RU2807578C1 - Flaperon with welded power part - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to aircraft tail units, in particular the aircraft flaperon. The aircraft flaperon includes a composite honeycomb block consisting of panels made of a polymer composite material filled with full-depth honeycombs, and a fully welded power box of variable width, having a straight rear wall, hinge units and a drive unit, combined in a welded box with a single weld. In this case, the drive unit and the linkage units are located in different planes. The composite honeycomb block and the welded box are mechanically fastened to each other on three sides of the welded box, ensuring the transfer of cutting force from the rear wall of the welded box to the longitudinal wall of the composite honeycomb block.

EFFECT: invention ensures minimal weight of the flaperon, increased manufacturability and reliability of the flaperon, ease of manufacture and assembly of the flaperon.

1 cl, 13 dwg

Description

The invention relates to the field of aviation, in particular to mechanization units for the trailing edge of an aircraft wing, in particular to an aircraft flaperon.

The aircraft has various mechanization units for the trailing edge of the wing (flaps, ailerons, elevons, flaperons, etc.) that differ from each other in purpose and methods of fastening, which introduces its own characteristics into the power work and affects the choice of their structural power schemes. A flaperon is an aerodynamic control that performs the functions of an aileron and/or flap. Flaperons are located in the wing roots and are used, for example, in active control systems. There is a need for a simple and reliable flaperon design with minimal weight.

Traditional designs of flaperons are widely described in the literature Voit E.S., Endogur A.I. and others. “Design of aircraft structures”, Kan S.N., Sverdlov I.A. “Calculation of aircraft strength”, Zhitomirsky G.I. “Airplane design. Textbook for students of aviation specialties of universities", Astakhov M.F., Karavaev A.V., Makarov S.Ya., Suzdaltsev Ya.Ya. "Reference book on aircraft strength calculations."

The task to which the invention is aimed is to develop a flaperon design based on the criteria of minimum weight, ease of manufacture and assembly.

The technical result consists in reducing the weight of the flaperon, increasing the manufacturability and reliability of the flaperon, and ease of manufacture and assembly of the flaperon.

The technical result is achieved by a flaperon with a welded power part, including a composite honeycomb block consisting of panels made of polymer composite material filled with full-depth honeycombs, and a fully welded power box of variable width, having a straight rear wall, hinge units and a drive unit, combined in a welded box with a single weld seam, while the drive unit and the hinge units are located in different planes, while the composite honeycomb block and the welded box are mechanically fastened to each other on three sides of the welded box, ensuring the transfer of cutting force from the rear wall of the welded box to the longitudinal wall of the composite honeycomb block.

The invention is illustrated by the following images:

Fig. 1a - traditional flaperon design,

Fig. 1b - flaperon of a traditional design as part of an aircraft wing,

Fig. 1c - traditional flaperon design,

Fig. 1g - load distribution in the traditional flaperon design,

Fig. 2a - design of a flaperon according to the invention,

Fig. 2b - flaperon design according to the invention as part of the wing

aircraft,

Fig. 3 - diagrams of force in the plane of the flaperon and torque,

Fig. 4 - section along the welded flaperon box in the area of the drive unit,

Fig. 5 - graph of the dependence of the weight of the welded box and honeycomb block on the position of the rear wall of the welded box,

Fig. 6 - forces acting on the welded flaperon box,

Fig. 7 - single welded flaperon box,

Fig. 8 - processing of welded box ribs,

Fig. 9 - connection of a welded box and a composite block.

The following symbols are used in the images:

1 - flaperon,

2 - linkage unit,

3 - drive unit,

4 - fairing,

5 - panel,

6 - axis of the welded box,

7 - circuit that perceives torsion,

8 - rear wall of the welded box,

9 - weld,

10 - plane of the rib,

11 - fungal cutter,

12 - welded box,

13 - composite honeycomb block.

The aircraft flaperon includes a composite honeycomb block 13, consisting of panels 5 made of polymer composite material, filled with full-depth honeycombs, and a fully welded power box 12 of variable width, mechanically fastened together. The welded box 12 has a straight rear wall 8, hinge units 2 and a drive unit 3, united by a welded box with a single weld.

In fig. Figure 2a shows a diagram of the mounting of a flaperon-type unit according to the claimed invention. The design of the proposed flaperon, in contrast to the traditional one (Fig. 1a), has a distinctive linkage scheme, in which the location of the plane of the drive unit does not coincide with any plane of the linkage unit, i.e. The hinge units and the drive unit are located in different planes. In this connection, the forces from the drive and the reverse force do not lie in the same plane. According to the proposed linkage scheme, the reverse force is distributed between two linkage units adjacent to the drive unit.

In the traditional flaperon design (Fig. 1c), the drive units are inserted between the skins of the panels 5 that make up the composite honeycomb block 13. As a result, in such a design, the composite skin is loaded unevenly by reverse force. In fig. Figure 1d illustrates the uneven loading of part of the flaperon.

The problem with significant reverse force in composite cladding can be solved only by varying the thickness of the panels. At the same time, the thickness of the panels in the zone of maximum loads will not allow placing a composite honeycomb block in this zone, due to the rapidly decreasing chord height of the flaperon.

Accordingly, the proposed flaperon design uses panels made of composite materials with variable thickness. The variable thickness of the panels ensures uniform loading of the composite honeycomb block.

In the proposed design of the flaperon, a power part is allocated that works on torsion and shear, from reverse forces, which is a welded box 12. The part of the flaperon, which is a composite honeycomb block 13, is removed from the zone of large concentrated forces. Thus, the flaperon includes a fully welded box 12, to which the composite honeycomb block 13 is mechanically attached. In this design, all the hinge units 2 and the drive unit 3 are combined into a single welded box. Due to the absence of mechanical connections in the welded box, the weight of the flaperon is reduced.

The main stages of designing a flaperon-type unit are: identifying the part of the circuit that works in torsion, forming a power box, including linkage and drive units, achieving an optimum weight limit, taking into account the technological features of the selected scheme.

From the point of view of structural mechanics, a flaperon-type unit is a multi-support beam of variable stiffness, loaded with a distributed aerodynamic force and the force from the control rod.

Diagrams of forces in the plane of the flaperon are presented in Fig. 3 Qxz - diagram of shear forces, Mkr - diagram of torque.

For the manufacturability of the joint with the composite honeycomb block, the rear wall of the welded box must be straight, without fractures. The factor that determines its position is the magnitude of the torque in two sections: in the drive unit bracket and in the one farthest from the drive unit bracket - the hinge unit bracket.

In fig. Figure 4 shows a cross-section of the welded flaperon box in the area of the drive unit. Circuit 7 shown in FIG. 4 is a contour that absorbs torsion.

The thickness of the panels 5 is selected in such a way as to prevent loss of stability, as well as to avoid difficulties during machining and welding. The optimal panel thicknesses must be maintained in other sections of the welded box to ensure welding is possible. With different positions of the panels, different masses of the welded box and composite honeycomb block are obtained. The position of the panels is selected in such a way that their mass is minimal.

In fig. Figure 5 shows a graph of the dependence of the weight of the welded box and composite honeycomb block on the position of the rear wall of the welded box b, mm. According to the dependence, the position of the wall is determined, which ensures the optimal weight of the composite honeycomb block and the minimum weight of the welded box.

In the proposed mounting scheme for a flaperon type unit, it is also necessary to take into account the reverse force. The contour of the welded box, working in torsion, is additionally loaded with the flow arising from the reverse force, as shown in Fig. 6.

The design of the flaperon type unit with a closed power welded box has a minimum weight due to the absence of a large number of fastening connections. The main difficulty in welding a closed power box is processing the closing seam. The ribs are processed using a cutter installed parallel to the weld. The processing of pockets in the rib belts is carried out with a fungal cutter (Fig. 8).

The connection of the welded box with the composite honeycomb block is made taking into account the criterion of the smallest mass of the flaperon and is a joint on three sides of the welded box with the composite honeycomb block.

In the area of the junction of the welded box and the composite honeycomb block, it is necessary to ensure the transmission of shearing force. The transmission of the cutting force is carried out directly from the rear wall of the welded box to the longitudinal wall of the composite honeycomb block (Fig. 9). The gap between the rear wall of the welded box and the longitudinal wall of the composite honeycomb block is filled with foaming glue, which, together with the bending of the panels, ensures the transmission of cutting force.

The proposed connection of a welded box and a composite honeycomb block ensures the smallest weight of the flaperon. Thus, the flaperon-type unit has a minimum mass and ensures the perception of existing loads.

The proposed design of the flaperon type unit has a minimum weight, is reliable and technologically advanced, and is easy to manufacture and assemble.

Claims (1)

Flaperon with a welded power part, including a composite honeycomb block consisting of panels made of polymer composite material, filled with full-depth honeycombs, and a fully welded power box of variable width, having a straight rear wall, hinge units and a drive unit, combined in a welded box with a single welded seam, while the drive unit and the hinge units are located in different planes, while the composite honeycomb block and the welded box are mechanically fastened to each other on three sides of the welded box, ensuring the transfer of cutting force from the rear wall of the welded box to the longitudinal wall of the composite honeycomb block.