RU2682697C1 - Design of connection of console wing with fuselage - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: invention relates to aircraft engineering. Design of the connection of console (1) wing with the fuselage is equipped with box-shaped beam (6) and contains a duct consisting of outer (7) and inner (8) longitudinal walls connected to upper (9) and lower (10) panels. Inside the box there are power frames (11). Each of spars (12) of console (1) of the wing is fixed (13) on power frame (11) of box girder (6), respectively. Ends (14, 15) of the box girder box are rigidly connected to power frames (16, 17) of the fuselage with the formation of a closed fuselage contour.

EFFECT: invention is aimed at increasing the functional space of the fuselage.

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Description

The invention relates to the field of aircraft, in particular to the design of the connection of the wing with the fuselage.

Currently, in aircraft, the wing and fuselage are connected mainly through the center section box, to which the left and right wing consoles are attached, for example, patent document US 2017066520 (A1); IPC B64C 1/06, B64C 1/26; publ. 09/03/2017.

The design using the center section reduces the internal free volume of the fuselage and imposes a restriction on the design of the installation of components and assemblies of the chassis, as well as on the distribution of in-flight communications.

A known design of the wing and fuselage connection, in which the wing box is bounded by the fuselage side, the power frames of the fuselage are fastened to the wing spars, and the fuselage skin panels are attached to the wing box panels (Patent US 8322656 (B2); IPC: В64С 1/06, ВСС 1 08, B64C 1/18; publ. 04.12.2012).

A known design for mounting the wing and fuselage, using the main frame, made in the form of a central annular section, mounted on the inner body of the fuselage, with which the side members of the left and right wing console are rigidly fastened. (Patent document US 4198018 (A); IPC B64C 1/06, publ. 04/15/1980)

There is a known design for fixing the wing and fuselage consoles, in which the coffer of each console, crossing the side panels of the fuselage skin, is extended inside the fuselage to a distance limited by the size of the functional compartment of the fuselage, all fuselage frames located on the section of the wing coffer are made, the building heights of their sides are also limited by the size of the functional compartment of the fuselage, and the upper and lower panels of the casing of the caisson of each console are connected inside the fuselage with the walls of the sides of the power frames (Patent RU 2154 003; IPC B64C 1/06, publ.).

In the above constructions, the use of the internal space of the compartment, including the area of connection of the wing (left and right wing console) with the fuselage, is provided, while the compartment itself can be represented as a center section with a large cutout inside.

When designing a glider, it should be borne in mind that the compartment containing the areas where the wing consoles and the fuselage are connected is one of the most loaded areas of the airframe design, in which large forces are transmitted from the wing to the fuselage power elements, which must be connected with other power elements in a closed the contour providing rigidity of a design of a glider. Usually, the area of connection of the wing with the fuselage is included in the design of the cargo (functional) compartment of the fuselage located between the nose and tail. If it is necessary to modify the design of the functional compartment associated with the “opening” of any of the elements of the closed loop, for example, equipping it with a hatch for landing cargo in flight, using the above structural schemes, it is necessary to change the entire power circuit of the airframe.

The prototype of the invention is the design of the connection of the wing with the fuselage disclosed in patent RU 2268196 C1; IPC B64C 1/26; Publ. 01/20/2006. In the design, the mount is made using the side (butt) rib with the formation of the area of connection of the wing with the fuselage, included in the design of the fuselage compartment located between the nose and tail.

At the same time, the wing and fuselage consoles are connected by attaching the wing box to the fuselage power frames, the side member belts and the power panels of the caissons of each console, intersecting the side panels of the fuselage skin with a fracture along the side in the vertical plane, continued inside the fuselage and closed along the upper and lower boundaries of the functional the fuselage compartment, without violating the cross section of the compartment, while the fuselage frames connected to the wing spars are made power; the sides of the power frames are limited by the width of the functional compartment of the fuselage and are connected to the upper and lower panels of the skin of the caisson of each console.

The disadvantage of the prototype is that the design in question cannot be modified with the "opening" of any of the elements of the closed loop, without changing the entire power circuit of the airframe.

When creating the invention, the technical task was to develop a design for attaching the wing consoles to the fuselage, providing the most complete use of the internal space of the compartment, including the connection area, with the possibility of upgrading this compartment, associated with the need to open the closed power circuit of the fuselage, without changing the circuit of this circuit.

The problem is solved by the design of the attachment of the wing console with the fuselage, with the formation of the area of connection of the wing with the fuselage, included in the design of the fuselage compartment located between the nose and tail parts, equipped with a box beam containing a box consisting of outer and inner longitudinal walls connected to the upper and bottom panels and box frames of power frames placed inside the box, joined and fastened to each of the side walls and panels, with each of the spars of the roof console la mounted on the power frame of the box-beam, respectively, and the ends of the box-box beam are rigidly connected to the power frames of the fuselage, with the formation of a closed contour of the fuselage.

The technical result consists in expanding the arsenal of technical means that can be used in the design of aircraft, while in the case of using the invention, an increase in the free usable volume (functional space) of the fuselage and the possibility of modifying the fuselage compartment, including the connection area with the wing consoles, without changing the closed circuit power circuit.

In special cases of execution:

- to enhance the rigidity of the structure and ease of installation, the side walls and panels can be made with ending thickenings at the joints;

- to transmit bending moment from the wing consoles to the torque of the box-beam, without additional bending moments acting on the box of the beam, the junction lines of power frames with side walls and panels can be in the same plane;

- to maintain a given cross-sectional shape of the box, it may contain auxiliary (non-power) frames, docked and fastened to each of the side walls and panels.

To clarify the invention, the following graphic materials are used:

- FIG. 1, Aircraft, side view;

- FIG. 2, Section AA of FIG. one;

- FIG. 3, Section BB of FIG. 2;

- FIG. 4, The power circuit circuit bending moment of the wing console on the contour of the fuselage.

The connection area (2) of the wing console (1) with the fuselage (Fig. 1) is included in the design of the fuselage compartment (3) located between the bow (4) and the tail (5) parts (Fig. 1). The mounting structure of the console (1) of the wing with the fuselage is provided with a box beam (6) containing a box consisting of an outer (7) and an inner (8) longitudinal wall connected to the upper (9) and lower (10) panels (Fig. 2, 3). Power boxes (11) of the box beam are placed inside the box. Power frames (11) are docked and fastened to each of the lateral longitudinal walls (7, 8) and the fuselage panels (9, 10). In the design, each of the side members (12) of the wing console (1) is fixed (13) to the power frame (11) of the box beam (6), respectively, that is, each spar and its corresponding power frame of the box beam are connected to each other. The ends (14, 15) of the box-beam box are rigidly connected to the power frames of the fuselage (16, 17).

A rigid connection of the ends of the box beam with the power frames of the fuselage allows you to form a closed contour of the fuselage, which closes the bending moment from the wing consoles (1). The power frames of the fuselage (16, 17) are essentially elements of the closed contours of the compartments adjacent to the compartment, including the area where the wing console and the fuselage connect (nose (4) and end (5) parts).

The junction lines of the power frames (11) with the side walls (7, 8) and panels (9, 10) can be in the same plane.

The beam box may contain auxiliary (non-power) frames (18), docked and fastened to each of the side walls and panels. Installation locations and the number of additional frames are determined after carrying out a structural strength analysis.

The manufacture and assembly of structural elements for connecting the console (1) of the wing to the fuselage can be implemented using known means and methods (for example, A. L. Abibov et al. “Aircraft Engineering Technology”, Textbook for Aviation Universities, M. Engineering 1982)

The side walls and frames can be made entirely milled or from rolled plates with ending thickenings at the joints, to enhance the rigidity of the structure and ease of installation

The connections between the side walls and the panels of the box beam, as well as the panels with frames can be made using bolted connections, using plates, fittings and / or continuous or multipoint welding seams.

Power frames of the box beam can be made prefabricated from metal materials of different sections.

The side members (12) of the wing consoles can be fixed to the power frames (11) of the box-shaped beam through the butt rib, or directly through the butt fittings, with the extension of the side members inside the box-shaped beam, while the power frames of the box-shaped beam and the side members of the wing consoles share a joint line .

During the flight of the aircraft, the power frames of the box beam perceiving the bending moment from the wing consoles M _{Con. ex.} (Fig. 4) they twist the box, transforming the bending moment (M _{Cons. Bend} ) into the torque of the box beam (M _{Cor. Beam. Twist} ), which closes on the power frames of the fuselage (M _Fus .), Thus M _{Cons bend.} passes through (M _{Cor. balck. steep} ) and closes with the bending moment of the fuselage frames (M _Fus. ). It is obvious that the given power circuit is applicable for both the right - Lev. And the left - Leo. wing consoles.

In the developed design, the center section box is not used, therefore, it is obvious that there is an increase in the useful volume (functional space) of the fuselage, and since the fuselage compartment (3) does not contain a transverse element of the power circuit, it can be modified without additional refinement of the entire closed power circuit of the fuselage, for example (Fig. 3) equipping it with an aperture in the bottom of the compartment, closed by pivoting wings (19) without changing the power circuit of the airframe.

The greatest effect from the use of the proposed solution can be achieved for aircraft in which the width of the cross section of the fuselage is greater than its height, for example, for aircraft with aerodynamic bearing fuselages, since the design in question reduces the midship of the fuselage.

Claims (4)

1. The design of the attachment of the wing console to the fuselage with the formation of the area of connection of the wing with the fuselage, included in the design of the compartment located between the nose and tail of the fuselage, characterized in that it is equipped with a box beam containing a box, consisting of outer and inner longitudinal walls connected to upper and lower panels and box frames of power frames placed inside the box, joined and fastened to each of the side walls and panels, while each of the wing spars of the wing console is fixed n on the power frame of the box beam, respectively, and the ends of the box of the box beam are rigidly connected to the power frames of the fuselage with the formation of a closed contour of the fuselage. 2. The design according to claim 1, in which the side walls and frames are made with ending thickenings at the joints. 3. The structure of claim 1, wherein the junction lines of the power frames of the box beam with the side walls and panels are in the same plane. 4. The construction according to claim 1, in which the box of the box-shaped beam contains auxiliary frames joined and fastened to each of the side walls and panels.

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