Flight Control System Design and Integration for a Small UAV Test Bed



Flight Evaluation of a Reactionary Envelope Protection System for UAVs
Unnikrishnan, Suraj; Prasad, J. V. R.; Yavrucuk, İlkay (2011-01-01)
This paper presents the development and flight test evaluation of a reactionary envelope protection method suitable for limit protection in uninhabited aerial vehicles (UAVs). The method is based on finite-time horizon predictions of limit parameter response for detecting any impending limit boundary violations. Limit violations are prevented by treating limit boundaries as obstacles and by correcting nominal control/command inputs to track safe-response profiles of limit parameters near the limit boundarie...
Flight control system design of an uncommon quadrotor aerial vehicle
Baskın, Mehmet; Leblebicioğlu, Mehmet Kemal; Department of Electrical and Electronics Engineering (2021-9-01)
In this thesis, design of a flight control system for an uncommon quadrotor aerial vehicle is discussed. This aerial vehicle consists of two counter-rotating big rotors on longitudinal axis to increase the lift capacity and flight endurance, and two counter-rotating small tilt rotors on lateral axis to stabilize the attitude. Firstly, full nonlinear dynamic model of this vehicle is obtained by using Newton-Euler formulation. Later, derived approximate linear model around hover is statically decoupled to sim...
Flight test maneuver design and aerodynamic parameter estimation for single use autonomous air vehicles
Vefa Yavuzturk, N.; Topbas, Eren; Yazıcıoğlu, Yiğit (null; 2017-01-01)
In this paper, a maneuver design and aerodynamic parameter estimation procedure is carried out for single use autonomous gliding air vehicles where allowable flight testing time is limited. At first, using the priori aerodynamics of a gliding vehicle, an aerodynamic model has been built and six degree of freedom simulation tool is generated. This priori aerodynamic knowledge is used to design a multi-sine input to excite the system at predetermined flight conditions during flight test. Afterwards, using the...
Flight control of a tilt duct uav with emphasis on the over actuated transition flight phase
Ünlü, Tuğba; Tekinalp, Ozan; Department of Aerospace Engineering (2009)
In the thesis, automatic flight control system is designed for Tilt Duct Unmanned Aerial Vehicle (UAV). The vehicle is a Vertical Take-Off Landing (VTOL) type with two symmetric rotors on the wings, one aft rotor on the aft body. It behaves like a helicopter but with higher speeds in forward flight. Transition flight of the aircraft from hover to cruise or take-off to forward flight is the primary concern of the thesis study with the nonlinearities and instabilities encountered, together with the over-actua...
Flight Control System Design for an Unmanned Air Vehicle
Yavrucuk, İlkay (null; 2009-08-17)
Citation Formats
O. Tekinalp and İ. Yavrucuk, “Flight Control System Design and Integration for a Small UAV Test Bed,” 2009, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/84609.