Matavian Propeller

Abstract

The present invention discloses an aviation propeller for both small drones and large aircraft comprising a vane-and-rim hub assembly and multiple V-connected pairs of rotor blades. Each V-connected pair of rotor blades shares a common hub connection. This propeller design produces both high thrusts and low acoustic signatures equivalent to toroidal non-Euclidian propeller designs. The aerodynamic geometries used facilitate ease of manufacture.

What is claimed: 
     
         1 . An aviation propeller comprising a hub and three V-rotor blade elements:
 the hub having a central core, a circumferential outer rim, and at least three radial vanes connecting the central core to the outer rim; the central core comprising a right circular cylinder, said cylinder having a diameter of ten percent or less of the aviation propeller overall diameter, and having one or more axial holes; the outer rim comprising a solid-walled radially non-porous hexagonal tube, said tube having an outer diameter of fifty percent of the aviation propeller overall diameter, and having an axial length equal to the maximum axial length of the V-rotor blade elements;   each of the three V-rotor blade elements comprising a pair of rotor blades and a hub connector at an inner end, wherein each pair of rotor blades and associated hub connector generally form a “V” shape; wherein the three V-rotor blade elements are arranged in circumferential symmetry about a longitudinal axis of symmetry through the central core of the hub;   wherein the airfoil cross-section of each rotor blade has a thickness-to-chord ratio between 15% and 18% inclusive;   wherein each rotor blade is configured with a spanwise constant chord;   wherein each rotor blade is configured with a spanwise constant thickness-to-chord ratio;   wherein each rotor blade is configured on the hub connector at a spanwise constant pitch angle between 5 degrees and 27 degrees inclusive;   whereby rotation of said aviation propeller about said axis of symmetry produces a net axial thrust, said axial thrust being larger in magnitude and lower in acoustic signature as compared to the axial thrusts and acoustic signatures produced by propellers having the same maximum diameter and rotating at the same revolutions per minute in air at identical atmospheric conditions.   
     
     
         2 . The aviation propeller according to  claim 1  wherein the airfoil cross-section of each rotor blade is comprised of either NACA 633-618, NACA 634-618, NACA 230115, or NASA NLF (1)-0115 shape. 
     
     
         3 . The aviation propeller according to  claim 1 , wherein materials for the aviation propeller comprise any combination from the following group: steel, aluminum, brass, carbon, pressed graphite, fiberglass/epoxy resin matrix, carbon fiber in an epoxy matrix, graphene fibers, graphene sheets, woven graphene yarn, thermoplastic 3-D printer filaments, nylon 3-D printer filaments, and ABS 3-D printer filaments.