US1220374A - Aeroplane. - Google Patents

Description

M. STUPAR.

AEROPLANE.

APPLICATION FILED FEB: I, I9I5.

Patented Mar. 27, 1917.

Y 2 SHEETS-SHEET I.

Nn N M. STVUPAR.

AEROPLANE.

APPLICATION FILED FEB.1.1915.

Patented Mar. 27,1917.

2 SHEETS-SHEET 2.

UNITED srarns MAXMILLIAN STUPAR, OF CHICAGO, ILLINOIS, ASSIGNOR 0F ONE-HALF TO HERBERT S. RENTON, OF CHICAGO, ILLINOIS.

AEROPLANE.

Specification of Letters Patent.

Patented Mar. 27, 1917.

Application led February 1, 1915. 'Serial No. 5,348.

To all 'whom'z't may concern:

Be it known that I, MAXAMILIJIAN STUPAR,

a citizen ofthe United States, and a resident of ('hicago, in ne county of Cook and State of illinois, have invented certain new and useful Improvements in Aeroplanes; and I do herelo)7 declare that the following is a full,lclear, and exact description thereof, reference being had to the accompanying draw- 10 ings, and to the characters of reference marked thereon, which form a part of this specification.

This invention relates to improvements in aeroplanes and refers more specificall) to an innjirovcd construction in the plane proper and controlling means therefor de signed to enablel the speed of a hea vier-thanair flying machine to be, varied while maintaining a given haul-carrying efficiency, and also arranged to effect and maintain lateral equilibrium of the machine.

vlt is the purpose of the invention to provide means for adjusting the ramber of an aeroplane, so constructed as to enable the camber to be adjusted at will. duriiig flight and to be maintained at a given adjustment. both for the purpose of enabling the speed of a flying machine carrying a given load to be Varied in a way thatI will admit of the natural functioning of the ordinary steering and controllingmeans of the machine, and which will also enable the lateral balance of the machine to be n'iaintained without warping the planes in a manner heretofore common in the control of aeroplanes.

One ofthe purposes of the invention is to provide an aeroplane having the characteristics above described wherein the adjustment 0f the camber, for thc purposes set forth, can be made without affecting the symmetry of the plane with respect to its center of pressure or change -in center of pressure Whenchange of angle of incidence is made, so that the machine is not thrown 45 out of balance, whereby changes in the angle of incidence of the planel meets with like responses in all eamher adjustments of the plane. `'Therefore variations of camber, for the purpose set forth. do not introduce new fi problems oi additional changes `in plane control. i

A further object is to provide an *aerowhich are very flexible so and prompt control.

A further object of the invention iS to provide an aeroplane having means to increase its lift without introducing undue or correspondingly increasing head resistance and which does not. present the. planes or auxiliary surfaces at unnatural or inefficient angles to the air.

Other objects of the invention are to produce a very simple method for controlling the camber of an aeroplane and to otherwise improve aeroplanes. and the invention consists in the combination and arrangement of the parts shown in the drawings and described in thespecification. together with the mechanical equivalents thereof, and is set forth in the appended clamis.

l`he system of speed control employed in my invention is based upon th i fact that a. plane with a deep eamber has a greater lifting` power. at a given speed, than a fiat plane or a plane having a small camber` 'l`herefore. in accordance with my i'i'zyeftision the speed of an aeroplane may be decreased or lowered bevond a normal speed, without limiting its load carrying capacity, by the operation of increasing the camber'iof the plane. lt has heretofore been the practice, in order to slow down the speed' of a flying machine. to materially increase the angle of incidence or an operation `which has been termed by aeronauticians as stalling. Such stalling operation does not. however, permit a very great range of speed, and is moremer dangerous inasmuch as if the en- .gine be killed during the stalling operation the machine is likel \v to glide or skid backwardl)Y before il can be controlleol for for` ward velplaning. 4""

ln using mv new principleof adjustable camber for lateral .stability of a flying machine he planes and control therefor are so adjusted relativel \Y to each other that when the eamber of the plane on the side toward which the machine tends to di|'l is increased. thereb v increasing the lifting power of such plane, the plane at opposite sii/le of the machine is siniultaneousl)r and auton'iatically decreased. and is therefore partially deprived of its lifting cfliciencyffso that said planes coact to bring the machine to an even keel or to a stabilized equilibrium.

'l`he method herein described for varying the .fn-roher of the planes of a flying machine as to insure easy may be conveniently correlated to the controlling mechanism which is under the direct supervision of the driver in such a way that through the action of the same hand operated device the camber of the planes at 'both sides of the machine may be simultaneously increased or decreased to vary the speed of a machine carrying a given load, or the reduction of the camber of one side may occur at the same time the camber at the other side of the machine is increased to' effect lateral balance ofthe machine.

I have shown in the drawings, in a somewhat diagrainmatic manner, one practical embodiment of my invention and have con'- fined the illustrated embodiment to two planes. It will be understood, however, that said planes may be the wings of a monoplane typc of flying machine, or that they may be the upper wings of planes of a b1- plane type of machine.

ln the drawings Figure 1 is a. diagrammatic top plane view of a monoplane flying machine and controlling elements' embodying my invention.

Fig. 2 is a transverse section of a plane embodying my invention.

Fig. 3 is an underside View of the skeleton frame of the machine.;

Fig. 4 is a fragmentary plan view plane.

Fig.. 5 is a detail section on the line 5-5 of Fig. 2.

Asv shown inthe drawings, and referring inthe immediately following parts of the of the 'specification to a single plane,10 designates the plane as a whole. The frame of the plane comprises an upper series oflongitudinal members or ribs 11 and a series of lower longitudinal members or ribs 12 which are spaced from each other by spacing blocks 13, 13, and transversely extending spars 14, 15 and 16, the latter spar being located at the entering edge of the plane. The said upper and lower members and spacing members or blocks constitute skeleton. or open work ribs which may be made of ample strength while yet sufficiently flexible to be readily bent or curved for a purpose hereinafter described. The said spars 14 and 16 are'herein shown as fixed to the upper Vand lower ribs 11 and 12, respecf tively, while the spa r v15 is fixed to the lower ribs and is unattachcd to the upper ribs.

The spacing blocks 13 are fixed to the lower ribs 12 but have sliding engagement with the upper ribs 11. Such engagement may be effected by providing the blocks 13 with grooves 17 which are engaged by guides 18 on the lower sides of the upper ribs 11. 19 designates one of a series of plates or webs ar -anged in rear of the spar 15 and iixcdly attached in any suitable manner to the associated lower member or rib 12 of the plane frame. Said'web or plate 19 is movable web or plate 19 at 21 and is attached at its other end to the upper fabric cover 22 of the plane which overlaps and terminates in rear of the forward edge of the fabric cover strip 23 at the trailing edge of the plane which is stretched between the spar 15 and a spar 21 at the said trailing edge of the plane. ployed and an equal number of plates or webs 19, and the purpose of the springs is to maintain the upper fabric covering 22 tight under all conditions and various degrees of cainbei and to aid to assist to decrease tlie caniber of the plane. Theplane number of said springs is em# is so constructed that it assumes a noriial lV 4are pivotally connected at their opposite ends in any suitable manner to the spars 14,

15, respectively, iii front aiul in reai' of the center of pressure of the plane. which center 1s herein shown as located about one-third -of the distance between the entering and trailing edges of the plane. The said rods are loosely connected at their adjacent ends to a controlling wire or cable 26, arranged beneath, and extending from end to end of, the plane for connection beyond ythe inner end of the plane with an operating mecha nism to be hereinafter described. A restoring member 27, which connects the outer end of each cable 2-6to the plane. frame at its outer end and which may have the form of a helical spring or of a stout elastic band, tends to normally draw the cable 26 outwardly. and acts in conjunction with the controlling gear hereinafter described to hohl the rods 25 iii adjusted positions and aids to restore thc plane to its normal Camher, as shown in Fig. 2 when the controlling gear is-adjusted to normal position. Ihe normal positions of said rods when the plane occupies its normal camber is show n in Figs. 1, 3 and l wherein it will be noted that they are disposed at a slight angle to cach other and to thcrribs and that they lie on thel .sides of their associated ribs adjai'apable of assuming. that the full line position of the plane as shown in Fig. 2 is the minimum camber thereof, and that -between these two positions the camber may be adjusted to any degree desired to correspond with a speed corrclative to the curve of the. cambcr and a given load.

Referring now to the manner ot' connect ing a central control device to the wings, it will be noted that cables QG extend inwardly past the inner end edges ot' the planes and are wrapped about a drum 2S located at the center of' the machine in f'ront of the driver`s position, and said cables are fastened to the drum in such a way that when the controlling lcver 2f) of the said drum is swung along a segment 30 both cables will be .wound upon the drum and, therefore. both lanes will be cambered ef uallv. through the P s 'operation of the rods 25, as is necessary to change the speed of the aeroplane. 'hen the lever Q9 is swung in the other direction the spring elements 27. assisted by the springs 20, restore thc` planes to a smaller camber. The lever Q9 may be provided with any well known means for locking it to the segment.

31 designates a handwheel which is adapted to be connected in any suitable manner, not necessary to be herein shown, with the Steering rudder of the machine. The steering wheel post or column on which the steering wheel is mounted is pivoted at 33 below the drum so that it may be swung from side to side and the drum is mounted in said column so as to be thereby shifted in an arcuate path, when the column is swung on its pivot. This movement of the steering column is provided for controlling the lateral balance of the machine through the camber adjustment described. Assuming` for instance, that the machine shown in Fig. 1 should tip down toward the left. the steering wheel column is swung to the right and this movement of the column and the drinn carried thereby acts through thelef't hand cable 26 and the associated bars to increase the camber of the lower plane while the spring elements 27, 2O act on the other cable. which is at this time slackening, to correspondingly decrease the camber of the higher plane. The efi'ect of increasing the camber of the lower plane is to increase the lifting capacity of the said plane and thc effect of decreasing the camber ot' the higher plane is to decrease its lifting capacity. 'l`hus the balancing functions of the adjustable camber on each side of the machine cooperate to bring the machine to an even keel without decreasing the load carryingr capacity of the machine or the speed of the machine. Assuming that the machine should tip toward the right the steering wheel column is swung toward the left with lthe result of' reversing thc operation of the parts 26, 25, Q() and 2 7 to bring the machine to' a balance. The tendency of the plane is to remain at the same camber at which it is manually set, regardless of the changes in the air pressure, the spring controlling elements keeping the wires QG tight and to assist in straightening the plane.

It will be observed trom an inspection of Fig. that the varying f -urvatures or cambers of the plane are symmetrical with respect to the center of pressure of the plane, so that the adjustment ot the camber does not tend to. or actually throw the plane out of' balance by presenting unnatural or inefficient angles of' the plane to the air, and this without regard to the angle of incidence at Iwhich the plane is presented to the air. In other words, the plane at its minimum camber has thc same characteristics. such as location of.ccnter of pressure and change in center ot' pressure, resulting in change of' angle of incidence, as at vthe greater cambcr.

lt will bc understoml that the essential tentures of' my invention are capable of embodiment in aeroplane. flying machines of varying structural details and that the invention is not limited to the particular embodiment shown except as the details are hereinafter specically claimed and as imposed by the prior art: and it is the intent to claim all ot' inherent novelty shown in the drawings and described in the Specification.

claim as my invention 1. ln an aeroplane flying machine, .means to vary the speed ot the machine compris ing means to adjust the camber of the plane at will during flight symmetrically to the fore and aft center of pressure of the plane Yembracing elmigated means extending from .of the center of pressure of thc plane.

Q. Tn an aeroplane flying machine, a plane comprising upper and lower longitudinally fiexible plane members extending fore and at't acrossI the center of' pressure of the plane.: transverse spars between said members fixed to the lower members and one of which is fixed to thc upper members, and means f'or moving one of the spars toward the'other to varythe caniber of the plane.

$5. ln an aeroplane flying machine, a plane comprising uppcrwand lower sets of flexible ribs` irout and rear transverse spars between the ribs. one of said spars being fixed to the upper and lower sets of ribs and the other spar being fixed to one set of ribs and slidable on the other set. and means for moving one spar toward the other.

4. ln an aeroplane flying machine. a plane comprising upper and lower sets of' ficxible ribs, front and rear transverse spars between thc ribs, one of' said spars being fixed to the upper and lower sets of ribs and the other spar being fixed to one .set of ribs and slidable on the'other set, a cable "extending transversely beneath the ribs between the spars, toggle bars loosely connected to said cable and to the spars, and operating means acting on the cable and acting through the .toggle bars to vary the camber of said plane. g

5. In an aeroplane flying machine, a plane comprising a frame consisting of flexible longitudinal ribs and meansfor varying the camber of the plane comprising a transverse cable and a series of toggle bars con- 'nected to said cable and connected also to jnectzed to the inner end of said cable and a resilient member to anchor the outer end of said cable to the plane structure. i

7 In an aeroplane flying machme, a plane comprising upper and lower longltudmally iexible plane members7 transverse spars between said members fixed to the lower members and one of said members being slidable relatively to the upper member, a cable arranged beneath the plane and connected at the inner end of the plane to an operating element and at the outer end of the plane to a resilient element, and cross bars connected to said cable and to said transverse spars. p

8; In an aeroplane flying machine, a plane comprising longitudinal ribs and transverse 'connected to certain of the. ribs and4 movable relatively to the other ribs, whereby when the-spars are moved one toward the other the camber of the plane is changed,

and a camber controlling cable extending transversely beneath the plane and connected to said spars.

9. In an aeroplane flying machine, a plane comprising longitudinal ribs and transverse spars connected to certain of the ribs and movable relatively to the other ribs, whereby when the spars are moved one toward the other the camber of the plane is changed, a cable extending transversely beneath the plane and connected to said spars, a plane controlling device connected vto the inner end of said cable and a resilientdevice for anchoring the outer end of the cable to the plane structure. ,t A

10. In an aeroplane flying machine, a

plane comprising longitudinal ribs and.

transverse spars connected to certain of the ribs and movable relatively to the other ribs,

ywhereby when the spars are moved one toward the other the camber of the plane ischanged, a cable extending transversely beneath the plane and connected to saidrspars, a plane controlling'device connected to the inner end of said cable, a resilient device. for anchoring Vthe outer end of the cable to the plane structure, a flexible plane cover, and resilient means for connecting the rear edge of said cover to the plane structure.

11. A11 aeroplane flying machine comprising planes at the sides of the machine constructed to be curved to vary the camber thereof, and means for curving the planes, including cables extending beneath the planes, Arestoring elements connected to the outer ends ofthe cables and to the plane frames, and manually operable means connected to the inner ends of said cables.

12.- An aeroplane flying machine comprising planes at the sides of the machine constructed to be curved to vary the camber thereof, and means for curving the-planes, including cables extending beneath the planes, restoring elementsfconnected to the outer ends of the cables and* to the plane frames, manually operable means connected to the inner ends lof said cables, a flexible plane cover and resilient means fixed to the rear edge of said cover. and acting in opposition to said manually operable means.

13. An aeroplane flying machine comprising planes at the sides of the machine constructed to be curved to vary the camber thereof, and means for curving the planes, including cables eitending-beneath the planes, restoring elements connected -to the outer ends of the cables. to the plane frames, a drum between the planesabout which the inner ends 'of the cables are loppositely wound, with means to rotate said drum to simultaneously increase or decrease the camber of both planes, asdesired, and means to lock the drum rotating means.

14. An aeroplane flying machine comprising planes at the sides of the machine constructed to be curved to vary the camber thereof, and means for curving cthe planes,

including cables extending beneath the planes, restoring elements connected to the outer englls of the cables and to the plane frames. a drum between the planes about which th`e inner ends of the cables are oppoplanes, restoring elements connected to the 'outer ends of the cables and to the plane frames, a drum between the planes about which the cables are reversely wound with means to rotate it to simultaneously c ange the plane cambers, vand means connected to the cables constructed to increase-the camber of one'plane simultaneously with the de- -crease of camber of the companion plane. 10

16. An aeroplane flying machine comprising planes at the sides of the machine constructed to be curved to vary the camber thereof, and means for curving the planes, including cables extending beneath the planes, restoring elements connected to the outer ends of the cables and to the plane frames, and a drum between the planes about which the cables are reversely wound with means to rotate it to simultaneously change the plane' cambers, and a pivoted column on which the drum is mounted, whereby swinging movement of the column serves to increase the camber of one plane simultaneously with the decrease of camber of the other plane.

17. An aeroplane ying machine, a plane comprising light, flexible longitudinal ribs, front andl rear transverse spars between them, with the center of pressure between thespars, and means acting on said spars to longitudinally camber the planes without changing the characteristics ofthe planes relatively to the center of air pressure at any angle of incidence.

18. In an aeroplane flying machine, means to vary the speed of the machine, comprising means to adjust the camber of the plane at will during Hight symmetrically to the fore and aft'center of pressure of the plane, embracing means extending from the inner to the outer end of the plane, and connected .to

said outer end of the plane, and connected between its ends to the plane in front and in rear of the center of pressure thereof a exr,

- position to the carnber adjusting means.

19. An aeroplane comprising longitudinal ribs and transverse spars Wlth adjusting means to vary the camber of the plane, members attached to the plane at the trailing edge thereof, a fabric cover for the plane terminating short of the trailing edge there of, and resilient elements connecting said rigid members to .the rear edge of the fabric cover and acting in opposition to the carnber adjusting means.

, 20. An aeroplane comprising longitudinal ribs, transverse spare, adjusting means to vary the camber ofthe plane, a plur lity of longitudinally arranged rigid mem ers attached to the rear ends of the lower ribs and movable relatively to the upper ribs a fabric cover for the plane and spring e ements connecting said members to the rear edge of the fabric cover.

21. An aeroplane comprising longitudinal ribs, transverse spars, adjusting means to vary the camber of the plane, a plurality of longitudinally arranged rigid members attached to the rear ends of the lower ribs and rigidi@ movable relatively to the upper ribs, a fabric cover for the plane and a cover piece overlapped at its forward edge by the rear edge of said fabric cover and attached at its rear edge to the trailing edge of the plane.

In testimony, that I claim the foregoing as my invention I aiix my signature in the presence of two witnesses, this 20th day of January, A. D. 1911i.A

MAXAMILLIAN STUPAR.

Witnesses: W. L. HALL,

G. E. Dom.

Images