SU12385A1 - Multi-plane - Google Patents

Description

The present invention relates to a multi-plane aircraft with carrier surfaces that are rotated in flight around axes transversely to the fuselage, in which these surfaces are controlled by means of auxiliary rudders that are positioned at the desired position from the pilot's seat.

Rotary-winged aircraft have the disadvantage that when the angle of rotation of the wings changes, the center of air pressure moves so that the resultant air drag force no longer passes through the axis of rotation of the wing, resulting in control moments by plane and causing unpleasant stresses in the wings.

The present invention aims to eliminate this disadvantage by moving the wings relative to the side members forward or backward, depending on the angle of inclination of the wings.

FIG. Figure 1 shows a side view of an aircraft composed of several elements with wings arranged one behind the other and one above the other.

FIG. 2 - view from above of the aircraft 1 - without skin.

FIG. 3 is a front view of the aircraft.

FIG. 4 is a side view of the control mechanism and one of the pilot's seats.

FIG. 5 is a top view corresponding to FIG. four.

FIG. b - front view corresponding to FIG. 4 and 5.

FIG. 7 shows a section along line 7-7 of FIG. 3

FIG. 8 is a side view of the second control mechanism with the pilot seat.

FIG. 9 is a top view corresponding to FIG. eight.

FIG. 10 is a front view corresponding to FIG. 8 and 9.

FIG. U-view from above of the mechanism controlling the front wheels of the aircraft.

FIG. 12 is a section along line 12-12 of FIG. 3

FIG. 13 is a schematic side view of the carrier wing and auxiliary steering wheel with a device for turning the latter.

The proposed multi-plane aircraft consists of several identical types of elements; The fuselage 1 (Fig. 1 and 2), built of light steel pipes, forming the core of the parallel side sections 2 and the bottom, is equipped with two seats 3 and 4 for the pilot, which are open at the front and rear. In front of each fuselage, there is a motor 5 with a propeller 6, and a motor 7 with a propeller 8; the bottom of the fuse is equipped with wheels 9 for landing on the ground and for the takeoff of the aircraft during takeoff.

Each of the wings of the same type 10 consists of a rigid frame, having a triangular shape in cross section (Fig. 7), and consisting of three longitudinal metal spars II, arranged along the wing and connected with each other by the ribs 12. Transversely of the frame thus formed a whole series of metal fins 13, having a trough-shaped form in cross section, the lower shelves of which 14 form a common plane. The rear horses of the fins 13 are tapered downwards, whereby flat flexible ends 15 are obtained, which are spring t if the fins are made of sheet steel. The outer end of each wing consists of five relatively small spring parts 16, 17, 18, 19, and 20, and each part is formed by ribs 13 having spring ends (Figs. 3 and 12). The skeleton is covered with matter, as usual.

Each wing is directed from the fuselage 1 upwards and outwards, as can be seen from FIG. 3, wherein some of the ribs 12 are provided with sleeves or bearings 21, by means of which the wing is pivotally connected to its support spar 22 (FIGS. 6 and 7), consisting of a steel tube and attached to the fuselage with bars 23 and spacers 24 Each spar 22, located in the transverse direction to the fuselage, forms an axis of rotation for the wing mounted on this spar; the bearing 21 is provided with a clip 25 perpendicular to it, mounted on the wing core rib 12 and able to relocate along this gap so that the wing 10 can be moved along its axis of rotation 22 parallel to the longitudinal axis of the aircraft until the desired front balance and the rear of the wing relative to its axis of rotation. The bolts 25y serve to fasten the clamp 25 on the ribs 12. From each core of the bearing surface there are two parallel rods 26, (figs. 1 and 2) consisting of steel tubes or other suitable material, with the rear ends of these rods connected transversely shtanga 27, and turning rod 28 is inserted at the outer ends of rods 26; the latter is therefore located transversely to the axis of the aircraft and parallel to the axis of rotation 22 of the wing and serves to support the rudder 29 turning the pilot's seat 3 from the pilot's seat 3 using a control mechanism (Fig. 4, 5 and b), which consists of a vertical plane the steering wheel 30 mounted on the steering shaft 31, pivoting in the steering rack 32 and carrying the sprocket 33; the two sprockets 35 and 39 rotate freely at the ends of the trunnion 36 fastened on the upright 32 and rotating in the bearing 37. In addition, on the upright 32 there is a sprocket 38 along which an endless chain 34 moves along the sprockets 33, 35 and 39 as shown in FIG. 4 and b, what the chain transmits is the movement of the steering wheel to sprockets 35 and 39 and associated with them. Part m; the sprocket 35 is provided with opposed segments 40 and 41 pivoting with the sprocket, and the wheel 39 is equipped with a corresponding pair of segments 42, 43; These segments are connected by steering surfaces 29, located on both sides of the fuselage, by means of cables that allow the rudders to turn without preventing the wings 10 from rotating around their axes of rotation 22. The cable 44 is attached at one end 45 (Fig. 4 ) to segment 40, the other end of the cable is attached to the lower parts of the lever 47, which is located on the steering surface frame (Fig. 13). To stiffen the lever 47, the struts 48 and 49 serve. Leading from segment 40 to lever 47, the cable 44 moves through the guide roller 50 (Fig. 13), mounted on one of the rods 26, and then bends around the rollers 51 (Fig. 13), 52 and 53 (Fig. 2), and the rollers 54 and 55 (Fig. 4). The guide rollers 51 and 52 lie in close proximity to the axis of rotation of the spar 22, so that turning the wing 10 around this axis does not interfere with the steering cable.

In a similar way,

cable 56 from segment 41 through guide rollers 57, 58 and 59 (Fig. 4), 60 (Fig. 3) and 61, 62 (Fig. 13). The last five of the rollers listed correspond to rollers 54, 53, 52, 51 and 50. From the guide roller 62, the cable 56 is directed to the upper end of the lever 47 of the steering wheel and is attached to it at point 63. The front right handlebar is connected by cables with segments 42, 43 in exactly the same way as the front left handlebar is connected by cables with segments 40, 41, (in the drawing, the corresponding parts of both sides are denoted by the same numbers). The two elements described above are connected sequentially to one another, in which case there are two seats 3 and 4 for the pilots. The control mechanism in front of the seat 4 corresponds exactly to the mechanism in front of the seat 3, with the only difference that the steering cables are not located in front of the seat, as in seat 3, but behind the seat. It is advisable to connect the control mechanisms of both seats with each other so that the rudders can be controlled from one of the seats 3 or 4. Such a connection is made using a cable 64 (Fig. 4) attached to one end of an endless chain. 34 and a guide disk 65 extending from below and on top of another guide disk 66. These guide disks sit on a lever 67 mounted on a trunnion 36, which is integral with the steering column 32 and can be rotated in the bearing 37 and, with bending the rack 32 back and forth, turning Swivels one way or the other. The passage 64 of the guide disk 66 of the cable 64 partially passes along the axis of the axle 36, so that when the axle is turned and when the stand 32 is tilted together with the steering wheel 30, the cable 64 does not experience interference in its operation. From the guide disk 66, the cable is guided through wolics 68, 69 (Figs. 1 and 6) and through the rollers of the rear control mechanism corresponding to the rollers 65, 66, after which the cable goes to the point 70 of the chain behind the wheel 35. The front end of the cable 64 attached to the front chain 34 in front of the wheel 35 in a place that is located

between the wheels 35 and 38. Similarly, the cable 71 is attached at one end to the front chain 34, and at its rear end to the rear chain 34 of the rear control mechanism. By this, when turning one steering wheel, the second one also rotates accordingly, so that the front and rear steering surfaces on both sides of the fuselage Ms. move simultaneously.

In order to ensure proper descent, devices are installed to protect each carrier surface 10 from accidental rotational movements, namely, each carrier surface 10 (Fig. 7) is equipped with a segment 72 having a recess 73 whose center lies on the axis of rotation of the wing 10: on the strut 24, a box 77 is fastened in which a spring is pressed, a bolt 75 pressed to the segment 76 is pressed to the segment. When the bolt 75 enters the recess 73, the wing 10 cannot be turned; for controlling the bolt 75 from the pilot's seat, the cable 78 is attached to the bolt, moving along the rollers 79, 80, 81, 82, while the free end of the cable is attached to the lever 83, placed on the side of the pilot's seat and rotating on the trunnion 84. The lever 83 is provided with a handle 85 and a delay 86 on the seat 3 holds the lever in a position opposed to the tension of the spring 76, while the bolt 75 is held in an inactive, extended position (Fig. 7). Each of the front bearing wings 10 is provided with a similar anti-rotation device, wherein the cables 78 from various safety bolts 75 converge into one common cable 78a (Fig. 5) attached to the lever 83, so that both safety bolts of the front wings are serviced one common cable. Similar devices can also be made for the remaining wings serviced from other pilot seats.

The described aircraft consists of two identical elements arranged one after the other, each of which has two bearing surfaces and two steering surfaces. Two or more tandem double elements can be located one above the other, and the aircraft depicted, for example, in the drawings has eight bearing wings 10 and eight steering wings 29, four engines and four pilot seats, with all wings having the same design. The fusels of both of these double units can be connected to each other by four links, of which two connections 87 are on the front side and two connections 88 are on the back side.

In order that the wings lying above each other move simultaneously, the bearing and steering wings are interconnected by links 89 and 90, at which the wings located one above the other are always kept in mutually parallel shape; in addition, devices for automatic rearrangement of the rear wings, formed as shown in FIG. 1 of a tandem consisting of parallel rods 91 hanging downwards, the upper ends of which are hinged to the frame at points 92, and the lower ends support the same weight, for example, cradle 93 in which one or two people can sit, or The cradle can be used to place gasoline, cargo, or similar items of tin. A transverse rod 94- (fig. 10) rigidly connects between itself rod 91 near their upper ends. A rod 95 is connected to the rod 94 at the hinge, the other end of which is pivotally connected at the point 96 to the lower end of the lever 97, which in turn can rotate around the lever hanging from the steering column 32a by means of the hinge 98 (Fig. 8). The lever 97 is equipped with a beam 99, one shoulder of which lies in front of the stub axle of the steering column 32a, and the second shoulder behind the trunnion. The upper ends of the arms of the yoke 99 are connected segmented like by a bar 100, on the upper side of which there is a recess 101 in the middle. A bolt 102 is pressed on the rack 32 and is pressed by a spring and equipped with a gripper 103 with which the bolt can be lifted with a finger, and the valve 104 can hold the bolt up. When the bolt 102 is raised, swinging the tambourine (cradle) has no effect on the steering wheel, since then only the lever 97 with the rocker 99 and the rod 100 rotates around the axis of the bolt 98. If the bolt 102 engages with the recess 101, then The lever 97 engages with the pillar 32a, and the movement of the lever is transmitted to the pillar, which rotates around the axis of the pivot, and the swing of the arm is transmitted to the steering mechanism so that the rear steering wings rotate in the same direction as the pilot.

FIG. 3 and 11, special arrangements are shown for controlling the front wheels 9 of the aircraft. The wheels are mounted on pins 105, which at points 106 can rotate around vertical axes, with both spindles interconnected by a transverse rod 107 connected by hinges to the brackets 108 of spindles 106; one end of the cable 109 is attached to one of the brackets 108, and the other end to the crosshead 110, located in the middle and equipped on both sides with foot pedals 111. In addition, the named cable bends the guide roller 112, while the second cable 113 is connected like in the same way, with the second bracket 108 and with the second side of the crosshead, another roller 112 bends around. Thus, a pilot sitting in the lower front seat can control his feet by turning the front wheels 9.

Any number of such aircraft can be connected to each other, being located one after the other or one above the other, and such a multi-plane aircraft can be controlled by one or several pilots. For raising or lowering the rudders, by bending the steering column, are placed obliquely downwards or obliquely upwards, with the result that the bearing wings take the corresponding and opposite one another direction. To rotate the plane, one or more steering wheels are rotated to the right or left, thereby causing the right and left handlebars to turn in opposite directions, resulting in a tilting moment and turning the plane to storbna. The subject of the patent. 1. A multi-plane airplane with wings arranged on the fuselage one after another forming an angle between themselves (transverse v} and automatically turning around the axes transversely to the fuse by means of pilot wheels rotated from the pilot’s seat, characterized by , with the aim of moving the wings relative to the side members 22 (FIG. 7) back and forth, rotary bearings 21 of the wings 10 (FIG. 1) are mounted on the latter, fixed by means of clamps 25 on the rod-ribs 12 (FIG. 7), and for fixing wings in this position — the latter have jagged segments 72, with which locking bolts 75 are coupled, controlled from the pilot’s seat, and a second airplane connected to it 87 and 88 can be placed above the plane, forming a single structural whole with the first (Fig. 1). 2. The use of the steering device described in Section 1 (Fig. 4-6 and Fig. 8-10), is distinguished by Y ///// 7y-h-h-h

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i: ii (due to the fact that the steering wheel 30 serves to simultaneously rotate in opposite directions two sprockets 35 and 39, mounted on rotary axles 36, columns 32 and supporting segments 40 and 41 or 42 and 43, connected by cables 44 to auxiliary steering wheels 29, and the chains of 34 sprockets of two controlled mechanisms arranged one behind the other are connected by cables 64, transmitting the movement of one chain to another and passing columns 32 and 32 about passing near the axes of rotation, so that the inclination of the columns does not affect cables and also in the case the locations of one aircraft above the other (Fig. 1), the supporting and auxiliary steering surfaces arranged one above the other are connected to each other by vertical links 89 and 90 (Fig. 1-3) 3. The use of the described in. 1 multi-plan the airplane of the pendulum device 91 and 93 (Fig. 1 and 8), which is rigidly connected to the column 32a with the help of rods 95 and 97 and by means of the tripping device 100, 101 and 102, while during the swinging of the master 93 the column is automatically rotated wings.