Conceptual Design of Tactical Solar Power UAV

9th Thai Society of Mechanical Engineers, International Conference on Mechanical Engineering

Jiajan, W.^1 ; Kampoon, J.^1 ; Klongtrujrok, J.^1 ; Yuthayanon, I.^1

Department of Aeronautical Engineering, Navaminda Kasatriyadhiraj Royal Air Force Academy, 171/1 Phaholyothin Rd, Saimai District, Bangkok

10220, Thailand^1

关键词: Aerodynamic characteristics;    Incident angles;    Intelligence , surveillance , and reconnaissances;    Low Reynolds number airfoils;    Mission requirements;    Operation time;    Takeoff weight;    Vortex lattice method;   

Others  :  https://iopscience.iop.org/article/10.1088/1757-899X/501/1/012011/pdf
DOI  :  10.1088/1757-899X/501/1/012011

来源: IOP

【 摘 要 】

The purpose of this research is to study and design a concept of the tactical solar power UAV. The mission requirements derived from military applications: Intelligence, Surveillance, and Reconnaissance) ISR (which including a longer operation time) 8 hours (, 350-1000 meters service ceiling, and less than 5 kg for take-off weight. This paper, a conceptual design of solar power UAV mainly based on Noth's methodology. A simple program coding created for sizing solar power UAV by using Scilab. In addition, the vortex lattice method) XFLR5 program (also employed to evaluate the basic aerodynamic characteristics for three different low-Reynolds number airfoils. The wing incident angle was then designed. From the conceptual design results, the coding indicated that the solar power UAV is the conventional type of aircraft, which is provided 4 meters in wingspan (Aspect ratio 13 (, 3.88 kg for take-off weight, and 69.13% for solar area to wing area ratio.