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This study aims to promote the conventional solar-powered unmanned aerial vehicle (UAV) to be used as a satellite known as a pseudo-satellite (pseudolite). The applications of UAV as a satellite are still in the initial stages because these proposed UAVs are required to fly for long hours at a specified altitude. Any solar-powered system requires extensive mission operation planning to ensure sufficient power to sustain a level flight. This study simulates the optimal UAV configurations at various global locations, and determines the feasibility of a solar-powered UAV to sustain a continuous mission. This study is divided into two different phases. An all-year operation of the average UAV (AVUAV) is simulated in Phase One and is designed specifically for each of 12 cities, namely, Ottawa, Honolulu, Quito, Tahiti, Brasilia, London, Riyadh, Tokyo, Kuala Lumpur, Accra, Port Louis, and Suva. Phase Two is a simulation of a solar-powered UAV design model known as 1UAV, applicable to any city around the world for a year-long flight. The findings state that a single UAV design is sufficient to operate continuously around the world if its detailed mission path planning has been defined.
Parvathy Rajendran; Muhammad Hazim Masral; Hairuniza Ahmed Kutty. Perpetual Solar-Powered Flight across Regions around the World for a Year-Long Operation. Aerospace 2017, 4, 20 .
AMA StyleParvathy Rajendran, Muhammad Hazim Masral, Hairuniza Ahmed Kutty. Perpetual Solar-Powered Flight across Regions around the World for a Year-Long Operation. Aerospace. 2017; 4 (2):20.
Chicago/Turabian StyleParvathy Rajendran; Muhammad Hazim Masral; Hairuniza Ahmed Kutty. 2017. "Perpetual Solar-Powered Flight across Regions around the World for a Year-Long Operation." Aerospace 4, no. 2: 20.
The current work presents the numerical prediction method to determine small-scale propeller performance. The study is implemented using the commercially available computational fluid dynamics (CFD) solver, FLUENT. Numerical results are compared with the available experimental data for an advanced precision composites (APC) Slow Flyer propeller blade to determine the discrepancy of the thrust coefficient, power coefficient, and efficiencies. The study utilized unstructured tetrahedron meshing throughout the analysis, with a standard k-ω turbulence model. The Multiple Reference Frame model was also used to consider the rotation of the propeller toward its local reference frame at 3008 revolutions per minute (RPM). Results show reliable thrust coefficient, power coefficient, and efficiency data for the case of low advance ratio and an advance ratio less than the negative thrust conditions.
Hairuniza Ahmed Kutty; Parvathy Rajendran. 3D CFD Simulation and Experimental Validation of Small APC Slow Flyer Propeller Blade. Aerospace 2017, 4, 10 .
AMA StyleHairuniza Ahmed Kutty, Parvathy Rajendran. 3D CFD Simulation and Experimental Validation of Small APC Slow Flyer Propeller Blade. Aerospace. 2017; 4 (1):10.
Chicago/Turabian StyleHairuniza Ahmed Kutty; Parvathy Rajendran. 2017. "3D CFD Simulation and Experimental Validation of Small APC Slow Flyer Propeller Blade." Aerospace 4, no. 1: 10.