US1350948A - Detachable stabilizing-fin for flying-machines - Google Patents

Description

M STUPAR.

DETACHABLE STABILIZING FIN FOR FLYING MACHINES. APPLICATION FILED 02c. I0, m9.

1,350,948. Y Patented Aug. 24,1920.

2 SHEETSSHEET I.

A TTORNEV M. STUPAR.

DETACHABLE STABILIZING FIN FOR FLYING MACHINES.

APPLICATION FILED DEC 10, 1919.

1,350, 948. Patented Aug. 24, 1920.

2 SHEETS-SHEET 2.

INVENTOR 4 TTORNEV UNITED STATES PATENT OFFICE.

MAX STUPAR, OF BUFFALO, NEW YORK, ASSIGNOR T0 ABRAHAM J. ELIAS, 0F BUFFALO, NEW YORK.

Original application filed .Tune 25, 1919, Serial No. 306,613.

Specification of Letters Patent.

Patented Aug. 24, 1920.

Divided and this application filed December 10, 1919. Serial No. 343,751.

To all whom it may concern:

Be it known that I, MAX STUPAR, a citizen of the United States, residing at Buffalo, in the county of Erie and State of New York, have invented certain new and useful Improvements in Detachable Stabilizing- F ins for Flying-Machines, of which the following is a specification.

My present invention relates generally to heavier-than-air flying machines, and more particularly to hydroaeroplanes of the type described and claimed in my copending application, Serial Number 306,613, which was filed June 25, 1919, and of which the present application is a division.

The object of my present invention is the provision of a readily attachable and detachable stabilizing fin which will be rigidly supported in effective position and which, when detached, may be packed in minimum storage space.

In the accompanying drawings, illustrating my present invention and forming a part of this specification,

Figure 1 is a side elevation of a hydroaeroplane provided with my present invention,

Fig. 2 is a-rear elevation of a portion of the tail structure,

Fig. 3 is a partial side elevation of the rear portion of the stabilizing fin and the tail post,

Fig. 4 is and Fig. 5 is a cross section through the upper portion of the fuselage adjacent to the forward end of the stabilizing fin, taken on line 55 of Fig. 1.

Referring now to these figures, and particularly to Fig. 1, I have shown a hydroaeroplane comprising a fuselage 10, tail structure generally indicated at 11, wings 12 and pontoons 13.

The stabilizing fin proposed by my present invention is seen at 14, disposed fiatwise in its operative position upon the upper rear portion of the fuselage 10, and has at each side of its forward )ortion, a depending hinged and apertureoi locking leaf 15 engageable with a laterally projecting rigid locking stud 16 at the respective side of the rear portion of the fuselage 10. The rear end of this stabilizer has at a central point a rearwardly projecting rigid stud 17 which,

a rear elevation of the tail post,

in attaching the stabilizer in place, is extended through the upwardly projecting apertured extension 18 of the tail post fitting 19 of the fuselage 10, as seen in Fig. 3.

From this latter figure and Fig. l, it will also be noted that the tail post 19 is securely fastened to the rear end of the fuselage 10 and has at its lower side portions oppositely projecting side ears 19 apertured to receive locking pins 20 detachably connecting the lower ends of the upwardly and outwardly projecting stabilizer braces 21. These braces are in the form of a pairof struts whose outer ends are connected to the lower surfaces of the rear side portions of the stabilizing fin 14L as particularly seen in Fig. 2.

Thus to disconnect and remove the stabilizing fin, it is simply necessary to release the locking pins 20 of its braces 21 and the locking pins utilized to hold the locking leaves 15 on the studs 16. Thereupon the stabilizing fin as a whole may be shifted forwardly and its rear stud withdrawn from the upper opening of the tail post 19.

In packing the fuselage of an aeroplane and the like for transportation, it isobvious considerable difficulty in crating will be avoided by removing the stabilizing fin and hence my improved fin with its ready adaptability in this direction is of striking importance, particularly as its reassembly upon nncratingmay be accomplished as quickly and with as little difiiculty as its removal.

I claim 1. A flying machine including a fuselage having a tail post provided with an upper apertured extension, a stabilizing fin having detachable connection at its forward portion with the fuselage, and a stud projecting from the central rear portion of the said fin and extending into the aperture of said tail p 2. A flying machine including a fuselage having a tail post provided with an upper extension, a stabilizing fin having means at its central rear portion detachably engaging the said tail post extension, and means detachably connecting the forward portion of the said fin to the fuselage.

3. A flying machine including a fuselage a stabilizing fin having detachable connections at the sides of its forward portion and at the center of its rear portion to said fuselage, and braces connected at their outer ends to the rear side portions of the stabilizing fin and having detachable connection at their inner ends with the fuselage.

4. A flying machine including a fuselage having upper laterally outstanding locking studs spaced from its rear end,4,a stabilizing fin having detachable connection at its rear end With the rear end of the fuselage, and

apertured hinged locking leaves carried by 10 the forward portion of said stabilizing fin arranged to depend over the said "locking studs, as described.

5. A flying machine including a fuselage and a stabilizing fin seated horizontally on the upper rear portion of the fuselage and having detachable connection at the sides of its forward and the center of its rear portion With the fuselage.

In testimony whereof I aflix my si nature.

MAX sTU'rAR.

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