US1705904A - Aeroplane - Google Patents

Description

March 19, 1929. E, DAVIS 1,705,904

AEROPLANE '7 Sheets-Sheet 1 Original Filed April 1. 1920 Inn/M109 ATTORNEY March 19, 1929. v s 1,705,904

' AEROPLANE Original Filed April 1, 1920 '7 Sheets-Sheet 2 INVENTO N A TTOR/VEY March 19, 1929. E, v s 1,705,904

AEROPLANE Original Filed April 1, 1920 7 Sheet s-Sheet 3 ATTORNEY E. DAVIS AEROPLANE March 19, 1929.

Original Filed April 1920 '7 Sheets-Sheet 4 INVENTOH Z B774 Z ATTORNEY March 19, 1929. E. DAVIS 1,705,904

AEROPLANE Original Filed April 1, 1920 7 Sheets-Sheet 5 72 Z1 0 I 66 J5 it? 60 I? 17" 74 1 f2 76 2,? 44 3 22 7 7a Z4 6, O I 24 i F 6; r fig? ATTORNEY March 19, 1929. E, DAVIS 1,705,904

AEROPLANE Original Filed April 1, 1920 7 Sheets-Sheet 6 A TTORNEY March 19, 1929. E. DAVIS 1,705,904

AEROPLANE Original Filed April 1920 '7 Sheets-Sheet '7 INVENTOR A TTORNEY Patented Mar. 19,1929.

UNITED STATES" PATENT-J'QFHCEQ.2'

array DAVIS, or crmwa'raa, aroma.

Rome for abandoned application Serial This invention relates to aeroplanes and particularly toapparatus of this class employing main lane sections disposed at pendent aeroplane units or sections coupled to provide an aeroplane which may, at will,

together to form a unit apparatus, and the object of the invention is to provide an'apparatus of the class employed which by reason of its construction will increase the safety and efficiency thereof a further objectbeing be increased or reduced in size with respect to an increase or decreaseof passengers and power of the machine; a further object being to provide means for controlling the operation of the aeroplane and its several units from one or more positions on the apparatus; a further object being to provide eflicient automatically operating means formaiintaining the equilibrium of the machine; and

a still further object being to provide means for effecting corresponding and differential mechanisms of the different plane units employed in a multiplane machine, and with these and other objects in view the invention consists in an aeroplane of theclass-and for the purpose specified, which is simple in construction and operation and efficient in use, and which is constructed as hereinafter described and claimed.

The invention is fully disclosed in the following specification, of which the accompanying drawings form a part, in which the separate parts of my improvement are designated by suitable reference characters in each of the views, and in which Fig. 1 is a side elevation of a multiplex.

aeroplane or multiplex machine comprising two duplex machines.

Fig.2 1s a fragmentary pla'n vlew of one of these units, the canvas covering of one of;

the planes being omitted.

' Fig. 3 is a front elevation of the multiplex machine.

Fig. i is a detail fragmentary side eleva tion, on a larger scale and show ng the steer-.

ing mechanism at one of the pilot seats.

Fig. 5 is a plan view of the same.

Fig. 6 is a front elevation of the parts shown in Figures 4 and 5. 4

Fig. 7 is a fragmentary detail sectional view, taken on the line 7- -7 of Fig. 3 and looking in the direction of the arrow at said line.

application, and A r l 1,

I Fig. 8 is a detail side view of the steering device and certain of the controlling devices at anotherpilots seat. Fig. 9 is 'a top lan'view of-the same. Fig. 10 is a ront elevation of the parts shown in Figs. 8 and 9.

Fig. 11 is a detail fra showing the steering mec wheelsof the machine.

' Fig. 12 is a diagrammatic view of one of the planes and correspondin toa section taken on the line 12-12 of Fig. 3 and look- 111%111 the direction of the arrows at said line.

ig. 13 is a diagrammatic side elevationof. one of the planes and its rudder or steering plane, and showing the manner of mounting and connecting the same.

. The aeroplane, shown for the purpose of illustratingone .method of carrymg my invention' into effect, is composed ofa plurality entary plan view, anism for the front of similar units, and to facilitate matters I W111 first describe the parts of one "unit and later set out the means or connected units to producejwhat I term a multiplex aeroplane.

sides 2, and a bottom suitably connected and braced. Each body, in the construction shown, is provided with two pilot seats 3v and 4 arranged fore and aft of the machine.

An engine 5 is carried at the front end for driving a propeller 6, and an engine 7 at the rear end for'driving-a propeller '8 Wheels 9 are also provided for supporting the lowermost body, shown in the" accompanying drawing, on the ground. or other surface to permitof-the starting as well as the landing of the aeroplane. The front wheels ,of the aeroplane may be steered in a manner later described. I

Each unit part of the aeroplane, which may be termed a duplexunit, comprises two main sup orting planes arranged on opposite sides of t e fuselage or body atthe front and rear, thereof, and each of these planes are alike, except that they are oppositely arranged, and the description of one will suffice for all. j

Each plane or wing is designated, as a whole, by the reference numeral 10 and comprises a rigid frame which is substantially triangular in cross sectional form (note Fig. 7). Each frame is made up with three longitudinally extending members 11 of light shaped in cross section throughout the maj or portion of their length to form integral webs 14, which prevent the ribs 13 from bending (note Figs. 2 and 7). At the rear ends of the ribs 13, the webs taper downwardly as indicated at 15, leaving flat resilient ends 15, which when the ribs 13 are composed of spring steel will be highly flexible as indicated in the drawing.

The tip of each plane is formed of five comparatively small feather sections 16, 17, 18, 19 and 20, each being formed in substantially the same manner with the ribs 13 and having flexible or resilient ends. The framework of each plane or wing iilcludin its feathers is covered with canvas or -otier suitable material as is usually the custom.

Each plane or wing extends upwardly and outwardly from the fuselage at an inclination, as seen in Fig. 3 of the drawing, and a number of the cross rods 12 are provided with coupling sleeves 21 by means of which the plane is connected to and mounted to turn freely or rotate on a supporting arm 22 (note Figs. 6 and 7 said arm being composed of steel tubing and is supported and braced to'the fuselage by struts or members 23 and 24 respectively. Each arm 22, therefore, constitutes a pivot bearing that extends transversely of the machine and on which the plane is mounted and free to oscillate.

As seen in Fig. 7 of the drawing, the sleeve 21 is provided with asleeve-like clamp 25 extending at right angles thereto and adapted to receive a rod 12 of the associated plane frame and permitting said rod to be adjusted longitudinally of the sleeve, thus providing fora fore and aft adjustment of each of the planes 10 with reference to its pivot 22, so that the desired balance or equilibrium between the parts of the plane in front and back of its pivotal center may be obtained. Suitable means such as bolts 25 (Fig. 7) may be employed to secure the clamps 25 on the rods 12 in different positions of adjustment. F ixedly connected to and extending rearwardly from the frame of each plane 10 are two parallel rods 26 formed of tubing or other suitable material, the rear ends of said rods being united by a cross bar 27 and a pivot rod 28 turns in bearings in the outer ends of the rods 26. The rod 28 extends transversely of the machine at about the same inclination as and parallel with the associated pivot arm 22, and constitutes a pivotal support for the frame of a rudder steering or guide plane,

designated as a whole by the reference numeral 29.

The steering planes 29 are controlled from the pilots seat 3 by a steering mechanism best seen in Figs. 4, 5 and 6 of the drawing, said mechanism comprising a vertically disposed steering wheel 30' fixed to ashaft 31 which tions in a bearing in an upright arm or steering post 32. The shaft 31 carries a sprocket wheel 33 and sprocket gears 35 and 39 are mounted to turn freely on the end portions of a spindle 36 fixed to the arm 32 and seated in a bearing in a supportingbase 37 and an idler sprocket 38 is rotatably mounted on the arm or steering post 32. An endless sprocket. chain 34 passes around the wheels 33 and 38 and the sprocket gears 35 and 39, in the manner seen in Figs. 4 and 6 of the drawing, to transmit the rotative motion of the steering wheel to the gears 35 and 39 and to the parts controlled thereby.

.The gear 35 has oppositely disposed sectors or sheaves 40 and 41 movable therewith, and

the gear 39 has corresponding sectors or sheaves 42 and 43. These sectors are connected to the front steering planes 29 on opposite sides of the fuselage by cables which give complete control of said planes without interfering with the-freedom of the supporting planeslO to turn on their own pivots 22.

Thus, a cable 44 is secured at one end, as at 45 in Fig. 4, to the sector 40 and the opposite end attached to the lower end 46 of a cross arm 47 secured to the frame of the forward lefthand steering plane 29 (note Fig. 13). The arm 47 is braced by strut-s or trusses 48 and 49.

The cable 44 in extending from the sector 40 to the cross arm 47 passes over-the guide pulley 50, Fig. 13, supported on the-rod 26, over pulleys 51 (Fig. 13), 52, 53, (Fig. 2), 54 and 55 (Fig. 4), it being observed that the pulleys 51 and 52 are arranged substantially coincident with the associated supporting rod 22 so that a length of the cable extends close to this rod, and'that portion of the cable which extends rearwardly of the pulley 51 may turn with the associated plane 10 Without interference with the cable.

In a like manner a cable 56 extends from the sector 41 over pulleys 57, 58. 59 (Fig. 4),

60 (Fig. 3), 61 and 62 (Fig. 13), the posiand the same references are employed to dis tinguish corresponding parts at opposite sides of the machines.

for two pilots, one to occupy the seat ,3an

another the seat 4. The steeringmechanism infront of the pilot seat 4 is essentiallythe same as that previously described, as are also the cable connections to the steering planes, etc., except that the cables pass up to the steering planes in the rear of the ilot seat instead of in'front thereof, and t e corresponding parts of the two constructions are designated by like reference numerals, thus further description of the planes mounted at the rear of the machine and the manner of controlling them from the seat 4 is deemed unnecessary.

I also preferably employ means for con-- pling the steering mechanisms of the seats 3 and 4 so that the operation of the steering planes at the front and rear of the apparatus, may be controlled from either one of the seats 3 and 4. This result is accomplished by a cable 64 (see Fig. 4) secured at one end tothe endless sprocket chain 34 passing down under a pulley 65 and over another pulley 66. These pulleys are mounted on a bracket arm 67 secured to one'end of the associated spindle 36, which it will be remembered is fixed to the steering post 32 and turns in the bearing 37, when the wheel is rocked back and forth. The passage of the cable 64 over said pulley, as stated, bringsthesame substantially to the axis of the spindle 36 thus the swinging movement of the wheel 30' has no effect on said cable, except to turn the upper part thereof a y a pulley 68, over a pulley 69 (Figs. 1 and 6) and around pulleys of the steering mechanism which correspond to the pulleys and 66 hereinbefore described, and then passes to a point of connection with its chain to the rear of the associated gear 35, as indicated at 70 in Fig. 6. The front end of the cable 64 is connected with the forward chain 34 in front of the gear 35 and intermediate said gear, and the gear 38, whereas the rear end of said cable is connected to the rear chain 34 in the rear of the gear 35 and between it and the gear 38. In like manner. a cable 71 is connectcd atits forward end to the front chain 34 and at its rear end to the rear chain 34 of the rear steering mechanism, and the effect of these connections is to produce a corresponding rotative movement of both fore and aft steering wheels when either is turned, and to effect a simultaneous and corresponding movement of the'steering planes against pivotal movement, and as" seenin 'Fig. 7 each frame which carriesa plane 10. has fixed thereto, a toothed sector, 7 2 having notches 73, and the center or axis of the arc of thissector corresponds with the p votal vided means for securing each plane 10 I axis of the associated frame of the plane 10. y

A housing74 secured-to the brace 24 receives a bolt 75 formed with a shoulder or flange 76 against which one end of a coiled spring 77 bears, the opposite end of the spring bearing against the ottom of theliousing, thus tending to force the bolt into one of the notches 73, and when the-bolt 75 is within one of the notches 73, the sector and frame which carry it are locked to a part of the body or fuselage, and the plane 10 is retained against. oscillation. It will also be understood that the plane against movement in any angular relation assumed thereby, when the aeroplane is in operation. In order that the bolt 75 may be controlled atwill by a pilot, I connect a cable 78 withthe bolt and pass the cable over pulleys 78,

80, 81 and 82 and secure the opposite end of the cable to a lever 83 pivoted at 84 to one side of the pilots seat 3. The'lever is provided with a handle 85 and a suitable catch 86 on the seat 3 and engages the lever to retain the same in position against the tension of the spring 76 to retain the pulley 75 in inoperative position as shown in Fig. 7.

It will be understood that each forward plane 10 is provided with a similar latch and corresponding cables, bearing the reference numeral 78, and extending over similar pulleys and merge into a single cable as indicated gt 7 8" in Fig. 5, and from this point the lever '83 of the cable passes as a single strand or member, so that the handle simultaneously controls both bolts of the two front planes and if desired similar bolts may be controlled supcrposing a second complete duplex plane above that already described. andwhich corresponds in all essential particulars withtha't previously described thus forming a multiplane, including eight planes 10 and their associated steering planes 29 and two fuselage or body portions and four engines and four pilots seats, and like reference numerals are applied to each of the upper andlowerduplex units.

The frames of the two duplex units are detachably, though rigidly, united by four upright stanchions, two of such stanchions 87 connecting the frames. at the forward parts thereof and two stanchions 88 connecting the .frames at the rear ends thereof, it being the frames of said planes. In like manner,

corresponding upper and lower steering planes 29 are united by rods 90 thus maintaining the planes of the two duplex machines in parallelism at all times and enables an operator on either machine to control the steering and supporting planes of the other machine without any connection between the steering gears of the two machines other than the rods referred to.

In addition to the construction thus far described, I may also employ means for automatically controlling the rear planes, but this means need not necessarily be employed, eflicient control of the machine being afforded without it.c However, from an inspection of Fig. 1, it will be seen that the automatically operated means referred to, comprises a pendulum consisting of parallel depending rods 91 pivoted at their upper ends, as at 92, to the upper body or fuselage and carrying a weight at the lower end thereof. The weighted end of the pendulum may, for example, be in the nature of a basket or container 93 connected to the rods 91 to swing therewith fore and aft of the machine, the pendulum being fixed against swinging movement in any other direction. The basket may form a seat for one or more persons, or the pendulum may constitute a container for gasoline, supplies or freight. A cross bar 9 1 (see Fig. 10) rigidly unites the pendulum rods 91. near the upper ends thereof and has pivotally connected thereto about midway of its length a horizontally disposed link or rod 95. The opposite end of this link is pivoted at 96 to the lower end of a lever 97, pivoted at 98 to an arm which depends from the steering post 32 of the upper rear steering wheel, as best shown in Fig. 8. The lever 97' has a yoke 99 formed integral therewith, one arm of the yoke extending in front of the pivot or spindle 36* of the steering post 82 and the other arm of the yoke extends to the rear of said spindle (note Fig. 8). The upper ends of the arms of the yoke 99 are connected by a segmental bar 100 provided with a centrally located notch 101 in the upper edge thereof.

A spring-pressed bolt or lock 102 is carried by the post 32 of the steering wheel and is provided with'a finger piece 103 by which it may be lifted against the force of its spring to disengage the boltfrom the notch 101. A

matically engages and holds the bolt in the elevated position when it is lifted to release it from the notch 101.

It will be understood that with this construction, an oscillation of the pendulum, when the lock 102 is released, has no effect on the steering gear, the same being wholly under the control of the operator. ,This is due to the fact that an oscillation of the pendulum merely results in turning the lever 97 with the yoke 99, the bar 100 forming part thereof, around the pivot 98 without effecting the steering gear. When, however, the bolt 102 engages the notch 104, the lever 97 is locked to the steering post and a movement of saidlever will cause it and the post to receive a pivotal movement around the axis of the spindle 36, and the pendulum action will be transmitted to the steering mechanism to automatically raise or lower all of the steering planes at the rear of the machine to automatically maintain the rear end of the machine on a level with the front end thereof.

I also preferably emplov means for steering the front wheels 9 of the apparatus. Re-

ferring particularly to Figs. 3 and 11, it will be seen that each of the front wheels 9 is mounted on a short spindle 105 pivoted at 106 to turn on a vertical axis. spindles are connected toturn together by a cross rod 107 pivoted at its ends to forwardly extending arms 108 on said spindles. One end of a cable 109 is connected to one of said arms 108, the opposite end of the cable being connected to one end of a cross head 110,

'pivoted midway in the length thereof and provided'at its ends with foot pieces 111. The cable in passing through the arm 108 to the cross head passes over a pulley 112. A second cable 113 is connected in a like manner to the other arm 108 and to the opposite end of the cross head providing simple means by which the operator in the forward lower-most seat of the machine may control, by the use of his feet, the guidance of amachine when traveling over the ground.

As herein set out any desired number of separate duplex machines may be readily connected to constitute a multi-plane or multiplex aeroplane, each duplex machine being complete in itself and constituting" an acreplane which may be operated separately, or in combination with other units connected therewith. In the present instance, these units are shown mounted one above another The two.

locking latch 104 is provided which autobut it will be apparent that any suitable or control all of the steering of a duplex ma chine. The effect of tilting the rear ends of the pairs of steering planes upwardly in unison will cause the rear end portion of the lanes cariiying such steering planes, to move ownward y around the axis of the arms 22,-

causin the front end of such planes to move upwar lythus causing an upward fli ht of the machine with'the fuselage in su stantially horizontal position. A reversal of this movement or.operation of all the units alike will cause the machine to move downwardly.

ward and backward bodily movements of the steering wheel, whilethe second named operation is accomplished by the rotation of the wheel which will be apparent. In both of the above described operations, the movement of the steerin wheel is transmitted to the steering planes tlirough the several cables employed which are mounted and coupled in the manner hereinbefore set out. It will also be understood that a machine may be operated in a combined operation of the steering wheel, that is'to say, the combined forward or backward and rotary movements elevate the machine and turn at the same time, or to lower the machine or aeroplane and turn in either direction at the same time,

and by virtue of the construction described the possibility of soaring of the entire machine without the use of motor power, or with the use of comparatively little motor power may be accomplished, and in all operations of the machine,the feathers havirng flexible end portions aid in the soaring or other operation of themachine.

As previously stated, oneor more units may separately or collectively actuate the machine, and the machine may be used for instruction purposes, a student pilot operating from one driving seat and a master or expe'rienced pilot controlling machine opera-- tion for correcting faulty operations of the student pilot at will, thus renderin the apparatus practical for all purposes or which the same is intended. It will also be apparent that my invention is not necessarily limited to the use of any particular number'of motors or other power plants, nor am I necessarilylimited to the specific combination or arrangement of units'herein shown and described nor to the manner of coupling said units together, and still further my invention is not necessarily limited to the specific structure of the plane units herein set out, and various other changes in and modifications of theconstruction herein shown and described maybe made, within the scope of the appended claims, without departing from and the steering planes at the opposite the spirit of my invention ,or sacrificing its advantages. j -Hav1ng fully described my invention, what I claim as new and desire to secure by Letters Patent, is

1. An aeroplane comprising a plurality of connected units, each constituting in itself a complete independently operable aeroplane,

.the units being arranged one above another and each unit constituting a duplex aeroplane having two sets of pivoted planes arranged fore and aft of the machine, and connections between the corresponding planes which are arranged one above another on the difierent units so that the planes may turn on their pivots in unison.

2. An aeroplanecomprising a plurality of connected units, each constituting in itself a complete independently operable aeroplane,

the units being arranged one above another and each unit constituting a duplex aeroplane having two sets of pivoted planes arranged fore and aft of the machine, connections between the corresponding planes which are arranged one above another on the different units so that the planes may turn on their pivots in unison, and operative connections between said planes on the same unit.

3. An aeroplane comprising a pair of steering planes, a steering wheel mounted to turn on-its own axis and also to receive a bodily movement, intermediate connections between said steering wheel and said planes whereby they will be moved simultaneously in the samedirection by a bodily movement of said wheel and will be simultaneously moved in opposite directions when the wheel is turned on its own axis, a second pair of steering planes similarly controlled by a second steering wheel, intermediate connections between said wheels and by which a turning movement of 4. A machine of the class described comprising two or more aeroplane units having front and rear supporting planes disposed at opposite sides of the body of the aeroplane, and each of said supporting planes being supported on pivot means to move freely relatively to each other.

5. A machine of the class described comprising two or more aeroplane units having front rear supporting planes, disposed at opposite sides of the body of the aeroplane, each of said supporting planes being'supported on pivot means to move freely relatively to each other, and means for adjustably supporting said pivot means.

6. A machine of the class described comprising two or more aeroplane units having front and rear supporting planes disposed at opposite sides of the body of the aeroplane, each of said supporting planes being supported on pivot means to move freely relatively to each other, and manually operated means for locking each of said planes against movement at will. I

- 7. A machine of the class described comprising two or more aeroplane units having each of said supporting planes being support-' ed on pivot means to move freely relatively to each other, manually'operated means for locking each of said planes against movement at will, a steering plane supportedby each of said first named planes, and manually controlled means for operating the steering planes to control saidsupporting planes.

9. A machine of the class described comprising two or more aeroplane units having front and rear supporting planes disposed at opposite sides of the body of the aeroplane, each of said supporting planes beingsupported on pivot means to move freely rela tively to each other, manually operated means for locking each of said planes against movement at will, asteering planesupported by each of said first named planes, manually controlled means for operating the steering planes to control said supporting planes, said last named means involving independent controls for the separate steering planes.

10. A machine of the class described comprising two or more aeroplane units having front and rear supporting planes disposed at opposite sides of the body of the aeroplane, each of said supporting planes being supported on pivot means to move freely relatively to each other, manually operated means for locking each of said planes against movement at will, a steering plane supported by each of said first named planes, manually controlled means for operating the steering planes to control'said supporting planes, said last named means involving independent controls for the separate steering planes, and means for coupling all of said controls whereby all steering planes may be actuated from a single control. r

11. A machine of the class described comprising two or more aeroplane units having front and rear supporting planes disposed at opposite sides of the body of the aeroplane, each of said supporting planes being supported on pivot means to move freely relatively to each other, and the rearand outer side edges of said planes being capable of automatic flexing in ,the operation ofthe aeroplane.

12. An aeroplane comprising multiplane structure, consisting of two duplex units each unit having front and rear aeroplane bodies bodies provided with independent power' plants, and said bodies being joined in a common fuselage.

14. An aeroplane comprising a multiplane structure, consisting of two duplex units, each unit having front and rear aeroplane bodies provided with independent power plants, said bodies being joined in a common fuselage, said units'being arranged one above the other in spaced relation, and means for coupling said units to ether.

15. An aeroplane comprising a body portion, main supporting planes movably supported at oppositesides of said body portion and adapted to change the angle of incidence with respect thereto,frames rigidly supported on said planes and extendingrearwardly of the central portion thereof, steering planes pivoted to the rear end of said frames and means under the control of the operator for chang ing the angle of incidence of each of said steering planes irrespective of the angular position of the supporting planes, means under the control of the operator for locking the supporting planes and said frames against relative movement to saidbody-portion, and

16. An aeroplane comprising a body por tion, main supporting planes movably supported at opposite sides of said body portion and adapted to change the angle of incidence with respect thereto, frames rigidly supported on said planes and extending rearwardly of the central portion thereof, steering planes pivoted to the rear ends of said frames and means under the control of the operator for changing the angle of incidence of each of said steering planes irrespective of the angular position of the supporting planes, means under the control of the operator for locking the supporting planes and said frames against relative movement to said body portion, said supporting planes and steering planes being inclined upwardly with respect to the longitudinal plane of said body portion, and brace members extending later ally fromopposite sides of the bodyportion to said main supporting planes and the frames thereof for bracing the same.

17. An aeroplane comprising a body portion, main supporting planes movably supported at opposite sides of said body portion and adapted to change the angle of incidence with respect thereto, frames rigidly sup-' ported on said planes and extending rearwardly of the central portion theerof, steering planes pivoted to the rear ends of said frames and means under the control of the operator for changing the angle of incidence of each of said steering planes irrespective of the angular position of the supporting planes. means under the control of the operator for locking the supporting planes and said frames against relative movement to said body portion, said supporting planes and steering planes being inclined upwardly wlth respect to the longitudinal plane of said body portion, and said main planes being ad justable forwardly and backwardly with re spect to said body portion on their pivotal supports. p v I 18. An aeroplane comprising a body portion, main supporting'planes movably supported at opposite sides of said body portion and adapted to change the angle of incidence with respect thereto, frames rigidly supported on said planes and extending rearwardly of the central portion thereof, steering planes pivoted to the rear ends of said frames and means under the control of the operator for changing the angle of incidence of each of said steering planes irrespective of the angular position of the supporting planes, means under the control of the operator for locking the supporting planes and said frames against relative movement to said body portion, said supporting planes and steering planes being inclined upwardly with respect to the longitudinal plane of said body portion, and said planes having rear and side edge portions capable of automatically flexing in the operation of the machine.

19. In an aeroplane of the class described,

a fuselage body, plane units each consistin of supporting and steering planes disposed at tions of said body, each unit being independently movable with respect to thebody to maintainsaid body in substantially horizontal position when the aeroplane is in flight and in the operation of ascending and descending, and the steering planes of said units being "manually and automatically controlled to automatically control the operation of said ,gsupporting planes.

21; In an aeroplane of the class described, a fuselage body, plane units each consisting of supporting I and steering planes disposed at opposite sides and front and rear end porti'ons of said body, each unit being independently movable with respect to the body to maintain said body in substantially horizon- .tal position when the aeroplane is in flight and in the operation of ascending and descending, the steering planes of said units being manually and automatically controlled to automatically control the operation of said supporting planes, and said steering planes being mounted on frames rigidly coupled with the supportin planes.

In testimony that claim the foregoing as my invention I have signed my name this 2nd day of April, 1927.

' EMRY DAVIS.

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