Large Angle Maneuvering with an Asymmetric Aircraft: A Single Loop Control Formulation

Automatic Control of an Asymmetric Fighter Aircraft Performing Supermanoeuvres

“…Sliding Mode Control is a robust nonlinear controller design technique particularly suitable for dealing with structured or parametric uncertainties [18][19]. This control approach is found to mitigate a wide range of uncertainties in the case of asymmetric aircraft [7][8][9]. However, the manoeuvre performance considerably deteriorates when the controller does not have an accurate information of the asymmetry.…”

“…This approach is, indeed, appealing because of the excellent capabilities of the feedforward neural networks for adapting to various changes in its input parameters even if the dimensionality of the data to be learnt is too high. Following the formulations as proposed in [8,9], first an SMC controller is designed using the actual asymmetric dynamics. From this simulation, the ∆F(x, u) values are stored as per Eq.…”

“…Aircraft having lateral asymmetry in inertial and aerodynamic properties inherent in their structure have recently gained prominence in aircraft flight dynamics and control research [1][2][3][4][5][6][7][8][9]. In civil aircraft, such an asymmetry may generally arise due to asymmetry in fuel consumption, partial structural damage in the wing etc.…”

“…In many cases the asymmetry induced due to the aforementioned reasons cannot be accurately identified and quantified. For example, identification of the asymmetry due to firing of stores needs online centre of gravity estimation in order for the controllers to be able to compensate for the changed dynamics, as considered recently in the literature [5][6][7][8][9]. Further, the changed dynamics is far more complex and control design based on them requires considerably more online computation power.…”