SU5408A1 - Aircraft wing - Google Patents

Description

Aircraft wings are usually constructed in such a way that the skeleton, which in most cases consists of two longitudinal trusses (spars) and i many crossbars (ribs), is laid down; wash the fabric, plywood or. similar material. Known; We have designs with a larger number of: spars than two; In this case, the perceived skeleton forces are distributed more evenly and,; in addition, some | guarantee against damage to the wing i in case of damage or destruction of one spar. Also known aircraft spars in the form of a lattice farm. The disadvantages of these already known wing structures are in the usual use of pliable sheathing material, at best, suitable only for transferring tensile forces. To preserve the right: willow-shaped wing, and also to: perceive torsional forces due to the plating ductility, i

it is necessary, for example, to consume a large number of cross-pieces (ribs), and thus making the wing workpiece more complicated and increasing its weight. For the transfer of air resistance forces acting on the wing, it is usually necessary to arrange a special wind connection between the side members and the ribs.

The proposed wing, built in the form of a hollow body, consists of lattice trusses lying along the wing and a casing made of tin fitted on all sides from these sides, provided with elevations in the flight direction, stiffening the wing, for example, of a wavy appearance and tp; this skin is firmly connected to parts of the truss in many places distributed throughout the wing.

The use of corrugated sheet to create plane of the plane is already known, but in such cases it was only relatively thin planes, the thickness of which is equal to the thickness of the sheet itself, and not relatively hollow shells, as in the present invention. In the already known structures located across the waves, which give the wing rigidity, the fasteners lie open in the stream of air and, therefore, create additional harmful air resistance; The side planes of corrugated sheet waves in such a design replace struts connecting the upper part of the rib with the lower one. In this case, thin tin is exposed to adverse forces.

In the proposed wing, the corrugated sheet is not located between the main bearing elements, but it encloses the skeleton of the wing on all sides from the outside and simultaneously protects parts of the core from the air jet. Owing to the corrugation of the shell, it is possible to create a sheath of sufficient thickness to transfer to relatively large distances and without noticeable changes in its shape as perpendicular forces acting on it from a tin of negligible thickness (this is necessary to avoid too much weight). the profile of the wing section (air forces, local loads, for example, if a person comes), and forces acting in the direction of the corrugation. The fact that the proposed skin is a rigid body itself makes it possible to assign it partly or even completely to those tasks for which, until now, it was necessary to provide for special elements in the wing skeleton. Therefore, in the proposed wing, crossbars (ribs), which usually serve to fix the exact shape of the wing profile, to join the side members between themselves and to perceive torsional forces, may fall off; the skin itself may serve as a wind link between the side members; thus, the wing structure is greatly simplified. In the event of damage in any part of the core, the forces acting normally on this part of the core can, if transmitted through the casing, be perceived by the adjacent other parts of the core, so that the safety of the wing with respect to local damage increases in comparison with conventional structures.

The main skeleton trusses, which lie along the wing, are made in the form of tube-type trusses. Accordingly, the load decreasing towards the ends of the wing is recommended to build the upper and lower spars of these trusses so that they consist of parts having different diameters or different wall thicknesses.

The corrugated skin is placed so that it directly lies on the upper and lower trusses of the wing with its elevations facing the plane. If the cladding is now tightly joined to the skeleton spars at each contact point, for example, by means of rivets, then a very large number of evenly distributed bondings are obtained throughout the plane, which, in turn, makes it easier for the cladding to perform the above tasks. Instead of simply joining rivets at the points of contact of the skin with parts of the core, other bonding methods can also be used.

The front of the wing, the so-called nose of the wing, is usually not in the form of a sharp edge, but receives a rounding. Since this rounding has a very small radius in comparison with the rest of the wing profile, the task of bending the corrugated sheet in order to give it this shape is difficult. Therefore, it is recommended to fabricate the front edge of the wing as a separate part and connect it with the upper and lower wing casing also manufactured separately. In this case, different types of manufacturing are possible. For example, you can make the front edge of the wing initially in the form of a gutter, the inner, strongly bent part of which is completely smooth, while both of its lateral parts with less rounding receive a corrugation corresponding to the skin profile, gradually deepening, starting from the beginning of the depressed places, towards the outside of the gutter. The front edge of the wing can also be profiled, which extends across it and is produced by special presses or by means of hammers, etc. Finally, the following is possible: profiling of the skin goes gradually into a smooth plane at the junction with the leading edge, which also has smooth form.

FIG. 1-3 of the schematic drawing shows the cross-section and longitudinal cuts of the wing, as well as its horizontal projection (in the latter case, only with a partially cladding); in fig. 4 is also a section of the wing, in FIG. 5 is a side elevational view of the wing truss; FIG. b - a special type of corrugation in section; in FIG. 7 is an example of attachment of a clad plate to trusses of a wing skeleton; 8-10 illustrate a method for performing a plane end edge and in FIG. 11 and 12 are exemplary embodiments of the leading edge of the wing.

According to FIG. 1-3, the core of the hollow wing consists of a relatively large number of lattice trusses, which consist of the upper spar 1, the lower spar 2, vertical strut 3 and the diagonals 4. On the skeleton, sheeting b, of corrugated tin; at the points of contact 7 her

waves with the main spars 1 and 2, it is motionlessly connected with them. Thus, it replaces the wind coupling between the individual main spars of the wing skeleton, which is otherwise necessary for the resistance to horizontally acting forces. From the bottom of one truss to the upper spar of the neighboring, diagonal struts 5 are laid, which, together with the skin, make the wing capable of perceiving twisting forces.

FIG. 4 shows a section of the wing similar to that shown in FIG. one; here, however, the upper and lower spars of the main trusses are offset from each other, so that the section of the core consists of approximately equilateral triangles. The upper and lower spars 1 and 2 (Fig. 5) are made up of parts of tubes that have, as they approach the end of the wing, an ever smaller diameter.

According to FIG. 6, the corrugation of the skin in separate, distributed along the entire length of the wing, places significantly strengthened to make it even more able to resist the change of its shape and give even greater rigidity to the wing, without a significant increase in its weight. Attached to the core part 1 and in any way the corrugated lining 6 is provided with a special profiling of waves 9 arranged with a certain gap, or reinforced by lining strips 10 extending either outside the full width of the wing or located inside the wing between the longitudinal spars. These protrusions can be provided to achieve rigidity, in turn, corrugation 11.

FIG. 7 illustrates a method of attaching a wave corrugated tin plate to a part of the core consisting of a tube using rivets 13.

FIG. 8 and 10 shows the device trailing edge of the plane. The corrugated corrugation of the upper surface 25 and the lower surface 26 of the wing are displaced relative to each other by half-waves, so that at the trailing edge of the wing the waves directly merge into one sharp wavy edge 27, respectively, in the shape of the corrugation of the casing. In order to connect the upper 25 and lower 26 surfaces of the skin between themselves at the rear edge of the plane, both rigid strips are attached to a wedge 28 lying between them from wood or the like, in the planes of whose cheeks the waves of the corrugation of the skin are hollowed out.

FIG. Pi 12 shows a section and front view of a separately made front edge of the wing for a carrier plane with a rounded front part and with corrugation, the corrugation at the front (Fig. 1) is bevelled sideways to displace the corrugation of the upper and lower sheaths in order to smoothly at the rear edge.

The subject of the patent.

1. A wing for airplanes using corrugated metal, the waves of which run parallel to the direction of the air jet, characterized in that the trusses located along the wing

(Fig. 1, 2, 3) completely enclose the casing 6 of corrugated metal, what is the casing 6 fixedly attached to the side members 1, 2 trusses at the points of contact 7, at which the waves of the upper surface 25 (Fig. 8-10) can be shifted relative to waves of the lower surface 26 to produce in the trailing edge of the wing a sharp wavy edge 27 (Fig. 9), reinforced with wavy wedges 28 (Fig. 8), while the leading edge can be made of smooth metal (Fig. 11) or This edge has an oblique corrugation (FIG. 12) to connect the displaced itelno another wave top and bottom surfaces.

2. Modification of a hollow wing specified in claim 1, characterized in that the spars 1 and 2 are displaced relative to each other (Fig. 4 and 5) so that the elements 3 connecting them lie in inclined planes, and the connection of the upper spars 1 between itself and the lower spars 2 between themselves is carried out by a corrugated metal cladding (Fig. 4), which in turn can be enhanced by special profiling of waves 9 (Fig. 6) or by attaching special strips 10 (Fig. 6) to it.

Tilo-lntografi «Red Pechatnik, Leningrad, INTERNATIONAL INTERNATIONAL, 75.

3 g