US1276032A - Flying-machine. - Google Patents

Description

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a. CHMIELINSKI.

FLY'IKG MACHINE. APPL IcATIoN FIITEDDEC-HKJ'QII Patented Aug. 20, 191

4 SHEETS-SHEET 2.

a. CHMIELINS'KI'.

FLYING meme.

APPLICATION FILED DEC-14 1911.

Patenfei Aug. 20, 1912 hemispherical bow or nose' l and a done GREGORY CHMIELINSKI, OF CHICAGO, ILLINOIS.

FLYING-MACHINE.

Specification of Letters Patent.

Patented Aug. 20, 1918.

Application filed December 14, 1917. Serial No. 207,151.

To all whom it may concern:

Be it known that I, GREGORY Cl-IMI-ELI1*{ sin, a citizen of Poland,'residing at Ch1 ca '0, in the county of Cook and State of Illinois, have invented new and useful Iniprovements in Flying-Machines, of which the following is a specification.

,This invention relates to flying machines of the heavier than air type, the broad object in view being to produce alflylng machine of great passenger and freight carrying capacity and which may be also used in times of war for transporting troops, ammunitions of war, and-also as a bomb dropping machine.

The invention relates more particularly to the frame structure and general arrangement of the fuselage or cabane and the aerial supportin and propelling means,

--whereby the mac ine may be handled with compariftive ease and whereby increased lifting properties are imparted to themachine, rendering the same comparatively safe in operation, while at the same time imparting an unusual degree of stabillty both in a fore and aft and lateral direction.

With the above and other objects in view the invention consists in the novel construction, combination and arrangement of parts, as herein described, illustrated and claimed.

In the accompanying drawings,

Figure 1 is a plan view of the improved flying machine.

Fig. 2 is a plan view partly in section of the frame of the fuselage or caban'e.

Fig. 3 is a fragmentary perspective view of one of the end portions of the frame of the fuselage.

Fig. 4 is a fra entaryvertical section on an enlarged sca e through one side of the fuselage.

Fig. 5 is a side elevation of the machine.

Fi 6 is a vertical transverse section on the line a-a of Fig. 5.

Fig. 7 is a front elevation of the machine.

Fig. 8 is a perspective view of one of the propellers.

Fig. 9 is a bottom lan view of the same.

Referring primari y to Fig. 1, the machine in its general arran ement and structure comprises front an rear lifting or gliding surfaces 1 and 2, which are super imposed above a fore and aft elon ated fuselage or cabane 3 having a su stantially spondingly shaped stern 5, imparting to the fuselage a stream-line formation which may be propelled through the air with a minimum head resistance.

Referring now-to Figs. 2, 6 and 7, the fuselage comprises a series of circular bands or hoops 6 constituting transverse members of the frame. All of the hoops or circular frame members 6 which are in the form of endless rings, are connected at suitable intervals by means of longitudinal tie bars or stringers 7 thus forming a reticulated hollow cylindrical frame for the fuselage. At the top and bottom of the frame members 6, there are other longitudinal frame members or stringers 8, 9, 10 and 11. The last named frame members are longer than the members 7 previously referred to and are also secured fixedly to the ring like frame members 6. The members 8, 9, 10 and 11, however, extend beyond the front'and rear members 6 where they are each bent into the form of a quarter circle. The member 11 has a bifurcated extremity 12'which straddles the adjacent extremity '9. The member 8 has a bifurcated end 13 which straddles the bifurcated end 12 of the member 11. The member 10 has a bifurcated end 14: which straddles the bifurcated end 13 of the member 8. A single fastener 15 which mayconsist of a bolt, is inserted throu h the interiitting ex tremities of said mem ers 8', 9, 10 and 11 as shown in Fig. 3, the extremities of all of said members being thus firmly secured together at the extreme bow and stern of the fuselage. A-covering 16 of any suitable ma terial, either metal or fabric is used as a sheathing for the fuselage frame. At/the bow quadrant shaped glazed port holes or' windows 17 are provided. for the use'of the aviator as well as other occupants of the machine.

As indicated in Fig. 1, I employ four separate and independent motors 18 and four separate and independent propellers 19. Each propeller is mounted upon an individual propeller shaft 20 having fast thereon a sprocket wheel 21 around which;

passes a chain 22 which extends around a sprocket wheel 23 on the shaft of the respective motor 18. Each shaft 20 is journaled in bearings 24: at; the lower extremities of' an equal numbed?" of hangers 25, which are connected at th r upper ends to fittings 26 on the under si e of the adj acen't supporting or gliding surf co l-or 2 as the case may be.

ill-aces or sprmdcrs 27 extend from the fuselag lalcraltv outward and havingtheir outer (Xlil'liiliiltfi fastened lo the bearings 2-}. Stays 28 have their outer cxllclnilics coin'nw'twl to the bearings 24 and the fittings 225i and baniln-iiinner extremities fast ned ing the rain of speed of the several l'notors,

. speed of the 'n'opellcrs may be obtained to assist in steering and banking operations and also for restoring and i'naintaining lat oral and ion 'tudinal stability. The aviascat 30 is arranged cci'itmlly of the shown in l ig. ii, and llCljllCGlll to desi i'ial'ccl generally at El 1.. By in m'n'isli'iwtion licro'iimborc out a sin o companioi'iway W is 'lormod length of tln-v fuselage as 'l and. (i and pa" nger ang-od at opposite sides may or sin c aisle.

the proprg-llcrs is preferably of a sulistantially rectangular plate light metal such 2 aluminum or alunnuni alloy. Onftlie ui' ler side of the plate cleats 36 arranged substantially parallel and in. spaced relation to each other are fastened to said sheet by means of rivets or die equivalent thereof. About centrally of their length, the. cleats 36 are formed with eyes 37 through which the respective pro- ?peller shaft 20 is insert-ed and fastened. By r=ference to Figs. '7 and 8, it will be observed that the end portions of the propeller are pitched or inclined at a suitable angle to propel the machine ahead and at the same time 't lifting propellers. Each of the s oiling or gliding surfaces 1 and 2 has .1d or wing portions upi-vardly inclined at and 7, while the extreme end portions there of are slightly rccurved in compound formation as shown in the same figures, giving a bird-like contour to said supporting and gliding surfaces.

In conjunction with each of the motors 18, I employ two fuel tanks 38 and 39: Said tanks are arranged in the front and rear portions of the fuselage and leading from each pair of tanks to the respective motor 18 are one'or more fuel feed pipes 40. At

the, stern of the fuselage, I arrange a rudder bracket 41 having a. semicircular base-.portion which is terminally fastened tothe fuse;- lagie at the points bracket 41 is bodying twotending arms rearwardly extending arms 44.. A. centrally upwardly and rearwardly excreased by the employment of the a dihedral angle as indicated in Figs. 15V

43 and two horizontally and comprising a fore and aft pivoted or bifurcated horizontal rudder 4-5 is mounted upon an operating rock shaft 46 journalcd in the horizontal. arms 4% of the rudder bracket, and a vertical rudder 47 is fast to an operating rock shaft 8 journaled in the horizontal arms -13 of said rudder bracket. Suitable rudder operating connections extend from said rock shafts inboard Where they are connected to one of the controls 31 hereinabove referred to.

The landing gear comprises an axle 49 extending transversely under the fuselage and having mounted thereon supporting wheels 00. Theaxle 49 is carried by the lower extremities of vertical plunger rods 51 which are slidable through openings in a bottom bracket 52 fastened to the bottom of the fuselage fralneas shown, for example, in Fig. 6. Encircling' each of the plunger rods 51 is a coil compression spring 53 which acts as a shock absorber and cushions the load of the machine in relation to the axle 49. It will be seen from F ig. 5 that front and rear axles 4.9 are provided for the proper support of the machine on the ground. Flexible stays 54 may be interposed between each axle l9 and the bottom frame 52 or the frame of the fuselage as may be preferred.

The construction hereinabove described provides for i a light weight, thoroughly braced fuselage and wing structure, the fuselage having a large carrying ca acity for passengers or freight. By emp oying the front and rear supporting or gliding sur' faces, the longitudinal stability of the machine is greatly increased as compared with the present date type of aeroplane which has the supporting and gliding surface'or surfaces arranged adjacent to the head or how of the fuselage. Both the lateral and longitudinal stability of the machine are also inpropellers under the arrangement described and shown. Ample clearance for said propellers is pro vided at opposite sides of the fuselage and beneath the supporting and gliding surface. The bearings for the propeller shafts and the outriggers or. hangers therefor, are

will also be found a very desirable feature in case of in my to either thehorizontalor 42. At the rear end, sald of cruciform format-ion, em-' vertical rud adds greatly I-claim';

1. In a flying machine,

er or the controls thereof. to the safety .of the machine.

a fpselage frames e1 1e s of circularhoops, longitudinal frame bars to which all of said hoops, are fastened, and other longitudinal frame bars to which said hoops are fastened, the last named frame bars extending beyond the front and rear hoops and having front end portions curved inwardly and fastened at their extremities to provide hemispherical bow and stern portions for said fuselage frame.

In a flying machine, a fuselage frame comprising a fore and aft series of circular hoops, longitudinal frame bars to which all of said hoops are fastened, and other longitudinal frame bars to which said hoops are fastened, the last named frame bars ex tending beyond the front and rear hoope end having front end portions curved in \i'nri'lly and fastened at their extremities 0 provide hemisl'iherieal how and stern per tions for said fuselage frame, propeller shafts extending parallel to the longitudinal axis of the fuselage frame, and supporting Outriggers for said shafts fastened to the fuselage frame.

3. In a flying machine, a fuselage frame comprising a fore and aft series of circular hoops, longitudinal frmne here to which all of said hoops are fastened, other longitudinail frame bars to which said hoops are fastened, the lust named frame here extending beyond the front and rear hoops and having front end portions curved inwardly and festened at their extremities to provide hemispheric-n1 bow and stern portions for said fuselage frame, the said curved end portions of the last named lon' itudinzrl frame bars being overlapped in bifurcated forms;- tion, and usingle fastener inserted through said overlapping extremities.

in testimony whereof I nflix my signature.

C: it l*l(l-( W Y ()H MIELIN SKI.

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