US1396459A - Aeroplane - Google Patents

Description

G. ORTGIER.

AEROPLANE.

APPLICATION FILED 050.10. 1920.

1,396,459. Patented Nov. 8, 1921.

'a SHEETS-SHEET 1.

R) 1 I k nav 6 may.

G. ORTGIER.

AEROPLANE.

APPLICATION FILED DEC. 10. I920.

Patented Nov. 8, 1921.

3 SHEETS-SHEET 2- In V612 Zorn- ?emye 0/" 3711 62". 57 d GEORGE OBTGIER, OF EAST ST. LOUIS, ILLINOIS.

annormim Specification of Letters Patent.

Patented Nov. 8, 1921.

Application filed December 10, 1920. Seriai No. 29,618.

To all whom it may concern.

Be it known that I, GEORGE ORTGIER, a citizen of the United States, and resident of the city of East St. Louis, county of St. Clair,'and State of Illinois, have invented certain new and useful Im rovements in Aero lanes, of which the ollowing is a specification, containing a full, clear, and exact description, reference being had to the accompanying drawings, forming a part hereof.

My invention relates to improvements in aeroplanes, and has for its primary object the construction ,of an aeroplane which is provided with a steering plane on its rear end and with ailerons, both of which may be controlled or adjusted to guide the plane in any desired direction.

This invention is an improvement on my revious application filed June 1, 1920, erial Number 385,588, allowed October 5, 1920.

In the drawings- Figure 1 is a top plan view of my improved aeroplane;

Fig. 2 is an end elevation, showing the adjustment in descending toward the left;

Fig. 3 is a similar view, showing the plane ad'usted in descendin toward the right;

ig. at is-a vertica -longitudinal section of the rear portion of the aeroplane with parts broken away;

Fig. 5 is a transverse section taken on the line 55 of Fig. 4, with parts broken away, looking in the direction of the arrows;

Fig. 6 is a section taken on the line 66 of Fig. 4 with parts broken away, looking in the direction of the arrows;

Fig. 7 is a fragmentary side elevation of the means for operating the ailerons; and

Fi 8 is a section taken on the line 6-6 i of Fig. at with the operating handle adjusted toward the right.

Referring by numerals to the accompanying drawings:

9 indicates the rear body portion of the aeroplane and within which is a skeleton or latticed member 10, and secured to the rear end of the latticed member 10 is a head 11, and secured to the front end of the latticed member 10 is a head 12, the head 12 carryin" the shaft 13, and on the head 13 is a but .14 mou ted i he bea i g 15- he shaft 13 and its contiguous parts are supported by a frame 16.

Secured to the shaft 13 is a sliding ear, composed of two portions 17 and 18. Fach of the sections 17 and 18 are provided with a T-shaped key-way 19, adapted to receive a key-shaped rib or key 20, formed on or carrled by the shaft, said construction bein illustrated in Fig. 6. These members 1% and 18 are independently movable and both rotate with the shaft 13.

21 indicates a yoke provided with teeth 22 on its upper and lower portions, which are adapted to mesh with the teeth formed on the members 17 and 18. The yoke 21 is provided with extensions 23 which are mounted in the bearings 24, thebearings 24 bein carried by the frame 16. The yoke 21.

' is a apted to move laterally by the rotation of the shaft 13 and the gear members 17 and 18.

Pivotally secured to the head 12 is an operating handle 25, which maybe moved forwardly and rearwardly and by means of which the skeleton member 10 and the shaft 13 may be rotated. The member 17 is pivotally connected to the handle 25 by means of a link 26 and the member 18 is pivotally connected to the operating handle 25 by means of a link 27.

As previously pointed out, the two members 17 and 18 are independently movable and move in opposite directions on the shaft 13 when the handle 25 is operated forwardly or rearwardly.

The head 11 is pivotally connected to the operating handle 25 by means of a link 28 and also is pivotally connected to the handle 25 by a link 29. The head 11 is provided with a reduced cylindrical portion 30.

mounted in an opening 31 in the rear end of the casing, so that the head may rotate therein.

Secured to the head 11 is a guiding tailplane 32. This tail-plane may be operated upwardly and downwardly by means of the handle 25 and may be also laterally adjustable.

By pushing the lever 25 forward the tailplane is inclined upwardl and by moving 1t toward the ri ht the tai -plane may be inclined toward the right.

Mounted in the rear body portio 9 i a aiding-plane 33 provided with stops 34.

his guiding-plane 33 is pivotally connected to the skeleton member 29 by means of a rod 35. When the skeleton member 29 is rotated by means of the operatin handle 25 the guiding-plane 22 is depresse When the plane is ad'usted for straight horizontal flight, this ui ing-plane is elevated as illustrated in Fig. 4, and acts merely as a steadyin lane. v

lngedly connected to the supportin plane 36 at each end thereof are ailerons 3% and secured to each aileron 37 is an arm 38. Mounted below the supporting-plane-36 is an operating rod 39 and secured to each end of the operatingrod 39 by a universal connection 40 are nks 41. The links 41 are pivotally secured to the arm 38. Pivotally secured to the o crating-rod 39 is an arm 42, one end of w ich is pivotally secured to the yoke 21. It will thus be seen that by the lateral movement of .the oke through the gear members 17 and 18, t e ailerons 37 may be adjusted as desired. In horizontal flight these ailerons are horizontal, and act as supporting surfaces.

When the plane 32 is merely tilted upwardly or downwardly by means of the operating handle 25, the ailerons are not adj usted but they are simultaneously adjusted when the tail-plane is first tilted and then laterally inclined, thi lateral adjustment being effected, as previously pointed out, by the rotation of the skeleton member 10 and shaft 13 by means of the operating handle 25, the rotation of the said shaft imparting a lateral movement to the yoke 21, which lateral movement will impart the desired adjustment to the ailerons 37 through the o crating rod 39.

It will be 0 served from Figs. 2, 3 and 5 that the support-in plane is arched at its center, as indicate by the numeral 44, so as to provide for about as much supporting area as that of the ailerons at the two ends of the plane.

It is also believed that this curved or arched portion will give asteadying action to the plane in horizontal flight, and will also act as a tendency to prevent side slippin fire device as shown in Figs. 4 and 5 is for a horizontal flight and in which no turns are desired to be made. In order to operate the ailerons it is necessary to tilt the guiding plane 32 sli htly, either upward or downward in or er to release one of the half gears so that the guiding plane may be laterally inclined, by which operation the ailerons are simultaneously adjusted. By this operation it will be seen, that the plane in making a turn must be either slightly rising or descending as when the plane 32 ishorizontal no lateral tiltin can be imparted to the tail 32, nor to .t e ailelQJls.

what I c aim is:

1. An aeroplane comprising a body portion and arear tubular portion, a partiallyrotating rigidskeleton member located within the tubular portion having one end pivotally mounted therein, an operating lever 'Havin fully described my invention,

guiding plane maybe vertically and laterally tilted, simultaneously, adjustable ailerons, and a connection between said ailerons tilted the said ailerons wil be simultaneously adjusted. j

2. An aeroplane having a supportin plane, an aileron pivotally secured to eac end thereof, a guiding plane capable of being upwardlyvand downwardly and laterally inclined, an operating lever, a connection between the operating lever and guiding plane whereby the guiding plane may be inclined upwardly and downwardly without ad'usting the ailerons, and the ailerons may e adjusted simultaneously with the lateral inclination of the guiding plane.

3. An aeroplane having a supportin plane provided with an upwardly arche surface in .its center, an aileron pivotally secured to each end thereof, a uiding plane capable of being upwardly and downwardly and laterally mclined, an operating lever, a connection between the operating lever and guiding plane whereby the guiding plane may be inclined upwardly and downwardly without adjusting the ailerons, and the ailerons may be adjusted simultaneously with the lateral inclination of the guiding plane. r

4:. An aeroplane having a supporting plane and a rear tubular body portion, a member rotatably mounted in said rear tubular portion, a guiding plane operable by said rotating member, a guiding plane capable of bein vertically and laterally inclined mounte in therear end of said tubular portion, a shaft carried by the rotating member located in said tubular portion, an aileron secured to each end of the su porting plane, a flexible shaft mounted -be ow said supporting plane and connected by the forward end o sa d Mat a .mem-' .whereby when the guiding lane is laterally her, a split gear wheel nonrotatably mounted operating handle carried by the rotating on said shaft, a yoke mounted on said split member located in the rear tubular porgear wheel, an aileron pivotally secured to tion for adjusting-the guiding plane and 10 each end of the supporting plane, a flexible the ailerons.

shaft secured below said supporting plane In testimony whereof, I have signed my and connected to said ailerons, a link conname to this specification.

nection between said shaft and yoke, an GEORGE ORTGIER.

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