Abstract
In this paper, a hybrid nonlinear control scheme combining nonlinear dynamic inversion (NDI) and adaptive sliding mode (ASM) control is proposed for high angle of attack fighter system with center of gravity perturbation and aerodynamic parameter uncertainty. By introducing the affine nonlinear model of inner loop angular velocity with center of gravity perturbation, an adaptive sliding mode control scheme based on the online estimation of radial basis function (RBF) neural network is designed, which can reduce the dynamic inversion error of NDI control and rapidly compensate the multi-coupled channel oscillation. The aerodynamic force and moment coefficients are estimated via the iterative weighted least squares (IRLS) method. Then an outer loop integral sliding mode (ISM) NDI controller is designed, which can be robust to disturbances and mismatched uncertainties through adjusting adaptive gain, and the rudder yaw chattering caused by the uncertainty of aerodynamic parameters is reduced simultaneously. The Lyapunov stability theory and Barbarat’s lemma prove the stability of the designed control scheme, and simulation based on F-16 model verifies the effectiveness of the control scheme.
Highlights
As a significant issue of the national army's air power, fighters have advantages such as wide flight envelope, fast flight speed, and close combat capability [1]
This paper proposes a hybrid adaptive sliding-mode nonlinear control scheme based on nonlinear dynamic inversion (NDI) for the F-16 aircraft system with center of gravity perturbation, uncertain aerodynamic parameters and external interference
The effectiveness of the proposed scheme is verified via MATLAB/Simulink simulation, and following conclusions are obtained: 1) The scheme based on the online estimation of radial basis function (RBF) neural network shows a faster estimation speed and higher estimation accuracy than the general observer estimation
Summary
As a significant issue of the national army's air power, fighters have advantages such as wide flight envelope, fast flight speed, and close combat capability [1]. SYSTEM DESCRIPTION AND PROBLEM FORMULATION This section introduces the nonlinear dynamics model of the F-16 fighters, the center of gravity perturbation model, and the aerodynamic parameter uncertainty model
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