Patent ID: 6589017
Filing Date: 2003-07-08
Classification: B64C

Abstract:
A helicopter rotatable airfoil assembly comprising:an aircraft body, a rotation mechanism rotatably supported on said body and presenting an upright axis of rotation, two airfoils with each one thereof disposed on a respectively diametrically opposite side of said axis and having a planar configuration extending in a substantially horizontal plane and with each one of said airfoils having an end disposed radially inwardly and an end disposed radially outwardly with respect to said axis, two air vortex baffles rigidly affixed to each of said airfoils with one of said baffles respectively disposed at and on each said end of each said airfoil and with each of said baffles rigidly extending continuously solidly from and above and below said horizontal plane and beyond said planar configuration of each said airfoil in a substantially and respectively vertical plane to thereby restrict air flight vortices action at both said ends of each said airfoils, each said vortex baffle is a flat and narrow member and extends in the vertical plane both above and below said horizontal plane, each of said airfoils has a span dimension extending radially relative to said axis and a chord dimension extending transverse to said span dimension and with the numerical ratio of said span dimension to said chord dimension having an aspect ratio less than the numerical value of one, and two flexible cables connected to each of said airfoils and to said rotation mechanism and being horizontally extendable from said rotation mechanism and arranged to induce orbiting of said airfoils about said axis upon rotation of said rotation mechanism and thereby move said airfoils radially outwardly from said axis under centrifugal force acting on the orbiting said airfoils.