RQ-11 UAV(Drone) Simple Aerodynamic Analysis: CFD Simulation by ANSYS Fluent
Price: $219
The problem numerically simulates an RQ-11 Raven UAV using ANSYS Fluent software.
We design the 3-D model with the Design Modeler software.
We mesh the model with Fluent Meshing software. The element number equals 5,300,212 and their type is polyhedra.
Multiple Reference Frames (MRF) are used to model the rotational motion of propellers.
RQ-11 UAV(Drone) Simple Aerodynamic Analysis: CFD Simulation by ANSYS Fluent
Price: $219
The problem numerically simulates an RQ-11 Raven UAV using ANSYS Fluent software.
We design the 3-D model with the Design Modeler software.
We mesh the model with Fluent Meshing software. The element number equals 5,300,212 and their type is polyhedra.
Multiple Reference Frames (MRF) are used to model the rotational motion of propellers.
Simple Aerodynamic Analysis: RQ-11 Drone CFD Simulation Training
Introduction
A lightweight unmanned aircraft system (UAS) with excellent mobility, the RQ-11 Raven, is designed for quick deployment.
The Raven is hand-launched into the air like a model airplane in mere minutes, and it lands itself by auto-piloting to a hovering position. It doesn't need landing strips that have been adequately prepared. The Raven is best suited for forward-deployed units because it doesn't require complex support facilities.
Thanks to its automated features and GPS technology, it is easy to use and doesn't require any specialized knowledge or extensive flight training.
An RQ-11 Raven UAV is modeled in this simulation using ANSYS Fluent software. The device moves at a speed of 13.9 m/s while the propeller rotates at an angular velocity of 1200 rev/min.
The geometry of the present model is three-dimensional and has been designed using Design Modeler software. We do the meshing of the present model with Fluent Meshing software. The mesh type is Polyhedra, and the element number is 5,300,212.
Methodology: RQ-11 RavenUAV CFD Simulation
The Multiple Reference Frames (MRF) method is used to model the rotational motion of the propellers.
Conclusion
After the simulation process was finished, contours and vectors for parameters such as velocity, pressure and turbulent intensity were obtained. As shown in the velocity contours, the vortexes behind the propeller and the air movement around the UAV are visible.
The maximum amount for the turbulent intensity parameter is exactly behind the propeller due to its rotation.
In the static pressure parameter case, as it was predictable, the UAV's front surfaces endure the highest pressure. The maximum static pressure is exerted on the nose of the UAV, the front surfaces of wings and propellers, which tells us about the necessity of the manufacturing focus on these components.