US1238031A - Aeronautical apparatus. - Google Patents

Description

L. LEWKOWICZ.

AERONAUTICAL APPARATUS.

APPLICATION FILED MAR. 28. I912.

Patented Aug. 21, 1917.

4 SHEETSSHEET 1- iq /J/ L. LEWKOWICZ AERONAUTICAL APPARATUS.

APPLICATION FILED MAR. 28. I912.

Patented Aug. 21, 1917.

4 SHEETS-SHEET 2.

L. LEWKOWICZ.

AERONAUTICAL APPARATUS.

APPLICATION FILED MAR. 28. Ian.

1 m38m3 1 Patented Aug. 21, 1917.

4 SHEETS-SHEET 4. MA 7 [/50 z 4% J7 fi' w J 'I i r N 1 .i LEWKOWICZ, OF NEW YORK, N. Y.

AIIEJRONATUTIGAL APPARATUS.

Specification of Letters Patent. Patented Aug. 21,1911

Application fl1ed March 28, 1912. Serial No. 6@6,933.

being had therein to the accompanying.

drawing.

My invention relates to improvements in aeronautical apparatus and has particular reference to aeroplanes. It is a well known fact that with an increased angle of incidence in the curved lifting surface of an aeroplane a greater lifting efiect is produced at a given speed of forward movement and one of the objects of my invention is to apply this principle in such a manner that the increased curvature and angle of incidence may be employed for climbing or for rising with a load, and for coming down, one of my obj-cots being to reduce this angle of incidence and curvature after the proper altitude has been attained in order to secure an increased forward speed, thus compensating for the reduced angle of incidence and smaller curvature while in horizontal flight. In carrying out this principle I may subdivide my winged surfaces into several sections adapted to swing upon transverse axes or I may swing the lateral portion or portions of my lifting surface or surfaces upon transverse axls or axes. Another object of my invention is to enable the operator to increase the curvature and angle of incidence tosuch an extent that a portion of the lifting surface 7 mg 'machm actually serves as a braking mechanism thus serving to reduce the speed of descent, and forthis purpose I prefer to connect the rear hinged portion of my lifting surface to the horizontal tail surface in, such a manner that when the said tail surface is tilted at an abrupt angle for a sharp descent, said rear portion of said lifting surface automatically swings downwardly to introduce a braking efi'ect upon the rapidly descend- Another object of my invention is to construct the by of the monoplane type of aeroplane triangular in cross section with the flat side downward thus g it possible to present a minimum lateral surface'to drift.

In carry out these objects I employ various forms of devices illustrated to advantage in the. accompanying drawings in which Figure 1 is a plan looking downwardly upon a monoplane showing an application of part of my invention. Fig. 2 is a side elevation lookingupwardly at Fig. 1. Fig. 3 is a plan view of the lifting surfaces of another form of my invention. Fig. 4 is a side elevation looln'ng upwardly at Fig. 3. Fig. 5 is a perspective view looking downwardly at another modification of my invention illustrating transversely pivoted lifting surfaces and the triangular body portion. Fig. 6 is a cross section of part of the body portion. Fig. 7 is a side elevation of a biplane type. of aeroplane illustrating an application of my invention. Fig. 8 is a plan view looking downwardly upon the front part of a monoplaneillustrating the lifting surfaces divided in several units upon horizontal axes. Fig. 9 is a side elevation looking upwardly at Fig. 8. Fig. 10 is a similar view to Fig. 8 except that each wing is divided in two sections. Fig. 11 is an enlarged cross sectional view of one of the wings illustrating the method of overlapping the sections. Figs. 12, 13, 14: and 15 illustrate various methods of control which may be employed for the machines illustrated in Figs. 1, 2, 8, and 9, and Figs. 16 and 17 illustrate variousmethods of control. which may be employed for the machines illustrated in Figs. 3, 4 and 10.

Referring now more particularly to Figs. 1 and 2, it will be observed that the main supporting surface 20 is provided with a hinged lateral portion on either side indicated by the reference characters 21' and 22. In Fig. 2 it will" be observed that the hinged portion in dotted outline as indicated by the reference character 23 shows the position of the same when it has been depressed for the purpose of increasing the angle of incidence and for obtaining an increased curvature in order to rise with a load or for the purpose of climbing. When the proper altitude has been reached and forward speed is desired,

hinged portion of the supporting surface is """"automatically thrown to its lowest position as indicated by the reference character 26 thus serving to brake the descent of the ma chine. 27 indicates the pilot wheel of the machine in front of the seat 28 of the operator. The operation of this pilot wheel is more particularly ascertained by reference to Figs. 12 and 13 to be hereinafter more fully described.

In Figs. 3 and 4 a supporting surface similar to that shown in Figs. land 2 is illustrated but it will be observed that the rear hinged portions of the supporting surfaces are four in number as indicated by the reference characters 29, 30, 31 and 32. With this arrangement it will be readily understood that tlie surfaces 29 to 32 inclusive may be operated simultaneously thus serving to accomplish the same results as the machine illustrated in Figs. 1 and 2 orsaid surfaces may be operated independently as followsi By allowing the surfaces 30 and 31 to remain in their normal position shown in full outline by the reference character 33 and by lowering either the surface 29 or 32, a lateral balancing efiect may be produced upon the machine. While this lateral balancing effect is being produced the surfaces 30 and 31 may also be depressed for introducing at the same time a change in the angle of incidence of the supporting surface or for producing abraking effect on the forward motion of the machine. In fact, the

surfaces 29 and 30 or the surfaces 31 and 32 may be depressed for the purpose of producing lateral balance. In Fig. 7 the biplane type of machine is illustrated and the ref erence characters 34 and 35 serve to indicate the hinged lateral portions of the support porting surfaces 36 and 37 are mounted upon a transverse axial bearing 38 so that either or both of said lifting surfaces may be rotated for purposes of lateral balance or for the purpose of changingthe angle of inci dence. 39 is the main part of the body portion or back .of the monoplane which is preferably covered and as will be observed by reference to Fig. 6, is triangular in cross section with the apex at the top. By this arrangement the height or depth of the back is reduced thus minimizing the tendency to lateral drift of the machine.

Referring now to -Figs. 8 and 9, the supporting surfaces it will be observed are di- .Yided in three sections on each side. The sections 40 to 42 inclusive, comprising the ,11'15ght }w ng of Fig. 8 and the fsections 43 to me usivecompiising the le wing of the machine illustrated in 8 may be used 1,2sa,o31

independently. It will also be observed that sections 42 and 45 may be used as ailerons or for braking purposes. position and operation of these sections is shown to advantage. Here it will be seen that when closed they interlock or fitsnugly forming a continuous surface with the outer frame 46, whereas when open it will be observed that an increase of lifting surface is brought into action. In addition to this each section serves to introduce a separate and increased angle of incidence, thus in every respect tending to increase the lift of the machine at a given speed. From this it will be observed that it is possible to rise with considerable load and after attaining In Fig. 11 thethe desired altitude to close the sections two sets of sections are employed for each u wing so that it is possible to operate the outer sections without disturbingthe inner ones or to operate the inner ones without disturbing the outer ones. It will of course also be understood that the sections on one side of the machine may be operated without operating the sections on the other side of the machine, thus also making it possible to maintain proper lateral balance of the machine. a 7

Referring to Fig. 12, we have in vertical elevation a view of one of the hand control devices, Fig. 13 being a view from right to left of the same, and Fig. 14 a plan view looking downwardly at Fig. 12, Fig. 15 being a detail of the lower portion of Fig. 12. This device is adapted to be used more particularly upon the machines illustrated in Figs. 1, 2, 8 and 9. By throwing the lever I 50 leftwardly looking at. Fig. 12 it will be observed that the cross bar 51 carried by "said lever also moves leftwardly thereby In Fig. 5 it will be observed that the supdrawing up on the two cables 52 and 53 which are in turn connected to the lateral hinged portions 21 and 22 in Figs. 1 and 2 and to the sections 40 to 42 and 43 'to 45 in Figs. 8 and 9, said sections being pivotally connected by the bars such as 54. When the 7 pilot wheel 27 is thrown leftwardly looking at Fig. 12 upon the universal joint 55, the cross bar 56 secured to the standard 57 1s thrown out of the horizontal andthe cables 58 and 59 connected thereto are accordinglyshifted. This action increases the move- .ment of the cables 52 and 53 as the lever 50 it will be understood is carried forward with the wheel 27. At the same time the cables 58 and 59 connected to the tail horizontal surface 24 cause the latter to shift.

by the reference naespar is thrown right or leftwardly, one ofthe cables 52 or 53 connected to the lateral hinged surfaces at opposite sides of the ma chine, are operated accordingly, the result being that the lateral hinged surface on one side of the machine is depressed according to the side the wheel 27 is thrown to, thus serving the function of an aileron for laterally balancing the craft as a whole. lhe machine is of course balanced when the standard 57 is perpendicular.

Referring now to Figs. 16 and 1?, the hand control device here illustrated is adapted for use upon the machines illustrated in Figs. 3, L and 10. This device includes practically all of the elements disclosed in Figs. 12 to 15 inclusive and in addition thereto it will be observed the arts shown to better advantage in Fig. l are included. 60 isa collar adapted to slide upon the standard 57 and is provided with a neck 61 which projects upwardly beneath the button 62 so that upon depressing the button 62 which is normally projected by the spring 63, the collar 60 slides down the standard 57 until the opening 64: engages the lever 65. 66 is a similar collar adapted to engage the lever 67, and is also provided with a spring retained button such f as 62 for causing said collar 66 to engage said lever 67. From this it will be seen that when the hand wheel 27 is thrown rightwardly or leftwardly either the lever 67 on 65, or both, may be engaged and shift later- Of course it will be understood that various modifications may be made without departing from the spirit of the invention as set forth in the claim.

I claim:

An aeroplane comprising a body a laterally extending supporting surface having on opposite sides rear extension portions hinged transversely and a tail surface pivoted to the rear body portion, a controlling device movable longitudinally for operating the hinged portions in the same direction to retard the advance and simultaneously inclining the tail surface upwardly to elevate the tail of the body, said controlling device including means movable laterally whereby either one of the hinged extensions can be operated and independently of the tail surface, and also including means for moving both extension portions together without afiecting the tail surface.

In testimony whereof l afix my signature in presence of two witnesses.

LlS LEOWICZ. Witnesses: LOUISE Entrants.

THoMAs A.

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