Gain scheduled automatic flight control systems design for a light commercial helicopter model

Erkan Abdulhamitbilal*, Elbrous M. Jafarov

*Corresponding author for this work

Research output: Contribution to journalArticlepeer-review

5 Citations (Scopus)

Abstract

In this paper, nonlinear rigid body dynamics for rotorcraft mathematical model is studied. A linearization of helicopter flight dynamics is evaluated. Automatic Flight Control System (AFCS) with gain scheduled LQ optimal control is designed based on look-up tables. Stability analyses are performed and results are illustrated graphically for open and closed-loop systems. As seen from results, LQ optimal control system pushes eigenvalues to left side of imaginary axis without excessive control inputs to maintain stability of naturally unstable rotorcraft dynamics. Proposed AFCS is tested by nonlinear flight dynamics model in Matlab-Simulink environment. Simulation results illustrate effectiveness of evaluated method and techniques.

Original languageEnglish
Pages (from-to)440-455
Number of pages16
JournalWSEAS Transactions on Systems and Control
Volume6
Issue number12
Publication statusPublished - Dec 2011

Keywords

  • Flight dynamics
  • Helicopter
  • Nonlinear model
  • Simulation

Fingerprint

Dive into the research topics of 'Gain scheduled automatic flight control systems design for a light commercial helicopter model'. Together they form a unique fingerprint.

Cite this