienced fault conditions, which has aroused extensive attentions by many scholars.…”

Finite-Time Attitude Tracking Control for Hypersonic Flight Vehicles with Actuator Saturation

“…Substituting the virtual control law (19) into the sliding manifold (18) and differentiating s 1 , we have…”

“…On account of its fast global convergence, simple algorithm, high robustness against external perturbation, and system uncertainties, SMC has been extensively applied to compensate for the lumped disturbances. In order to improve the robust performance and obtain finite-time convergence, the terminal sliding mode (TSM) controller based on the backstepping frame is designed [18]. However, by reason of the difficulty to obtain the upper bound of uncertainty or disturbance in practice, compound control methods may lead to large chattering phenomenon and energy loss.…”

Hybird Nonlinear Control for Fighter With Center of Gravity Perturbation and Aerodynamic Parameter Uncertainty

“…The center of gravity perturbation has varying degrees of influence on the stability and maneuverability of the fighter, which manifests as the rise or fall of the flight trajectory, the sudden change of the flight speed, and the fighter maneuvering overdrive [11], where the fighters may deviate from its nominal dynamics. The control system has difficulty adapting to changes in dynamics and control characteristics, and robust stability and consistent performance cannot be guaranteed [12][13]. Jing Zhang et al 2 used a dynamic inverse control based gravity center position estimation method to compensate for the controller, but the model they built could not reflect the dynamic process of center of gravity changes, and it is difficult to extend to the general cases [14]; sliding mode control as a common control method to adapt to uncertain system dynamics and center of gravity deviations through variable structural sliding mode, can compensate for external perturbations on the system, however it will introduce chattering to the control system, which requires additional compensation to eliminate it [15][16][17]; another simple and effective method is the robust flight control method based on the linear matrix of inequality (LMI), which can effectively guarantee the robustness against external disturbances and changes of internal parameters [18][19], but this method is based on a simple short-period approximate longitudinal model, which ignores the inherent nonlinear characteristics of the fighters, and the differences between the linear model and the actual nonlinear fighters affect the control performance and stability of the fighters.…”