A benchtop flight control demonstrator

Abstract

A feedback control demonstrator is described. The demonstrator is intended for the demonstration of control principles applied to flight control of fixed-wing aircraft and hence is suitable for aeronautical programmes. The demonstrator consists of a two degree-of-freedom wing assembly where the wing is free to pitch in an airflow provided by a simple, benchtop wind tunnel. The second degree-of-freedom is provided by a hinged elevator which is actuated by a servomotor. The wing pitch angle is measured with a potentiometer attached to a pivot shaft, thus allowing feedback control of the elevator pitch to be implemented. The aerodynamics of the wing are modelled, the wind tunnel design is described and computational fluid dynamics analysis presented. An embedded controller that implements a proportional–integral–derivative controller and a graphical interface has been developed. Some details of these are also given.