US1169883A - Aeroplane. - Google Patents

Description

H. T. STOKES.

AEROPLANE. APPLICATION FILED MAR. 9, 1910. 1,169,883.. Patented Feb. 1, 1916.

2 SHEETS-SHEET I.

H. T. STOKES.

AEROPLANE.

APPLICATION FILED MAR. 9. 1910.

1,169,883.. Patented Feb. 1, 1916.

2 SHEETS-SHEET 2.

zventor: 77261165565 Harlaw 7? Makes,

WM 1 av his Attorneys,-

-HARLOW T. STOKES, OF NEWARK,

NEW JERSEY.

AEROPLANE.

Specification of Letters Patent.

Patented Feb. 1, 1916.

Application filed March 9, 1910. Serial No. 548,156.

To all whom it may concern:

Be it known that I, HARLOW T. STOKES, a citizen of the United States, residing in Newark, county of Essex, and State of New Jersey, have invented certain new and useful Aeroplanes, of which the following is a specification.

This invention is an aeroplane embodying a novel construction and organization of planes whereby increased weight sustaining or lifting power is secured, coupled with a reduction of resistance to the air during flight, suitable provision being made for controlling the planes at the will of the aviator in order that the craft may be steered in any direction, and at a desired elevation, so as to sail with or against the wind or air pressure.

An important feature of the invention resides in the main or weight-sustaining planes, comprising preferably three planes so disposed with relation to each other as to produce a space between them. Two of said planes extend outwardly from Y the main frame or car of the craft, said planes meeting each other at their inner ends so as to produce a dihedral angle, or the inner end of one plane may be spaced relatively to the corresponding end of the other plane, the angle being the same in either arrangement. The third plane is positioned above the two inwardly converging (or outwardly diverging) planes just mentioned. so that the third plane extends across the adjacent or meeting ends of the two first named planes; and said third plane may be joined at its end portions to the outwardly diverging planes at points intermediate the ends of said latter planes, but it is preferred that the end portions of the third plane be spaced; relatively to said outwardly diverging planes, it being obvious that the ends of said third plane should be connected, as by struts, to the diverging planes. It is preferred to curve each of said three planes, that is to say, ach plane is curved from end to end, or longitudinally, and, furthermore, each plane is curved transversely, or from front to rear. The use of the third plane in conjunction with the two outwardly diverging planes increases area of surface for wind or air pressure by reason of the fact that the under surfaces of all the planes are exposed, and said surfaces are curved both longitudinally and transversely so as to secure the maximum effect of wind or air pressure upon said surfaces.

Another part of the invention consists of" auxiliary planes, preferably triangular in shape, positioned at the rear of two of the main planes and controllable separately at will for the purpose of turning said auxiliary planes at an angle to the main planes.

Another part of the invention consists of wing tips positioned at the outer end portions of two main planes. Said wing tips are controlled by the operator, and according to my invention, they move in unison with each other, to the end that said planes may both be moved downward simultaneously, or upward simultaneously, whereby the wing tips are controlled at the will of the aviator. The object of said wing tips is to alter at will the end portion of each main plane with respect to the general shape thereof, viz., forming as they do a continuation of each main plane and drawn downward slightly below the level of the end of said main planes, thetotal lateral curvature of the under side of each main plane A B is increased. When raised slightly above the end of each main plane, the total lateral curvature of each main plane is decreased, it being understood that these wing tips are designed to be moved to a position determined by circumstances to'be the most efiicient in effect in securing the lateral balance of the machine due to certain weather conditions, winds, and the direction of the wind with reference to the direction of flight, and after being so set the wing tips remain in such positions until the conditions of the wind, weather or flight require a different setting with reference to the angle of the under curvature of each main plane. From the nature of the connections, said wing tips cannot be used as lateral stabilizers alone, as they act equally on each side of the machine atone and the same time. Any suitable locking device, such as a sector and pawl (not shown), may be used to lock the controlling lever for the wing tips in any desired position, and thereby, also, through the cable connections lock the wing tips in the desired position for the moment.

Another part of the invention consists of elevating planes positioned in advance, and to the rear, of the main planes, each of said scend.

The invention consists, also, of auxiliary planes positioned in front of the main planes, said auxiliary planes being at opposite sides of the front elevating plane, and said front auxiliary planes being connected operatively with the rear auxiliary planes for simultaneous movement therewith when the auxiliary planes are shifted by the aviator.

It is obvious that the auxiliary planes positioned in front of the main plane and on each side of the center of the aeroplane may be changed in position without altering the purpose or use of this part of the invention.

Various other parts of the invention not heretofore mentioned will appear in the course of the subjoined description.

In the accompanying drawings I have illustrated one practical embodiment of the invention, but the construction shown therein is to be understood as illustrative, only, and not as defining the limits of the invention.

Figure 1 is a front elevation of my new aeroplane. Fig. 2 is a side elevationthereof. Fig. 8 is a plan View, and Fig. 4 is a detail cross section onan enlarged scale and in the plane of the dotted line 4-4 of Fig. 3.

The weight-supporting elements of my aeroplane consist of three main planes, A, B, C, which are associated with a suitable frame, D, adapted to support a car, E, when the craft is in flight.

In one embodiment of the invention an engine or motor of any suitable type, indicated by the reference character, F, is positioned within the forward part of said car,

and to the shaft,

of this motor are geared counter shafts, f

which extend outwardly to the shafts, F, of propellers, F the latter being positioned at opposite sides of the longitudinal axis of the craft, and forwardly of the weight-supporting planes.

Said planes, A, B, G, constitute an important part of the invention. Planes, A, B, extend outwardly from frame, D, at the respective sides thereof, it being preferred to extend the inner ends of planes, A, B, to the axial line of the craft, although said inner ends of planes A, B, may be separated so as to leave an intervening space between said ends, whereby the inner ends or roots of planes A B may be attached to the side portions of a central car or fuselage of the aeroplane. Planes,

vmay be attached to some A, B, are shown in thereof, and, furthermore, each plane is.

curved transversely, or from front to rear, the longitudinal curvature of said planes being clearly shown in Fig. l, and the transverse curvature beingindicated in Figs. 2 and 4. v

It will be understood that the shape of the planes just mentioned is illustrated diagrammatically as a single surface in the drawings for the sake of clearness only. As a matter of construction, however, these planes are composed of skeletonized framesv covered on the top and bottom with suitable material, each main plane being shaped so as'to produce a plane of the bird-wing type, the same being essentially a natural and proper way ofobtaining the most efiicient results in lifting power and natural stability. The planes A-B are shown as having a variable curvature from end to end anda variable curvature from front to rear, said planes being substantially free from obstructions to the passage of the air at this point, and said bird-wing type of plane securing a mechanical wing of the greatest efficiency for lifting purposes, stability in flight, and minimum resistance to the forward progress of. the machine through the am tion, being of arched form and possessing a moderate curvature, a curve of about .18

inches in 16 feet having been found to be most efficient. The end portions of the plane C are open or spaced with respect to The third plane C is similar in-construc- I planes A B to facilitate the free passage of air both laterally and horizontally. It is apparent that the end portions of plane 0 portion of planes A B intermediate the ends of the latter, as for example by struts, braces, or other suitable means, such as D in Figs. land 2.

It will be understood that all the planes including the ailerons and wing tips are providedwith double covered surfaces, each being composed of a skeleton frame covered on both sides with suitably treated or varnished fabric, metal sheets, or other suitable covering. i

The plane C is positioned in such relation to planes A B that the end portions of said plane C are spaced relative to planes A and B to allow the free egress of air over said planes A and B and beneath the end portions of plane C.

As best shown in is tapering in shape, each plane being at the inner end thereof. The front edge, a, of each plane, A, B, C, is at a right angle to the longitudinal axis through the craft, but each plane, A, B, is provided with an inclined rear edge, a, the latter extending at an angle to the longitudinal axis of the craft so as to produce a plane which in plan view decreases in width from the inner end toward the outer end, the outer end of said plane being thenarrower. Plane, C, is provided with a front edge, 0, which is at a right angle to the longitudinal axis of the craft, as shown in Fig. 3, but the rear edge, 0', of said plane, C, is slightly convex, thus resulting in a plane possessing the curvature characteristic of a bird wing.

G, G are auxiliary the rear of main planes, A, B, said auxiliary planes being hinged directly to the main planes, as at g, whereby the auxiliary planes are carried by the respective main planes, and said auxiliary planes are adapted for move- Fig. 3, each plane, A, B,

ment up and down at the rear of the main planes. The auxiliary planes are precluded from moving upwardly above the main planes, A, B, by certain stop devices, herein shown as cords or cables, g, attached to the auxiliary planes and to certain arms, 9 Furthermore, the auxiliary planesare normally lifted by the action of springs, y all as shown diagrammatically in Fig. 4:. The auxiliary planes cooperate with the main planes, A, B, to substantially increase the area of the weight-supporting surface, but said auxiliary planes serve the important function of retarding planes in order to assist in arresting the motion of the craft when sweeping downward toward the earth prior to coming to rest so that the operator may alight. For this purpose the auxiliary planes are controllable at will, and, as shown in Fig. 3, certain operating cables, g, are attached to the free rear edges of said planes. The cables, 9*, g, g, gflthe ends of said operating cables eing attached to knee levers, G G which are within convenient. reach of the aviator adapted to occupy the cock pit, e, of the car, E, see Fig. 3. The knee levers are operated independently by the aviator, but it is apparent that the knee levers may be operated simultaneously so that at and while alighting and running along the ground both ailerons may be brought down at a right angle to the main plane,.thus producing a resistance to the forward movement of the machine, and securing the effect of a wind brake.

the widest portion of ciated the operating cables,

planes positioned at extend over guide pulleys,

the end of a flight Extending upwardly from the bow of the car, E, is a suitable supporting frame, h, and rising from the rear or stern part of the car is another supporting frame, 71., see Fig. 2. On these frames h, h, are supported elevating planes, H, H, which are positioned in front and rear, respectively, of the main or weight-supporting planes, A, B, C, and the auxiliary planes, G, G. Each plane, H, H, is curved longitudinally, or from end to end, as shown in connection with the plane, H, in Fig. l, and, furthermore, each plane is curved transversely, or fromYfront to rear, as shown in Fig. 2. Said planes are mounted for movement on horizontal axes in frames, h, h, and with said planes are assoh which extend around guides, 71. h, it, h to a hand lever, J see Figs. 2 and 3. The lever is positioned within cock pit, e, to be in convenient reach of the aviator, and by movement of the lever in one direction, the elevating planes may be tilted downwardly and forwardly, whereas the reverse movement of lever enables the elevating planes to be tilted upwardly and rearwardly. Obviously, when the elevating planes, H, H, occupy horizontal positions, to fly in a substantially horizontal direction; by tilting the planes upwardly and rearwardly they are inclined to' the horizontal plane of the craft, and the pressure of the wind or air against their under sides has a tendency to cause the craft to travel in an upward direction, but, an adjustment of the planes to a downwardly and forwardly inclined position causes the air or wind to exert pressure on the top surface of the planes, and thereby directs the craft in a downward path. As shown more clearly in Fig. 1, each steering plane, H, H, is hung for movement on a horizontal axis, which axis is at right angles to the longitudinal axis of the craft. Each steering plane is provided with a straight front edge, inclined rearwardly diverging end edges, and curved rear edges, this particular form of the plane having certain advantages from a practical standpoint.

In addition to auxiliary planes, G, G, the craft is provided with other auxiliary planes, I, I, the latter being positioned in front of main planes, steering plane H. Said auxiliary planes, I, I, are hinged to an outwardly extending supporting member, I which is attached to the bow end of car, E, and extends in inclined directions outwardly and upwardly therefrom, as sho wn'in Fig. 1. Said planes, 1, I, are hingedly connected at their forward edges to supporting member, 71 so as to move on horizontal axes, the axis of movement of each plane, I, I, being at a right angle to the longitudinal axis of the car.

the craft will have a tendency A, B, and below the Auxiliary planes, I, I, are adapted, preferably, for movement simultaneously with auxiliary planes, G, G. This is secured by employing cables, 6, attached to planes, I, 1, near their rear edges and extending over suitable guides, 2', 2' to the cables, 9*, said cables, 2', being attached to said cables 9", whereby planes, 1, I, and G, G, are adapted for operation by knee levers, G G As shown in Fig. 3, the auxiliary plane, G, at one side of the craft and auxiliary plane, I, at the same side of the craft are connected to knee lever, G whereby planes, G, I, will be operated simultaneously by said lever. In like manner, the auxiliary planes, G, I, on the same side of the craft are connected with the other knee lever, G so that the operation of lever, G will simultaneously move said auxiliary planes, G, I.

J, J designate wing tip planes positioned at the outer ends of the main planes, A, B, respectively. Each wing tip plane is positioned for its longitudinal axis to be substantially parallel to the longitudinal axis of car, E, and said planes are hinged or pivotally connected at their inner edges to the outer ends of the respective planes, A, B, the axes of movement of balancing planes, J, J, being parallel to thelongitudinal axis of the car. To the planes, J, J, are attached operating cables, j, which extend to the middle part of car, E, and are operatively connected to a shaft H having hand wheel, H or other suitable controlling member, positioned within cock pit, 6, so as to be within convenient reach of the aviator, said shaft, H being shown more clearly in Fig. 2. Both wing tip planes, J, J, are connected with a single hand shaft, H so that the planes may move up and down through an arc of 120, said planes moving in unison with each other. The operating devices for wing tip planes, J, J, are so arranged and proportioned that each plane moves an equal extent at the same time and in the same direction, it being understood that a movement of the shaft, H .in one direction will pull down planes," J J, simultaneously, whereas a movement of the shaft in an opposite direction will allow the planes to move upwardly simultaneously. \Vhen 1 planes, J, J, are moved downwardly, more or less as required, they conform to the longitudinal curvature of main, planes, A, B, substantially as shown in Fig. 1, and should the planes be moved downwardly to a still further extent, they will assume angular positions to the outer end portions of planes, A, B. The main purpose of the planes, J, J, is to increase the curvature of the end portions of the main planes when sailing downwardly at a slight angle. It may be'remarked that planes, J, J, are usefuhmainly, when gliding down from a height at a steep angle, and they have something of the ef- -taken in connection with fee? of a parachute in the descent of the era t.

Extending upwardly from car, E, is a rudder post, is, which carries a vertical rudder, K. To the lower part of this rudder post are attached operating cables, is, extending forwardly to a foot lever, K, shown in dotted lines in Fig. 3, the same being positioned within cock pit, e, of the car, whereby the operatoris enabled to change the position of rudder, K, by the pressure of the feet against said lever, K.

It should be remarked that each of the planes employed in my' aerial craft is curved from end to end, or longitudinally, and from front to rear, or transversely, the curvature of said plane being on a radius to be determined by actual conditions of use.

In cross section, frame, D, and car, E, are triangular, with the vertex of the triangle at the bottom of car, E. Said car, E, may, however, be of any suitable construction, but said car is shown in the d awings as substantially canoe shaped in order that the craft may float on the water should it descend when over a river or other body of water. The canoe shaped car is constructed so that it will afford the least resistance to the movement'of the craft through the air, and in the embodiment shown in the drawings, said car, E, is provided at its forward portion with inclined sides, e, diverging from the bow rear-wardly. The diverg'ng sides, 6, e, extend from the bow rearwardly to a point below the we ght-carrying planes, A, B, C. Below said planes the sides, e of the car are parallel to each other to a point opposite cock pit, 0, but in rear of the cock pit the sides, 6 of the car convergetoward the stern. the angle of-thc sides, e being less than the angle of the bow portion, 6, of the car. The flotation of the car is increased by the employment of cylinders, L, positioned at the respective sides of the car, and suitably attached to the respective sides thereof. Said cylinders are adapted to serve as reservoirs for the hydrocarbon or othe' fluid combustible which is to be supplied to the cylinders of engine, F, but said cylinders, L, perform the function, mainly, of floats to increase the buoyancy of the craft when used as a marine vessel.

As is usual in crafts of this character, the car is provided with a suitable running gear, M, below the forward part of thecar, and at the boW and stern of said car are provided skids, N, said skids being composed of yieldable material and so attached to the car that they will serve as shock absorbers when the craft comes into contact with the earth at the time-of alighting.

It is thought that the operation and advantages of this invention will be readily understood from the foregoing description the drawings.-

'ing

Having thus fully described the invention, what I claim as new, and desire to secure by Letters Patent is:

1. In an aeroplane, a plurality of main weight-supporting planes, two of which diverge outwardly, and a thirdplane being positioned above said diverging planes, a plurality of propellers positioned on opposite sides of the longitudinal axis of the aeroplane, a plurality of auxiliary planes positioned at the rear of said outwardly diverging eight-supporting planes, each auxiliary plane being hinged for movement on a horizontal axis, and means for turning said auxilary planes to an inclined position with respect to said weight-carrying planes.

2. An aeroplane embodying a plurality of main weight supporting planes two of which diverge outwardly and a third plane positioned over said diverging planes, said third plane being in a predetermined fixed relation to said diverging planes, wing tip planes hinged to the diverging planes at the outer ends thereof, said wing tip planes being positioned distant from the ends of the third plane, and means for shifting the wing tip planes in the same direction and at the same time whereby in one position of said wing tip planes the latter constitute extensions or prolongations of the main diverging planes.

3. An aeroplane embodying a plurality of three relatively fixed main planes two of which diverge outwardly and a third plane.

diverging planes and spaced relatively thereto, each plane being curved lengthwise and'crosswise, wing tip planes hinged to the. diverging planes at points distantfrom the ends of said third plane, and means for controlling said wing tip planes whereby the positions of said wing tip planes relatively to the other planes may be changed at will.

4. In an aeroplane, a plurality of weightsupporting planes each curved longitudinally, two of said planes occupying outwardly diverging relation to each other, and a third plane positioned above the diverging planes, longitudinally curved balancing planes positioned at the outer ends of the two first named planes, and means for imparting movement to the balancing planes simultaneously and in'the same direction whereby the balancing planes are adapted to be moved into position wherein the longitudinal curvature thereof corresponds to the a re of the first two planes.

In an aeroplane, two weight-supportplanes, curved lengthwise and divergwith respect to each other, and a third plane positioned over the inner portions of said diverging planes, longitudinally curved balancing planes positioned at the outer ends of the two first named planes, and means for imparting movement to the balpositioned over said ing ancing planes simultaneously and in the same direction whereby the balancing planes are adapted to be moved into position wherein the longitudinal curvature thereof corresponds to the arc of the first two planes.

6. In an aeroplane, two longitudinally curved weight-supporting planes positioned in diverging relation to each other, and a third plane over the inner portions of said diverging planes, said third plane being curved longitudinally and being spaced, for the major part of its width, relative to said diverging planes, longitudinally curved balancing planes positioned at the outer'ends of the two first named planes, and means for imparting movement to simultaneously and whereby the balancing planes are adapted to be moved into position wherein the longitudinal curvature thereof corresponds to the arc of the first two planes.

7. An aeroplane embodying a plurality of three relatively fixed main planes two of which diverge outwardly and a third plane positioned over said diverging planes, the end portions of said third plane being spaced relatively to "said diverging planes, and wing .tip planes hinged at the outer ends of said diverging planes, each wing tip plane being curved in the same'general direction as the diverging plane to which it is hinged, said hinged connections between the wing tip planes and the diverging planes being distant from the respective end portions of said third plane.

8. In an aeroplane, two relatively diverging weight-supporting planes, a third weight-supporting plane over said two planes, each plane being curved lengthwise and transversely, and balancing planes positioned at the outer ends of the two first named planes, each balancing plane being curved and movable to a position wherein its curvature corresponds to the longitudinal curvature of one of the two first named weight-supporting planes so as to form an extension thereof,

9. In an aeroplane, a plurality of not less than three weight-carrying planes, two of which are positioned in diverging relation, and the remaining plane being over the two said planes and cooperating therewith tostiffen the same, auxiliary planes positioned at the rear of the two diverging planes, means for operating said auxiliary planes whereby they may be positioned at an angle to the surfaces of the diverging planes, balancing planes hinged at the outer ends of the two first named planes and forming extensions thereof, and means for operating the balancing planes simultaneously and in the same direction.

10. In an aeroplane, a plurality of weightsupporting planes, each decreasing in width toward the outer end thereof, a plurality of plane being auxiliary planes positioned at the rear of, and movable at an angle to, said weightsupporting planes, whereby the auxiliary planes may exert a retarding effect on the flight; of the craft, each balancing plane in creasing in width toward its outer end, balancing planes positioned at the outer ends of the weight-supporting planes, and separate operating means for the auxiliary planes and the balancing planes.

11. An aeroplane embodying a plurality of main planes two of which diverge outwardly and a third plane positioned over said diverging planes and spaced relatively thereto, wing tip planes hinged at the outer ends of said diverging planes, each wing tip being curved transversely from front to rear and said wing tip being curved in the same general direction as the diverging plane to Which it is hinged.

12. In an aeroplane, a plurality of'weightsupporting planes, two of which diverge relative to each otherand a third positioned over said diverging planes, said diverging planes decreasing in width toward the outer ends thereof, a plurality of auxiliary planes at the rear of said diverging weight-sup porting planes, each auxiliary plan'e being substantially triangular and extending for substantially the length of one diverging plane, means for shifting the positions of said auxiliary planes relative to the weightsupporting planes, balancing planes'positioned at the outer ends of the weight-supporting planes and beyond the ends of the triangular'auxiliary planes, and means for operating the balancing planes.

13. An aeroplane embodying three relatively fixed weight-carrying planes two of which diverge outwardly, and the third plane being positioned oversaid diverging planes and spaced relatively thereto, each plane being curved in the direction of its length, wing tip planes hinged to said diverging planes at points distant from the respective ends of said third plane, and

means for operating said wing tip planes for moving them downwardly so as to form extensions of the diverging planes.

14. An aeroplane embodying three relatively fixed weight-carrying planes two of which diverge outwardly, and the third positioned over said diverging planes and spaced relativelv thereto. movable wing tip planes hinged to said diverging planes at points distant from the respective ends of said third plane, means for operating said wing tip planes for moving them downwardly so as to form extensions of the diverging planes, other movable planes hinged to the rear of said diverging planes, and means for limiting or arresting the movement of certain of said movable planes with respect to said diverging planes.

15. In an aeroplane, three longitudinally curved weight-supporting planes two of which occupy diverging relation to each other and the third is positioned over the said diverging planes, a plurality of auxila iary planes each positioned at the rear of one of said diverging planes, means for separately adjusting the auxiliary planes, whereby said planes may assume different positions and at an angle to the diverging planes, balancing planes positioned at the outer ends of the diverging planes and beyond the auxiliary planes, and means for operating the balancing planes simultaneously and in the same direction, whereby the balancing planes are adapted to be moved downwardly so as to conform to the curvature of the diverging planes.

16. In an aeroplane, a plurality of weightsupporting planes, a plurality of auxiliary planes at the rear of said weight-support ing planes, each auxiliary plane being curved lengthwise and transversely.

In an aeroplane, a plurality of weightsupporting planes two of which are in diverging relation to each other and a third plane positioned over said diverging planes, auxiliary planes having hinged connection with said diverging planes, means for operating the auxiliary planes, balancing planes positioned at the outer ends of the weight-supporting planes and beyond the auxiliary planes, and means for operating the balancing planes simultaneously and in the same direction.

18. In an aeroplane, the combination of weight-supporting planes positioned in diverging relation to each other, each plane having an inclined rear edge so that said plane decreases in width toward the outer end thereof, substantially triangular aux iliary plane's positioned at the rear of the diverging planes, .each auxiliary plane being hinged to the inclined edge of one diverging plane, a retractor for lifting each auxiliary plane, a stop device for limiting the movement of each auxiliary plane, said retractor and stop device operating to retain each auxiliary plane in substantial alinement with the diverging plane to which it is attached, and means for operating said auxiliary planes. I

19. In an aeroplane,-two relatively diverging weight-supporting planes, athird weight-supporting plane, over said diverging planes, elevating planes positioned-at the front and rear of all the weight-supporting planes, means for adjusting the elevating planes, balancing planes positioned at the outer ends of the two diverging planes, and means for operatin the balancing planes simultaneously and in the'same direction.

20. In an aeroplane, a plurality of weightsupporting planes, two of which diverge outwardly and a third plane being positioned over the inner adjacent end portions of said diverging planes, elevating planes at the front and rearof said weight-supporting planes and each adapted for move. ment on a horizontal axis, and means for operating the elevating planes simultaneously and in the same direction, balancing planes positioned at the outer ends of the two diverging planes, and means for operating the balancing planes simultaneously and in the same direction.

21. In an aeroplane, two relatively diverging weight-supporting planes, longitudinally curved balancing planes at the outer distant ends of said diverging planes, and means for operating the balancing planes simultaneously and in the same direction.

22. In an aeroplane, two relatively diverging and longitudinally curved weightsupporting planes, longitudinally curved balancing planes hingedly supported at the distant ends of said weight-supporting planes, and operating means connected to said balancing planes whereby they are operated simultaneously and in the same direction.

23. An aeroplane embodying three weight-carrying planes two of which diverge outwardly and the third plane is positioned over said diverging planes and is spaced relatively thereto, each plane being curved in the direction of its length, wing tip planes hinged to said diverging planes at the outer ends thereof, each wing tip plane being curved in the same general direction as the curvature of the diverging plane to which it is hinged, and means for operating the wing tip planes so as to move the same downwardly so as to form extensions or prolongations of the diverging planes.

24. In an aeroplane, the combination of two relatively diverging weight supporting planes each curved in the direction of the length thereof, auxiliary planes hinged to the rear edges of the diverging planes and positioned at the respective sides of a longitudinal medial line through the machine,-

each auxiliary plane being curved lengthwise, a third weight supporting plane positioned above the diverging planes, the end portions of said third plane terminating intel-mediate the end portions of the diverging planes and the auxiliary planes, means for operating said auxiliary planes whereby they are movable into positions inclined to the surfaces of the diverging planes, and other auxiliary planes positioned in advance of the diverging planes and at the respective sides of the longitudinal medial line through the machine.

25. In an aeroplane, a plurality of weightsupporting planes, auxiliary planes positioned'at the rear of the weight-supporting planes, an elevating plane at the front'of the weight-supporting planes, other auxiliary planes positioned in advance of and disconnected from the weight-supporting planes, the auxiliary planes at the front and rear of the weight-supporting planes being at the respective sides of the longitudinal axis through the machine, and balancing planes positioned at the outer ends of the weightsupporting planes.

In an aeroplane, the combination of weight-supporting planes, auxiliary planes positioned at the rear of said weight-supporting planes, other auxiliary planes positioned in advance of, and disconnected from, said weight-supporting planes, the auxiliary planes at the rear and the front of'said weight-supporting planes being arranged at the respective sides of a longitudinal medial line of the machine, and connecting means between said auxiliary planes, one of said means connecting a front auxiliary plane on one side of the medial line with a rear auxiliary plane on the same side of said medial line, whereby the two pairs of auxiliary planes are operated simultaneously.

27. An aeroplane having main weightsupporting planes extending at the opposite sides thereof, forming a dihedral angle with each other, the planes curving from end to end, curved balancing planes positioned at the outer ends of said main weight-supportingplanes, and means for operating the balancing planes simultaneously and in the same direction.

28. In an aeroplane, the combination of two main planes disposed in diverging relation to each other, each main plane being curved longitudinally, a third longitudi nally curved main plane positioned over the diverging planes, the ends of said third plane terminating opposite to the diverging planes and intermediate the ends thereof, curved balancing planes positioned beyond the ends of the third main plane, each balancing plane being hinged to theouter end portion of one of said diverging planes, and means for simultaneously operating said balancing planes whereby they may at one movement be drawn downwardly for the curvature thereof to correspond to the curvature of the main diverging planes.

29. An aeroplane having two main weightsupporting planes extending at the opposite sides thereof,a third weight-supporting the two main weight supporting planes.

30. An aeroplane having main weightsupportmg planes extending at the opposite sides thereof and forming a dihedral angle concave sides of the sides thereof, a third with each other, the planes curving from end to end and from front to rear, with the planes facing downwardly, said planes decreasing in width toward their outer ends, auxiliary planes hinged at the rear ends of said mainweightsupporting planes, and knee operated levers for adjusting the positions of the auxiliary planes relative to the weight-supporting planes. 7

31 An aeroplane having two main weightsupporting planes extending at the opposite Weight supporting plane arched over the inner end portions of the main planes and secured intermediate the ends thereof, auxiliary planes hingedat the rear of the two main planes, means for adjusting the auxiliary planes, balancing planes hinged at the outer ends of the two main planes, and means for adjusting the balancing planes, said auxiliary planes and the balancing planes being disconnected from the third weight-supporting plane.

32. An aeroplane having two main weightsupporting planes curving upwardly and outwardly at the respective sides thereof, a third weight-supporting plane arched over the inner portions of the main planes,

1 curved balancing planes hinged at the outer ends of the two main planes and positioned beyond the third plane, curved auxiliary planes hinged at the rear edges of the two main planes, and separate means for-operating. the balancing planes and the auxiliary planes.

An aeroplane having main weightsupporting planes extending at the respective sides thereof and formingv a dihedral angle with each other, each plane decreasing in width from the inner to the outer ends thereof, auxiliary planes hinged at the rear edges of the main planes and adapted, when extended rearwardly therefrom, to form planes of approximately uniform width, and knee operated levers for adjusting the auxiliary planes.

3l. An aeroplane having main weightsupporting planes extending at the respective sides thereof and forming a dihedral angle with each other, auxiliary planes positioned along the rear edges of the main planes and hinged thereto, and knee operwhich diverge outwardly, and the third plane being positioned over'said diverging planes and spaced relatively thereto, each plane being curved in the direction of its length, movable wing tip planes hinged to said diverging planes at oints distant from the ends of said third pl flne, each Wing tip plane being curved in the same general direction as the diverging planes, means for operating the wing tip planes so as to draw them downwardly and to form extensions of said diverging planes, other movable planes hinged to the diverging planes at the rear thereof, and'means for limiting the movement of certain of said movable planes to preclude the latter from lifting above a line horizontal with respect to the diverging planes. 1

37. An aeroplane having main weightsupporting planes extending upwardly and outwardly at the respective sides thereof, and a balancing planehinged to the outer end of each main plane, each of said planes being curved from front to rear.

38. An aeroplane having main weightsupporting planes extending at the respective sidesthereof, a third weight-supporting plane arranged over the main planes and forming in connection therewith a dihedral angle, auxiliary planes hinged at the rear edges of the .main planes, and balancing planes hinged at the outer ends of the main planes. 7

39. An aeroplane having main weightsupporting planes extending at the respective sides thereof, a third weight-supporting plane arranged over the main planes and forming in connection therewith a dihedral angle, auxiliary planes hinged at the rear edges of the main planes, and balancing planes hinged at the outer ends of the main planes, each of said planes being curved from end to end and curved from front to rear.

40. An aeroplane having a plurality of weight supporting main planes, and planes for steering the aeroplane in a vertical direction, said main planes being positioned intermediate said steering planes and free from overlapping relation thereto, each steering plane being curved from front to rear and from end to end.

41. An aeroplane having a plurality of weight carrying planes, and a steering plane for controlling the flight in a vertical direction, said steering plane being spaced in a fore and aft direction relatively to said weight supporting planes so as to be free from overlapping relation thereto and saidend to end and from .planes mounted for messes porting plane extending over the inner por-' tions of the main planes and connected thereto intermediate their ends, balancing movement relative to the outer ends of the two main planes, auxiliary planes hinged at the rear edges of the two main planes, said balancing planes and the auxiliary planes being disconnected from the third Weight-supporting plane, and

1 steering planes positioned at the front and Copies of this patent may be obtained for five cents each, by addressing the 1 Washington. D. G.

the rear respectively of the main planes, each steering plane being mounted to swing forwardly and rearwardly.

In testimony whereof I have signed my name to this specification in the presence of 15 two subscribing witnesses.

HARLOW T. STOKES.

Witnesses:

JOHN C. BERGEY, JOHN J. HAMPSON.

"Commissioner of Patents.

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