Aeroelastic analysis of an unmanned aerial vehicle

Download

index.pdf

Date

2008

Author

Susuz, Umut

Metadata

Show full item record

Item Usage Stats

503
views

235
downloads

In this thesis aeroelastic analysis of a typical Unmanned Aerial Vehicle (UAV) using MSC®FlightLoads and Dynamics module and MSC®NASTRAN Aero 1 solver was performed. The analyses were carried out at sea level, 1000m, 2000m and 4000m altitudes for Mach Numbers M=0.2, 0.4 and 0.6 for the full model of the UAV. The flutter characteristics of the UAV for different flight conditions were obtained and presented. The effect of altitude on flutter characteristics has been examined and compared with the theoretical and experimental trends in the literature. Also the divergence characteristics of the full model UAV was obtained. In the study, some verification and test cases are also included. The results of the analyses of an untapered swept-wing and AGARD 445.6 wing models were compared with wind tunnel data and a maximum error of 1.3 % in the flutter speed prediction was obtained. In two different wing models the effect of taper was investigated.

URI

http://etd.lib.metu.edu.tr/upload/12609225/index.pdf
https://hdl.handle.net/11511/17467

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

Aeroservoelastic Modelling and Analysis of a Missile Control Surface with a Nonlinear Electromechanical Actuator Mehmet Ozan, Nalcı; Kayran, Altan (null; 2014-06-16) In this study, aeroservoelastic modeling and analysis of a missile control surface which is operated and controlled by a power limited, nonlinear electromechanical actuator is performed. Linear models of the control fin structure and aerodynamics together with the nonlinear servo-actuation system are built and integrated. The resulting aeroservoelastic system is analyzed both in time and frequency domain. Structural model of the control fin is based on the finite element model of the fin. Aerodynamic model ...
Development of an autopilot for automatic landing of an unmanned aerial vehicle Arıbal, Seçkin; Leblebicioğlu, Mehmet Kemal; Department of Electrical and Electronics Engineering (2011) This thesis presents the design of an autopilot and guidance system for an unmanned aerial vehicle. Classical (PID) and modern control (LQT, Sliding Mode) methods for autonomous navigation and landing in adverse weather conditions are implemented. Two different guidance systems are designed in order to navigate through waypoints during normal and/or emergency flight. The nonlinear Pioneer UAV model is used in controller development and simulations. Aircraft is linearized at different trim points and total a...
Optimal Design of a Miniature Quad Tilt Rotor UAV Kahvecioglu, Ahmet Caner; Alemdaroglu, Nafiz (2015-06-12) This paper describes the design procedure of a convertible miniature (mini and micro) quad tilt rotor unmanned air vehicle (UAV), which has about 2 meters of wing span, one hour of mission time and 5 kilograms of total weight. The aircraft is driven by four brushless direct current motors, and the structure of it completely made of composite materials. When the wing and tail of the aircraft are dismounted, it operates as a quad- rotor with tilting rotors. The aircraft is planned to carry a gimbal camera wei...
Autonomous quadrotor flight with vision-based obstacle avoidance in virtual environment Eresen, Aydin; Imamoglu, Nevrez; Efe, Mehmet Onder (Elsevier BV, 2012-01-01) In this paper, vision-based autonomous flight with a quadrotor type unmanned aerial vehicle (UAV) is presented. Automatic detection of obstacles and junctions are achieved by the use of optical flow velocities. Variation in the optical flow is used to determine the reference yaw angle. Path to be followed is generated autonomously and the path following process is achieved via a PID controller operating as the low level control scheme. Proposed method is tested in the Google Earth (R) virtual environment fo...
Aerodynamic design and control of tandem wing unmanned aerial vehicle Kaya, Taşkın; Özgen, Serkan; Department of Aerospace Engineering (2019) This thesis presents an approach towards the design methodology of electrical propulsion, tandem wing unmanned aerial vehicle. Due to its possible rewarding features, tandem wing design is investigated as the main subject of this study. The stability and control characteristics of tandem wing aircraft are critical since the interference between the two wings may result in nonlinear aerodynamic characteristics for varying angles of attack. Thus, the design of the controller system requires careful handling, ...

Citation Formats

U. Susuz, “Aeroelastic analysis of an unmanned aerial vehicle,” M.S. - Master of Science, Middle East Technical University, 2008.