A VORTEX MODEL OF A HELICOPTER ROTOR
Journal Title: INCAS BULLETIN - Year 2009, Vol 1, Issue 1
Abstract
A vortex model of a helicopter rotor is presented. Each blade of the rotor has three degrees of freedom: flapping, lagging and feathering. The motions after each degree of freedom are also known for all blades. The blade is modelled as a thin vortex surface. The wakes are free fluid surfaces. A system of five equations are obtained: the first one is the integral equation of the lifting surface (rotor), the next three describe the wakes motion, and the last one relates the vortex strength on the wakes and the variation of vorticity on the rotor. A numerical solution of this system is presented. To avoid the singularities that can occur due to the complexity of vortex system, a desingularized model of the vortex core was adopted. A Mathcad worksheet containing the method has been written. The original contribution of the work. The calculation method of the motion of the wakes free vortex system, the development of the vortex cores in time and a new method to approximate the aerodynamic influence of remoted wake regions
Authors and Affiliations
Valentin BUTOESCU
Keywords
Related Articles
- EP ID EP85511
- DOI 10.13111/2066-8201.2009.1.1.5
- Views 148
- Downloads 0
Take-off and landing of aicraft
In this paper, the take-off and landing segments of an airplane trajectory are studied. The equations of motion for the ground run are derived and solved for distance. Then, specific formulas are obtained for the take-of...
A computational methodology for a micro launcher engine test bench using a combined linear static and dynamic in frequency response analysis
This article aims to provide a quick methodology to determine the critical values of the forces, displacements and stress function of frequency, under a combined linear static (101 Solution - Linear Static) and dynamic l...
STATE OF THE ART TECHNIQUES USED FOR NOISE SOURCE IDENTIFICATION ON COMPLEX BODIES
Over the last few decades, many approaches have been undertaken in order to asses detailed noise source identification on complex bodies, i.e. aircrafts, cars, machinery. Noise source identification implies to accurately...
Equilibrium stability analysis by numerical simulations for a linear system with time-delayed control
The work starts from the linearization of a nonlinear mathematical model of the electrohydraulic servomechanism with structural switching and delayed control. The delay, as well as the switching structure, can lead to in...
Control of unmanned aerial vehicles during fire situation monitoring
The issues of increasing the efficiency of fire situation monitoring are discussed, during which the search for objects of interest is being conducted to organize rescue operations and plan activities to fight the fire a...