SU11204A1 - Bearing surfaces for aircraft - Google Patents

Description

The present acquisition relates to a device for the wings of aircraft. The wings of the flying apparatuses are supplied, generally speaking, as the main longitudinal beams, with two spars on which edges are arranged one behind the other, ensuring that the wing maintains its shape.

While forces arriving in the plane of the longitudinal beams can be easily transferred to the wing halves of the wing halves through the carrier connecting these beams between themselves trusses to transfer several times greater forces from the right longitudinal beams to the longitudinal plane. the truss is located, in essential features, perpendicularly or at a considerable angle to the plane of the longitudinal beams.

In the simplest case, a similar farm consists of a pair of braces, running approximately from the middle of each half of the wing in an oblique direction from the bottom to the fuselage or

the apparatus casing. Since the longitudinal beams are only a short distance apart from each other, as a result of the displacement of the forces causing the rise, very significant stresses arise in the said braces, i

To reduce these stresses, the present invention provides for an increase in the distance of the braces; from each other, so that the braces can get a smaller cross section, due to which their weight and air resistance are reduced at the same time. This increase in the distance between the braces is achieved by the fact that the points of influence on these braces are located on a beam perpendicular to the longitudinal beams and are located completely or partly in their plane. The present invention thus makes it possible to give the main wing skeleton, at the same time, a particularly simple form, for example, the shape of a cross using only one spar and

one transverse beam to which the above-mentioned bracing is attached. The longitudinal beam is attached to the body of the aircraft either directly or through the structure of the truss structure, while the cross beam rests on the lower part of the body, opposed to the above, using two braces. The ribs used to transfer the air forces to the longitudinal beam, the ribs, which are performed in a well-known manner, are connected to this beam by a rigid oCpaaosir.

Since the support of each half of the wing requires only three points of flank, then along with both reference points, which are installed on the crossbar, another third point of support is needed, which is expediently positioned on the Kfpuse apparatus in the same pad, nnm. Supporting each half of the wing, a big cross. thus, it receives support at both ends of the transverse beam and at the inner end of the longitudinal beam. For

At the same time, to avoid too high load of the ribs, which give the wing a certain shape and iodine supporting it, is a target that, from the spot of the statics, performs each half of the wing in the form of a rectangular 1ka, and with a strong rounding of the angles load the ribs far distant from the yoke, so that each half of the wing has in plan, in c.vш; stereo features, Elliptical shape. In HpfKH, a conventional wreck caused by AO5 aerodynamic research, it turns out that this does not cause any significant inconvenience. Along with the static floor that is attainable. There is also a further advantage that pilot land use and a modern wing are not narrowed down. Further, with single-wing aircraft, due to the significant stretching of the aircraft flying aaparate lying in the propollernaya jet, only a weak disrupted jet is obtained. Thanks to this, in such aircraft it is possible to achieve a higher efficiency of the P) oeller. Corresponding investigations have also shown that in this case there is a whole impact on the whole picture of the air flow being created.

For some unloading of the side members, it is advisable to open the front edge of the wing in the form of a support beam. Under certain conditions, it is also recommended to reinforce the rear edge of the wings, so that in this case the entire wing frame, together with the cross formed by the longitudinal beams, is a stiff truss.

On. The attached drawing shows several exemplary forms of carrying out the proposed bearing surfaces, wherein FIG. Hcd represents 4 planes half a wing, according to the proposed invention; FIG. 2 is shown along the middle of the wing in the B-direction of motion, respectively, of the line A, Ara, fig. one; fig.Z-wing section along the line B, B pa fig. I; FIG. A 4-in-one with a flying machine, in a reduced scale compared to FIG. 1-3; FIG. 5 t is another embodiment, corresponding substantially in FIG. one; FIG. 6 is a front view of one half of the aircraft; FIG. 7 is a cross-section of the wing along the line C, C in FIG. five.

In the embodiment of FIG. 1-4, the wing frame consists of a single longitudinal beam a, connected in a rigid in the sense of bending manner with a transverse beam. B Both of these beams are represented in de double box girders. The ribs f are firmly connected to the longitudinal beam a. At the hub of the lateral bdlky b with the help of hinges d are attached

braces with, which at its lower end are connected to the body of the apparatus by means of a hinge. Half of the wing; at one of: its ends h is provided with a hinge, not shown in more detail in the drawing, intended to be connected to the housing. The front edge of the wing is reinforced, due to which it creates unloading of the longitudinal beam. In the embodiment of FIG. 4, both halves of the wing, Ic converge at one point, so that a good field of view opens from the pilot seat. It can also be seen that the effect produced by the halves on the air jet generated by the propeller, in this case, is significantly less than in other structures. The wing depicted in FIG. 5-7, is provided with two longitudinal beams oi, “2 connected in a rigid way in the sense of bending with the transverse beam 7. At the ends of this last beam, two braid spits are again attached. The wing k is made with the mouth, in contrast to the design of FIG. 1-4, going continuously on all the industry .1.

M.G.

The thrust is wide and is introduced by the hull still in the middle with braces / ha. ,

The subject of the patent.

1. Bearing surfaces for lees (Tileers, characterized by;) using a cross-member connected to each surface, the ends of which are led out respectively behind the front and rear edges of the surface and connected to the body of the apparatus by means of braces.

2. The form of implementation of the supporting surfaces described in paragraph 1, characterized in that each of the two separate surfaces is removed from one side member b (Fig.) And has an approximately elliptical outline in its plan (Fig. 4), both surfaces connected to each other by a hinge, designed to attach them to the body of the apparatus.

3. The form of execution of the bearing surfaces described in paragraph 1, characterized in that the surfaces are made in the form of one common wing, which extends throughout the span and is equipped with two spars (Fig. 5-7). . K .., / ,; the patent of the foreign firm “0-in metal structures Dornier on ogre. rep. JNfe 11204

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FIG. 6

FIG. 7