Adaptive inversion sliding mode control method and device for nonlinear binary airfoil

Abstract

The invention provides a self-adaptive inversion sliding-mode control method of nonlinear binary wings. The method comprises that (a) a mathematical model of a nonlinear binary wing aeroelastic system is established according to the aeroelatic theory; (b) according to inversion control, self-adaptive control and sliding-mode control theories and the mathematical model, a self-adaptive inversion sliding-mode controller of the nonlinear binary wing aeroelastic system is designed; and (c) and the self-adaptive inversion sliding-mode controller with the control law is used to carry out self-adaptive inversion sliding-mode control on the nonlinear binary wings. The invention also provides a self-adaptive inversion sliding-mode control method of the nonlinear binary wings. The control device comprises a system modeling device, a sliding-mode controller, an inversion controller and a self-adaptive controller. Thus, the parameter uncertainty and external disturbance of the nonlinear binary wing system are overcome, the anti-interference capability of the system is improved, and the drift displacement and expected pitch angle of the wing aeroelastic system can be rapidly and accurately tracked.

Description

technical field [0001] The invention relates to the technical field of flight control, in particular to an adaptive inversion sliding mode control method and device for a nonlinear binary wing of a symmetrical structure wing model. Background technique [0002] Flutter is a complex aerodynamic instability phenomenon, including limit cycle oscillation, bifurcation and chaotic motion. Flutter can cause the wing to vibrate violently, causing structural fatigue and damage to the wing section. With the continuous increase of aircraft speed and the continuous decrease of weight stiffness, the problem of aircraft aeroelasticity has become more and more prominent, and the control requirements for aeroelastic wings in practical applications have also been continuously improved. Traditional control methods have been difficult to meet the safe operation of aeroelastic systems. demand. [0003] Sliding mode control is often used for wing flutter control because of its strong robustnes...

AI Technical Summary

Problems solved by technology

Flutter can cause the wing to vibrate violently, causing structural fatigue and damage to the wing section

With the continuous increase of aircraft speed and the continuous decrease of weight stiffness, the problem of aircraft aeroelasticity has become more and more prominent, and the control requirements for aeroelastic wings in practical applications have also been continuously improved. Traditional control methods have been difficult to meet the safe operation of aeroelastic systems. needs

[0003] Sliding mode control is often used for wing flutter control because of its strong robustness and good dynamic and static response characteristics. Its sliding mode can be freely designed and has nothing to do with object parameters and disturbances, and has strong anti-interference ability, but the conventional sliding mode control has chattering phenomenon due to the non-ideality of the switching device, and there is also a limitation of the relative order

Due to the high complexity and nonlinearity of wing flutter, active nonlinear flutter suppression technology is often used at home and abroad. For example, a sliding mode control method disclosed in patent application CN104238357A uses disturbance observers and neural networks to simultaneously Disturbances and faults are dealt with. Aiming at the problem of actuator input saturation, the control law is designed using the saturation upper bound of the actuator, and the designed auxiliary variable is used to adjust the output of the actuator to ensure that there will be no problem of excessive output of the actuator. However, this method of using the upper bound method of uncertainty and disturbance to design the sliding mode controller will have a large discontinuous control amount and cause serious system flutter; for example, a hypersonic vehicle based on a predictive model disclosed in the patent application CN102880053A The sliding mode control method transforms the existing hypersonic vehicle discrete Euler model to obtain a prediction model containing only one equation. The controller adopts the nominal method and considers the lumped uncertainty of the system at the same time. The value of the uncertain part of the predictive model calculation history is used for feedback design. The entire controller does not need to perform adaptive parameter estimation, and the design is simple and easy to implement in engineering. It is difficult to achieve ideal results due to complex nonlinear and even wing systems with system uncertainties and external disturbances; for example, patent application CN103425135A discloses a robust control method for near-space vehicles with input saturation. The slow loop and fast loop in the attitude motion system of the spacecraft are designed with sliding mode controllers respectively. However, this robust sliding mode control method increases the difficulty of designing the sliding mode controller due to the complex matrix calculation.

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