Патент USA US2125063код для вставки
July 26, ‘193$. 2,125,063 R. H. BURGESS PROPULSION MECHANISM FOR AIRCRAFT Filed May 27, 1936 ‘ INVENTOR. ugess. BY/Zf/, ,4”, ATTO EY ‘2,125,063 Patented July 26, 1938 UNITED STATES PATENT OFFICE , 2,125,063 PROPULSION MECHANISM FORv AIRCRAFT Richard H. Burgess, San Antonio, Tex. Application May 27, 1936, Serial No. 82,119' 5 Claims. (Cl. 244—-'72) This invention relates to an improved pro pulsion’ mechanism for aircraft, being especially designed for use in conjunction with aeroplanes and gliders. Among other objects, the invention seeks to 5 provide a Wing tip which may be oscillated, ei ther manually or by power, relative to the body of the Wing for propelling the aircraft forwardly with the greatest ei?ciency in proportion to the 10 effort expended. A further object of the invention is to provide a wing tip composed of a plurality of parallel blades and wherein said blades will be so con structed and mounted that as the wing tip is 15 swung upwardly, the blades will yieldably de?ect downwardly to act on the air for driving the air craft forwardly while, as the wing tip is swung downwardly, the blades will yieldably de?ect upwardly to act on the air for a like purpose. And the invention seeks, as a still further ob 20 ject, to provide a wing tip of unique and novel construction. Other and incidental objects of the inven tion not speci?cally mentioned in the foregoing 25 will appear during the course of the following description and in the drawing which forms a part of my application, Figure l is a plan view of my improved mech anism. Figure 2 is an enlarged detail sectional View showing the construction of the blades of the wing tip. Figure 3 is a transverse section through one of the blades and showing the manner in which the blades are adapted to be de?ected both upwardly and downwardly. Figure 4 is a detail section showing the levers for rocking the wing tip. Figure 5 is a fragmentary section showing a slightly modi?ed form of blade. Figure 6 is an enlarged detail section of the modi?ed structure. Referring now more particularly to the draw ing, I have shown the body of an aeroplane or glider wing at Ill. The wing body may be of any approved construction and is straight at its outer end. Mounted to swing up and down relative to the wing body H1 at the outer end thereof is a 50 wing tip. This wing tip comprises a hinge rod or header II from which projects a plurality of spaced parallel lateral studs l2 and ?xed to said studs are blades I3 slightly spaced apart and all normally lying in the same plane. Each of the blades I3 includes a flexible re silient stem l4 looped .at its free end portion to provide a substantially U-shaped frame [5 and slipped over said frame from the outer end there of is a bag of canvas or the like forming a web H5. The bag is closed at its outer end and will be held taut by the resiliency of the frame I5, the overlapping thicknesses of the bag being cemented together by dope which will also serve to secure the web on the frame. While any ap proved material may be employed still, the stems 0 l5 are each preferably formed of a length of bamboo cored out at its larger end and slipped over one of the studs l2 to- which the length of bamboo is suitably ?xed. This construction is light in weight and the bamboo possesses the 15 necessary strength, toughness and resiliency. Extending between the stems near their inner ends is an appropriate brace rod ll. If preferred, a straight length of bamboo may be employed to form a stem [8 and ?xed to said stem at spaced points are loops IQ of resilient wire. These loops are provided With studs 20 which extend through the stem and securing the loops to the stem are cotter pins 2|. The sev eral loops provide a frame which carries a web 25 22 like the webs I 6. Projecting from the outer end of the wing body l0 are spars 23 to which the rod H is hingedly connected in any appropriate manner and ex tending laterally in opposite directions from said 30 rod are levers 24. Attached to said levers are cables 25 which extend into the fusilage of the aircraft and may be operated manually or by power for swinging the wing tip up and down. As the wing tip swings upwardly, downward canting of the webs l6 of the blades l3 will be‘ resisted by the stems M of said blades but the Webs will, however, be de?ected by the air and move into a downward angular position to act on the air for propelling the aircraft forwardly. Similarly, as the wing tip swings downwardly, the webs l6 of the blades will be de?ected into an up ward angular position for propelling the aircraft forwardly so that both the upward and down ward movement of the wing tip will be utilized for driving the aircraft ahead. Having thus described the invention what I claim is: 1. Propulsion mechanism for aircraft including in combination with a wing body, a wing tip '“ hinged to the wing body and composed of a plu rality of blades including ?exible stems provided with lateral webs, the stems being resiliently twistable to torsionally resist but yield to both upward and downward de?ection of the Webs by 2 2,125,063 the air as the wing tip is swung, and means for swinging said tip. 2. Propulsion mechanism for aircraft including a header, ?exible resilient stems carried by the header and looped to form U-shaped frames each having a single leg thereof ?xed to the header, envelops ?tting over said frames and pro viding blades having webs extending laterally from the stems, the several blades forming a wing 10 tip, means for hingedly connecting said tip with a wing, and means for swinging said tip. 3. Propulsion mechanism for aircraft including a rod having spaced studs extending therefrom to form a header, ?exible resilient stems ?xed to 15 said studs and looped to form frames each hav ing a single leg thereof engaged with one of said studs respectively, fabric bags engaged over said 20 frames and forming blades having webs extend ing laterally from said stems, the several blades forming a wing tip, means for hingedly con necting said tip with a wing, and means for swinging said tip. 4. Propulsion mechanism for aircraft includ ing a wing body, a plurality of double-acting blades hinged at the outer end of the wing body to form a swingingly supported wing tip, the blades being spaced to freely and individually twist downwardly as the wing tip is swung up wgardly and upwardly as the wing tip is swung downwardly and being torsionally resilient for exerting a forward propelling force on both the upward and downward movement of the wing 10 tip, and means for swinging said tip. 5. Propulsion mechanism for aircraft including a plurality of blades, means supporting the blades to swing as a unit, said blades being spaced to freely and individually twist downwardly as the 15 blades are swung upwardly and upwardly as the blades are swung downwardly and being torsion ally resilient for exerting a forward propelling force on both the upward and downward swing ing movement of the blades, and means for 20 swinging the blades. RICHARD H. BURGESS.