Design of A Medium Range Tactical UAV and Improvement of Its Performance by Using Winglets

Date

2015-06-12

Author

Turanoguz, Eren
Alemdaroglu, Nafiz

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

576
views

0
downloads

This paper presents the design, performance analysis and aerodynamic improvement of a designed medium range tactical unmanned aerial vehicle. Main requirements are set as following; cruising altitute above 3500m, endurance of approximately 10-12 hours, range of 150 km and payload of 60 kg. The conventional design phase is based on the employment of historical equations and experiences. The aerodynamic improvement process is related with rise in span efficiency by employement and comparison of different wingtip geometries, which results rise in L/D ratio, climb rate, endurance or reduction in weight, required power. In short, the study underlines a cost effective aerodynamic improvement process by reducing engineering time and complicated algorithms for an UAV. In addition, considerable difference between conceptual and CFD L/D ratio results have underlined the validation need of conceptual design outputs by nowadays computational or experimental tools.

Subject Keywords

Aircraft, Mathematical model, Geometry, Aerodynamics, Performance evaluation, Computational modeling, Unmanned aerial vehicles

URI

https://hdl.handle.net/11511/65009

Conference Name

International Conference on Unmanned Aircraft Systems (ICUAS)

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Design of a medium range tactical UAV and improvement of its performance by using winglets Turanoğuz, Eren; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2014) The study encompasses the design, performance analysis and aerodynamic improvement of the designed medium range tactical unmanned aerial vehicle. Main requirements are set as following; cruising altitute above 3500m, endurance of approximately 10-12 hours, range of 150 km and payload of 60 kg. The conventional design phase is based on the employment of historical equations and experiences. Nowadays, employement of well known equations and experiences during the desing process are not enough to reveal a comp...
Design and analysis of a hybrid trailing edge control surface of a fully morphing unmanned aerial vehicle wing Tunçöz, İlhan Ozan; Yaman, Yavuz; Department of Aerospace Engineering (2015) In this thesis, the design and analysis of a hybrid trailing edge control surface of a fully morphing unmanned aerial vehicle wing having the ability to perform both camber and decamber morphings were conducted. The design of the control surface was done by CATIA V5-6R2012 package program. Two distinct designs, so-called open cell and closed cell designs were initially analyzed via Finite Element Method by using the commercial software ANSYS Workbench v14.0 in in-vacuo condition. Several trade-off studies i...
Design, Modeling, and Control Allocation of a Heavy-Lift Aerial Vehicle Consisting of Large Fixed Rotors and Small Tiltrotors Ozdogan, Gokhan; Leblebicioğlu, Mehmet Kemal (2022-02-01) In this article, we propose an unconventional heavy-lift aerial vehicle (HLAV), present the design and its control allocation analysis, and prove the concept by the demonstration of the experimental test prototype in the outdoor environment. We aim for a mechanically robust and simple vehicle design that efficiently performs heavy lifting compared to other common aerial vehicles under certain width constraints, without using a complex swashplate mechanism. The HLAV performs the task of carrying the main loa...
Design of a high speed decoy UAV Baykara, Umut; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2016) This study consists of design, CFD aerodynamic analysis and optimized selection of a high speed decoy UAV. The mission requirements for the high speed decoy are based upon the previous experiences in literature. The requirements are specified as: Maximum altitude of 15000 ft, maximum speed of 450 kts and an endurance of at least 1 hour. The decoy UAV is launched from a pneumatic catapult and lands via a parachute system. It is a highly agile aircraft having a very high maneuverability capability. The aircra...
Design and Analysis of an Unmanned Aerial Vehicle Hybrid Trailing Edge Control Surface Having Camber and Decamber Capabilities Topaç, Ömer Tanay; Taşdemir, Burcu; Gürses, Ercan; Çöker, Demirkan (2015-09-12) This paper presents the design and analyses of an unmanned aerial vehicle hybrid trailing edge control surface having camber and decamber capabilities. Initially, a brief introductory information were given about morphing concepts. Then, the structural design and analyses in in-vacuo condition are presented. The aerodynamic loadings were calculated at the morphed configurations, and these loads were transferred to the structural mesh in order to assess the design capability under the aerodynamic loading. It...

Citation Formats

E. Turanoguz and N. Alemdaroglu, “Design of A Medium Range Tactical UAV and Improvement of Its Performance by Using Winglets,” Denver, CO, 2015, p. 1074, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/65009.