US1079167A - Aerodrome. - Google Patents

Description

R- G- DRESSLER.

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. 1910. 1,079,1 67., Patented Nov. 18, 1913.

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UNITED STATES PATENT oEEIoE.

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` Specication of Letters Patent.

Patented Nov. 18, 1913.

To all whom may concern Be it known that I, RUDOLPH G. Dnnss- LER, a. citizen of the United States, residing at Coney Island, in the county of Kings and State of New York, have invented certain new and useful Improvements in Aerodromes, of which the following is a specilication.

This invention relates'to improvements in flying machines or aerodromes ot that type which are operated by revolving propellers and supported by aeroplanes.

The object of this invention is to provide a. machine of this kind which will be eilicient in use, which may be easily controlled` and which will be Stable in flight. 'To this end I have provided a flying machine comprising a frame supported by an aeroplane consisting of one or more horizontal planes, said frame carrying a revolving propeller and a suitable motor for rotating the same, and a rudder moving in both horizontal and vertical planes.

A further part of my invention consists in providing soaring blades operative inconnection with the plane, whereby the draft is decreased and lifting power increased.

A still further part consists in the lateral balancin rudder, whereby the aerodrome is kept horizontally imposition; and lastly in the mechanism et the steering rudder.

In the accompanying drawings, Figure 1 is a perspective view of one form of my invention, Fig. 2 is a rear view of the same,

,Figa 3 is a side elevation of'another form of my invention, and F ig. 4 is a front View of the same.

Similar reference characters indicate corresponding parts throughout the several gures.

Referring more particularly to Figs. 1 and 2, the irst form of my invention is shown comprising upper and .lower planes 5 and 6 suitably braced and spaced apart by vertical and cross braces 7 and 8, and carrying by means off supporting rods 9 the car 10 carrying a gasolene or other improved form of motor 11 having a crank shaft 12 on which is carried the propeller 13. The planes 5 and 6 are slightly inclined to the horizontal position of the car 10 with their forward ends upward, the planes and car being held in this relative position by means of the supporting rods 9 and the cross rods or wires 14. Rearwardly projecting from the rear part of the car 10 is the ruddersupport 15 carry-ing the helm 16 pivoted at its middle part .for movement in both vertical and horizontal planes to vsaid support 15 by means of the universal joint 17. Attached to the rear part of said helm is the rudder 18 comprisinga horizontal plane 19 and a vertical plane 20; The forward end of the helm 16 has pivoted thereto a downwardly projecting link 21 adjustably secured by means of a hand-screw 22 to a pivoted sleeve 24, pivoted to a cross bar 25 in the car 10. The car 10 is provided with a plurality of supporting wheels 26 to be used in commencing an ascent and for alighting.

The planes 5 and 7 are set at that angle which has been found to .be most eiiicient when the machine is moving at a constant height. When it is desired to ascend, the helm 16 is lowered thus causing pressure to be exerted upon the top of the planeV 19 of the rudder, and causing the planes 5 and 6 to assume a position abnormally inclined to the horizontal, the front ends of said planes being highest. As it is well understood this will cause the machine to ascend. On the other hand, when-itis desired or'the machine to descend, the helm 16 is raised, thus causing pressure to be-.brought to bear upon the lower part of the plane 19 and causing the machine to "tilt forwardly and to ldescend. When the correct horizontal position of the helm 16 for continued flight is found, said posit-ion may be maintained by securing the link 2l to the sleeve 24 by means ofthe hand-screw 22. Since the sleeve 24 is pivoted to the bar 25 and the link 21 to the helm 16, the helm may be, when thus .held in the desired horizontal plane, shifted substantially in said plane to cause the machine to be guidedv to one side or the. other. en it becomes necessary to guide the machine both vertically and horizontally at the same time this is done by simply moving the helm in the horizontal and vert-ical planes. et the' same time.

It will be noted the car 10 together with the motor 11 is carried much below the center of the lifting force of the machine, thus insuring extreme and automatic stability.

Referring to the form of the invention illustrated by Figs. 3 and 4, the machine is shown supported by a single aero lane 51 which is sllghtly curved upwar ly and placed Vnormally slightly inclined to the horizontal. Said plane 51 carries a framework 52 to which is attached wheels 53 and a spring runner 5,4: for purposes of supporting the machine when commencing a flight or alighting. This frame-work also carries the seat 55 for the aviator, and a motor 56 having a crank shaft 57 carrying the propeller blades 58.

The propeller blades 58 are not, as heretofore, placed in the same plane of revolution, but are placed rather in a very -obtuse cone of revolution extending forwardly of the. -point where the blades are secured to the propeller shaft. As will be readily seen this causes the air from the propeller blades to be driven off at a considerable angle to the propeller shaft, both on account of the position of the blades and the centrifugal force acting upon the air. The effect of thisis that a rearwardly extending cone of rela-- tively still air with its apex at the forward part of the propeller shaft immerses the space above and about the seat 55, thus permitting the aviator to ride in substantially still air and not be subjected to the rapidly moving air from the propeller blades. By this cone a counter current is produced in a forward direction striking the aviator at the back, and if anything, `assists the forward movement of the aerodrome.

The frame-work 52 has a rearward eXtension 59 to which is pivoted, for movement in both vertical and horizontal planes, the

-helm 60 by means of a universal joint 61,

At the rearpart of said helm is provided a 'rudder62 comprising vertical and horizontal planes 63 and 64 intersect-ing eachother 4at the helm. Intermediately of the ends of the framework 52 the supports 65 and 66 are provided, carrying universal joints 67 to which are pivoted for movement, in both vertical and vhorizontal planes, the handle lever 68 and the intermediate lever 69. The intermediate lever is connected at opposite end'sto 'the handle lever 68 and the helm 60 bymeans of universal and sliding connections 70. On account of this arrangement the raising of the handle 71 Vof the handle lever 68 causes the raising of the forward end of the helm 60 just the same as if the forward end of the helm itself had been raised. In like manner, the shifting to one side or the other of the handle 71 vcauses the shifting int-hat same direction of the forward end of the helm.

To the rear edg'e of the plane 51 is suitably mounted a transversely elongated iexible blade 72. This blade is made with a desired'degree of elasticity and has secured to its free rear edge adjusting cords 73 passing forwardly and downwardly and adjustably secured in any suitable manner to the seat 55 as at 74. lVhenthe machine is in flight the flexible blade may be bent by the pressure of the air to the position shownby the dotted lines of Fig. 3. This soaring blade has suiiicient elasticity to permit one end to be pulled down lower than the other end, whereby the operation and balancing o-f the aerodrome is facilitated. The advantageous action' of the soaring blade depends on the elasticity of compressedA air relieved of its compressing force. By a proper manipulation of the soaring-blade the draft may be decreased, by decreasing the resist-` ance to be overcome, and second, -by contributing to the amount of propelling power, by reason of the expansive effect of the compressed air immediately below the soaring blade. V'Vhen the engines are stopped either purposely or accidentally, the action of the soaring blade is such as to maintain t-he forward impetus indefinitely, and thereby prevent a dropping and consequent probable destruction of the aerodrome.

The soaring blade in Fig. 4 is shown as extending the entire width of the aeroplane but it may, also extend only 'a part of it.

At the enter of the forward part of the upper face of the plane 51 is an upwardly projecting support v75 to which-is pivoted for movement in a substantially horizontal plane, thev vertically disposed balancing plane 76. To each face of said plane are secured shifting cords 7 7 passing over pulleys or the like 78 through the plane 51 down to a convenient gripping device 79 at the forward part of the machine. If the machine should at any time show any tendency to tilt to one side, said balancing plane is shifted to that side by means of the cords 77, the pressure exertedon said plane being suiiicient to right or erect the machine. The operation of the second form of machine is similar to that ofthe first so far as it relates to the rudder 62 and the commencing of. an

ascent.

When the propeller rotates by motor power it drives the machine first over the -ground and as soon as it has gathered enough speed it rises from the ground and can be guided by shifting the rudder in horizontal or vertical planes, or both, to any elevation. If the motor is stopped, the soaring blade 72 forces the machine forward by its inward propulsion for a considerable distance by the action of the soaring blade. This soaring can be stopped by pressing the soaring-blade 72 from the position shown by thedotted'lines of Fig. 3 to the position shown by full lines and fasteningthe same by means of said device 79.. Lateral guidance and erection of the arodrome can be procured by the plane `76 and' secondary lateral guidance is automaticall obtained therein Without departing from the spirit of my invention.

Having thus described my invention, l claim as new and desire to secure by Letters 5 Patent the following:

In anlaerodrome, an elongated frame, a helm, a rudder thereon, having horizontal and vertical planes, an intermediate lever slidably and pivotally connected at its rear l0 end to said helm, a handle lever slidably and pivotally connected at its rear end to said intermediate lever, and supports to Which said helm and levers are pivoted by 'uni- Versal joint Connections, whereby the rudder may be moved in any direction.

In testimony, that I claim the foregoing as my invention, I have signed my name in presence of two subscribing Witnesses. i

RUDOLPH G: DRESSLER.

Witnesses:

FANNIE Fien, JOHN MURTAGH.

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