US1364752A - Flying-machine - Google Patents

Description

J. HALLSTEAD.

FLYING MACHINE. APPLICATION FILED IAN-10, 1920 1,364,752, Patented Jan. 4, 1921.

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FLYING MACHINE. APPLICATION FILED JAN. 10, 1920.

Patented Jan. 4,1921.

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FLYING MACHINE.

APPLICATION FILED JAN-10, I920.

Patented Jan. 4,1921.

3 SHEETS-SHEET 3 .5. I T? h IWENTOR v JoH/v HALLSTEAD 23 2/ er 2 Z ATTORNEYS Bronx, in the county UNITED STATES PATENT OFFICE.

JOHN HALLSTEAJ), OF NEW YORK, N. Y.

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Specification of Letters Patent.

Patented Jan. 4, 1921'.

Application filed January 10, 1920. Serial No. 350,624.

To all whom it may concern:

Be it known that 1,, JOHN HALLsTEAD, a

citizen of the United States, and a resident of the city of New Yorkigborough f the spects the invention is similar to the conventional or standard aeroplane.

Among the. objects of the invention is to provide a flying machine in which are combined in the same member or members the features or functions of the usual propellers and lifting or sustaining planes.

More specifically stated I provide a machine in which the power elements are devices rotatahlearound a horizontal; axis transverse to theline of flight and comprising a plurality of wings which have many.

of the characteristics of the wings of an aeroplane, but which include a plurality of parallel blades pivoted along one edge and movable with respect to the general plane of the wings. I

Another object of the invention 1s to, provide power devices pivoted upon horizontal axes and combining the functions of lifting, propelling, or sustaining or gliding means With the foregoing and other objects in;

view the invention consists in the arrangement and combination of parts hereinafter described and claimed, and while the invention is not resltricted to the exact detailsof construction disclosed or suggested herein,

still for the purpose of illustrating a practical embodiment thereof reference is bad to the accompanying drawings, in which like reference characters designate the same parts in the several views, and in which Figure 1 is a side elevation of a diagrammatic representation of one embodiment of this'invention. Fig, 2 is a vertical. longitudinal section through one of the power devices, other parts being broken away.

Fig. 3 is a plan view showing the principal parts of my improvement, parts being broken away to conserve space.

Referrin' now more specifically to the drawings show my improvement as applied to a flying machine having a body 10 which in all general respects is or may be substantially the same as the body of an ordinary aeroplane having cock pit 11 and any suitable rudder or tail mechanism 12 controllable from the cock pit, but with which features per 86 I am notparticularly concerned.

Located within the body or at any desired elevation with respect thereto is an engine 13 hav ng a shaft 14 extending laterally from both sides of the body.

F xed in any suitable manner in a vertical plane on each side of the body is a stationary disk 15 having in its periphery an annular groove 16 adjacent to which are journaled an annular series of anti-friction rollers 17.

Fitte d upon the disk and adapted to rotate in said groove and anti-frictionally upon the rollers is what- I term a compensator comprising an annulus 18 and a series of radiall disposed arms 19 of equal length,

f the wings above referred to I show for each power member four wings each indicated at 19 and comprising two parallel end bars 20 having the general form of the chord of an ordinary aeroplane and fixed --last rod 22 constitutes a stop for the rearmost blade 23 limiting its upward movement and so each of the other rods except the foremostone acts as a stop forthe blade aheadof-it. The forward or downward swing of the blades is limited by any suitable flexible connections 24. As will be understood from Fig. 2 these blades 23 are adapted to lie approximately in the same plane asthe frame of the wing or to be swung downward and forward around their several pivots to a position approaching a right angle or in the position most favorable for beating rearw'ard upon the air for forward propulsion of the machine as shown at A, or to slip freely upward toward the position B. In stage 6 the wing acts as a sustaining or gliding member and from such position to the position D it acts to beat downward upon the air for a lifting function.

Secured to the engine, shaft 14 between the. compensator and the inner end of each power member is a spider 25 comprising four radial arms 26 of the same effective length from the center of the shaft as the effective length of the arms 19 from the center of the compensator. The engine shaft however is eccentric to the disk and compensator, or in other words the compensator is arranged to rotate readily and freely around one center or axis, while the spiders rotate arounda different axis.

Secured rigidly to each wing is a crank 27 one end of whichis coaxial with the pivot bar 21 and the other end of which is pivoted at 28 at the outer end of a compensator arm 19. A spider arm 26 is pivoted freely upon the pivot bar 21 at 29 adjacent to the crank 27. The effective length of the crank between centers of the pivots 21 and 28 is equal to the distance between the axes of the shaft 14 and compensato'r.- Thus thearms 19 and 26 form two sides of a parallelogram, while the crank and-distance between the centers just referredto constitute the other two sides of the same parallelogram. .By virtue of this design of th machine the wings arealways carried a the cidence.

same angle of incidence, such angle beingv approximately the same as that of an ordinary aeroplane wing, although I wish it to be distinctly understood that I am not to be limited to any particular angle of in- With the rotation of the engine shaft l l the spiders will be rotated accordingly and such rotation of the spiders around the axis of the engine shaft will cause the wings and compensators on opposite sides of the body to similarly rotate around the axis of the compensators, the wings always reamining parallel or to maintain the same angle of incidence. "The operation of the power devices will be appreciated from the drawings in view of the following brief summary: Whilethe wings are caused to swing or revolve around the axis of the engine shaft the blades 23 thereof may be said to assume four different stages indicated at A, B,'C and D. At stage A the wing is being propelled rearward assuming that the direction of rotation of the engine shaft is as indicated by the arrows on Figs. 1 and 2. At this time the blades 23 are projected downward so as to produce a rearward thrust on the air or a resulting forward thrust on the machine. From stage A to stage B the blades remain open and ascend in idle position having no propulsive function, nor with a'tendency to resist the free movement of the power device. .From stage B to stage C there is a transition from the open position of the blades to the closed I position in which the blades constitute in effect a structure similar to an ordinary sustaining orqifgliding aeroplane wing, the blades overlapping one another and making an airtight structure. In this position of stage C the wings have every function of the standard aeroplane wing. F'rorn -stage C to stage D each wing has a lifting effect beating downward upon the air with a resulting reaction v of the machine upward. From stage D to stageA there is a transition again to the open position of the blades for.

the rearward beatingefi'ect By means of the mechanism set forth herein I contemplate a mechanical device for navigating the air at any desired speed and with respect to vertical or forward directions. In other words while I believe this machine has the possibilities for favorable or superior comparison with standard aeroplanes, it is adapted to rise and alight in practically vertical lines. From the construction shown it will be appreciated that the angle of incidence of he'win-gs will be ing from the axis of the pivotal connection between the wing and its spider arm, a disk through which the power shaft extends eccentrically and having an annular peripheral groove, and acompensator journaled for rotation upon and around said disk and including a series of radialarms pivotally connected to the ends of the cranks remote from the wing pivots.

JOHN HALL-STEAD.

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