Document Details

Document Type : Thesis 
Document Title :
CONCEPTUAL DESIGN OF HIGH ALTITUDE LONG ENDURANCE SOLAR POWERED UAV
تصميم طائرة شمسية غير مأهولة وطويلة التحمل للارتفاعات العالية
 
Subject : Faculty of Engineering 
Document Language : Arabic 
Abstract : This research is carried out with the aim of realizing the concepts of solar powered high altitude long endurance unmanned aerial vehicle through multidisciplinary design optimization. And model a prototype before manufacturing with available technologies to take steps to reach eternal flight. The experience gained from former medium altitude long endurance versions, Sun falcon 1 - a solar powered monoplane for day flight and Sun falcon 2 -an upgraded model capable of flight during night from energy saved in daytime were used to introduce the high altitude long endurance concept. This work proposes a conceptual design methodology of solar UAV with high operating altitude and long endurance characteristics by reviewing the history of UAVs, difficulties of HALE concepts and applicability of solar powered propulsion in accordance to design requirements. Some benchmarks were selected to get the current trends in the design approach in HALE and solar trades. Mass estimation models were adopted, and verification tests were conducted to comprehend them properly with the help of flight diagram including the conventional approach. A survey on multidisciplinary design optimization is conducted and are studied different methods up to date extensively. Considering the requirements, computations and complexity, multidisciplinary feasible method was selected with genetic optimization algorithm. The objective was to optimize the mass adhering to various efficiencies and flight conditions. At first, a conceptual design methodology was adopted with specific design requirements and come up with a model of 1340 kg total mass with a day and night endurance maintaining altitude of 9 km using MATLAB Simulink. FX63 137sm was chosen as the airfoil due to its high L/D ratio with the help of 2D and 3D analysis in XFLR5 and later conducted a stability check. A 3D model was developed in OpenVSP v3.15. The second part of the work was to convert the developed Simulink model into a multidisciplinary design optimization framework and to create an optimum model with an objective of minimizing total mass. An optimum model was selected from the generated sets of design configurations with 1254 kg total mass with almost same solar cell power output. A model of UAV is presented which has 150 kg payload mass and a day and night endurance with probable capability of restarting the solar cycle for next day. 
Supervisor : Dr. Wail I. Harasani 
Thesis Type : Master Thesis 
Publishing Year : 1439 AH
2018 AD 
Co-Supervisor : Dr. Amer Rafique Farhan 
Added Date : Wednesday, April 25, 2018 

Researchers

Researcher Name (Arabic)Researcher Name (English)Researcher TypeDr GradeEmail
سعد نصرالدينNazarudeen, Saad ResearcherMaster 

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