US1186630A - Aeroplane. - Google Patents

Description

B. WARCHALOWSKI.

AEROPLANE.

APPLICATION FILED DEC. 13, I915.

Patented June 13, 1916.-

4 SHEETS-SHEET I.

B. WARCHALOWSKI.

I AEROPLANE.

APPLICATION FILED DEC. 13. I9l5.

4 snsnssnsir 2.

mum

-llllli.

' IIIIII Fig.2.

B. WARCHALOWSKI.

AEROPLANE.

APPLICATION FILED DEC. 13. 1-915.

1,186,630. Patented June 13, 1916.

4 SHEETS-SHEET a.

B. WABCHALOWSKI.

AEROPLANE.

APPLICATION FILED DEC. I3, 1915.

Patented June 13, 1916.

4 SHEETS-SHEET 4.

BOLESLAW WARCHALOWSKI, OF HERKIMER, NEW YORK.

AEROPLANE.

Specification of Letters Patent. Patented June 13, 1916.

Application filed December 13, 1915. Serial No. 66,55?

To all whom it may concern:

Be it known that I, BOLESLAW WARCHA- 1L0wsKI, a citizen of the United States, re-

siding at Herkimer, in the county of Herki- ,mer and State of New\.York, have invented certainnew and useful Improvements in Aeroplanes, of which the following is a specification.

' type and designed for sustaining and transferring heavy loads, the same being provided with elevating and sustaining means including an automatic balancing device.

A further object of the invention is to provide a multiple engine-driven monoplane having continuously operable propellers ac tuated by one engine at a time and provided with automatic means for automatically starting and connecting up the other engine in the event of an accidental stopping of the engine at work.

The invention'hereinafter specifically described, incorporates a novel form of monoplane framework which is especially designed for propulsion by the arrangement of propellers herein set forth, while the safety in navigating the device isinsured by the provision of two driving engines,

only one of thesame being operated at a time and having automatic means nsuring the operation'of one or the other of the engines continuously whereby the movement of the propellers will be free from interruption.

- In providing a monoplane for carrying heavy loads, it is desirable to maintain the same horizontally positioned in the air during flight and an automatically operated stabilizer is arranged upon thepresent form of frame designed therefor and whereby a return influence will be imparted to either side of the monoplane in the event of a downward tilting thereof in that direction. An efficient steering means is also required for giving the desired directions to such aeroplanes designed for heavy loads and the same is now provided in the form of a motor -driven rearwardly positioned propeller, the latter being mounted for universal movement in effecting the steering of the device in its aerial flights.

W th these general objects in View and othersthat will appear as the nature of the invention is better understood, the same consists in the novel combination and arrange-v ment of parts hereinafter more fullyv described, illustrated in the accompanying drawings, and pointed out in the appended claims.

In the drawings forming apart of this application and in which like-designating characters refer to corresponding parts throughout the several drawings :Figure 1 is a top plan view of the device. Fig. 2 is a side elevation thereof. Fig. 3 is a rear elevation of the same. Fig. 4 is a side'elevat-ion of a clutch member of the shaft of one of the driving engines. Figs. .5 and 6 are central longitudinal sectional views thereof taken upon planes perpendicular to each other. Fig. 7 is an enlarged elevational view of the automatic equilibrator provided upon the device diametrically illustrating a portion of the electric circuits. Fig. 8 is a side view thereof. Fig. 9 is a horizontal sectional view through the suspension means for the steering motor the latter being shown in elevation and the motor shaft broken away. Fig. 10 is an inner elevational view thereof with parts broken away, and Fig. 11 is an elevational view of the automatic start-- ing clutchdevice for the aeroplane engines, the same being illustrated detached and operatively positioned.

The present aeroplane comprises a main frame 10 of boat shaped formation and constructed of any desirable strong material which is light in weight. The forward'end 11 of the-said main frame '10, is bowed outwardly and forwardly similar to the prow' prow. The frame is provided with a squared f rear end 13 similar to the'stern of a boat,

while the adjacent rear portionld of the frame is slightly tapered adjacent thereto and the. frame intermediate the said prow and stern portions is of substantially uniform width throughout.

Upper and lower V-shaped side frames 15 are arranged in parallelism laterally projecting from pairs of side posts 16 of the main frame 10 and being disposed in spaced relations between the top and bottom of the main frame 10. Each pair of frames 15 is connected together by an upright post 17 po tioned adjacent the free p inted ends 18 of the frames. Parallel rearwardly extend- -ing'supporting strips 19 are carriedby the upper ones of the frames and are connected by means of a transverse strlp positioned perpendicularly to the posts 21 have their extreme end portions 25 arranged outwardly of. the strips 19. Strengthening wires 26 are connected to the str1ps,1 9

. through the wings 16 and are secured above 'theavings adjacent the tops of the frame post 24, while similar Wires 27 are connected to: thestrips 19 and extend beneath the wings 22 and are anchored adjacent the lower ends of the frame post 23. Similar sustaining planes 28 may be arranged at opposite sides of the frame 10 and in the same plane as the planes 22 forwardly thereof, thesaid planes 28 being mounted flatly upon theupper V-shaped lateral frames 15 and the adjacent ends of the strips 19. Elevating planes 29 project forwardly in'an ob lique manner from the forward edges of the said planes 22 and are secured to the frame 10 and to the strips 19, while guy wires 30 connect the forward edges of the planes 29- with the adjacent side of the upper frames 15, braces 31 being also secured beneath the elevatingplanes 29 andmounted upon the cross strips 20. v

Opposite V-shaped brackets32 project in opposite directions from the posts 16 and outwardly at thesides of the frame 10 and have propeller shafts 33 journaled therethrough lying longitudinally of the main frame 10 and spaced substantially equal distances from the upper and lower V-shaped frames 15. Operating propellers 34 are carried by the opposite ends of the shafts 33. The propellers 34 at the forward ends of the shafts 33 lie forwardly of the frames 15 and forward planes 28, while the ro- 501 pellers upon the rearends of the shafts 33 lie substantially between the planes 28 and 22 and upon a level therebeneath, as shown in Fig. 2. Beveled gears 35 are carried by the shafts 33 and are actuated for propelling the propellers 34 by means of mecha nism hereinafter described, the same positioned in the inclosure formed by the frames 15 and a portion of the main frame 10 therebetween.' There will also be hereinafter 00 fully described the equilibrator and the steering propeller with which the device is provided.

The aeroplane is mounted upon traction wheels 90 whereby the device may be pro- 06 pelled along the ground or other support 1,1se,eso

manner the aeroplane is forwardly moved in the launching operation.

The eguilz'bmtor.An equilibrator in the form of a stabilizer for maintaining the equilibrium of the aeroplane when in midair is arranged. Each of the end posts 17 of the V-frames 15 are provided with outwardly extending electric motors 36 secured thereto and having their revoluble armature shafts 37 journaled through the frame ends 18 and provided upon their opposite freeends with propellers 38 adapted to revolve in horizontal planes.

An automatic controlling switch for the stabilizing propellers 38 is arranged at any desirable point upon the aeroplane being preferably centrally positioned thereon and having a mounting board 39 here illustrated as being transversely secured substantially centrally beneath the frame 10. A swinging pendulum 40 is mounted upon the board 39 by means of a pivot 41 and is provided with blades 42 of a knife switch pivotedas at points 43 to the board 39 and connected by pivotal links 44 with the outer ends of a cross-piece or head 45 carried by the pendulum 41. Each blade 42 is adapted to close the circuit between the spring terminals 46 of the'opposite motors and spring terminals 47 of a battery 48, it-being understood that the spring terminals 46 and 47 are the usual form employed in a knife switch, the blades 42 being received within the said terminals.

The battery 48 is shown diagrammatically in Fig. 7 of the drawing and may be of any desired form such as a storage battery and positioned at any convenient point upon the aeroplane and is connected by means of a circuit wire 50 with each of the oppositely arranged motors 36, the wires for the stabilizer being concealed in the framework of the device. Awire 51 connects the battery 48 with each of the terminals 47, while the terminals 46 for each switch are connected circuit wires52 and 53 respectively.

The pendulum 40 is provided with an adjustable weight 54 and is adapted to maintain'a vertical position upon any side shifting or tilting of the aeroplane frame In the event of a tipping of the aeroplane to either side, this normally vertical position of the pendulum 40' allows the knife-blade 42 of the switch at the side of the aeroplane which is depressed to close the circuit between the terminals 46 and 47 and thus allows the battery 48 to set in motion the motor 36 at that side of the device, thus operating its elevating propellers 38. The propellers 38 at this side of the aeroplane being in operation while those at the opposite side thereof are at rest, returns the frames 15 to a substantially horizontal position 1,1ee',eso

and 47, thus breaking the motor circuit and stopping the propellers 38. The complete circuit for each of the motors 36 will be apparent from this description thereof as well as the automatic closing of such switches upon a tilting of theaeroplane and it will be seen that thereby the aeroplane is automatically maintained in equilibrium and substantially horizontal in the air.

Steering mechanism.A steering means is provided for the aeroplane in the form of a propeller 55 mounted for universal movement within the squared stern 13 of the main frame 10, the same having a rectangular mounting frame 56 therein. A rectangular frame57 is pivoted Within the frame 56 upon horizontally arranged trunnions 58 and is provided with a central circular opening 59 within which an electric motor 60 is swingingly mounted upon vertical trunnions 61. A triangular frame 62 is secured to the outer face of the motor 60 and has opposite side braces 63, while the motor shaft 64 is journaled centrally through the squared outer end 65 of the frame 62. Flexible steering members 66 are attached adjacent the top and bottom of the frame 57 and have their forward ends connected to a pivoted steeringlever 67 whereby the frame 57 as well as the motor 60 and propeller 55 are vertically adjusted for steering the aeroplane upwardly and downwardly. Similar flexible connectors 68 are attached to the opposite sides of the motor 60 and'havetheir forward ends connected to a cross piece 69 carried by a steering post 70 which is journaled as at 71 in the main frame 10 and adjacent the afore-mentioned steering lever 67. By slightly turning the post 70, the motor 60 and propeller 55 are swung from side to side and thereby, the course of direction of the aeroplane is accurately regulated. With this manner of steering device, the aeroplane may be directed in its course by means of the steering post 70 and steering lever 67., The steering propeller55 may i be continuously operated by the motor 60 and the latter actuated by the battery 48 or a separate battery if desired, the connections for the motor 60 being not herein illustrated, although the motor 60 might. also be supplied with electric current from a generator (not shown) connected up with the engines 72 and 73.

The propelling means-The operative propellers 34 heretofore described are op erated for moving the aeroplane by means' of two explosive engines 72 and 73 oppositely' positioned longitudinally of the main frame 10 and being provided respectively with driving shafts 74 and 75. The pinions 35 of the propeller shafts 33 are in constant mesh with pinions 7 6 upon a transverse pinion 78 in constant mesh with 1 their opposite outer'ends.

. thereon by shaft 77 having an inwardly positioned oppositely arranged pinions 82, which latter pinions are upon the free ends of stub shafts 83 in longitudinal aline'ment with each other and provided with cylindrical clutch heads 84 having. clutch engaging teeth 85 at The engine sha fts 74'and are provided with clutch heads 86 and 87 respectively slidably maintained means ofsuitable splines 88 whereby the clutch heads 86 and 87 are rotarily propelled by the said engine shafts upon which they aremounted. The clutch heads 86 and 87 are provided with an annular arrangement of engaging teeth 89 adapted to cotiperate with the teeth of the clutch heads 84 forrevolving the .said clutch heads 84 and operating the propellers 34 when either clutch is closed during the forward movement of the respective shaft clutch heads.

An important feature of the present invention is the provision of'an automatic means for disengaging the clutch of either of the engines 72 or 73 upon a stopping of the same and to automatically start the engine in reserve and operatively close the clutch for continuing the movements of the propellers 34. This automatic 'mechanism is best illustrated in Fig. 11 of-the draw ings being omitted from the remaining figures thereof, while the journaling brackets of the several shafts for the operating means socket 93 of each of the saidengine shaft" carried heads and bears against the rods 91 for normally resiliently holding the said and 87 are slidably heads projecting outwardly of the ends ofthe said shafts as best illustrated in Figs. 5 and 6 of the drawings P The two engines 72 and 73 are positioned respectively forwardly and rearwardly of the propeller shaft 77 or if desired may be arranged laterally of the main frame 10 and the clutching members for the said engines are constructed so that when one engine. accidentally stops, its clutch will automatically open, but at the same time the other engine will bestarted to operate and its clutch will be automatically thrown in. This operation will be briefly described with special reference. to Fig. 11 of the drawings. When either engine such as'the engine 73 stops in its operation of driving the propellers 34, the continued movement of the said propellers due to momentum will slightly turn the shaft 83 of the clutch head 84 which is in clutching engagement with the clutch head 87 of the said engine. is movement will force the teeth 85 and 89 of the clutch heads. 84 and 87 to disengage, thus sliding the head 87 longitudinally upon the shaft 75. -A rock arm 99 is centrallypivoted as at 100 and is connected by a pivot link'101 with a catch 94 pivotally named lever connections, thus releasing the mounted as at 95 and also by a link 102 with a similarly oppositely positioned catch 103 positioned adjacent the opposite clutch head 87. Balancing springs 104 are provided for each of the catches 94 and 103.

The longitudinal movement of the head 87 forces the conical end face 109 against a projecting finger 96 of the catch 103,'which elevates the said finger 96 and swings the catch 103 upon its pivot 95, which movement shifts the opposite catch 94 in a corresponding manner by means of the above head 86. Thesaid pivoted catch 103 will engage the finger 96 thereof within a helical groove 97 of the clutch head 87 and the momentum of the engine shaft 75 will cause i the clutch head 87 to turn slightly, allowing the catch finger 96 to run up the groove 97 and snap over and engage an annular shoulder 98 of the said head 87, thus holding the clutch teeth separated and in their unclutched positions. The above described movement of the catch 94 which accompanies the opening of the clutch 84-87 automatically releases the finger 96 of the catch 94 from the shoulder 105 of the clutch head 86 and thereby allows the spring 92 of the head 86 to close with its teeth 89 in operative engagement with the teeth 85 of the adjacent head 84. Each of the engines 72 and 73 is provided witha similar starting device (not shown) and thrown into operationlby a lever 106 having an arm 107 pivoted as at 108 and normally seated against the outer face 109 of the adjacent engine shaft head by means of a spring 110. During the closing of either clutch head, such as the head 87 as above described, the arm 107 is allowed to move forwardly thus forcing the starting lever 106 rearwardly and starting the engine 73 so that the said engine 73 being other is ready to betripped by the opposite clutch so as to release the open clutch for allowing thesame to close.

While the form of the invention herein shown and described is what is believed to be the preferred embodiment thereof, it'is nevertheless, to be understood that minor changes may be made therein without departing from the spirit and scope of the invention as claimed.

What is claimed as new is 1. An aeroplane comprising a centrally arranged boat-shaped frame, oppositely arranged lateral V-shaped equilibrator frames, forward sustaining planes flatly engaging the tops of the said lateral frames, rearwardly arranged sustaining planes of substantially the same dimensions as the forward planes carried 'by the main frame in the same plane as the'forward planes, and upwardly and forwardly inclined elevating planes attached to the forward edges of the said rear planes.

2. An aeroplane comprising a boat-shaped frame having a curved bowand squared stern, rearwardly and forwardly arranged sustaining planes carried in the same plane by said frame, an inclined elevating plane positioned between the said sustaining planes, actuating propellers carried by the said frame in planes at opposite sides of one of the said sustaining planes, equilibrating propellers arranged adjacent the outer ends of the forwardly positioned sustaining plane and above and below the same, and a steering propeller universally mounted upon the stern of the frame.

3. An aeroplane comprising a boat-shaped frame, having a curved bow and a squared stern, rearwardly and forwardly arranged sustaining planes carried in the same planes by said frame, an inclined elevating plane positioned between the said sustaining planes, oppositely projecting lateral supports carried by the said frame beneath one of the said sustaining planes, supporting strips for the said sustaining planes, guy wires between the said strips and frames at opposite sides of the other of the said planes, actuating propellers carried by the said frame in planes at opposite sides of one of the said sustaining planes, pairs of equilibrating propellers journaled in the op osite outer ends of the said supports, an a steering propeller mounted for universal movement in the stern of the said frame.

4. An aeroplane comprising a boat-shaped if frame, opposite pairs of propellers carried thereby, a drive shaft for the said propellers, oppositely positioned actuating engines for the said drive shaft, selective clutch connections between the said engines and drive shaft, and an automatic actuating means for the said clutch connections whereby t e clutch means of one engi e s d sconmeaoao nected and the other connected upon the stopping of one of the engines.

pellers, operating shafts for the said pro-.

pellers, power shafts operatively connected to the said operating shafts, oppositely positioned clutch heads secured to the said ower shafts, oppositely positioned engines having their shafts in axial alinement with the said power shafts, slidable clutch heads splined upon the said engine shafts, ad-

jacent the clutch heads of the said power shafts, and automatic means for closing one set of clutch heads simultaneously with a disconnecting of the other pair of clutch heads.

7. An aeroplane com rising a frame, propellers, operating shats for the said propellers, power shafts operatively connected to the said operating shafts, oppositely positioned clutch heads secured to the said power shafts, oppositely positioned engines havin their shafts in axial alinement with the sai power shafts, slidable clutch heads splined upon the said engine shafts, adjacent the clutch heads of the said power shafts, automatic means for closing one set of clutch heads simultaneously with a disconnecting of the other pair of clutch heads, and a selfstarter lever arm in operative engagement with the splined clutch head of its respective engine.

In testimony whereof I afiix my signature.

BOLESLAW WARCHALOWSKI.

copies of this patent may be obtained for five cents each, by addressing the "commissioner of fiawnw, Washinstan, B. Q."

Images