US1049820A - Aeroplane. - Google Patents

Description

A. J, A. DEPBRDUSSIN.

Patented Jam 7, 1913.

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AEROPLANE.

APPLIOATION FILED JAN. 16, 1911.

Patented J an. 7, 1913.

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I Specification of Letters Patent.

Patented'Jan. 7, 1913.

To all whom it-may concern: Be it known that I, ARMANI) lie of France, and'a resident of 9 Rue 'des Entrepreneurs, Paris, France, have invented new and useful Improvements in Aero--' planes, of which the following is a specnication.

My invent-iop relates to aeroplanes and, consists in improvements in monoplane inachines wherein it is Sought to improve and ing and operation thereof.

simplifythe devices which eflect the balanchand wheel journaled "upon a pivotedv column, the wheel'operating by means'of a;

age, the ends of the arms of the bow being pivoted at two fixed points located on either side of the fuselage, one of the arms of-the bridge carrying the cables which" operate the altitude rudder. Such arrangement per- Inits utilization of the rigidity of the main frames to resist the pull of the cables while athe shape of the bridge allows room for the pilots legs. .With this arrangement the controlling cables are separated the whole width of the frame; it is therefore convenient to connect them to the ends of the long horizontal arms of a three-arm lever placed upon the landing frame of the apparatus and havin a short third arm attached to the operatlng cables which pass toward the planes over two ulleys located substantially at the same eight as the end of the short arm. r

The use of a chain wheel or pulley at the bottom of an aeroplane frame which is connected to the planes by chains or cords and controlled by two lever -armsthrough the medium of cords which are led downfrom the operating hand wheel are well-known;-

in the present instance, however, the m rangement of the long horizontal levers,

lpplication flled 1m 16, i911. Serial No. 602,902.

. 1 K I v Q v 1 corresponding to the width of the frame, JEAN AU-' GUSTE DEPERDUSSIN, a citizen of the Repub aild the provision of the-short vertical arm with the guide pulleys whereby vertical reactions are obviated, present especial advantages.

.Thelattice' girder which forms the'main frame or fusela "th'eusual tailmad :tieal planes or flukes at its rear end, while at thearear end of the'frame the steering of the machine carries e up of horizontal and verrudder is pivoted, the altitude rudder being'lo'cated in a cell or compartment of .the

"girder in front of the pivot of thesteering rudder. I

Reference is to be had to the accompanying sheets of drawings forming a part of thisv specification in which similar characters denote'corresponding parts in all the views and in which'- Figure 1 is an eletation of the apparatus; Fig. 2 is a plan view thereof; Fig, 3 is a sectional view on' the line 3.3 of Fig. 1 looking from the left; Fig. 4 is a detail elevation on a larger scale showing the horizontal rudder and the controlling means for tilting; Fig, 5 is a side view corresponding to Fig. 4; Fig. 6 is a sectional view on the line 6-6 of Fig. 4;.Fig. 7 is an elevation of the rear portion of the frame; Fig. 8 is a corresponding plan view.

The "structure consists of a frame, consisting ofa light lattice girder A'- carrying at its front end tiltable lateral wings A and supporting at its rear a tail piece with horizontal and vertical planes or flukes I, J, and the altitude and steering rudders I, J.

At the front of and underneath the frame there is provided a hollow hull B, preferably formed of sheets of wood or metal laid .upon ribs, This hull being located beneath the front of the lattice girder reinforces'the front of the frame and increases its resistance to shocks. It moreover allows forming an opening in the lattice girder to accommodate the aviator, the engine, and tanks. "At the rear end of the lattice girder A (Figs. 7 and 8) an open cell or compartment is provided for the accommodation of the horizontal rudder I; this altitude rudder forms an extension of the horizontal .plane or fluke .I of the tail while the rudder J,-which efiects'the steering, forms an extension of the horizontal plane or fluke I ,steering laterally, forming an extension of the vertical plane orofluke J, being mountedupon the extreme edge of the lattice girder. By this arrangement the rudders constitute surfaces continuous with the flukes and any division or break between these respective surfaces is avoided.

The control of the tilting of the wings and of the rudders is effected in the following manner: In front of the aviators seat is arranged a wheel I) journaled upon a -bridge c of inverted U-shape, mounted upon (i secured to the landing frame; from the lower arm (i two cables e extend, provided with turn-buckles and passingover rollers e to a junction 6 attached to a number of ca- =bles f secured to the cross bar g of the wings of the apparatus (Fig. 3 and dotted lines of Fig. 2). Upon this same cross bar but on the upper side of the win cables f are secured which correspond to t e cables I and lead to junctions which are connected by a cable f which passes over rollers f" fixed to the uprights j which form part of the fuselage.

Upon each side of the bridge 0 loops or bridles c are arranged which have cables 0* leading to the extremities of rods 5 secured to the vertical rudder I. One end of the cables passes directly over a pulley i in order to effect the operation of the rudder in both directions; these cables are guided by means of tubes 2' fixed to the fuselage.

In order to effect the tilting of the ma chine, the aviator turns the wheel b'in the required direction, the three-arm lever swinging and pulling one of the cables 6, while the other slackensthe same amount, the lower cables and upper ones f follow- 1ng this movement and producing the tilting of the wings. To operate the altitude rudder the airman pushes or pulls, as the case may be, upon' the hand wheel 6, the bridge 0 swinging around the ivots 0 (shown in dotted lines in Fig. 5 thereby operating the rudder I by means of the cables 0. This movement of the bridge 0 does not affect the control of the tilting because the cables I) pass substantially through the centers of rotation c in a well-known manner.

The steering or horizontal rudder J is actuated by means of a foot lever j which is pivoted at its center.

Having thus described my invention, I claim as new, and desire to secure by Letters Patent 1. An aeroplane comprising a longitudinal frame having a seat for the aviator near its front end, and lateral tiltable wings, a bridge frame having an inverted U form which spans the main frame and whose legs are pivoted at their lower ends in advance of the aviators seat, the upper end of the ivoted frame being thus adapted to swing orward and back, cables connected with the wings, and a wheel located on the swinging frame and'adapted for access to and operation by the aviator for taking up and slacking the cables, as described.

2. An aeroplane comprising a longitudinal frame, controllable steering devices mounted thereon, a swinging frame pivoted on the main frame, a wheel journaled in said frame, cables operatively connecting the wheel and steering devices, a threearmed lever pivotally carried at the lower portion of the landing frame of the apparatus, the said cables being in engagement with the extremitiesof the two long arms of the said levers, warping or steering cables secured to the short arm of the said lever, the said warping or steering cables passing over suitable pulleys which are located at substantially the same height as the end of the short arm.

3. A monoplane flying machine, comprising a longitudinal frame, said frame consistin of a lattice girder, side planes attache to the front of said frame and adapted to be tilted, cross-bars secured" to said planes, a tail secured to said frame, vertical and horizontal surfaces to said tail, a rudder controlling the elevation, said elevationrudder being in extension of said horizontal surface, a steering rudder, said steering rudder being in extension of said "ertical surface, a structure mounted within reach of the operator, said structure adapted to be tilted about an axis, reciprocal connections from said tiltable structure to said elevation rudder, a hand-wheel mounted upon said structure, a pulley, revoluble by said handwheel, and tensile connections from said pulley to said cross-bars, said connections passing near the tilting axis of said structure.

In testimony whereof I have signed my name to this specification, in the presence of .two subscribing witnesses.

V ARMAND JEAN AUGUSTE DEPERDUSSIN.

Witnesses:

Jacques LEJEUNE, H. C. 00x11.

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