Conceptual design of a hybrid (turbofan/solar) powered HALE UAV

Download
index.pdf
2016
Mermer, Erdinç
Show full item record
566
views
369
downloads
The aim of the thesis is to design a HALE UAV using both turbofan engine and solar energy in order to obtain 24 hours endurance with 550 lb payload capacity and 30000 ft service ceiling. During daytime, required power is obtained from solar panels. However, excess solar energy is used for charging the lithium-ion battery. It is assumed that turbofan engine is used only for climbing to the required altitude. During loiter, only solar energy and battery power are used. The design methodology consists of two main parts. In the first part, typical conceptual design methodology is used. Weight analysis, wing loading and thrust loading, required power analysis, aircraft performance analysis are performed. While performing the conceptual design, aircraft is assumed as only turbofan-powered aircraft. Due to long wingspan and large wing area, typical structural weight determination techniques are not suitable for the HALE UAV. Therefore, a new structural weight prediction model is used. vi In the second part of the thesis, solar energy and battery energy are examined in order to assess whether endurance and service ceiling requirements are satisfied. Solar radiation model is used for verification. Also a simulink model is constructed for examining the flight duration. It is considered that propulsion system consists of one or two small turbofan engines and four electric powered engines with one propeller each. Solar panel efficiency is assumed as 30% and 40%, in order to show the effects of cell efficiencies on flight endurance. Finally, endurance of the aircraft is predicted for four different times of the year.
Drone aircraft., Flying-machines., Solar energy., Airplanes
http://etd.lib.metu.edu.tr/upload/12619948/index.pdf
https://hdl.handle.net/11511/25617
Graduate School of Natural and Applied Sciences, Thesis

Suggestions

Design and manufacturing of a solar powered unmanned air vehicle
Özcan, Servet Güçlü; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2015)
The aim of this thesis is to describe the conceptual design, performance analysis including solar energy collection and manufacturing process of a solar powered unmanned aerial vehicle (UAV) and validate the design through ground and flight tests. Through a literature survey of solar powered aircraft, main design requirements are chosen. The solar powered UAV designed for this study is a small scale aircraft and intended to be used simply and frequently by end-users. Therefore it is designed as a flying win...
Conceptual Design of a Hybrid (Turbofan/solar) Powered UAV
Mermer, Erdinç; Özgen, Serkan (2017-07-03)
The aim of the study is to design a HALE UAV using both turbofan engine and solar energy in order to obtain at least 24 hours endurance with 250 kg camera and 750 kg battery total 1000 kg payload capacity and 6096m (20000 ft) to 9144 m (30000 ft) service ceiling. During daytime, required power is obtained from solar panels. Morover, excess solar energy is used for charging the lithium-ion battery. It is assumed that turbofan engine is used only for climbing to the required altitude. During loiter, only sola...
Aerodynamic and structural design and analysis of an electric powered mini UAV
Demircan, Alpay; Kayran, Altan; Department of Aerospace Engineering (2016)
The aim of this study is to describe the aerodynamic and structural design of an electric powered portable Mini UAV. Conceptual design, structural design and analysis of the wing and detail design phases of the UAV are presented in the study. Fixed wing mini UAV configuration with fixed – pitch propeller has been chosen for the design. In order to provide multi-mission capability, payload of the UAV is designed as a replaceable mission compartment. System requirements and mission profiles of the airplane ar...
Design of a solar powered unmanned airship
Sönmez, Onur Sinan; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2015)
This thesis presents the design and analysis of a low altitude, high endurance Unmanned Airship which is capable of carrying payloads up to 70 kg to 1000 meters altitude. This UAV has an endurance of 2 weeks and can resist winds up to 90 km/h. It is completely solar powered and it uses Helium as the lifting gas and uses electric motors to change it’s location. The purpose of this thesis is to design an unmanned, completely solar powered airship to be used for various missions such as: reconnaissance mission...
Design and manufacturing of a high speed, jet powered target drone
Özyetiş, Ender; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2013)
This thesis presents the design and manufacturing of a high speed jet powered UAV which is capable of flying at M=0.5. Flight time of the UAV is 30 minutes at 1700 m above sea level. Aerodynamic and structural design of the UAV is conducted for 6g sustained and 9g instantaneous loads. Low aspect ratio blended wing-body design is decided due to low drag and high maneuverability. The Structure of the UAV consists of the composite parts such as frames and skin and mechanical parts such as landing gears which a...
Citation Formats
E. Mermer, “Conceptual design of a hybrid (turbofan/solar) powered HALE UAV,” M.S. - Master of Science, Middle East Technical University, 2016.
METU IIS - Integrated Information Service open@metu.edu.tr