Aggressive Maneuver Oriented Robust Actuator Fault Estimation of a 3-DOF Helicopter Prototype Considering Measurement Noises

This article presents a robust actuator fault estimation strategy design for three-degree of freedom (3-DOF) helicopter prototype which can be adapted to aggressive maneuvers. First, considering large pitch angle condition during flight, nonlinear coupling characteristic the system is exploited. As measured in real time, polytopic linear parameter varying (LPV) model developed system. Furthermore, measurement noises actual system, dynamical modified accordingly. Then, based on LPV model, unknown input observer realize estimation, both and are considered. Robust performance proposed approach guaranteed by using energy-to-energy strategy. And gains calculated matrix inequalities. Finally, 3-DOF prototype, simulations experiments conducted. The effects sufficiently demonstrated. effectiveness as well advantages verified comparative analysis.