US1315044A

US1315044A - shabkey

Info

Publication number: US1315044A
Authority: US
Publication date: 1919-09-02
Anticipated expiration: 1936-09-02

Description

' SHARKnY, a citizen of theUnited States, re,

l To all whom t may concern:

DOMINIGK WQ SHARKEY, OF SYRACSE, NEW YORK.

Lemma.

. Application fledi November 27, 1917. Serial No. 204,156.

Be it. known that 1,. DOMINICK W.-

sidingat Syracuse, in the county of Onondaga and State of New York, have invented a certain new and useful lmprovement in Aeroplanes, ofV whichl the following 1s a specification, reference being had therein to the accompanying drawings, forming part thereof. My invention relates yto aeroplanes and has for its `general Object great `strength7 high speed, reliability, durability'and other objects and advantages which will `hereinafter appear. My present invention relates more particularly to the propelling means, and the wing or plane constructionfdisclosed herein forms the subject of my copend-ing divisional application for Patent Serial No.` 268,148, ined December 24., 1918. l

, My invention includes apropulsion tube formingthe body of the aeroplane and prof vided with an, annular adjustable air discharge, opening together withmeans, such,

for example, as a screw propeller, for producing an increased pressure of air within such tube, such tube being tapered toward its rearend.V `My invention also includes, in combination, wings forming planes secured to and extending laterally from the vsides of such tube, a frame comprising a plurality 'of longitudinally extending members at the' outsideof the body-forming propulsion tube, and a plurality of rings tying such frame pieces or members together. My invention further includes features of construction and combinations of parts, as will-appear from the following description.

I shall now describe the aeroplane embodying my invention illustrated vin the accompanying drawings and shall thereafter point out my invention'in claims.

Figure .'1 is a topor plan view.A

Fig. Qis an enlarged partial longitudinal vertical section of the rear end of the aeroplane on a plane indicated by the line 2-2 of Fig. 1 as viewed from below.

Fig. 3 is a transverse section on planes indicated by the line 3-3 .of Figs. l and 2 as viewed from the left7 and drawn to a scale somewhat less enlarged than is Fig. 2.

Fig. 4 is asimilar section on a plane indicated by the line 1li-4 of Fig. 1 as viewed from the right.

Fig. 5 is a partial section similar to Fig. l but showing a wing as detached.

Fig. fis :a front elevation on a reduced` scale.

Fig. 7 is a side elevation'V as viewedy from y below indig. 1 and from the left in Fig. 6. Fig. 8 is 'a somewhat enlargedcentral ver tical longitudinal section with parts omitted. Fig. 9 is a transverse section on a plane indicated Iby the line 9,-.-9 of Fig. 8 as viewed from theright.

Fig.j10 is a-similar view on theline 10-10 of Fig. 8.

Fig. 11' is a muchenlarged vertical longitudinal section of one of the wings on a plane indicated by vtheline 111-11 of Fig. 1 -as viewed from below..

Fig. 12 is a similar view on the line L12-1 :0f Flg. 1. 1 v

In the aeroplane embodying my invention illustrated in the accompanying drawings, a gradually rearwardly tapered sheet metal tube 1 forms a part of the body frame or fuselage of the machine. A sheet 4metal hood Q of substantially semicircular crosssection and shownas slightly tapered in a forward direction extends forward from the upper part of the `forward end of the tube '1,

forming a forward .continuationof the up per part of the tube 1, this semicircular hood 2 also forming'a part of the wing-support- Aing framework or fuselage of the machine. The framework or fuselage also includes vlongitudinal frame .pieces 3, shown as four in number, equidistantly transversely circumferentially spaced and tied together -at intervals by means of transversely arranged rings i, these frame able metal or alloy. j j VWings or planes, forming more particularly `the subject of my above mentioned divisional application, project laterally in opposite directions from the fuselage and Y. are detachably securedto the sides of the body-forming rearwardly tapered tube 1l and to the lower edges ofthe forwardly extended hood These Wings have gradually outwardly tapered Vshaped sheet 'metal ribs 5 extending laterally in parallel relation at right angles to the longitudinal axis of the machine, and shown as seven in number for each wing, and these wingribs 5 vary as to their length andcross-section. The lower air-engagingwing surface of the wing is formed by a lower metallic sheet 6, which is firmly secured by means of rivets 7 (Figs. `11 and 12) to lateral flanges parts being of any suitare all 0f similar construction, but

machine, and are shown as thus secured in place bymeans of two sets of upper short bolts12 and by a single set of lower long bolts or tie. rods 13 which extend transversely from side to side through the lower edges .of thevhood 2 and transversely across the tube l just below the axis or center line thereof. Simply by removing the outwardly exposed nuts from these bolts 12 and rods 13, the `wings may be detached from the body or fuselage, thus providing for convenient transportation and for the easy making of repair'sfT-lieylat.sheet metal plate 6 forming thelowe'r wing surfaces is provided between the wing-ribs 5 with apertures 14 of comparatively small diameter, these holes 14. permitting the passage o f small quantitie'sof'air from the lower to the upper sides*- the wing-ribs 5.

of the wings between the ribs 5, so as thereby `to preventv the forming of objectionable eddy currents in the air above the wings by It will be noted that the wings and entire body structure or fuselage are formed entirely of metal, so that their construction is such as to provide great strength combined with'lightness. 0

In carrying out my present invention, the body-'forming tube 1 of the fuselage is also a propulsioritube for driving the aeroplane forward, and Afor accomplishing this result means are provided for compressing air in the tube 1, which may enter at the rward open end of the tube, and which, by reason of such compression, will be forcibly expelled from the rear contracted end of this tube 1. In the construction illustrated in the drawings, a screw propeller 15 is located within the tapered tube 1 near its forward flaring end 4and has a large number ofy blades, shown a`s six, for thereby effec-l tively compressing the air within the tube 1 at the rear Qf the propeller 15, which is of a diameter substantially filling the tube l. The propeller 15 is fixed upon a propeller shaft 16, and the propeller :shaft 16 is shown as extending axially through the tube 1 from end to end thereof, at its rear end being journaled in a bearing 17 carried by a strut 18 at the rear end of the tapered propulsion tube 1, and at the flaring forward end of this tube 1, the propeller shaft 16 is journaled in a bearing 19 carried by a strut 20. From the bearing 19 the propeller shaft 16 extends forward to `an engine 21, which may be of a usual or of any suitable construction, and is shown as located at the forward end of the body framework or fuselage forwardly of the forward edge of the Wings. The engine 21 drives the propeller 15,y and air entering the forward flaring or enlarged 4open end of the propulsion tube 1 is compressed within this tube by the propeller 15, and by reason of this compression the air is ejected rearwardly through the reduced rear end of the tube 1, and by its reaction drives the aeroplane in a forward direction.

In order to obtain a maximum propulsive effect, a restricted air discharge opening of. annular form isprovided at the rear end of the tube 1. A forwardly tapered'or rearwardly flaring cone is located centrally of the vrear end of the rearwardly tapered tube l `for.producing a restricted air outlet of annular form, whereby air under compression may accumulate within the rearwardly tapered propulsion tube l at .the rear of the l propeller 15 and by reason of its compression will be discharged at high velocity through such restricted annular outlet. Means are provided for adjusting the area of this ani nular air outlet, and inl they construction illustrated in the drawings, the cone is made adjust-able for radial expansion or contraction of its periphery. For effecting such adjustment the cone is shown as comprising a plurality of tapered curved overlapping sheet' metal plates 22, which at their forward endsare hinged or pivoted to a central front member or collar 23, which is slidable upon the propeller shaft 16, which is shown as of reduced diameter rearward from the propeller 15.. Each of the curved tapered sheets 22 is pivotally connected ata median point thereof by means of a linlr 24( with a stationary central member or spider 25 shown as formed upon the forward end of the rear bearing 17 for the propeller shaft 16.

It will be noted that'the links 24 are inclined toward the rear as they approach the spider 25, so that sliding movement of the collar 23 upon the propeller shaft 16 will cause the overlapping cone plates 22 to open or to close substantially like an umbrella, the arrangement being such that movement of the sliding collar 23 tn the rear will cause an openingmovement of the cone, and forward movement of the collar 23 will cause a closing movement of the cone. In the lconstruction illustrated in the drawings, manually operated means are shown for effecting the opening or closing movement of the cone-forming plates 22. In this construction such manually operated means comprise a bell-crank lever 26 pivoted on a bearing 27 carried by the rear strut 18 and having an upstanding arm which is pivotally connected by means of a link 28 with one of the links24, and this bell-crank lever 26 has a frear arm which is connected by an operating rod or link 29 with the longer rearwardly extending arm of a double bell-crank or T-shapedv lever 30, which is pivoted upon a bearing bracket 31 shown as projecting from the rearinostring et of the fuselage or framework of the machine. `The two remaining arms of the T-shaped or double bellcrank levers -30 are connected by means of two operating `wires with a similar double bellecrank or T-shaped lever 33 pivoted upon a bearing bracket 34 shown as mounte upon the top of the forwardly extending sheet metal hood 2. The remaining and forwardly extending longer lever larm of the double bell-crank lever 33 has a handle rod 35 pivoted thereto 4and extending downward through an opening in the hood 2 to" a convenient. position for operation bythe aviator. This rod or bar 35 is shown as notched to provide ratchet teeth for engaging the edge-of the hood 2 at the opening, and these teeth are adapted `to be held in engagement by means of a retractile spring 36. It will'now be evident `that by moving Y the handle rod 35 up or down to different positions of adjustment, the overlapping coneforming plates 22 will be opened or closed, thereby correspondingly adjusting the peripheral dimension or dia-meter of the i cone which they forni and correspondingly varying the area of the annular air outlet between such cone and the reduced rear end of the rearwardly tapered propulsion tube 1. In the drawings this cone is shown as adjusted to substantially maximum diameter for correspondingly restricting the annular air .outlet to a minimum arca which -may be enlarged by reducing the diameter of the adjustable cone, as will be readily understood and as is clear from the 1t will entry to the open larger forward e'nd of the propulsion tube l, particularly to the lower half of such forward end, it4 being noted that there are no 'nearby obstructions adjacent to the forward open end of this tube 1. The propeller 15 compresses the entering air within the tapered tube 1 and the escape of this compressed air rearward through the tapered restricted annularv out# let drives the aeroplane in the forward direction. The adjustment of the area of this air discharge outlet, effected by means of the peripherally adjustable cone as hereinbefore described, provides for obtaining a maximum propulsive edect under different conditions, such for example, as at different speeds of forward travel and also for'the different conditions encountered at various altitudes, the rarefied air at high altitudes requiring more compression. ln the construction illustrated Vin. the drawings, an aviators seat 37 is shown in Fig. 1 as lousual in aeroplane construction.

be noted that the air has free cated beneath the hood 2, 4such machine being supposed to be of sufficient size to permit` ofv the aviator `sitting within and beneath` Other parts of the aeroplane, som'e of which appear in the .accompanying draw.

ings, 'and not hereinbefore. particularly vdescribed, may be of a usual or of any suitable construction. t will be" noted 'that there are provided a vertical rudder-3S, a horizontal rudder 39, a control wheel 40, and a landing gear 4l, all" substantially as It is further to be noted that lateral balancing-control. may be effected in substantially a usual way by warping the outer ends or tips of the wings, which are sufficiently flexible for this purpose, and this warping of the wings to obtainthe lateral balancing control may be effected in substantially a usual way by means of usual guys 42, appearing in Fig. 6.4 These guys 42 alsoistrengthen the wings in a substantially usual way.

It is obvious that various modifications may be made in the construction shown in the drawings and above particularly demy invention". j Y

l claim: l 1. An aeroplane having, in combination,

v a longitudinally extending propulsion tube tapered at its rear end to form a reduced air i discharge outlet, .a rearwardlyflaring cone disposed in the discharge end of said tube so as to provide a further reduced annular air discharge outlet, and Vmeans for compressing the air within said tube at the l front of said cone.

which means are provided for adjusting `scribed within the principle and scope of i the size or area of the annular air discharge outlet between said cone and the inner wall of said tube.

4. The invention claimed in claim 1 in which means are provided for adjusting said cone so as to vary the air discharging capacity of the annular air outlet within said tube around the periphery of saidcone.

5. The invention claimed in claim 4; in which `said cone is adapted for radial eX- pansion or contraction of its periphery.

6. The invention claimed in claim 1 in' which `said propulsion tube is a body-forming tube, in combination with wings forin- `ing'planes attached to the. sides `of and projecting laterally from said tube.

7 The invention claimed in claim 6 in planes secured to the lower edges of-said hood and to the sides of said tube.

9. The invention claimed in claim 8 in combination with tie rods extending transversely from side to side and connecting together the lower edges of said hood.

10. The invention claimed in claim 8 in combinationwith tie rods connecting 'together the lower edges of said hood and other simi-lar tie rods extendingtransversely across said. body-forming propulsion tube. 11. The inventionclaimed in claim 1. in

' which said cone comprises a plurality of tapered transversely curved peripherally overlappingplates, and'means for varying the extent of overlap of the plates for thereby eiecting radial and peripheral expansion or contraction of the cone.

i 12. An aeroplane having, in combination, a longitudinally extending propulsion tube, a rearwardly flaring cone disposed in the rear end of said tube to provide an annular yfront member to which the forward reduced ends of' said plates are pivoted for radial swinging movement, a central rear member, llnks pivotally connecting said plates to said rear central member, and means for varying the distance between said front and rear central members for thereby varying the diameter of the larger end of the cone.

13. The invention claimedin claim 12 in which said air compressing means is a screw propeller, in combination with a propeller shaft upon which said cone is mounted.

14C. The invention claimed in claim 12 in which said forward central member of the cone is movable and said rear central member is stationary.

15. The invention claimed in claim 13 in which said rear central member. of the cone is stationary and said forward central member 'is slidable along the propeller shaft for adjusting the diameter of the cone.`

In testimony whereof I have affixed my signature to this specification.

DOMINICK W.y SHARKEY.