US1083565A - Aeroplane. - Google Patents

Description

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R. SEIDELINGER. ABROPLANB.

APPLICATION FILED MAY 5, 1910. 1,083,565. Patented Jan.6,1914. A

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AEROPLANE.

Specification of Letters Patent.

Patented Jan. 6, 1914.

Application filed May 5, 1910. Serial No. 559,453.

To all whom t may concern.'

Be it known that I, Ronin SEIDELINGER, of the city of IVilmington, county of Newcastle, and State of Delaware, have invented certain new and useful Improvements in Aeroplanes, of which the following is a specification, reference being had to the accompanying drawings.

The invention relates to new and useful improvements in aero-planes and has for an object to provide means for preserving stability in direct flight and in turning to the right or left.

A further object of the invent-ion is to provide means for rctarding the movement of the aeroplane, which means is so disposed and constructed as to tend to cause the aeroplane to descend on an even keel.

A further object of the invention is to provide means for swinging the vertical rudder which means is so constructed that the rudder will be held in its various positions of adjustment.

A still further object of the invention, is to provide a supporting frame for an aeroplane, which includes yielding brackets carrying running wheels on which the aeroplane may rest in the initial starting of the same, and on which it may light at the finish of its flight.

These and other objects will in part be obvious and will in part be hereinafter more fully described.

In the drawings which show by way of illustration one embodiment only of my invention; Figure I, is a perspective view, showing an aeroplane embodying my improvements. Fig. II, is a horizontal sectional vicw through the rudder showing the means for adjusting the same. Fig. III, is a vertical section through the main supporting plane from front to rear. Fig. IV, is a detail showing the retarding plane and the manner of varying the exposed retarding surface of the same. Fig. V, is a detail showing the pivot support for the subplanes.

My improved aeroplane consists of a main frame having an upper strut 1, running from the front of the machine to the rudder support at the rear end thereof, and alower strut Q, which is substantially parallel with the upper strut 1, and which is secured thereto by suitable vertical posts 3.

The main frame is supported at its forward end on an auxiliary depending framework, consisting of a forward U-shaped support 4, which is suitably secured to the strut 2, at its upper end, and a supporting post 5, also secured to the lower strut 2. Said U- shaped support and said post 5, are connected by cross struts 6. A seat 7, is secured to the cross struts 6, and the post 5.

Brackets 8, 8, are pivotally attached to the U-shaped frame 4.-, and are connected at one end to springs 9, 9, which springs are suitably secured at their other ends to cross studs 6. Th-e brackets 8, S, at the lower end carry running wheels 10, 10. Said brackets 8, 8, are preferably curved as shown in the drawings, so that the connection between the brackets and the running wheels 10, 10, is disposed in the rear of the pivotal connection between the brackets and the U-shaped frame 4f. IVhen the weight of the frame or aeroplane rests on th-e wheels 10, 10, the tendency thereof will be to swing the brackets 8, 8, about the pivotal supports against the action of the springs 9, 9. It will, therefore, be seen that I have provided yielding brackets which carry the forward running wheels, and that these brackets will yield when the aeroplane lights, thus taking the shock of impact off from the structure of the aeroplanes.

The main frame near its rear end is provided with a depending post 11, on which is pivoted an arm 12, carrying at its lower free end, a running wheel 13. The opposite end of the arm 12, is jo-incd to springs 14, which are attached at their other ends to certain parts of the main frame. It will readily be seen that the weight of the rear end of the aeroplane will be yieldingly supported on the running wheel 13, and that the arm 12, will yield in a manner similar to the brackets 8, 8, when the aeroplane lights.

My improved aeroplane is supported during flight by a main plane 15. Said main plane consists of a suitable frame on which is stretched any suitable material commonly used for forming planes of this character. The forward member 16, of the supporting frame for the main frame, is tapered to a cutting edge, as clearly shown in Fig. III. The end frames 17, are substantially straight, on their lower edge and gradually taper from their central portion toward their outer end, so as to form an upwardly flexed portion extending centrally through the main plane longitudinally of said plane. The upper edges of said end frames 17, may

be straight or curved as desired. At suitable distances throughout the main plane, I have provided cross partitions 18, which are shaped similar to the end frames 17. The lower edges of the cross partitions are on a line with the lower edges of the frame for the main plane, and the upper edges of the partitions are in contact with the material forming the main plane. Said cross partitions will therefore, form a series of separated pockets, which materially increase the supporting power of the main plane and also strengthen said main plane. The upper strut 1, of the main frame is shaped so as to support the main supporting plane centrally of the same, and to also form a cross partition. At each end of the main supporting plane, I have provided as herein shown, extensions 19, each of which consists of a frame on which is stretched canvas or other suitable material, which will increase the supporting surface of the main supporting frame. These extensions as herein shown are attached rigidly to the main supporting frame, and are inclined upwardly and outwardly relative to said main plane.

It will be understood that suitable bracing rods and guy wires may be used for holding the various parts of the frame and the supporting plane in rigid relation to each other.

In order to increase the stability of the aeroplane when in direct flight or when turning to the right or left, 4I have provided laterally spaced sub-planes 20. These subplanes each consist of a suitable frame on which is stretched canvas or other desired material so as to form a supporting surface. As shown, the sub-planes 20, 20, are mounted on the outer ends of a cross bar 21. The upper strut 1, of the main frame, is provided with a downwardly projecting lug 22, which has a circular opening formed therein, adapted to receive a bearing 23, (see Fig. V), which is secured to the lug by pivot pins 24. The cross bar 21, is pivoted to the bearing 23, by a pivot pin 25, which extends in a direction substantially at right angles to the pivot pins 24.

The pivot pins 24, are arranged on the line d of Fig. I, which is slightly inclined rearwardly to the vertical. It will readily be seen that the connection between the cross bar 2l, and the supporting lug is a universal connection which will allow the subplanes to be swung forward and back and up and down.

In order to rigidly support the sub-planes in their various adjusted positions and to move them in the desired relation to the main supporting plane, I have provided cam guiding tracks 26, 26, one of which is located on each side of the pivotal support of the bar 21. Said tracks may be secured in any desired way to the main supporting frame, and their lower cam guiding edges normally rest against the upper face of the cross bar 21. The pivotal support for the cross bar 21, as herein shown is located substantially in line with the rear edge of the main supporting plane, so that when said cross bar 21, extends at right angles to the longitudinal axis of the aeroplane, a portion of each sub-plane will be underneath the main supporting plane. If, however, the cross bar 21, is swung in one direction about its pivotal support, then one sub-plane 20, will be moved farther underneath the main auxiliary plane and the other sub-plane 20, will be moved farther out from underneath the main support-ing plane. It will also be noted that as the sub-plane swings farther underneath the main supporting plane, the guiding track 26, on one side of the pivotal support will allow the cross bar to swing upwardly and the guiding track on the opposite side will cause the cross bar to swing downwardly, thus bringing the sub-plane which moves underneath the main supporting plane up closer to the under surface thereof, and cause the other sub-plane which is moving out from under the main supporting plane to move downward and away from the main supporting plane. It will readily be seen therefore, that I have provided laterally spaced sub-planes which may be swung simultaneously relative to the main supporting plane so as to carry one of said sub-planes underneath said main supporting plane, and the other out from under said main supporting plane, and at the same time shift the position of said sub-plane relative to the vertical axis of the aeroplane. By this movement of the sub-planes, I am able to increase the effective supporting surface on one side of the longitudinal axis of the aeroplane, and at the same time decrease the effective supporting surface on the other side thereof. By the proper manipulation of these sub-planes, the aviator may preserve the balance or stability of the aeroplane, overcoming the iin-balancing eect of unequal air currents on opposite sides of the aeroplane or the iin-balancing eifects due to the turning of the aeroplane to the right or left while in flight.

As a means for manipulating the subplanes, I have provided a vertical shaft 27, on which is mounted a sleeve 28. Projecting arms 29, are loosely mounted on said sleeve and are connected by suitable cords 30, to the cross bar 21. A hand wheel 31, is fixed to the sleeve for turning the same. The aviator may swing the projecting arms 29, about the sleeve 28, and thus shift the position of the sub-planes.

A suitable propeller 32, is mounted on the end of the propeller shaft 33, journaled in bearings carried by certain of the vertical posts 3, of the main frame. The engine operating the propeller may be mounted in the forward portion of the depending frame and connected in any suitable way to the propeller.

The rudder 34, .is mounted in a frame 35, which substantially surrounds the rudder and is made a part of the main frame. The frame 35, carries a yoke 36, having suitable bearings in its outer ends for supporting a screw shaft 37. The rudder has rigidly attached thereto, a nut 38, which engages the screw shaft 37. At its inner end said rudder engages a U-shaped guiding bracket 39 (see Fig. II). By manipulating the screw 37, the nut 38, will be moved to the right or left as shown in dotted lines in Fig. II, and the U-shaped bracket 39, will form a sliding pivo-t for said rudder, allowing the same to have the above movement.

The screw 37, carries a pulley at each end, over which pass guiding wires 40, 40. The guiding wires 40, frictionally engage a pulley 41, on the shaft 27. Said shaft 27, may be manipulated by a hand wheel 42. By turning the hand wheel 42, the screw shaft will be rotated and the nut 33, moved one way or the other, according to the rotation of the shaft and the rudder swung about its sliding pivotal connect-ion with the frame.

As a further means for preserving the stability of the aeroplane and for causing horizontal flight, I have provided spaced auxiliary planes 43, 43. Said auxiliary planes as herein shown, are located on each side of the main frame and in a position adjacent the rudder or rear end of the frame. It is obvious however, that the position of said auxiliary planes may be varied, if desired. Each of said auxiliary planes 43, consists of a supporting frame on which is stretched a canvas, or any other suitable material, so as to form a supporting plane. The auxiliary planes 43, are rigidly attached to a shaft 44, which shaft serves as a pivotal supportfor said planes. The upper strut l, of the main frame carries spaced bearings in which the shaft 44, is mounted. A sector gear 45, is rigidly attached to the shaft 44, and coperates with the worm gear 4G, on the vertical shaft 47, which is mounted in suitable bearings in the main frame. The vertical shaft 47, carries a pulley which is connected by a suitable belt or wire to a pulley on the sleeve 2S.

By turning the hand wheel 3l, the shaft 47 may be rotated and the auxiliary planes swung about their pivot support. These auxiliary planes may be manipulated by the aviator, in order to keep the aeroplane on an even keel, and to cause it to move upward or downward when it is desired.

As a means for retarding the flight of the aeroplane, I have provided a flexible retarding plane 53. Depending from the mainl frame are spaced posts 49, and 50. Mounted on the posts 49, and 50, is a frame 5l, which has slotted side members adapted to guide t-he cross bars 52, of said flexible plane 53. The flexible plane 53, is made of canvas or any other desired material which is suitably secured to the cross bars 52. The frame 5l, as clearly shown in Fig. IV, is formed with a horizontal section and with an inclined section. The flexible plane 53, is shorter than the length of the frame 5l. IVhen said flexible plane is at the rear end of the frame 51, said flexible plane will be substantially horizontal or parallel with the main supporting plane, and will merely serve as a supporting surface. IVhen, however, said flexible plane is moved to the forward part of the frame 51, it will be inclined downwardly relative to the main supporting frame, and will operate as a retarding plane or surface.

The supporting posts 49, and 50, carry guiding pulleys 54, over which a cord 55, extends, which cord is joined to each end of the flexible plane, and extends over the guiding pulley 56, adjacent the aviators seat. By manipulating the cord 55, the retarding plane may be rendered effective or ineffective.

The operation of my device will be apparent from the above description. Subplanes may be manipulated to secure the desired effect in preserving the stability or balance of the aeroplane. The rudder may be quickly shifted from one position to another and held in its adjusted positions. The auxiliary planes may be swung about their horizontal pivotal support in order to direct the horizontal flight of the aeroplane and the retarding plane may be thrown into effective position when it is desired to light, thus quickly stopping the movement of the aeroplanes and furthermore, by its position relative to the main supporting plane, cause the aeroplane to descend on an even keel, and the aeroplane in alighting will be received by the yielding supported running wheels which take up the impact and reduce to a minimum the jar on the various rigid portions of the aeroplane.

IVhile I have shown and described herein a single supporting plane, it will be obvious that from certain aspects of the invention, more than one main supporting plane may be used. It will also be obvious that minor changes in the details of construction and the arrangement of parts may be made without departing from the spirit of my invention, or sacrificing the principles thereof.

Having thus described my invention, I claim:

l. An aeroplane including in combination, a main supporting plane, of laterally spaced sub-planes located in rear of the main plane, means for supporting said sub-planes, and means for moving said sub-planes bodily simultaneously` in opposite directions, to-

ward and from a position underneath said main plane.

2. An aeroplane including in combination, a main supporting plane, laterally spaced sub-planes located in rear of the main plane, and means for supporting said sub-planes whereby the same may be moved about an axis inclined to the vertical, and about an axis inclined to the horizontal bodily in opposite directions toward and from a position underneath said main plane.

3. An aeroplane including in combination, a main supporting plane, laterally spaced sub-planes, a cross bar on which said subplanes are rigidly mounted, means for pivotally supporting said cross bar, whereby said sub-planes may be moved in opposite directions toward and from a position underneath said main plane.

4:. An aeroplane including in combination, a main supporting plane, laterally spaced sub-planes, a bar to which said sub-planes are rigidly attached, a universal joint for supporting said bar, tracks for guiding said bar whereby said sub-planes may be moved about an axis inclined to the vertical, and an axis inclined to the horizontal, simultaneously in opposite directions.

5. An aeroplane including in combination, a main supporting plane, laterally spaced sub-planes located on opposite sides of the longitudinal center of the aeroplane, means for moving one of said sub-planes bodily underneath or away from the main supporting plane for increasing or decreasing the effective supporting` surface of the aeroplane on one side thereof, and for simultaneously moving the other sub-plane bodily away from or underneath said main supporting plane for decreasing or increasing the effective supporting surface of said aeroplane on the other side thereof.

6. An aeroplane including in combination, a main supporting plane, laterally spaced sub-planes located in rear of the main plane, means for supporting said sub-planes, means for moving said sub-planes bodily simultaneously in opposite directions toward and inclined position.

from a position underneath said main plane, laterally spaced auxiliary planes, means for pivotally supporting said auxiliary planes, whereby the same may be swung about a horizontal axis, and means for simultaneously swinging said auxiliary planes upon said horizontal axis.

7. An aeroplane including in combination, a main supporting plane, laterally spaced sub-planes located in rear of the main plane, means for supporting said sub-planes, means for moving said sub-planes bodily simultaneously in opposite directions toward and from a position underneath said main plane, a flexible retarding plane and means for gradually moving said flexible plane from a horizontal position to an inclined position for gradually increasing the effective retarding surface of said flexible plane.

8. An aeroplane including in combination, a main supporting plane, a flexible retarding plane, consisting of a guiding frame having grooved side pieces, a port-ion of said side pieces being horizontal and a portion thereof being inclined, cross bars engaging said grooved side pieces, a flexible material secured to said cross bars, and means for sliding said cross bars and flexible material on said grooved side pieces, whereby said flexible plane may be moved from a horizontal position gradually to an 9. An aeroplane including in combination,

a main supporting frame, a supporting plane, a vertical rudder, a frame extending about said vertical rudder, a screw threaded shaft carried by said frame, a nut mounted on said shaft, and pivotally connected to said rudder, a U-shaped bracket for slidingly supporting one edge of said rudder, and means for rotating said threaded shaft.

In testimony whereof, I have hereunto signed my name at Philadelphia, Pennsylvania, this twenty-sixth day of April 1910.

ROBIE SEIDELINGER.

Witnesses:

JAMES H. BELL, E. L. FULLERTON.

Copies of this patent may be obtained for five cents each, by addressing the Commissioner of Patents, Washington, D. C."

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