Sürekli Zaman Genelleştirilmiş Denetleyici İle F-16 Uçuş Denetim Sistemi Tasarımı
Özet
Autopilot and flight control systems have an extremely important place in today’s
aviation and defense technologies. To be able to accomplish long and successful
missions with aircrafts, decreasing or even eliminating the human workload is one
of the major research areas of aerospace industry and many R&D studies are
available about flight control systems for this purpose. These studies are rlying on
different control methods and high performance military aircrafts are just one of the
application areas.
Primary goal of this thesis is to contribute to the autopilot and flight control systems
of the 5𝑡��ℎ generation fighter aircraft which will be the outcome of newly started and
ongoing Turkish Fighter aircraft project (TF-X). For this purpose, as a high
performance military aircraft, F-16 is chosen to design a flight control system. The
main reasons for choosing F-16 as the aircraft model in this thesis are its being in
use in Turkish Air Forces and being in production in Turkey. Also, there are many
resources available about F-16. Firstly, a nonlinear model of F-16 is built with using
high fidelity aerodynamic database then trim conditions and linear model are
iv
obtained from the nonlinear model. After obtaining the linear model, a comparison
and validation is done with the nonlinear model and both pilot suported and semiautonomous
flight control system are designed with using this linear model.
Continuous time Generalized Predictive Control (CGPC) method is used as a
control law. CGPC is a powerful control method which is based on prediction of the
system output. The reason for choosing the CGPC method is that it is a high
performance controller and easy to choose the controller paramaters to obtain a
desired performance.
All the flight controller designs are done with regard to criteria’s about the flight
quality, handling quality and military standards and a detailed analysis is perfomed
with this respect. In order to reduce the pilot workload and also have successful
missions, satisfying the handling criterias while designing flight controller is so
important, especially for the manned aircraft. Moreover, controller designs must be
done to stay out of the PIO phenomenon which defines the mismatch between the
pilot and the flight control system. So, flight control systems to support the pilot are
designed with regard to these criterias.
With the designed controllers, aircraft lateral-directional and longitudinal stability are
achieved and each controller tracking performance are analyzed for both time and
frequency domains. To be able to make more realistic simulations, sensor models,
actuator models and extra time delays associated with software and hardware, are
added into the nonlinear model.
