Aero-structural design and analysis of an unmanned aerial vehicle and its mission adaptive wing

Download

index.pdf

Date

2010

Author

İnsuyu, Erdoğan Tolga

Metadata

Show full item record

Item Usage Stats

329
views

383
downloads

This thesis investigates the effects of camber change on the mission adaptive wing of a structurally designed unmanned aerial vehicle (UAV). The commercial computational fluid dynamics (CFD) software ANSYS/FLUENT is employed for the aerodynamic analyses. Several cambered airfoils are compared in terms of their aerodynamic coefficients and the effects of the camber change formed in specific sections of the wing on the spanwise pressure distribution are investigated. The mission adaptive wing is modeled structurally to observe the effect of spanwise pressure distribution on the wing structure. For the structural design and analysis of the UAV under this study, commercial software MSC/PATRAN and MSC/NASTRAN are used. The structural static and dynamic analyses of the unmanned aerial vehicle are also performed under specified flight conditions. The results of these analyses show that the designed structure is safe within the flight envelope. Having completed aero-structural design and analysis, the designed unmanned aerial vehicle is manufactured by TUSAŞ Aerospace Industries (TAI).

Subject Keywords

Aerospace engineering.

URI

http://etd.lib.metu.edu.tr/upload/12611657/index.pdf
https://hdl.handle.net/11511/19355

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

Design and analysis of a mode-switching micro unmanned aerial vehicle Cakici, Ferit; Leblebicioğlu, Mehmet Kemal (SAGE Publications, 2016-12-01) In this study, design and analysis of a mode-switching vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) with level flight capability is considered. The design of the platform includes both multirotor and fixed-wing (FW) conventional airplane structures; therefore named as VTOL-FW. The aircraft is modeled using aerodynamical principles including post-stall conditions. Trim conditions are obtained by solving constrained optimization problems. Linear analysis techniques are utilized for trim ...
Tilt duct vertical takeoff and landing uninhabited aerial vehicle concept design study Armutcuoglu, O; Kavsaoglu, MS; Tekinalp, Ozan (American Institute of Aeronautics and Astronautics (AIAA), 2004-03-01) A new autonomously controlled tilt-duct vertical takeoff and landing uninhabited aerial vehicle concept is proposed. This design combines the vertical flight capability of a helicopter and forward flight performance of a fixed-wing conventional aircraft. The two main engines and propellers are located inside the tilting ducts attached to the wing tips. There is a third engine-propeller combination located inside the all fuselage for pitch and yaw control during hover and transition. The advantages and disad...
Flight control system design for an over actuated UAV against actuator failures Işık, Sinem; Tekinalp, Ozan; Department of Aerospace Engineering (2010) This thesis describes the automatic flight control systems designed for a conventional and an over actuated unmanned air vehicle (UAV). A nonlinear simulation model including the flight mechanics equations together with the interpolated nonlinear aerodynamics, environmental effects, mass-inertia properties, thrust calculations and actuator dynamics is created; trim and linearization codes are developed. Automatic flight control system of the conventional UAV is designed by using both classical and robust co...
Investigation of rotor wake interactions in helicopters using 3d unsteady free vortex wake methodology Yemenici, Öznur; Uzol, Oğuz; Department of Aerospace Engineering (2010) This thesis focuses on developing and examining the capabilities of a new in-house aerodynamic analysis tool, AeroSIM+, and investigating rotor-rotor aerodynamic interactions for two helicopters, one behind the other in forward flight. AeroSIM+ is a 3-D unsteady vortex panel method potential flow solver based on a free vortex wake methodology. Validation of the results with the experimental data is performed using the Caradonna-Tung hovering rotor test case. AeroSIM+ code is improved for forward flight cond...
Mathematical model development of the anti torque system of a notar helicopter Bakır, Hüseyin Murat; Yavrucuk, İlkay; Department of Aerospace Engineering (2008) The anti-torque mechanism of a NOTAR helicopter is a complex system including vertical tail and pressurized tail boom which provides air ejection used for both circulation control around the boom and creating directed jet air at the end of the boom. This thesis targets the modeling of this mechanism and integrating it to a helicopter simulation model. Flight tests are performed on the MD 600N helicopter to verify the results. Finally, the simulation is compared with flight test data.

Citation Formats

E. T. İnsuyu, “Aero-structural design and analysis of an unmanned aerial vehicle and its mission adaptive wing,” M.S. - Master of Science, Middle East Technical University, 2010.