US1381611A - Aeroplane - Google Patents

Description

J. ZURUK-ZURINSKY.

AEROPLANE.

APPLICATION FILED FEB-19.1920.

1,381,611 PatentedJune 14, 1921.

3SHEETS-SHEET 1.

J. ZURUK-ZURINSKY.

AEROPLANE.

APPLICATION FILED FEB. 19, 1920.

1,381,61 1 Patented June 14, 1921.

3 SHEETSSHEE'I 2.

WWNEN' NvEm-mR TfiI/ww l J. ZURUK-ZURINSKY.

AEROPLANE.

APPLICATION FILED FEB-19,1920.

3 SHEETS-SHEET 3.

INVENTOR @WZM WITNEss Patented June 14, 1921.

UNITED STATES PATENT OFFICE.

JOHN ZURUK-ZU'RINSKY, F MCKEESPORT, PENNSYLVANIA.

AEROIPLANE.

Specification of Letters Patent.

Patented June 14, 1921.

Application filed February 19, 1920. Serial No. 359,895.

, is a specification.

This invention relates to new and useful improvements in aeroplanes, particularly of the biplane type, and the object thereof is to provide in an aerial vessel of the type stated, in the manner as hereinafter set forth, stabilizing means to prevent dangerous tipping, swerving, and overturning of the vessel, and to reestablish its balance and maintain its equilibrium, even when disturbed, during the operation thereof, by untoward wind, air, and weather conditions,-

under such conditions providing for the efiicienttravel of the vessel and reducing to a minimum the liability of accident.- to the aviator.

Further objects of the invention are to" provide an aerial vessel of the character described which is comparatively simple in its construction and arrangement, strong, durable and efficient in its use, and inexpensive to manufacture.

To the accomplishment of these and such other objects as may hereinafter appear, the invention consists of the novel construction, combination and arrangement of parts herein specifically described and illustrated in the accompanying. drawings wherein is shown an embodiment of the invention, but it is to be understood that the device shown is merely illustrative and that a various changes in the form, proportion and minor details of construction may be resorted to, Without departing from the principle or sacrificing any of the advantages of the invention, which come within the scope of the claims hereunto appended.

In the drawings forming a portion of this specification and wherein like numerals ofreference designate corresponding parts throughout the several views:

Figure 1 is a side elevation of the biplane in accordance with this invention.

Figs. 2 and 2 are top plan views of respective portions thereof.

Fig. 3 is a front elevation of the aeroplane.

Referring to the drawings in detail 1 indicates the tonneau or main body 1 of the aeroplane, which may be of any suitable construction or form, and comprises the power plant 2, and compartments 3 and 4 for pilot and passenger, respectively. A tractor propeller 5 operates at the forward end of the main body 1 and the products of combustion from the engine are exhausted through the rearwardly extending pipe 6, which is positioned well toward the top of the main body 1. 3

An upper plane 7 and a lower plane 8 are rigidly secured together in spaced relation with respect to each other by the central. inverted V-shaped stanchions 9, the intermediate pairs of stanchions 10 and 11, respectively, and by the end mast stanchions 12 and 13, which are arranged between the planes 7 and 8, near the ends thereof, and each of which is disposed forwardly with respect to the longitudinal center of the planes. The stanchions 9,10 and 11 are suitably braced by the gu'y wires 14, and the stanchions 12, 13 are braced by the guy wires 14 and 14'.

The lower plane 8 is embodied in the main body 1, which latter is rigidly secured in the plane structure by being fixedly attached to the stanchions 9.

Each rear corner of the upper plane 7 is cut away, as at 15. so that the edge thereof will extend transversely, longitudinally and forwardly on an inclination, with respect to the plane 7 The transverse portion of the edge merges into the longitudinal portion and the latter merges into the inclined portion, the latter terminates at the end of the plane 7 Arranged within the cut-away portion 15 is an auxiliary wing 16, hingedly connected. as at 17, to the longitudinal part of the edge of the cut-away portion 15. Each of the wings 16 consists of a rectangular body of greater length than the length of the cut-away portion 1'5 and projects beyond the end of the plane 7, and at the outer part of the rectangular body of the wing 16, the said body is formed with a triangular extension whichopposes the inclined part of the edge of the cut-away portion 15.

Each of the auxiliary wings 16 is operated by a pair of flexible members 19 and 20, both attached to the lower face of the wing, the former near the rear end thereof and the latter at the front end of the extension 18, thereby permitting the operation of the wing on the hinged connection with the upper plane? when the flexible members 19 and 20 are manipulated by the pilot. The flexible members 19 and 20 extend vertically from. each wing to the lower plane 8, and through the latter to respective levers 21 and 22, operatively mounted on the shaft 23 in the pilots compartment 4. The operation of the. wings 16 is adapted to prevent overturning sidewiseand to assist in the steering of'the biplane. As but a single end stanchionis employed, and which is disposed forwardl'y with respect to the longitudinal center'of, the plane 7, provision is made-whereby a wide rectangular body of the wing 16 can be employed, under such conditions obtaining a greater working surface for the wing, than if the ends of the planes 7 and -8"we;re braced and supported by two end stanchions', as if these two latter were employed the body of the wing 16 would be compelled to be narrow.

As clearly shown in Fig. 2, of the ,drawings, the lower plane 8 inclines rearwardly from its center toward each end thereof and projects beyond the rear edge of the upper plane 7. This construction of the lower plane 8 is primarily provided to augment the efiiciency of the operation of the wings 16 on the upper plane-7, as it permits amore direct action of the air against the said wings 16 than if the said lower plane 8 extended farther forward, without detracting from the sustaining capacity of the said plane.

The fuselage 24, is provided at its rear with a supporting bracket 24, which is secured centrally thereof to the fuselage 24, has a rear straight edge, and each side edge formed with a rearwardly and outwardly inclined portion and a rearwardly and inwardly inclined portion. The outwardly inclined portion of the side edge of the bracket 24' is of materially greater length than the inwardly inclined portion of said edge. The bracket 24 is provided as a carrier for the rudder 25. The latter is horizontally disposed and is formed at its front with a cutaway portion into which extends the bracket 24, and the rudder 25 is hinged to the bracket 24. The rudder 25 has a pair of outwardly inclined edges which form continuations of the outwardly inclined edges of the bracket 24. The rear edge of the rudder 25, inclines forwardly and outwardly from its center toward each end. The side edges of the rudder 25 are straight. Flexible members 27 are employed for operating the rudder 25. The fuselage 24 is provided at its rear with a vertically extending supporting bracket 25 to which the vertical rear rudder 26 is hinged, the latter overlaps the bracket 25' and is operated by the flexible members 28.

The members 27 and 28 pass from their respective rudders forwardly through the inclosedportion of the fuselage 24 and connect to respective operating levers 29 and 30 which are carried by the shaft 23 in the pilots compartment '4.

The lower portion of the fuselage 24, atthe rear thereof, see Fig. 1, of the drawings, is formed with an enlarged tri-angular shaped opening or passage 32, with the framing at that part of the fuselage 24 exposed. This construction of fuselage offers less re sistance to the cross currents of air, thereby preventing lateral swerving of the aeroplane and assisting in maintaining its equilibrium while operating in untoward air, wind, and weather conditions. The inclosed lower portion 31, of the fuselage 24, provides an ideal location for the fuel tankv 33, being remotely removed from the power plant 2, thereby rendering the aerial vehicle less liable to fire in case of accident. The portion 31 of the fuselage 24, which is inclosed provides sufficient support when resting on the water, which would not be the case if such portion 31 was constructed solely of the frame work of the fuselage 24.

The lower portions of the forward inverted V-shaped central stanchion 9 form the supports 34 for the landing chassis 35. Each of the supports 34 is provided with a spring shock absorber 36 to counteract the landing impact of the aeroplane. The tail of the aeroplane is provided with the usual rearwardly extending and resiliently mounted landing leg 37 The supports 34 are rigidly braced by the rearwardly extending bracing members 38.

Any desired type of landing chassis may be employed in connection with my improved aeroplane, or same may be'provided with suitable substitution to permit of its use for starting or landing on water.

lVhat I claim is:

1. An aeroplane comprising a fuselage having the lower partof the rear thereof formed with an enlarged triangular shaped opening.

2. An aeroplane comprising a fuselage having the lower part of the rear thereof provided with an enlarged triangular shaped opening, and that part of the fuselage below the forward part of said opening being inclosed.

3. An aeroplane comprising a fuselage having the lower part of the rear thereof pro vided with an enlarged triangular shaped opening and that part of the fuselage below the forward part of said opening being in closlgd and providing a chamber for a fuel tan 4. An aeroplane comprising a fuselage, a horizontally disposed bracket secured central thereof to the rear end of the fuselage and having its side edges each inclined rearwardly and outwardly and rearwardly and inwardly. said outwardly inclined portion of greater length than the inwardly inclined portion of the side edge, and a horizontally disposed rudder having its forward portion cut away to abut the inwardly inclined portion of the side edges of the bracket, said rudder further having inclined edges forming a continuation of the outwardly inclined edges of said bracket, and said rudder further having its rear edge inclined forwardly and outwardly from its center toward each end of said edge.

5. An aeroplane comprising an upper and a lower plane, end stanchions, each of said stanchions arranged between said planes near the ends of the latter and disposed forwardly with respect to the longitudinal center of the planes, and said upper plane having each rear corner thereof to provide an edge to extend transversely, longitudinally and at an outward and forward inclination with respect to said plane, and an auxiliary wing mounted in each cut-away portion and conforming in contour to the shape of the said cutaway portion and further hinged to the longitudinal portion of said edge.

6. An aeroplane comprising an upper plane having each rear corner thereof cut away to provide an edge having portions to extend transversely of the plane, longitudinally of the plane and at an outward and forward inclination with respect to the plane, said transverse portion merging into said longitudinal portion and the latter merging into the inclined portion, the latter terminating at the end of the plane, and an aileron mounted in and of the same contour as the cut-away portion and projecting beyond the end of the plane.

7. An aeroplane comprising an upper and a lower plane, an inverted V-shaped stanchion interposed between and secured to said planes, pairs of intermediate vertically disposed stanchions interposed between and secured to said planes, and an end stanchion interposed between and secured to the planes near the outer ends thereof, each of said end stanchions arranged forwardly with respect to the longitudinal center of the planes.

In testimony whereof I afiix my signature.

JOHN ZURUK-ZURIN SKY.

Images