US1150970A - Aerohydroplane. - Google Patents

Description

.|. SCHLESINGER.

AEROHYDROPLANE.

APPLICATION FILED sEPT.19.1914

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AEROHYDROPLANEx APPLICATION man SEPT. 19. 1914.

Patented Aug. 24, 1915.

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AEROHYDROPLANE.

APPLICATION FILED SEP.I9.1914.

Patented Aug. 24, 1915.

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AGOB SCHLESINGER, 0F LANSING, MICHIGAN.

.AEROHYDROPLANE madero.

Specification of Letters Patent.

Patented Aug. 24, 1915.

Application filed September 19, 1914. Serial No. 862,590.

To all wh-0m t ma concern Be it known t at I, JACOB SCHLESINGER, subject of the Emperor of Austria-Hungary, residing at Lansing, in the county of Ingham and State of Michigan, have invented certain new and useful Improvements in Aerohydroplanes, of which the following is a specification, reference being had to the accompanying drawings.

My invention relates to certain new and useful improvements in aero-hydroplanes and particularly that type designed to be used for war pur oses.

One ofthe objects of my invention is to provide a flying machine of the character stated with main planes and ailerons so connected to one of the main planes that they shall offer a minimum of atmospheric resistance and at the same time shall continue the carrying surface of the main plane to which they are attached.

A further object is to rovide a biplane with a rearwardly exten ing medially disposed tail structure upon which the usual rudders are mounted and provide the lower plane of the biplane with ailerons as previously stated and provide lateral rudders disposed on each side of the tail and extending longitudinally thereof, these rudders being pivoted .for vertical movement and also creating a minimum of atmospheric resistance and assisting in carrying the machine.

Another important object is to so construct and arrange the tail wing rudders as to reduce the atmospheric pressure and increase the carrying surface.

Still another important object is to so construct the boat that it shall constitute a receptacle for the principal parts of the mechanism and 'offer minimum resistance to the air and serve as a gravity pendulum.

With these and other objects View, my invention consists in the ,details of construction, arrangement and combination of the many parts and devices as will be hereafter Afully described and as represented in the drawings. .l

In order that those skilled in the art to which my invention appertains may fully understand my invention, I will now describe thev same referring the accompany-l ing drawings in which- Figure 1 is a diaggxamlnatic top or plain view. Fig. 2 is a side view showing the apparatus resting upon a body of water and showing the tail slightly elevated. Fig. 3 1s a similar view showing the apparatus restin upon the land with the boat held out o contact therewith. Fig. 4 is a front elevation on enlarged scale. Fig. 5 is an enlarged side elevation showing the machine in the air and some of the details more clearly. Fig. 6 is a fragmentary, enlarged top view with the top plane shown in dotted lines. Fig. 7 is a longitudinal, vertical section through the boat, the upper and rear parts of the machine being omitted. Fig. 8 is a section on line a-a, of Fig. 5, looking in the direction of the arrow. Fig. 9 is an enlarged fragmentary elevation showing the tail rudders. Fig. 10 is a detail side elevation of the ailerons or rudders on the rear edge of lower plane. Fig. 11 is a fragmentary plan of the same. Fig. 12 is a fragmentary perspective view of the means for attaching the stabilizing planes to the rear tail support. Fig. 12B-sectional view of bomb magazine. Fig. l-section on line b-b, of Fig. 13 in direction of arrow, showing in` dotted lines the hand valve, open, and Fig. 15 isa section on the line c--c, of Fig; 7, looking in the direction of the arrow.

Similar reference numerals indicate like parts in the several figures of the drawings.

1- represents a boat occupying a middle position relative to the planes 2 and 3, the frames and braces of which may be of the ordinary or any preferred construction and 4 is the propeller. The uppermost plane 2 is disposed transverse to the line of Hight and it is continuous from end to end while the lowermost plane consists of two sections v disposed on each side of the boat 1. Both of these planes are rearwardly and downwardly curved as illustrated most clearly in Figs. 2 and 3.

5 are the forward and 6 the rear traction wheels, the former journaled in hangers 7, mounted upon a shaft 8, which extends through the boat and is mounted in any suitable manner. This shaft has a radially extending arm which is connected by a rod 9, to a lever handle pivoted to a sector rack 11, as clearly shown, so that when the apparatus is being propelled upon the water, the wheels 5 may be raised and held in the position shown above the water and thus offer no resistance.

The boat 1, as clearly appears is located centrally with reference to the wings with the bow slightly in advance and the stern slightly short of the wings, so that in this relationland with all of the workingmechanism within the boat, the center of gravity will be disposed at the forward end of the machine.

I have learned from experience that by constructing the frame in this manner and disposing the planes at the forward end of the machine and disposing the boat between the sections of the lower plane and so disposing the weight that the center of lgravity is at the forward end of the machine, less resistance will be offered both to air and water. The boat is sharp at the bow and broad and flat at the stern so as to secure a quick start from the water. i

The tail frame 12, extends rearward from the stern of the boat and to this tail frame is secured the rear wheel 6, and likewise the horizontal tail rudder 13, and the vertical tail rudder 14, which are by suitable cords 15, traveling around the pulleys 16, and leading to the aviators position readily manipulated to guide the flight of the ship. Mounted on each side of the tail frame 12 and medially disposed with relation thereto are the tail wing rudders 21 and 22. These taper from their rear ends to their forward ends and are hingedly mounted so that they may be turned up or down as desired, or held in a median position. Suitable cords 22a are secured to these tail wing rudders whereby they may be manipulated. By providing independently adjustable tail wing rudders in connection with independently adjustable side wing rudders, the lateral rudders may be adjusted in correspondence with@ each other so that the tendency of the machine to vtip may be counteracted. Furthermore,

these tail wing rudders are so disposed as to guide the air beneath the tail rudder 13 so that when the rudder 13 is lowered at an angle to a horizontal plane, the rudder will exert a maximum of force. In landing also these tail wing rudders resist the tendency of the tail end of the machine to turn, and furthermore as these tail wing rudders taper toward their forward ends with approximately that of the tail wing frame, they will, when they are turned in opposite directions, act in the manner of a screw, resisting any tendencv of one side of the machine to tip. Ifthe rear rudders should be broken or not in working order, the tail wing rudders may be sistance offered by such rudders, but on the used or will to some extent perform the function of these rear rudders.

Referring now to Fig. 6, particular attention is called to the four side, front rudders, `or ailerons 17, 18, 19, and 20, which as will be' seen are not located between the two planes, or carrying surfaces, but are attached directly to the lower plane; such arrangement not only eliminating the ordinary re- 7 5 contrary they coperate with the plane to increase the carrying surface, and through which with other ailerons Iam enabled to attain a high degree of stability. Upon a. depression of oneV of the ailerons 17, 18, 19 or 20, that side of the machine will be lifted and the speed will be reduced. This is counteracted to some extent by the rudders at the end of the tail frame, but in order to prevent a sidewise shifting of the relatively long tail, particularly in landing, these longitudinally extending lateral rudders are provided which may be turned into a vertical or nearly vertical position at this time so as to present a surface resisting lateral slip of the aeroplane. Furthermore, these rudders lend stability to the machine and particularly to the tail. If there be an increase of wind pressure on the left side of the machine, the left tail wing. rudder 22 is bent downward while the one on the right hand side 21 is lifted. The wind pressure is thus balanced and the machine is prevented from tippingover. If on theV contrary the wind pressure be increased on the right hand side,

the rudders are moved in a contrary position. In fair weather the tail wing rudders are so shaped that they extend downward and upward at an angle of about 45, this being the most eective angle for resisting ,the downward movement of the tail. The tail wing rudders 21 and 22 also reduce the atmospheric pressure against the rear rudder and increase the carrying surface. I

have found from experience and observation 110.

that not only are the advantages recited obtained, but. that in the event of a fall, lmuch more safety is offered to the aviator;

Referring now more particularly to Figs. 5, 6, and 7, it will be seen that lthe two forward wheels 5 can be readily raised to the position shown in Figs. 5 and 7, through the medium of the rods 9 connected with the vibrative wheel carrying frames and the operating levers 10 before referred to, and when 120 so raised and the boat 1- is resting upon the water as shown in Figs. 2 and 5, the forward wheels offer no draggingresistance in the water, and that the weight carried by the boat elevates the tail to such a degree that only the rear wheel 6- contacts with tlie water surface, so that the only resistance to the water is offered by the boat.

As my improved aero-hydroplane is especially designed for war purposes, I will now recite the features of construction and arrangement relating thereto.

Referring to Figs'. 13and 7 a bomb magazine in the form a tube 23 is secured upon suitable supports 24, within the boat and is preferably longitudinally Ldisposed as shown in Fig. 7 This magazine is provided at the forward end with a reciprocating piston rod 25, having a head 26, and is operated by a heavy coil spring 27, constantly under tension which cai be regulated by any suitable means. The open end of the magazine is closed by a' circular plate 28, pivoted at 29, and operated by a handle 30. When inthe position shown, a series of bombs 31, are obviously held against escape, but when in the position shown in dotted lines at Fig. 14, a bomb may be projected by the spring piston. This plate which may be designated as a valve, is free to be vibrated through a suitable semi-circular slot 32, in the side of the tube'f23. The bomb casing I propose making of aluminum and in placing the bombs in the reservoir rubber or other suitably resilient blocks 33 are placed axially between the bombs. Two of these magazines may be located in the boat, one at each -side and with the exit end curved and extending slightly beyond the side of the boat.

As the boat has a suitable carrying capacity, a seat is provided for the aviator or pilot behind, but adjacent to the several levers, by which he is enabled to operate all of the rudders, heretofore referred to, and also the mechanism by which the engine is controlled. The engine as shown diagrammatically at 34, in Fig. 4, is located and secured in any suitable manner about centrally between the planes 2 and 3, and the gas `for operating the engine is delivered through pipes 35, leading from a -tank or tanks 36.

VBack of the gas tank is arranged a water tank 37. In rear of the pilots position is a small space 38 designed to accommodate a Marconi system, and adjacent thereto is a cabin 39, which may be utilized for any required service.

40 is an apartment designed for commissary stores. Back of this apartment is located asmall rapid lire gun 41, mounted upon a suitable support 42, and 43 is a magazine for the ammunition. Below this magazine may be stored pontoons 44.

In. front of the pilot or aviator is a glass wind shield 45, which not only protects him from the air currents but enables him to clearly make all necessary observations.

Thil'e in order to avoid confusion of reference numerals I have not particularly described all of the devices by which the pilot may be enabled to promptly operate all of the` various rudders, and likewise, while I have shown many details vof construction which I have not specifically described, it

will be understood that I have done so because I desire it to be understood that these and many other mere details of construction may be varied without departing from the spirit of my invention which resides in the generic features shown and described and which constitute the subject matter of the claims.

A hydro-aeroplane constructed in the manner heretofore described, is capable of descending with much less danger than is the case with aeroplanes constructed in the ordinary manner. It is also obvious that in making a landing, the shock of contact with the ground will be broken first by the wheels 5 and 6, then by the boat,'and finally by the planes and that it is possible with my construction to depress the rear end of the device in making a landing so that the rear wheel will iirst contact and the shock will be thereby transmitted to the tail structure 22, thus cushioning the contact of the boat or forward portion of the structure with the ground.

Having Vdescribed the construction, arrangement and advantages of my. improved aero-hydroplane, what I claim as new and desire to secure by Letters Patent is 1. In a flying machine, upper and lower transversely extending main planes, the lower plane being in two sections, means for supporting the aviator between the two lower planes, ailerons extending entirel across and pivoted to the rear edges of eac of the two sections of the lower plane, means for angular adjusting the ailerons, a tail frame extending rearward from the main planes below the level of the lower main planes, vertical and horizontal rudders at' tached to the end of the tail frame, and 105 laterally disposed rudders hingedly mounted upon and extending entirely along the sides of the tail frame, said rudders ing 4"relatively wide at their rear ends and tapering to the width of the tail frame at their forward ends, said rudders being independently angularly adjustable.

2. In a flying machine, upper andlower transversely extending main planes, said planesfbeing rearwardly and downwardly curved and rigidly connected to each other, the lower main plane being formed'in two laterally disposed sections, a buoyant body disposed between said sections and Voperatively connected thereto, a pairo ailerons hinged to thev rear edge of each section of ythe lower main plane, means for angularly adjusting said ailerons, a skeletonic rearwardly extending tail frame extending from said body` and having 4a width approxi 125 mately equal thereto, vertically and horizontally disposed. rudders at the rear end of the tail frame and laterally disposed rudders extending entirely along the tail frameA and hingedly connected at their inner edges l" thereto for angular adjustment, said lateral rudders at their rear ends projecting laterally a distance equal to the lateral projection of the hinged rudders and tapering toward their forward ends, the total Width of said lateral rudders at their forward ends being approximately equal to that of the skeletonic tail frame, said lateral rudders

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