RU2400394C1 - Aircraft airframe assembly - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: invention relates to aircraft engineering, namely to airframe section design, method of its production and airframe design. Airframe section comprises 1^st inner tube, 2^nd inner tube, 1^st set of surrounding plates, 2^nd set of surrounding plates. Note here that said 1^st and 2^nd inner tunes are enclosed in outer tube and jointed thereto by flexible joint. Said 1^st inner tube is enclosed in 1st set of surrounding plates and said 2^nd set of surrounding plates in enclosed in 2^nd set of surrounding plates. Method of producing airframe section comprises producing 1^st inner tube, 2^nd inner tube, jointing inner tube to produce combined tube, enclosing combined tube into outer tube and jointing outer tube to combined tube. Airframe comprises at least two sections that incorporate respective front surfaces intended for jointing sections together to make integral airframe.

EFFECT: ease of assembly.

10 cl, 19 dwg

Description

Field of Invention

The present invention relates to the field of aircraft fuselage assembly technology. In particular, the invention relates to a fuselage section which, when using the new assembly method, is essentially made of three pipes. In addition, the invention relates to a fuselage that is assembled from several sections of the fuselage in accordance with the present invention.

BACKGROUND OF THE INVENTION

Currently, the assembly of the fuselages of modern aircraft is usually performed in such a way that a plurality of vertical fuselage frames in the longitudinal direction are attached to a plurality of horizontal stringers that are aligned strictly perpendicularly to said vertical frames, forming a frame onto which individual sections of the fuselage skin are riveted or attached from the outside. In this process, the fuselage is not created as a solid block, instead, separate sections of the fuselage (also known as cylinders or segments) are created first, which are connected in series to form a solid fuselage tube. To separate the passenger compartment from the cargo compartment located under it, a floor grill is installed in individual segments of the frame. With this known method of assembly, the fuselage is made of a large number of individual elements (frames, stringers, sections of the outer skin) in a complex assembly process, as a result of which the cost increases significantly during the assembly of the fuselage.

In addition to these difficulties related to production techniques, there are additional inconveniences both in the passenger compartment and in the cargo compartment due to low air pressure at high altitudes, which requires sealing during flight. Therefore, it is necessary that in the case of decompression (pressure drop) in the passenger compartment or cargo compartment, which may occur, for example, due to damage to the outer skin at high altitude, a quick pressure equalization between these two spaces is performed, since otherwise the fuselage structure may be damaged by pressure acting on one side of the floor grate, which is not designed for such loads. To ensure equalization of pressure, pressure equalizing valves are usually installed on both sides of the floor along the entire length of the fuselage, however, these pressure equalizing valves create additional problems in the event of an emergency landing on water, because through them water very quickly fills the entire fuselage.

SUMMARY OF THE INVENTION

There is a need to create an aircraft fuselage structure that is simpler and more economical to execute as a result of an improvement in the manufacturing process.

This need can be realized by the fuselage section of the aircraft of the present invention, suitably assembled by the fuselage, as well as by the method of manufacturing the fuselage section of the present invention. The fuselage section of the present invention is described below, with the corresponding explanations also applicable to the fuselage of the present invention and a method for manufacturing the fuselage section of the present invention.

Instead of manufacturing the passenger compartment and cargo compartment in the usual way, as is done in modern aircraft manufacturing, by simply dividing the fuselage cylinders into two parts using an intermediate floor, the present invention uses a completely different approach. The passenger compartment consists of a separate first pipe, and the cargo compartment consists of a separate second pipe, both of which are completely independent of one another. In a continuous production or pre-production process, these two pipes can be made in the form of supporting shell structures. To connect these two separate pipes in order to form a solid fuselage, they are placed in an external pipe, with which they are connected with the possibility of free movement. Thus, the fuselage section of the present invention essentially consists of a first movable prefabricated separate inner tube and at least one movable separate prefabricated second tube, both of which are enclosed in the outer tube and are freely movable. Since the inner pipes are separated from each other, during an emergency landing on water, they will not so quickly fill with water, which will fall into one of the two pipes.

To obtain this effect, both the inner tubes and the outer tube can be designed as supporting shell structures so that the loads tested during flight are mainly transmitted by the tubes themselves and not by the frame containing frames, or ribs and stringers, as is usually the case in the case of an aircraft built using traditional technology.

Although the material from which the pipes are made is not so critical, fiber reinforced composite materials or metals, in particular aluminum, can be used.

In order to provide additional stability to the inner tubes, as well as to install said inner tubes in the assembled state at a distance from the outer tube, the first inner tube may be enclosed in a first plurality of surrounding linings. Similarly, at least the second pipe may also be enclosed in a second plurality of surrounding linings. With this arrangement, the linings, like the pipes themselves, can be made of reinforced fiber composite materials or metals, such as aluminum. The shape of these linings may, for example, be similar to the known shape of the frames of an aircraft of conventional design with a cross-section in the form of a lattice with rays directed radially from the inner tubes to the outer tubes. Both the first and second sets of peripheral linings for both inner pipes can also be manufactured in a continuous production or preliminary production stage, and they can be dimensioned so that they need only to be pulled onto the corresponding inner pipe to assemble, while the pipes are separately from a friend and then connect these pipes. To connect the lining, you can, for example, pull or rivet to the pipes. If both pipes and linings are made of metal, they can also be welded to each other. Corresponding linings, therefore, hold the two inner tubes at a certain distance from each other, so that in the assembled state of the inner and outer tubes, the outer tube is removed from the inner tubes due to these linings. To ensure reliable stability between the outer and inner pipes, they are fastened together by linings, the linings being attached, riveted or, in the case of metal, welded to the corresponding inner or outer pipes.

Two inner pipes are two separate pipes, the cross-section of which corresponds to the standard shape of a conventional passenger compartment and a conventional cargo compartment, respectively. In this case, the first inner pipe for the passenger compartment has a curved upper region and a flat floor, and the second inner pipe for the cargo compartment has a curved floor and a flat ceiling. Thus, these two pipes can be connected, while the flat ceiling and floor are located opposite each other, although they are separated by means of overlays. In this intersecting region between the pipes, in which the floor of the first pipe faces the ceiling of the second pipe, separated from it by corresponding plates, the individual plates of the first set of plates are alternately offset from the individual plates of the second set of plates, so that in each case the plate of the second pipe is between two overlays of the first pipe. Of course, it is also possible that between the first two pads there is more than one second pads, which can be, for example, in those areas where the loads acting on the fuselage are especially high. Instead of arranging two groups of linings with alternating displacement relative to each other, it is also possible to use oval or round linings, which, with the help of a belt-shaped linings, are divided into two halves for tight connection of the corresponding inner pipes.

To make the assembly of the fuselage the easiest and most efficient, the inner tubes and the lining covering them are made in the initial stage of in-line production. Accordingly, a first plurality of surrounding linings is applied to the first inner pipe. Similarly, a second plurality of surrounding linings is applied to the second inner tube. In order to be able to connect the inner pipes containing the linings mounted on them, as accurately as possible in a certain position, the linings have adjusting tips that are positioned so as to install the first inner pipe and the second inner pipe in a certain position relative to each other. These adjusting tips can, for example, be mounted on the ends of the horizontal sections of the linings, which are arranged so that they are adjacent to the flat floor area or to the ceiling area of the first and second pipes, respectively, forming a guide for the corresponding other pipe when connecting these two pipes.

As described above, the first inner pipe forms a section of the passenger compartment, while the second inner pipe forms a section of the cargo compartment, the two sections being separated from each other by the intersection area of the linings (strips), which thus forms the floor grid for the passenger section salon. Thus, the two inner pipes are completely separated from each other, and they are mutually connected (for example, attached or riveted to each other) using overlays in the area of intersection of the overlays. The floor grill formed by the plates is designed so that it can withstand one-way pressure, which can, for example, result from a pressure drop in one of the two inner pipes.

In order to provide the fuselage section in accordance with the present invention with an additional part, for example a vertical tail, between the two connected inner tubes and the outer tube, a tubular transition casing can be inserted, the transition casing comprising a connecting element that is connected to the vertical tail. With this arrangement, the connecting unit protrudes outward into the corresponding recess in the outer pipe, so that the vertical tail can be attached to it. The adapter cover covers both connected inner tubes in order to be able to reliably transfer loads from the vertical tail to the fuselage.

In accordance with another objective of the present invention, the subject of the invention is a fuselage consisting of at least two sections of the fuselage described above. For this purpose, the corresponding front regions of the individual sections of the fuselage include suitable connecting elements with which the individual sections can be connected to form the same or integral fuselage.

As can be seen from the previous explanations, in contrast to the existing practice of manufacturing the fuselage from one large composite outer tube composed of frames, stringers and parts of the outer skin, the main principle of the present invention is to manufacture the fuselage from two separate inner tubes, which are enclosed in an outer tube, in this case, each pipe can be designed as a supporting (stressed) shell structure so that with the help of these three pipes the load is transferred in accordance with structural rigidity.

In accordance with another objective of the present invention, the subject of the invention is a method of manufacturing a fuselage section, which can be performed in several separate stages, and some individual stages can be performed in different order. The first inner pipe and at least one of the second inner pipes are created as a supporting shell structure. The first inner pipe can serve as a passenger compartment, and the second inner pipe can serve as a cargo compartment. The first inner pipe may thus have a curved top and a flat floor. Accordingly, the second inner pipe may have a curved floor and a flat ceiling. Then, these two prefabricated inner tubes can be combined to form a tube combination in which the floor of the first inner tube is mounted on the flat ceiling of the second inner tube. Then, the combined pipe created in this way can be enclosed in the outer pipe and attached to it, for example, by soldering, riveting or welding, forming a fuselage section.

Instead of implementing the method in the manner described, the execution order of the individual stages can be changed, for example, first producing an outer pipe, in which two separate inner pipes can then be manufactured and connected to the outer pipe. However, for reasons of production technology, it is more profitable to first make two inner pipes and an outer pipe on the stream, then connect the two inner pipes, forming the aforementioned combined pipe, which is then simply inserted into the prefabricated outer pipe and connected to it.

In order to increase the stability of the two inner tubes and the outer tube, the prefabricated first inner tube may be enclosed in a first plurality of surrounding linings. Similarly, at least one prefabricated second inner tube may be enclosed in a second plurality of surrounding linings. In this design, the linings for the first and second inner pipes can also be manufactured at the in-line production stage, or they can be made later so that they can be precisely fitted to the first and second inner pipes. In the case where individual linings of the first plurality of linings and individual linings of the second plurality of linings were prefabricated to provide an exact fit for the corresponding pipe, the individual linings can simply be pulled dry onto the corresponding prefabricated pipe and then attached, riveted or welded to the corresponding inner pipe .

In order to prevent the overlays of the first and second sets of overlays from overlapping when the two inner tubes are connected to form a combination pipe, the separate overlays of the first and second sets of overlays are placed on at least two inner tubes so that the separate overlays of the first and second sets the linings in the connected state of the pipes in the intersection area would be alternately offset relative to each other.

In order to increase the stability of the fuselage section, which comprises or consists of an outer tube and inner tubes, the first and second plurality of linings are connected to the outer tube with free movement after inserting the combined tube into the outer tube. Such a connection can ensure that structural loads will not be perceived by the outer tube alone, but by the entire fuselage structure, including linings and inner tubes.

BRIEF DESCRIPTION OF THE DRAWINGS

Further, the present invention is described in more detail using an example embodiment of the invention with reference to the following drawings:

Figure 1 shows the projection and cross section of the fuselage section in accordance with the invention;

Figures 2-4 - various stages of manufacturing the front section of the fuselage;

Figures 5-8 - various stages of manufacturing the middle section of the fuselage;

Figures 9-17 - various stages of manufacturing the rear section of the fuselage;

Figure 18 is a three-dimensional image of the fuselage containing three sections of the fuselage or consisting of them before the final assembly; and

Figure 19 illustrates three sections of the fuselage of Figure 18 assembled.

Identical or similar components in different drawings have the same numeric designations.

Detailed description of an embodiment of the invention

Figure 1, in particular, on the right diagram shows the basic principle of the invention, according to which the fuselage section 1 of the present invention mainly contains three different pipes 2, 3, 4, which are manufactured in separate stages and are connected only at the final assembly the fuselage. Thus, the fuselage section 1 contains an outer tube 4, which covers two inner tubes 2 and 3, inserted into it, as shown in the right diagram of figure 1. In this arrangement, the first inner tube 2 forms a section of the passenger compartment, and the second inner tube 3 forms section of the cargo compartment, respectively. As shown in the right diagram of FIG. 1, the two inner pipes 2 and 3 are located separately from each other inside the outer pipe, with the flat floor area of the first pipe being mainly parallel to the flat ceiling area of the second pipe 3. Separation of the two inner pipes 2, 3 and their separation from the outer pipe 4 is provided by a plurality of plates 5, 6, which cover the first inner pipe 2 and the second inner pipe 3, located alternately and offset from each other, which is clearly shown, for example, in the right diagram of figure 4. In ok nchatelnom state laths 5, 6 is securely connected to the two inner tubes 2, 3 and the outer tube 4, wherein a connection can be established by welding, fastening, or riveting.

The assembly of the various fuselage sections is described below with reference to other drawings. The left diagram of FIG. 2a shows a plurality of prefabricated linings 5, the shape of which corresponds to the outer contour of the prefabricated first inner tube 2. Accordingly, FIG. 2b shows the second plurality of prefabricated linings 6, the shape of which corresponds to the outer contour of the second inner tube 3. FIGS. 3a and 3b shows the manufacturing steps that follow the prefabrication step shown in figures 2a and 2b. In this arrangement, the individual linings 5 and 6 are already made, pulled over the corresponding inner pipes 2 and 3 and are securely connected to the inner pipes, for example, riveting or in the case when the linings 5, 6 and the inner pipes 2, 3 are made of metal (for example, aluminum), by contact or welding.

In the next manufacturing step, the first inner pipe 2 and the second inner pipe 3 are connected together to form a combination pipe, as shown in the right diagram of figure 4. As shown in this diagram, the linings 5 and 6 in the assembled state of the inner pipes 2 and 3 are offset each other and form a floor grating under the floor of the inner pipe 2 for the first pipe 2. To ensure reliable positioning during assembly of the first inner pipe 2 and the second inner pipe 3, the linings 5, 6 at their respective ends of straight sections contain adjusting tips 9 protruding in the direction of the other pipe 3, 2, so as to ensure that the position of said pipe in the assembled state. The combined pipe thus obtained can then be inserted into the outer pipe 4, as shown by the arrow in FIG. 4, and then the combined pipe can be welded, attached or riveted to the outer pipe 4.

Next, with reference to figures 5-8, the assembly of the middle section of the fuselage is described, however, in this case, the corresponding assembly positions basically correspond to the above-described positions. Figures 5a and 5b alternately show the first plurality of 5 linings and the second plurality of 6 linings, the contours of which also correspond to the outer contours of the respective inner tubes 2 and 3, so that the first and second plurality of linings can be screwed and pushed onto the preformed tubes 2, 3, as shown in figures 6a and 6b. Then, the inner pipes 2 and 3, containing the linings 5 and 6 so attached, are connected, as shown in the left diagram of FIG. 7, so that the flat region of the floor 7 of the first inner pipe 2 is located essentially parallel to the flat region of the ceiling 8 of the second pipe 3. As also shown in this diagram, the adjusting lugs 9 optimally adjust the two connected inner tubes 2, 3 with respect to each other and, moreover, ensure that the two inner tubes 2, 3 cannot be shifted laterally relative to each other. The combination pipe obtained in this way is then reinserted into the prefabricated outer pipe 4, as shown by the arrow in FIG. 7, and finally connects to the outer pipe 4 with free movement.

The following describes the installation of another section of the fuselage, which has a feature consisting in the additional installation of an integrated vertical tail unit. First, as in the previous case, the first and second sets of overlays 5, 6 are pushed onto prefabricated inner tubes 2, 3, as shown in figures 9-10b. Here, the individual linings of the first and second sets of overlays 5, 6 are placed with a significant offset relative to each other, so that the two inner pipes 2, 3 can be connected to form a combined pipe, as shown in figure 11. In the next stage, the front outer pipe 4 ' shown in figure 12, slides in front of the combined pipe, thus obtained. In order to attach the vertical tail unit 11 (FIG. 14), the adapter cover 10 shown in FIG. 13 is pushed back onto the combination pipe, while the upper part of said adapter comprises a connecting unit onto which the vertical tail unit 11 can be attached, for example, with bolts or rivets. As soon as the casing of the adapter 10 is attached to the combination pipe of figure 11, as described above, an additional outer pipe 4 "can be pulled back onto the combination pipe 2, 3 of figure 11, while the upper part of the combination pipe 2, 3 contains a recess for the connecting element adapter housing 10 (Figure 15.) For clarity, the last stage of installation and / or assembly of the individual components is again shown in a disassembled image in Figure 16, which clearly shows the placement of the individual components.

In conclusion, figure 18 shows the assembly of the three above-described sections of the fuselage 1, while the three sections 1 are located opposite each other and sequentially connected by suitable connecting elements, forming a single fuselage, as shown in figure 19.

It should be noted that the term “comprising” does not exclude other elements or steps. In addition, the elements described in connection with various embodiments may be combined. It should also be noted that the digital position in the claims is not limiting the scope of the claims.

List of digital items

1 - Fuselage Section

2 - The first inner pipe

3 - The second inner pipe

4 - Outer pipe

5 - Pads of the first set of pads

6 - Pads of the second set of pads

7 - Flat floor area

8 - Flat ceiling area

9 - Adjusting tip

10 - Adapter cover

11 - Vertical tail

Claims (10)

1. Section of the fuselage (1), containing a prefabricated first inner tube (2); at least one prefabricated second inner pipe (3); outer pipe (4); the first set of surrounding pads (5) and the second set of surrounding pads (6), the first inner pipe and the second inner pipe (2, 3) are enclosed in the outer pipe (4) and connected to the outer pipe (4) by a non-rigid connection, the first inner pipe (2) is enclosed in a first set of surrounding pads (5), and at least one second inner tube (3) is enclosed in a second set of surrounding pads (6), wherein the first and second sets of pads (5, 6) are connected to outer pipe (4) non-rigid connection. 2. The fuselage section (1) according to claim 1, in which the individual pads (5) of the first plurality of pads (5) are arranged alternately with offset relative to the individual pads (6) of the second plurality of pads (6) in the intersection region. 3. The fuselage section (1) according to claim 2, in which the pads (5, 6) of the first and / or second plurality of pads (5, 6) contain regulating tips (9) designed to locate the first inner pipe (2) and the second the inner pipe (3) in a certain position one above the other. 4. The fuselage section (1) according to claim 2, in which the first inner tube (2) is formed as a section of the passenger compartment, and the second inner tube (3) is formed as a section of the cargo compartment, and these sections are separated from each other by the lining intersection region ( 5, 6) forming a floor grate for the passenger compartment section. 5. The fuselage section (1) according to any one of claims 1 to 4, further comprising a tubular adapter casing (10) that is inserted between two connected inner tubes (2, 3) and the outer tube (4) and contains a connecting element for attaching a vertical tail unit to it (11). 6. The fuselage containing at least two sections of the fuselage (1), in which at least one first section of the fuselage (1) is made according to any one of claims 1 to 4 and the second section of the fuselage (1) is made according to any from claims 1 to 5, and in which at least two sections of the fuselage (1) contain corresponding frontal surfaces intended to connect at least two sections of the fuselage (1) to form a single fuselage. 7. A method of manufacturing a section of the fuselage (1), including the manufacture of the first inner pipe (2); the manufacture of at least one second inner pipe (3); connection of at least two inner pipes (2, 3) to form a combined pipe; the conclusion of the combined pipe in the outer pipe (4); the connection of the outer pipe (4) with the combination pipe (2, 3), and the prefabricated first inner pipe (2) is enclosed in a first set of surrounding linings (5), and at least one second inner pipe (3) is enclosed in a second many surrounding pads (6). 8. The method according to claim 7, in which individual linings (5) of the first plurality of linings (5) and individual linings (6) of the second plurality of linings (6) are made in advance and pushed onto the corresponding prefabricated inner pipes (2, 3). 9. The method according to claim 7, in which individual linings (5) of the first plurality of linings (5) and individual linings (6) of the second plurality of linings (6) are located on at least two inner tubes (2, 3) in this way that the individual pads (5, 6) of the first and second plurality of pads (5, 6) in the connected state of the inner pipes (2, 3) in the intersection are arranged alternately with a shift relative to each other. 10. The method according to claim 7, in which the first and second plurality of linings (5, 6) are connected to the outer pipe (4) by a non-rigid connection after the combination pipe is inserted into the outer pipe (4).

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