Adaptive integral-sliding-mode control strategy for maneuvering control of F16 aircraft subject to aerodynamic uncertainty

Highlights：

• The nonlinear dynamics of F16 aircraft is first partitioned into inner faster and outer slower loop. For each loop, the adaptive ISM control strategy is proposed where the baseline controller is designed using nonlinear-dynamics-inversion (NDI technique)

• The aerodynamics coefficients, that are the nonlinear function of angle-of-attack α, and side slip angle β, are estimated using iterative reweighted least square algorithm. The estimated information is available to the controller design where the estimation error is treated as unmatched uncertainty.

• A detailed analysis is performed to show that the aircraft internal dynamics are stable for the applicability of NDI controller.

• A detailed comparison is performed with NDI controller and ISM/NDI controller to validate the dominant performance of proposed scheme.

摘要

•This research emphasizes on an adaptive nonlinear integral-sliding-mode (ISM) controller design for F16 aircraft. The objective is to attain the desired maneuvering subject to the unknown external disturbance and aerodynamical uncertainty effects.•The nonlinear dynamics of F16 aircraft is first partitioned into inner faster and outer slower loop. For each loop, the adaptive ISM control strategy is proposed where the baseline controller is designed using nonlinear-dynamics-inversion (NDI technique)•The aerodynamics coefficients, that are the nonlinear function of angle-of-attack α, and side slip angle β, are estimated using iterative reweighted least square algorithm. The estimated information is available to the controller design where the estimation error is treated as unmatched uncertainty.•A detailed analysis is performed to show that the aircraft internal dynamics are stable for the applicability of NDI controller.•A detailed comparison is performed with NDI controller and ISM/NDI controller to validate the dominant performance of proposed scheme.