During the aircraft maneuvering at high angle of attack, the dynamic characteristics of the aircraft show strong coupling and highly nonlinear characteristics with the uncertainty of aerodynamic parameters. The traditional NDI (Nonlinear Dynamic Inversion) control method is highly dependent on the model, although it can improve the nonlinearity of models and the dynamic decoupling. When there are parameter uncertainties in the aircraft model, the response of attitude angle (such as angle of attack, sideslip angle and roll angle) and attitude angular velocity will oscillate to different degrees. Aiming at such problems, an adaptive NDI control method is proposed in this paper, and the NDI control laws and the aircraft attitude control are designed. The aircraft attitude control turned to two sub-loops method: fast loop and slow loop. In the fast loop, we introduce the uncertainty of aerodynamic parameters, and separate the parameters of the affine nonlinear model. Then based on the Lyapunov stability theory, the adaptive control law and the matrix of estimating uncertainty parameter are proposed. Finally on the published F-16 fighter model, the system convergence is verified through the simulation experiments.
Parameter Estimation and Adaptive Nonlinear Dynamic Inversion Applied to Coordinated Turning Control
27.10.2023
1488149 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
British Library Conference Proceedings | 2010
|Nonlinear Adaptive Dynamic Inversion Applied to a Generic Hypersonic Vehicle (AIAA 2013-5234)
British Library Conference Proceedings | 2013
|Nonlinear dynamic inversion control with adaptive compensation for flight control system
British Library Online Contents | 1997
|