US1037214A

US1037214A - Monoplane.

Info

Publication number: US1037214A
Application number: US65791011A
Authority: US
Inventors: Anthelme Desaye
Original assignee: Individual
Current assignee: Individual
Priority date: 1911-11-01
Filing date: 1911-11-01
Publication date: 1912-09-03
Anticipated expiration: 1929-09-03

Description

A. DESAYE.

MONOPLANB.

APPLIUATION Hmm Nov.1. 1911.

Patented sept. 3,1912.

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i212 ,fa-fein A. DESAYE. MONOPLANE.' Arnmnlon 111111111011, 1911.

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' UNITED STATES PATENT oiaEicEe ANTHELME DESAYE, 0F CLIFTON, NEW JERSEY. l

MONOI?LANE.

Specification of Letters Patent. Patented Sept. 3, 12912.

Application led November l, 1911. A Serial ilo. 657,910.

To all'wwm 'it may concern Be it known that I,- ANTHELME DEsAYp, a citizen of the Republic of France, residing f at Clifton, in the county of Passaic and State of New Jersey, have invented a new and useful Mcnoplane, of which the'following isa specification.

This invention relates to flying machines of the moiioplane type.

The object in general of the invention is to provide an improved` monoplan'e having great flying stability which will be highly cfticient in operation and easy'to control. f

A more particular object of the invention.

is to provide a monoplane havingimproved steering, elevating and descending means.

Other objects willappear from tliefollowing description. I

A desirable embodiment of my invent-ion is illustrated in the accompanying drawings in Which- A Figure 1 is a side elevation of the invention; Fig'. 2 is a front elevation thereof;

Fig. 3 is a plan View thereof; Fig. 4 is a longitudinal sectional'VieW ofthe invention taken on the line 4 of Fig. 3.

Similar characters of reference refer to similar parts in the drawing throughout thel several views.

Body/. The body 1 `of my improved monoplane comprises a suitable frame 2, provided with partitions 3 and 4, which, divide the body into three longitudinal compartments 5, 6 and 7, and also form central.

.braces for lthe body.

Illa/n pZancs.-I `ulcrumcd respectively at 8 and 9 'at the upper side edges of the body 1 are the side planes 10 11, Which eX` tend the entire length ofthe body. The top coveringr v12 of the body of the machine constitutes the intermediate rigid section' of the monoplane 13, which comprises said y intermediate section and the side sections formed by the side-planes 10 and 11. Each of the planes 10 and 11 is wider at its front end than at'its rear endto provide a greater.

ai'ea of sustaining surface at the front end of the machine than at the rear end thereof, inasmuch as the front end of the machine'is the heavier, owing to the fact that the avi-V ator and mechanism hereafter describedare located in thev forward part of the machine.'

Each of .f the' planes 10- and 11 is inclined 4 of the plane.

slightly upwardly at its front end and slightly downwardly at its rear end from its fulcrum point,` so as tc provide the up wardly inclined front sustaining surface 15, which extends from `the front end ot the plane to a point ','fandthe downwardly inclined rear sustaining .iirface 20, which extends from said point wctothe rear end Auxiliary planes of the body 1, respectively at 25 and 26, directly below 'the fiilcruin'fpoints 8 and 9 .are the auxiliary planes ltqandY 11a which e extend the entire length Vof ther-body 1 pai`- `vallel with the planes '-10 and 1l and'provide auxiliary inclined sustaining and protective surfaces 15 and 2()a respectively at the front yand rear of the machine,` vthe vinclination and lengt-h of which correspond to the inclination and length of the surfaces '15 and 2G respectively of the side planes 10 andl ll.` Said auxiliary planes assist the side planes.

in sustaining the machine and also' break the force of any violent-upward atmospheric pressure against the planes l() and l1, whereby said planes are protected and relieved of undue strain. Said auxiliary planes add materially to the strength, durability and eliiciency of the planes 10 and 11.

T he formation of the planes '10 and 1l and the auxiliary. planes 10a and 11 is such that under normal horizontal flying conditions the action of the air against the forward angular surfafes 15 and 15EL of said planes and the reaction of the air against said surfaces, will sustain the forward end of the machine, while the action of the surfaces 2O and 20a of said planes against the air and.

the react-ion of the air againstsaid 'surfaces will sustain: the rear end of the machine on .'the'rein. This construction of the tubular nelements providesthe sides 30a, 30b and '30c I for the element 30 and the sides 31a, 31b'xand 31 for the element 31 which sides provide pressure surfaces which act upon the air in the manner and for the purposes hereafter described.

Steering mtl ole voti-ng flaccms.--F ulcrumed at the uppeil vrear edge of the body 1 directly over the rear end of each of the tubular elements 3() and 31,- and extending rearwardly of the machine, lare the rudders and elevating planes 40 and 41 respectively,

Journaled in the downwardly depending supports 45 rigidly secured to the under frame-work of the body of the machine at the rear end of the body, are the cushioned wheels 46 by means of which the rear of the machine is longitudinally movably supported whenthe machine is upon the ground. J ournaledin the forward ends of the compound curved springs 47 which are securedfat their rearward ends to the downwardly depending support '49, secured to the frame-workof the Y body of the 1nachine,'at the front end of said body, are the cushioned wheels 50, by means of which the front end of the machine is A `longitudinally movably supported, when the machine is upon the ground. The curvature and arrangement of the springs 47 are such as Ito allow considerable backwardly yielding'movement of the wheels 50, when said wheels come in contactwith the ground or any other non-yielding surface, l With the direction of movement of the'rnachine at such inclination tothe ground or other surface that the reaction of the ground or such surface will press 'bacl'iwardly upon said wheels with unusually `great force and violence, whereby the danger of the wheels and front structure of the machine being broken i and also the shock of the impact of the wheels' against the `round or such su-rface,willlfbe reduced to a minimum.

.P1 Welling meclaamsmrThe machine is propelled by the propeller which is mounted in front of the eentral'upper partv of the machine,'on the forward end of the shaft 61, which eXt-endsce'ntral'ly, longi-r tudinally ofthe machine,l and is Journaled in bearings 62 in the upper frame-workV of the body of the machine. The propelliar is driven by engine 63, mounted in the forward part of the machine through sprockets 64 and 65', respectively' on the'dri-ve shaft'66 of the engine, and on the reafend of prochine and is jou-rnaled in bearings 95on tne peller shaft 61,'and chain 67 which runs onA said sprockets.

Controlling means for rudders and eleoat l and elevating planes-40 and 4l by means of i rod 72, bell crank lever 74 and rod 76, and by means 0f rod 73, bell crank lever 75 and 'rod 77. The rod 72 is connected at its respective ends to lever and one arm of bell crank lever 74, which lever is fulcrumed in the lower rear frame-work-of the body of the machine. The vother arm of said bell crank lever is connected to one end of rod 76, the other end of which is connected to the rudder and. elevating plane 40. rod 73 is connected at its respective ends to level 71A and one arm of bell crank lever 7 5, which lever is fulcrumed in the lower rear frame-work of the bod-y of the machine.

vThe other arm of said bell crank lever isl connected to one end of rod 77, the' other The end'ofwhich in connected to the rudder and elevating plane 41.

Controlling means for side and auxiliary planea-The side plane 10 and auxiliary plane 1()a and the side plane 11 and auxiliary plane l1EL are respectively controlled by levers 80 and i81, which are located in the forward end of the compartment 7- of the body of the machine, at the'respective sides of said compartment which correspond to the sides of the machine. to which the side plane 10 and auxiliary plane l()a and the side plane 11 and auxiliary plane 11a are respectively fulcrumed. The levers80 and 81 are ref spectively connected to the side planes 10 and auxiliary planes 10a and the side planes 11 and' auxiliary planes l1a by means'l of eveled gears 84 and '86 shafts u82 and 83, and 85 and 87,

shafts

88 and 89, arms S30-and `

91jandf'rodgs

92 and 93. The lever 80 is `mounted 'ononeend of shaft 82 which is j ournaled in bearings 94 on the lower frameworkof' the machine.

l Beveled gear 84 is mounted" on the other vend of shaft'v82 and" [meshes with 'beveled gear 8,6, which is -mounted on the shaft 88, The shaft 88 ex-` tends longitudinally of the body of the ma- I 1 framework lat the lowerl lside edge lof the body below the lanes 10 and 10s; 'Each of -thefarmsgO is xed to the shaft 88 and is connecte'd:'at vits outer end toa rod 92 which in turn is connected to the planes 10a and 10.

The lever81is mounted on'one end of shaft- 83.which is j ournal'ed in bearings 96, on

the lower franie-work of the machine. ,Bew

and 11. The

rods

92 and 93 are respectively connected to the planes l()aL and l and ll2L and 11 at such points that the lifting and .lowering force applied to said planes will be eqi'xally distributed thereto."

Ati-citons SML- seat 100 is located in the for 'ard end of the compartment 7 upon which the aviator sits to operate the machine.

The operation of my improved monoplane is as follows Assun'iing the machine to be on the ground in the position shown in Fig. 't ofthe ilrawing and the aviator desires to ascend and tly in the machine, he first swings the elevating planes 40 and 41 upvardly in unison with each other upon their fulcrums by means ot levers 70 and T1 and their connections with saidn planes and starts the engine G3, whereupon the machine is propelled.forwardly by the propeller G0;

' as the machine moves forwardly the action of the elevating' planes against the air and the reaction of the air against said elevatingl planes will hold down the rear end of the machine, while theaction lof the air against the forward surfaces l5 and 15a ofthe side and auxiliary planes l0 and il and l()a and llil respectively, under these conditions, will cause the front end of the machine to rise; when the forward end of the machine has lrisen to such posit-ionthatl the machine assumes the desired angle of liight to elevate the machine, the aviator then swings down the elevating planes 4() and 41'by means of levers T() and7l and connections to such angle that the rear end of the machine isheld down with such force that the machine asl cends at such desired angle of flight until the desired altitude is reached, when the aviator swings the elevatingl planes down by said levers into their horizontal positions, whereupon the machine is brought into horizontal ppsition and assumes a horizontal line of Hight.

Vilhcn the aviator desires to turn the machine to the right he swings up the right rudder li() by means of lever TO and its conncctions w ith said rudder, (which lever is in convenient reach of his right hand), whereupon the action of the rudder against the air and the reaction of the .air againstthe rudder will retard the velocity of the right` side of the machine and allow the left side thereof to go ahead atp greater velocity than that of the right side, whereupon the machin-e will swing around to the right. iis'v the machine swings around to the right,`the action of the rudder 40 against the air and ,the reaction of the air against said rudder will cause the right side of the inachine'io` I descend. ln order to maintain the machine in lateral equilibrium, when the right rnd-- der 40 is swung up and the right side of the machine starts to descend, the aviator, by

, means of lever 8l (which is within convenient reach of his left hand) through thev connections between said lever and the side and auxiliary planes 11 and l1a swings said planes upwardly on their fulcrums until theyv assume such an angle, that the areas of the sustaining surfaces of sa id planes will be reduced to such dimensions, that the sus'- .tain'ing power of the left side of the machine will equal that of the right side thereof,whe1eupon the left s'idc of the machine will descend at the same velocity at which the right side thereof descends and on a level with the right side. Up'on returningthe rudder and planes to their initial positions the machine will assume its normal horizontal direction of Hight.

lVhen the aviator desires to turn the machine to the left he swings up the left rude der all `by means of lever 71.(wl1ich is within convenient v reach of his lefty hand) through the connections between said lever and rudder, whereupon the action of the rudder against the air and the reaction of the air against said rudder, will retard the velocity of the left side of the machine and allow the right side thereof to go ahead atv a greater velocity than that of the left side, whereupon the machine will swing around vto the left. As the machine swings around within convenient reach. of his right hand) through theconnections between said lever and the side and

auxiliary planes

10 and 10 swings said planes upwardly on their fulcrums until they assume such an angle, that the areas of the sustaining surfaces of said planes will be reduced to such dimensions that the sustaining power of the right side of the machine will equal that of the lleft side thereof, whereupon the right side of the machine will descend at the same vcloc ity at which the left side thereof descends and on a level with the left side. Upon returning said rudder and planes to their initial positions ,the machine will assume its normal horizontal direction of flight.

. The columns of air which pass through the tubular elements 30 and 3l duringflight of the machine afford great. stability to the v machine. In case either side of the machine should suddenly ascend, .an upward action upon the aircolumn on such side of the machine by the inner surfaces of the sides 30a or 3l;L of the tubular element 30. or 31,

as-the case may be, will be produced, whereupon the downward reaction of- .said air.

column against said surfaces, willcausesaid side of the machineto descend until laterall equilibrium of the machineis restored. Conversely if either' side of. the machine should suddenly descend, a downward action uponv the air column on such side ofthe machine, by the inner surfaces of the sides 301 and 30'c or 31h and 31 of'the tubular element 30 'or 3 1',`as the case may be, will be roduced,

whereupon the upward reaction o .said air column against said surfaces, will cause said side of .the machineV to ascend. until lateral equilibrium of the machine is restored.

The lateral stability afforded by the passage of the air column through the air chambers of the

tubularl elements

30 and 31, is such, for example, that the machine may easily maintain a straight line of light, at a rate of twenty-five miles anhour, in a breeze blowing at a rate 'of twelve miles an hour at right angles to the li-ne ofi-flight, Incase' the machine should dro on: account of failure ofI theengine, orv orv other reasons, and the forward end of the machine, which is heavier than the rear end thereof, shouldv tend to'dropI foremostly,1with the machinein a verticalposition, the aviator, by swinging up hisrear elevating planes Liandfll may swing the forward endofthe machine upwardly to suchnan extent that the action of the air column passing through the tubu- ,

f'lar elements

30 and 31 will attord themachine sutlicient buoyancy endl-stability to.

enable the Amachine to descend longitudinally with the front end foremost, at an angle to the earth, .while the elevating planes 40 and 11 will retard the falling velocity v'of the machine to such an extent that vthe ma.

vchine will descend slowly and safely to the earth with parachute effect. 1 'f The elevating .power of the elevating

f planes

10 and 41 and' the stabilizing power of the

tubular elements

30 and 31 plus the force of gravity, are in such ratio to each other' that 4it is impossible for saidplanes to velevate' the front end of the machine high enough to causethe jmachine to turn overbackwardly.

By means of tubular elements 30 and 31 i the aviator may descend with safety at 4any time, of his ownV volition, at a relatively high velocity, upon stopping the engine entil-ely, or at a relatively'lewer velocity,.gov erned by the speed,A below minimum flying speed. to wil'lli he reduces his engine.

I do nomiimysel to the exact construction herein shown and described as variations' and modifications of myinvention may be made within the scope of the invention.

Havin described my invention I claim: -1. A ying machine of .the monoplane 'type eomprising'a body, a sustaining plane,

propelling means, elevating and steering means, and stabilizing and descending cle- I vices comprising hexaofonal tubular elements open at. their ends an at their 'lower sides,

located at the respective sides of the body`-`l and extending lon 'tudinallythereof.

2. A flying mac ine' of the i monoplane type comprising a body, a's'usta'ining plane c tonsisting of an intermediate stationary section and a side section pivoted to each side lof said intermediate section, 4atubular element located at each side of the longitudivnal center of the" machine and extending longitudinally thereof, a horizontally pivoted rudder located rearwardly of eachA of said.

tubular elements in alinement therewith, operating means respectively for the rightand' for the left rudder, and :operating means respectively for the right and for therleft side section ofthe sustaining planej 3. A tlyin machine comprising a body, a sustaining p ate stationary section, and al side section Vpivoted-.to each side of said intermediate section,l` a`"tubular element located at each sideof the longitudinal 'center o f the machine' and extending longitudinally thereof,

said-:tubular elements being open at their ends and at their under sides, a rudder located in the rear ofeach fof. said elements, operating means respectivelyfor the right and for the leftrudder and operating means for the right-and for the left side sections respectively of the sustaining plane.

. 4; A tlyin machine'comprising a body, a

sustaining p aneconsisting of an interinediate 'stationary ,section and a. vside section pivoted to each side of said intermediate section, va tubular element located at each side ofthe longitudinall center of the machine and extending longitudinally thereof, a rudder located in the rear of each of said tubular elements, operating means respe ctively-for the right-and for the left rudder,

and operating means respectively for the 5.v A flying machine comprising a body, a sustaining plane consisting of an intermedi- `ate stationary section and av side sect-ion ane consisting'of an intermedi- 4right and for the left side section of the sustaining planerespectively for the right and for the left' with, operating means res ectively for the side section of the sustaining plane. right and for the left rud er and operating .6. A flying machine comprising a body, a means respectively .for the right and for the sustaining `plane consisting of an intermedileft side section' of the sustalning plane. .15

5 vate stationary section and a side Section In testimony whereof I h'ave signed .my pivoted to each side ,of saidintermediate name to this specification in the presence of section, a hexagonal tubular element located two subscribing Witnesses.

at each side of the longitudinal center of the ANTHELME DESAYE. machine and extending longitudinally there- Witnesses:

10 of, a rudder located rearwardly of emach of Y T. W. RENNYsoN MECHEW,

said tubular element-s in alinement"there ELIA DESAYE. x