Anti-windup Compensation of Input Constrained Systems

This work studies the design and implementation of
anti-windup compensators for systems with magnitude
and rate-limited actuators; the work contains four
main contributions. The first is the development of a
new method for anti-windup compensator design, based
on the solution of a single Riccati equation, for
systems with magnitude saturated actuators. The
second contribution shows how this new method can be
adapted to systems with rate saturation. The third
contribution describes the application of the
anti-windup techniques developed to a complex
experimental aircraft model in order to reduce the
susceptibility to pilot-induced-osicalltions. The
work culminates with a description and analysis of
the implementation of these anti-windup compensators
on a real aircraft and the subsequent flight tests.
The flight test results clearly illustrate the
advantages of employing anti-windup compensation in
terms of improved handling qualities and reduced
susceptibility pilot-induced-oscillations.

Autorentext
Jorge Sofrony was born in Bogotá, Colombia, in 1978. He received a degree in Electrical Engineering from the Universidad de los Andes in 2001. He traveled to the UK to obtain his MSc in Control Systems at Imperial College. In 2003 he joined the Control and Instrumentation Group at the University of Leicester, and in 2007 received his PhD title.

Klappentext
This work studies the design and implementation of anti-windup compensators for systems with magnitude and rate-limited actuators; the work contains four main contributions. The first is the development of a new method for anti-windup compensator design, based on the solution of a single Riccati equation, for systems with magnitude saturated actuators. The second contribution shows how this new method can be adapted to systems with rate saturation. The third contribution describes the application of the anti-windup techniques developed to a complex experimental aircraft model in order to reduce the susceptibility to pilot-induced-osicalltions. The work culminates with a description and analysis of the implementation of these anti-windup compensators on a real aircraft and the subsequent flight tests. The flight test results clearly illustrate the advantages of employing anti-windup compensation in terms of improved handling qualities and reduced susceptibility pilot-induced-oscillations.