Flight Tests on fault-tolerant autopilot control laws in laboratory aircraft Citation II

Dr. ir. A.C. in ‘t Veld, Delft University of Technology, DUT, Delft, The Netherlands
Ir. T.J. Mulder, Delft University of Technology, DUT, Delft, The Netherlands
Dr. ir. G.H.N. Looye, German Aerospace Center, DLR, Wessling, Germany

Abstract

The Delft University laboratory aircraft Cessna Citation II has the capability to implement and test new auto pilot control laws. The aircraft is equipped as a Fly-By-Wire testbed, that enables the user to control the aircraft through an experimental computer and directly have control over the control surfaces. An extra control stick is mounted on the righthand side in the cockpit from where the aircraft can be controlled in a closed loop. The gains can be adjusted in-flight. An experimental display in the cockpit showed the setpoints for the rate and direct control in pitch and roll.

The control laws that were tested are developed by the department of aircraft systems dynamics of the German Aerospace Center together with Delft University of Technology. The control laws are based on Incremental Nonlinear Dynamic Inversion (INDI). INDI uses synchronized measurements or estimations of (angular) accelerations and control surface deflections. This way it is not dependent on an airplane model, but it is able to automatically adapt flight control laws to changing dynamic behavior of the aircraft, even in case of major system failures or damage to the airframe. The INDI controller directly controls the current to the control surface actuators.

This paper treats the execution of the test flights.