US1216652A - Aeroplane. - Google Patents

Description

A. soHRA's & 'F.QIRIARTE.

AEROPLANE.

APPLICATION FILED APR. e. 191e.

P: Ltented Feb; 20, 1917.

3 SHEETS-SHEET l 3 nnen fofz,

N 21.6% ma) @L L n s N M A. BORR/xs e F. IRIARTE.

AEROPLANE.

APPLICATION FILED APR. 8, 19| i.

1 ,216,652. Petented Feb. '20, 1917.

45 indicate the Wings, 3 indicates the propeller,

UNITED STATES PATENT OFFICE.

AEBOPLANE.

Speciflcation of Letters Pate nt.

Patented Feb. 20, 1917.

Application llled April B, 1916. Seria l No. 89,758.

To allwhomitwza1/.concern. l

le it known that we, ANTONIO BonRs and FERNANno Inrau'rE, citizens of the Republic o Portugal and of Argentina, re spertively. and both residents of the city of menos \ires, Arnentina, have invented certain ne and usetillImprovements in Aeroplanes, of which the following is a specification.

)ur invention relates to an improvement in aeroplanes and has as its object the provision oi' a novel control for the aeroplane rudder whereby a single lever may be actuated to incline the rudder up O1' down or slunting sidewse'in either direction or a combination of such motions. By this means the. aeroplane may be directed up or down or to either side, or directed to climb spirally in either a right or a left hand direction or permitted to volplane downward in a similar way. f

In the following we have described, in connection with the accompanying drawings, a structure illustrating oneI way of earrying out our invention, the features thereof being ino/re particularly pointed out herein-v after in the claims.

` Tn the. drawings Figure 1 is a plan View of a, mono-plane. equipped with a rudder and steeringr =mechal'iism embodying our invention; Fig. 2 is a detail sectional view, on a slightly larger scale, of the rudder operatingY means; Fig. 3 is a central vertical sectional, View of the rear portion of the structure shown in Fig. l. parts being broken away; Fig. l is a view similar to Fig. 3 butin horizontal section; Fig. 5 is a perspective view of the steering mechanism `detached and.

Figs. (l andl 7 detail views of the steeringr mechanism. ,Y

Similar numerals of reference indicate similar parts throughoutthe several views. l indicates the body of the aeroplane, which may be made of any suitable light weight material such as aluminum, ete., 2, 2

parts of driven by any suitable means (not shown), 4, '-1 indicato the sik'levanes and 5 indicates the rudder. 6 indicates a. rod extending transversely of rudder 5 and rotatably jour'- nalod in yoke. 7. -8 indicates a. ,shaft journaled in bearing.4 l) aud l0 in body 1 and attached firmly to .yoke 7, |n'el'erably as shown in Fig. 2, where yoke 7 is shown as provided with a projecting portion llV over which shaft 8, here shown as hollow, lits and to Aable beari lgs in opposite sides which it' may bte-.fastened in any convenient way. 12, 12 indicate ball bearings on which yoke 7"t\ 'rns against bearing 10. 13 indicates a s1' rocket wheel mounted on =the end of sliaft E. 14 indicates the pit of the aeroplane and l5 a seat for the operator. 16 in,- dieates a lever pivoted in'strapu17 at 18. 1E), 1U indicate hollow trnnnions to which strap 17 is firmly attached at each end, the trunnions being rotatably mounted `in suit of the body. 20, 2() indicate. auxiliary levers ixedly mounted on trunnions` 1l), 19. 2l indicates a third al Kilian)r lever fixedly mounted on rod (i in tlze rudder. 22, 22 and 23, 23:1 respectively ind rate connections between the upper ends of levers 20, 2() and the upper end of lever il and vthe lower ends of levers 20,2() and the lower end of lever 21. 24 indicatesl a connection, preferably in the form of an endl rial, fastened 'at 25 to lever L6, running through a portion'of each of hollow trunnions 19, .9, and thence over guide rollers 2G, 2G over sprocket 13. 27 indicates 'a sprocket c lain forming a part of rope 24, passing o\ er sprocket .wheel 13 4and 28 a shield to prevent disengagement of" the sprocket cl ain and wheel.

'In opentiner or directing the rudder a backward 1nd forward movement of lever' 1liw-ill raise the rlulder, through auxiliary levers 20. J and 2l and connections and 23, to be lowered or raisedhorizontally, 1ever 2l beir ,e l'ast on rod (i und rod (l being rotatably nonnted in yoke 7. Point 25, where rop( 2l is fastened to lever 1.6, and point lS where lever 1G is pivoted to strap 17 being at silistantiallyermal distances from the center et' rotation, through trunilions 1l),

1*.) extended, the turned motion moved from point 1S, tl en 'sprocket 13 the rudder is caused to be raised or lowered at its ends according to the' motion given 'zo lever 16. It will also be seen that it' the ever yoke 7 is not actuated to be during.:` the lmckward` and forward of lever 1b'. But if-1evcr 16 is i then shifter` forward'or lmckwa-rd,'wldonib nation of n otions may be given to' therdder. For e mmple, if thel leverlG Vis shifted backward rudder 5 will be depressed horizontally and the air currents striking.,r against the sa me will cause the aeroplane to descend; il" the .lever is shifted forward rud- Y ss llexible rope of suitable mate-` side to side upon its pivotal4 through rope 24 passing over" is moved to either sidealid der will be elevated horizontallyand the f air currents striking against the same will cause the aero lane to rise; if the lever 1s shiftedf'to the eft (in the drawing) the lever standing neutral as to rope 24-that is rudder5 being in a horizontal position, the right'hand end of the rudder willbe depressed and the aeroplane will turn sidewise tothe right; if the lever is however shifted to 'the right under the i conditions las set forth, theleft hand end of the rudder will bede ressedandl-the aeroplane will turn sidewise to the/left; if the lever 16 be shifted backward and tothe left, at the sameftime* the rudder. will be depressed horizontally and depressed at the right hand,Y end, thus' permittin the aeroplane to vol-plane down'- Ward circ ing to the right. `If the lever be shifted forward and to'the -left atthe vsame time, the rudder will `be elevated horizontally. and depressed at the right hand end and the aeroplane will climb spirally` cir-l cling to the right. If the lever 16 be shifted backward and to the right at the same time, .the rudder will be depressed horizontallyl vand depressed -at the left hand end",` thus permitting the aeroplane to vol-plane down-'- ward circling to the left. If the lever -16 he the left. v

I shifted A:forward and to the right at the samel time, the rudder will be elevated` horizontally and depressed at the left hand end 'and the aeroplane will climb spirally`v circling to It is-clear thatwehave provided a rudder 1 control wherein by a shifting of a singlecontrol lever, the 4various motions of the aeree' f plane may be directed and the aeroplane guided as vdesired.

. The particular construction and arrangement of parts is not essential and we do not restrict ourselves to such further than the scope of the appended claims demands.-

We claim: l

- 1. In an aeroplane, a yoke rotatably carriedby the aeroplane body, a rod rotatably journaled in the yoke and extending beyond the same at each end, a* rudder mounted on said rod, a lever fixedly mounted on the rod and a common operating means for con'- trolling the movement of said yoke and rodl either simultaneously on dissimultaneously.

2. In an aeroplane, a rudder suspended to be free to move up and down 'andito be tipped sideWise in. either direction, a control lever,;a strap to which said lever is piv` oted, a pair of rotatable trunnions to which the lends`of said 'strap are fixed, auxiliary levers iixedly mounted on the trunnions, an auxiliary .lever carried by the rudder,-con nections between said auxiliary levers on the trunnions and the auitiliar'y lever on the p mounted on'the rod, a' control lever and con# nections actuated-by the movement of the r control lever to move the 'yokel and the auxiliary lever either simultaneously or dissimultaneously.' p y In testimony whereof we have signed this specification. y

- ANTONIO BORRS.

FERNANDO IRIARTE.

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