Dynamics and control of a single tit-wing UAV

Author

Hong, Sung-Tae ; Lee, Moonkyou ; Kim, Do-Myung ; Bang, Keuk-hee ; Kim, Seungkeun ; Suk, Jin-Young

Author_Institution

Dept. of Aerosp. Eng., Chungnam Nat. Univ., Daejeon, South Korea

fYear

2012

fDate

17-21 Oct. 2012

Firstpage

430

Lastpage

432

Abstract

This paper presents dynamic analysis and control of a single tilt-wing unmanned aerial vehicle. A single tilt-wing shown in this paper has the advantage of flying like a fixed-wing aircraft with vertical take-off and landing capability. A variety of flight modes including fixed-wing, VTOL, and transition mode are considered. Dynamic model is obtained using rotor thrust, aerodynamic lift and drag due to the induced velocity from the rotor, and unwetted aerodynamic forces and moments. Trim analysis is conducted based on gradient method from the nonlinear dynamics. A model-based control system is designed and flight tested successfully.

Keywords

aerodynamics; aerospace components; aircraft control; aircraft testing; autonomous aerial vehicles; control system synthesis; drag; gradient methods; nonlinear dynamical systems; rotors; VTOL; aerodynamic lift; drag; dynamic analysis; fixed-wing aircraft; flight modes; flight testing; gradient method; model-based control system; nonlinear dynamics; rotor thrust; single tilt-wing unmanned aerial vehicle control; transition mode; trim analysis; unwetted aerodynamic forces; vertical landing capability; vertical take-off capability; Aerodynamics; Aircraft; Atmospheric modeling; Military aircraft; Propellers; UAV; dynamic modeling; flight test; single tilt-wing; trim analysis;

fLanguage

English

Publisher

ieee

Conference_Titel

Control, Automation and Systems (ICCAS), 2012 12th International Conference on

Conference_Location

JeJu Island

Print_ISBN

978-1-4673-2247-8

Type

conf

Filename

6393478