m.a.sadrnia

Nonlinear dynamic inversion is one of the well-known methods in the field of dynamic flight control, which its development refers to the Incremental Nonlinear Dynamic Inversion (INDI). Based on this, in this paper, the non-linear slow and fast modes of the aircraft is separated into two parts. Then, a distinct control is designed for each part. In the outer and inner loops, the PID and the sliding mode controller are designed, respectively. In addition stability analysis, the simulation results for Boeing 747 are presented and compared with the reference model modes and the conventional INDI.Nonlinear dynamic inversion is one of the well-known methods in the field of dynamic flight control, which its development refers to the Incremental Nonlinear Dynamic Inversion (INDI). Based on this, in this paper, the non-linear slow and fast modes of the aircraft is separated into two parts. Then, a distinct control is designed for each part. In the outer and inner loops, the PID and the sliding mode controller are designed, respectively. In addition stability analysis, the simulation results for Boeing 747 are presented and compared with the reference model modes and the conventional INDI.

This paper presents a fault tolerant approach for overactuated-oversensed systems subject to multiplicative and additive faults. The main idea is to use a reconciliatory unit in charge to discover online the possibly faulty physical sensors and exclude their measures from the generation of the ”virtual” sensors. In the proposed approach, the energetic based approach has been used to estimate the actuator multiplicative faults. In the next step, an unknown input observer has been coupled with the energetic based estimator to estimate sensor multiplicative and additive faults. Finally, the control allocation approach has been used to reach the desire output. Finally, a simulation example is reported in details to show the effectiveness of the scheme.