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Study of a Flexible UAV Proprotor

Abstract : This paper is concerned with the evaluation of design techniques, both for the propulsive performance and for the structural behavior of a composite flexible proprotor. A numerical model was developed using a combination of aerodynamic model based on Blade Element Momentum Theory (BEMT), and structural model based on anisotropic beam finite element, in order to evaluate the coupled structural and the aerodynamic characteristics of the deformable proprotor blade. The numerical model was then validated by means of static performance measurements and shape reconstruction from Laser Distance Sensor (LDS) outputs. From the validation results of both aerodynamic and structural model, it can be concluded that the numerical approach developed by the authors is valid as a reliable tool for designing and analyzing the UAV-sized proprotor made of composite material. The proposed experiment technique is also capable of providing a predictive and reliable data in blade geometry and performance for rotor modes.
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Submitted on : Monday, July 30, 2018 - 3:43:18 PM
Last modification on : Wednesday, June 24, 2020 - 4:18:55 PM
Long-term archiving on: : Wednesday, October 31, 2018 - 1:25:46 PM


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  • HAL Id : hal-01851642, version 1
  • OATAO : 9154


Fazila Mohd Zawawi, Sebastien Prothin, Peng Lv, Emmanuel Bénard, Jean-Marc Moschetta, et al.. Study of a Flexible UAV Proprotor. 48th International Symposium of Applied Aerodynamics, Mar 2013, Saint-Louis, France. pp.0. ⟨hal-01851642⟩



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