An Iterative Method to Control Angle of Attack and Sideslip Angle Based on Model Correction

Aiming at controllingthe angle of attack and sideslip angle for air breathing aircraft at ignition time of the engine after separation quickly and accurately. This paper proposes an iterative method to control the angle of attack and sideslip angle based on model correction. Firstly, the relationship between those angles and overload which measured by IMU system is established, so the angle of attack and sideslip angle are predicted by using trim aerodynamic model. At the same time, aiming at reducing the deviation between the actual force of the aircraft and the force calculated by the trim aerodynamic model, a multi-dimensional Newton iteration is used to correct the prediction method by real time. Validated by simulation, the deviation of the angle of attack at the ignition time of the engine is less than 0.3
$\circ$
and the deviation of sideslip angle is less than 0.
$4^{\circ}$
by using the method proposed in this paper. This method has high engineering application value.