Finite Time Convergence Incremental Nonlinear Dynamic Inversion-Based Attitude Control for Flying—Wing Aircraft with Actuator Faults

Abstract

In this paper, a two-loop fault-tolerant attitude control scheme is proposed for flying-wing aircraft with actuator faults. A regular nonlinear dynamic inversion (NDI) control is used in the outer attitude loop, and a finite time convergence incremental nonlinear dynamic inversion (FINDI) control combined with control allocation strategy is used in the inner angular rate loop. Prescribed performance bound (PPB) is designed to constrain the tracking errors within a residual set, so the prescribed system performance can be guaranteed. An optimal anti-windup (AW) compensator is introduced to solve the actuator saturation problem. Simulation results demonstrate the effectiveness of the proposed approach.

A Model Free Adaptive Scheme for Integrated Control of Civil Aircraft Trajectory and Attitude

“…In terms of aircraft attitude control, the commonly used methods include sliding mode control [16,17], model predictive control [18], active disturbance rejection control [19,20], dynamic inversion control [21] and so on. In these studies, accurate aircraft dynamics models are usually used, where the aerodynamic coefficients need to be obtained through wind tunnel experiments and flight tests [18].…”