US1787370A - Aeroplane wing - Google Patents

Description

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W. S. HALL AEROPLANE WING Filed Dec. 16, 1929 2 Sheets-Sheet 1 mks-Hall,

INVENTOR -ATTORNEY I 244. AERONAU \US w. s. HALL AERoPLAiqE: WING Dec. 30, 1930.

- mm'a- 244. Atnuwnu luo Patented Dec. 30, 1930 UNITED STATE oFicE AEROPLANE WING Application fi1ed December 16, 1929. Serial No. 414,512.

This invention relates to improvements in aeroplanes and more particularly to a novel wing structure, and therefore one of the primary objects of the present invention is to provide a novel flight wing of such contour and so arranged as to possess much greater lifting efficiency than the ordinary flght wings of aeroplanes as heretofore constructed and arranged.

Another object of the invention is to provide an aeroplane wing having less resistance to travel and one which will permit of slackening of the speed of travel of the aeroplane, independently of the operation of the propellers, so that landing may be effected with less difficulty and without the liability of the accidents attending the usual landing of an aeroplane.

Another object of the invention is to provide, in combination with the body of an aeroplane, a flight wing so constructed and mounted, and capable of such adjustment that the direction of an aeroplane to a higher or lower elevation during flight, may be readily effected without any liability of the occurrence of a tail spin.

Another object of the invention is to provide an aeroplane embodying a flight plane so constructed that the plane may be started on its flight and landed without the necessity of adjusting the elevating fins and wings as in the caseof aeroplanes as ordinarily constructed, thus relieving the pilot of the aeroplane of the task of adjusting the elevating fiins or planes, in addition to controlling the flight planes, and thereby rendering the control of the flight of the aeroplane more ready of performance.

This invention also consists in certain other features of construction and in the combination and arrangement of the several parts to be hereinafter fully described, illustrated in the accompanying drawings and specifically pointed out in the appended claim.

In describing my invention in detail reference will be had to the accompanying drawings wherein like characters denote like or corresponding parts throughout the several views, and in which Figure 1 is a view in side elevation of an aeroplane constructed in accordance with the present invention.

Figure 2 is a top plan View of the aeroplane illustrating clearly the marginal contour of the planeembodying the invention and the disposition thereof with respect to the body of the aeroplane.

Figure 3 is a view in front elevation of the aeroplane.

Figure 4 is a detail view illustrating the adjusting means for the flight plane, embodying the invention, the aeroplane and propellers, proper, being shown in broken lines.

Figure 5 is a similar view in side elevation of the adjusting mechanism for the plane of the present invention.

The flight plane of the invention and the means for adjusting the same may be embodied in aeroplanes of various types, but it is here shown installed upon an aeroplane of the Zepplin type, and in the drawings the body of the aeroplane is indicated in general by the numeral 1, and is of the usual construction, and the propellers, which are two in number, are arranged at the forward end of the body, these propellers being indicated by the numeral 2 and being mounted upon shafts 3 driven by engines 4 mounted upon the opposite sides of the aeroplane body. The aeroplane, proper, includes the usual landing wheels 5 and the usual steering rudder 6 for directing the flight of the aeroplane toward the right or left, in making turns, or in changing the direction of travel.

The flight plane embodying the invention is indicated in general by the numeral 7 and as shown clearly in Figures 1, 2 and 3 of the drawings, is of true elliptical marginal contour, and is transversely of concavo-convex form, and, in mounting the plane, struts 8 are secured at their lower ends at the opposite sides of the body of the aeroplane, and the said struts, at each side of the body are inclined upwardly toward each other and are connected at their upper ends to a cross rod 9, which is mounted transversely of the under side of the plane 7 at a point midway between the ends of the plane so that, assuming that the aeroplane body is so constructed,

and the engines tareso arranged as shown in Figures 1 an'd 2 of the drawings, as toequally distribute the load being carried by the pilot, the flight plane 7 will be in equilibrium with respect to the body of the aeroplane and the fins therefor.

In order that the flight plane 7 may be tilted about its axis so that, when its forward end is elevated, and its rear end is lowered, as for example, in taking off, and, con versely, when the lower end is lowered and the rear end is elevated as in landing, means is provided which will now be described. The said means comprises a shaft 10 mounted near the forward end of the body of the aeroplane and in the cabin thereof, and in front of the pilots seat which is indicated by the numeral 11 and, a shaft 12 which is mounted within the body near the rear end thereof. Pulleys 13 and 14 are mounted, fixedly, upon the shafts 10 and 12 respectively, and these pulleys have trained about them cables 15 and these cables are led longitudinally within the body, between the respective pulleys 13 and 1 1, and have upper stretches 15 which are connected to the under side of the flight plane 7 near the front thereof at points equidistantly spaced at opposite sides of the longitudinal middle of the plane, and other upper stretches 16 which are connected to the under side of the flight plane near tlierear end thereof and at points equidistantly spaced from the longitudinal center line of said plane. A worm gear 17 is fixed upon the shaft 10 and a yoke 18 is connected at the ends of its arms with the shaft 10 at opposite sides of the worm gear, and provided upon its connecting portion with a bearing 19 in which is rotatably mounted a shaft 20 provided at its lower end with a worm 21 which meshes with the worm gear 17, a hand wheel 22 being fixed at the upper end of the shaft.

Preferably the shaft 20 is braced, near its upper end by being journaled at its said portion in a bearing 23 provided midway between the ends of a cross bar 24 mounted within the body of the aeroplane.

From the foregoing description of the invention it will be evident that, by rotatably adjusting the hand wheel 22, the flight plane 7 may be tilted to assume either a position parallel to the upper surface or longitudinal axis of the body of the aeroplane or an upwardly or downwardly titlted position as desired, and that in this manner the aeroplane may be caused to ascend and descend, and this result accomplished without the adjustment of any tilting fins or wings as has heretofore been necessary. It will also be evident that in preparing for flight, the flight wing may be suitably adjusted so as to tilt the same with its forward end elevated so that when the aeroplane is started, the wing will cause the aeroplane to leave the ground surinsasro face and there-f oi'e thi s simple adjustment ac complishes thesaineresultjin a 1rfore-effec tive manner than the' op' eration ce ist-ides controls for tilting fins an'clwings; 7 In practice, the upper and "under" 'sur facesof the flight plane 7 will be smoothly finished and the major axis of the said. plane will of course be located in the same 'v'erti cal plane as the axis of the body of the aeroplane.

IVhat I claim is I The combination with the body of-an aeroplane, of upwardly inclined strutsfmounted at opposite sides of the body,'ashaft sup ported by the upper ends ofthe struts, a flight plane of elliptical marginal contour mounted upon said shaft for tilting movement and having its longitudinal axis in'the same verti cal plane as the longitudinal axis of the body, and means connected with the plane'near the ends thereof for tiltab'ly' adjusting the said plane, the said means comprising shafts rotatably mounted in the'body of the aero plane at points transversely below the' f ront and rear end portions of the flight plane, drums upon the shafts, cable's wound about and extending between the corresponding drums of the shafts and having their "terminal stretches extending upwardly from the drums and connected to the flight plane adjacent the ends thereof,"and inanually oper able means for rotating the forward one of said shafts. I In testimony whereof I affix my signattii'el IVILLIAM S. HAIJLQ' roe awn

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