EFFECTS OF PROPELLER BLADE TWIST ON RECONNAISSANCE QUAD-ROTOR UAV | ||||
| The International Conference on Applied Mechanics and Mechanical Engineering | ||||
| Article 90, Volume 15, 15th International Conference on Applied Mechanics and Mechanical Engineering., May 2012, Page 1-15 PDF (1.65 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/amme.2012.37087 | ||||
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| Authors | ||||
| A. S. Imam1; R. Bicker2 | ||||
| 1PGR Student, Department of Mechanical and Systems Engineering, Newcastle University, U.K. | ||||
| 2Senior Lecturer, Department of Mechanical and Systems Engineering, Newcastle University, U. K. | ||||
| Abstract | ||||
| ABSTRACT Rotors play a pivotal role in the overall performance of a rotary-wing aircraft. Forces and moments required for flight are achieved through effective, compact and high-lift rotor design. Important rotor parameters are thrust, power and torque, which are functions of blade twist and rotor radius. A robust and efficient rotary-wing UAV flight control system must provide the vehicle with the ability to perform safe flight manoeuvres. This comprise normal flight conditions and proportionate regulation of thrust in response to the variation in power demand, which comes to play due to changes in aerodynamics conditions within the vehicle operating environment. This paper presents an in-depth analysis on the effect of variations of propeller blade twist and diameter with the view to designing an autonomous flight control system for a micro rotary-wing UAV. Virtual Blade Model (VBM) was used for the analysis and the result validated using a quad-rotor vehicle. The study comes up with an efficient propeller choice suitable for autonomous reconnaissance quad-rotor UAV. | ||||
| Keywords | ||||
| Autonomous Flight Control System; Reconnaissance; RUAV; Rotors; Blade Twist; VBM and ANSYS FLUENT | ||||
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