RU202616U1 - Aircraft fuselage from truss filler - Google Patents

Abstract

The utility model relates to the field of aviation, namely to multilayer panels and fuselage structures containing multilayer panels, and can be used in the manufacture of aircraft. The fuselage of an aircraft made of truss filler is a volumetric structure consisting of a load-bearing set of transverse and longitudinal elements, external and internal skins, between which the truss filler is located. In this case, the truss filler is made of rod elements, which are located in the longitudinal and transverse directions, and is a structure of composite material in the form of zigzag rod elements, which are located throughout the volume between the inner and outer skins, which are interconnected with the help of grooves and spikes, forming at the junction of the longitudinal and transverse zigzag bar elements of the tops, which are directed in opposite directions and are connected to the outer and inner skins. Moreover, the lower part of the tops of the frames is supported by the inner skin, and the upper part of the tops of the spars is reinforced by the outer skin. The skins have holes for connecting to the tops of frames and side members. Moreover, the grooves and tops of the frames and spars are interconnected by means of adhesive elements. In this case, the rods located between the tops in the longitudinal and transverse directions and in the bases of the transverse elements give the shape of a circle to the outer and inner skins, forming a cylindrical shape, and open cavities are formed between the zigzag rod elements for laying cables and pipelines. The technical result of the claimed utility model is the creation of an effective fuselage of the aircraft by reducing the weight of the structure while increasing the strength characteristics by simplifying the structure and increasing its rigidity. 4 ill.

Description

The utility model relates to the field of aviation, namely to multilayer panels and fuselage structures containing multilayer panels, and can be used in the manufacture of aircraft.

The problems associated with moisture condensation in structures used in conditions of varying temperature and humidity are well known in the prior art, and especially in aircraft construction. Moisture condensation occurs during flight when humid air meets a cooled structure at a low air temperature overboard and the outer surface of the skin. If the temperature of the structure is below the freezing point of water, this moisture turns into ice. The lowering of the aircraft and the heating of the skin leads to thawing of the ice, and the water flows down, collects in the arches and recesses of the structure. When multilayer panels are used in the fuselage structure, containing two skins and a filler located between them, moisture condenses inside the multilayer panel, which can lead to an increase in the weight of the fuselage and the destruction of adhesive joints, including adhesive joints between the core and the skins. The amount of condensed moisture depends mainly on the configuration and design of the aircraft. Operating conditions, environment and maintenance. At the same time, since humid air inevitably collides with the cooled metal, condensation of water, in principle, cannot be avoided, therefore, an important task is to create such designs of multilayer panels and fuselages, as well as drainage methods that provide the ability to remove condensed liquid from multilayer fuselage panels, which increases the strength , and as a result, the reliability of the design.

Known is a multilayer panel containing the first and second skins and a zigzag corrugated filler placed between them, unfolding onto a plane, with side faces located at an angle to one another with the formation of alternating protrusions and depressions and having contact areas with the upper and lower skins (Patent RU 2038265 C1, B64C 3/26, publ. 27.06. 1995)

The disadvantage of the known multilayer panel is the absence of through channels designed for natural and / or forced passage of air and / or liquid and its removal from the multilayer panel, which reduces the strength and ultimately the reliability of the multilayer panel.

Known "Multilayer panel" containing several layers of filler of various designs, including skin, honeycomb filler formed by corrugated strips connected to each other, and additional filler layers in the form of a zigzag corrugation, located between the skin and honeycomb filler, forming channels for draining condensed liquid ( Patent RU 2085671 C1, E04C 2/32, B32B 3/12, B32B 3/28, publ. 27.07.1997)

The disadvantage of this design of a multilayer panel is the insufficient strength and reliability of both the multilayer panel itself and the joints of the panels with each other, since to ensure the passage of condensate through the channels of the zigzag trapezoidal corrugation, at least two sides of the honeycomb filler are made of windows and, accordingly, these the edges are not connected with additional layers of zigzag core, which reduces the strength and rigidity of the panel as a whole. In addition, the panel lacks any longitudinal and transverse elements along its contour. Consequently, the panels are connected to each other only along the skin and core, which reduces the strength of the panels' joints.

Also, the disadvantage of this design is that when such a flat panel is deformed in order to give it a curvature in any direction, the edges of the honeycomb and zigzag fillers are deformed so that the windows and channels for condensate drainage can completely overlap, which reduces the strength and reliability of the structure.

The closest in technical essence and taken as a prototype is "Multilayer panel, fuselage and fuselage drainage method", containing a fuselage, with a load-bearing frame, having transverse load-bearing elements located across the longitudinal axis of the fuselage, and the multilayer panels fixed on them contain the first and second skin and the filler located between them, located across the longitudinal axis of the fuselage, and to the two opposite sides of the multilayer panel located along the longitudinal axis of the fuselage, docking elements in the form of hollow tips are attached, in each of which, in the side wall adjacent to the filler, a system of holes is made, connecting the through channels with a completely corresponding ending and allowing air and / or liquid to pass through the through channels and the cavity of the corresponding ending (Patent RU 2297948 C2, B64C 1/00, B32B 3/00, publ. 27.12.2006).

The disadvantage of the known technical solution is the large weight of the structure due to the filler made in the form of a corrugation, the impossibility of making cable channels, pipelines in the transverse and longitudinal direction between the inner and outer skins, due to the design features of the corrugated filler, which reduces the compressive and torsional rigidity fuselage, the lack of the ability to control the connection of the corrugated core and skin, which generally leads to a decrease in the strength and reliability of the panel.

The task of the utility model to be solved is to reduce the weight of the structure due to the constructive implementation of the filler for the three-layer structure of the fuselage skin, while simplifying it and manufacturing the aircraft fuselage - without the slipway assembly of the skin, as well as increasing the strength characteristics by increasing the rigidity of the fuselage structure by arranging zigzag rod elements along the entire internal volume of the fuselage skin space, the open cavities of which can be used as channels for laying cables and pipelines. The fuselage connection through the spikes and grooves increases the strength of the skin and core connections, as well as the quality of the connection control. The connection of the tops of the base of the frame forms a circle, which makes it possible to connect the inner skin to the filler without the use of additional slipways, which also increases the efficiency of the fuselage.

The technical result of the claimed utility model is the creation of an effective fuselage of the aircraft by reducing the weight of the structure while increasing the strength characteristics by simplifying the structure and increasing its rigidity.

The technical result is achieved by the fact that in the aircraft fuselage from truss filler, which is a volumetric structure consisting of a load-bearing set of transverse and longitudinal elements, external and internal skins, according to which a truss filler is located between the external and internal skins, and the filler is made of core elements that are located in the longitudinal, replacing the spar, and the transverse, replacing the frame, directions of the power set, and is a structure of composite material in the form of zigzag bar elements that are located throughout the volume between the inner and outer skins, connected with each other using grooves and spikes, forming at the junction of the longitudinal and transverse zigzag bar elements of the tops, which are directed in opposite directions and connected to the outer and inner skins, and the lower part of the tops of the frames is reinforced by the inner sheath vkoy, and the upper part of the tops of the spars is reinforced by an outer skin, the skin has holes for connection with the tops of the frames and spars, and the grooves and tops of the frames and the spars are connected to each other using adhesive elements, while the rods located between the tops in the longitudinal and transverse directions and in the bases of the transverse elements, they give the shape of a circle to the outer and inner skins, forming a cylindrical shape, and between the zigzag rod elements, open cavities are formed for laying cables and pipelines.

To clarify the technical essence, consider the drawings:

in fig. 1 - shows the fuselage of an aircraft in the form of a three-layer structure with external and internal skin;

in fig. 2 - shows the fuselage of the aircraft in the form of a three-layer structure with a lower skin;

in fig. 3 - frame made of zigzag rods;

in fig. 4 - spar in the form of zigzag rods, where:

1 - holes in the skins for the spikes;

2 - external cladding;

3 - inner lining;

4 - a spar made of zigzag rods, in the longitudinal direction;

5 - frame made of zigzag rods, in the transverse direction;

6 - spikes in the frame for the inner lining;

7 - grooves in the frame;

8 - grooves in the spar;

9 - thorns in the spar for the outer skin;

10- spikes in the side member for the inner lining;

11- rods between vertices in the transverse direction;

12 - rods connecting the tops of the base (inner lining);

13 - rods between the tops in the longitudinal direction;

14 - rods connecting the tops of the rods, reinforcing the outer skin;

15 - open cavities

The novelty of the claimed useful model of an aircraft fuselage is a decrease in its weight characteristics with a simultaneous increase in the strength characteristics of the aircraft fuselage, performed due to the location between the outer and inner skin of the truss filler, and the filler is made of rod elements that are located in the longitudinal, replacing the spar and transverse, replacing the frame, the direction of the force set and is a structure made of composite material in the form of zigzag bar elements, which are located throughout the volume between the inner and outer skins, interconnected by means of grooves and spikes, forming at the junction of the longitudinal and transverse zigzag bar elements, the tops that are directed in opposite directions and are connected to the outer and inner skins, the skins have holes for connection with the tops of the frames and spars, and the grooves and tops of the frames and the side members are connected to each other using glue elements, while the rods between the tops in the longitudinal and transverse directions, as well as in the bases of the transverse elements, give the shape of a circle to the outer and inner skins, open cavities are formed between the zigzag rod elements for laying cables and pipelines.

The structure of the aircraft fuselage made of a composite material (metal), which is a structure made of carbon fiber (metal) material, consisting of an outer skin 2 (Fig. 1) and an inner skin 3 (Fig. 1), holes on the inner and outer skin 1 (Fig. .1, 2) for the spikes of the longitudinal zigzag elements (spars) 4 (Fig. 2) and transverse zigzag elements (frames) 5 (Fig. 2), and the transverse zigzag rod elements 5 (Fig. 3) have grooves 7 of the frames (Fig. .3) to connect them with the grooves of the side members 8 (Fig. 4), spikes 6 (Fig. 3) for connection with the holes 1 (Fig. 1) of the inner lining 3, longitudinal bar elements 11 (Fig. 3) are located between the tops in transverse direction with grooves 7 (Fig. 3) and the base of the inner skin, transverse bar elements 4 (Fig. 4) have spikes 9 (Fig. 4) for connection with the outer skin, transverse bar elements 14 (Fig. 4) located on the basis of zigzag rods, spikes 10 (figure 4) connect with outer skin 2 (Fig. 1) through holes 1 (Fig. 1), rods between the tops in the longitudinal direction 13 (Fig. 4), located in the middle between the rods 14 (Fig. 4) and the tops with spikes 10 in the spar under the inner sheathing (Fig. 4).

Truss aggregate construction production:

The assembly of the structure is carried out as follows: The transverse bar elements (frames) 5 (Fig. 2) are connected to the longitudinal zigzag bar elements (spars) 4 (Fig. 2), so that the tops of the transverse zigzag bar elements, on which the grooves 7 of the frames ( Fig. 3) entered the grooves 8 of the spars (Fig. 4), at the ends of the longitudinal zigzag rod elements (spars) 4 (Fig. 4), studs 9 (Fig. 4) are made for connection with the outer skin 2, transverse zigzag rod elements (frames ) 5 have thorns 6 (Fig. 3) for connection with the inner lining 3 (Fig. 1) through holes 1 (Fig. 1), transverse zigzag bar elements 5 have rods 11 (Fig. 3) located between the tops of the thorns 6 and grooves 7, and rods 12 (Fig. 3) connecting the tops of the base of the inner skin with the grooves 6 (Fig. 3), forming a circle to give the inner skin a cylindrical shape, the longitudinal rod elements 4 have rods 13 (Fig. 4), located data at the same distance between the tops with the spikes 10 for the inner skin 3 and the spikes 9 for the outer skin (Fig. 4), the rods 14 (Fig. 4) connect the tops with the slots of the spars 8, reinforcing the outer shell (Fig. 4), forming a shape circle to give the outer skin 2 the shape of a cylinder, thus reducing the weight of the aircraft fuselage structure by performing a truss filler throughout the entire fuselage skin, consisting of outer 2 and inner 3 skin with holes 1 over the entire surface of the fuselage for longitudinal 9 and transverse spikes 6 elements of the strength set of the skin filler by simplifying the structure with a simultaneous increase in its rigidity due to the connection of the longitudinal 4 and transverse 5 rod elements using holes 1 in the outer 2 and inner 3 skin and pins 6, 9 located at the tops of their connections, while the emergence of the possibility visual inspection of the joints between sheathing and filler, also increases the stiffness characteristics Ki. The fuselage connection through pins 6.9 and grooves 7.8 increases the strength of the skin and core connections, as well as the quality of the connection control. The connection of the tops of the base of the frame 5 forms a circle, which makes it possible to connect the inner skin 3 with the filler without the use of additional slipways, which also increases the efficiency of the fuselage.

In terms of its technical and economic advantages, in comparison with the known analogues, the claimed fuselage structure made of truss filler allows to reduce the weight of the aircraft structure while increasing the strength and stiffness characteristics of the aircraft fuselage due to the implementation of a truss filler throughout the entire volume of the fuselage skin, consisting of external and inner skins with holes along the entire surface of the fuselage for the spikes of the longitudinal and transverse elements of the load-bearing set of the skin filler, and the power set of elements is located over the entire surface of the fuselage skin from longitudinal and transverse elements and is made of rods of a zigzag profile over the entire surface, which ensures the distribution of a uniform load the torques arising in flight on the entire surface of the fuselage, and simplification of the structure with a simultaneous increase in the rigidity of the structure due to the connection of longitudinal and transverse rod elements with p by means of holes in the outer and inner skins and spikes located at the tops of their joints, as well as the possibility of visual inspection of the joints of the skin and filler, which also increases the rigidity characteristics, reducing the quality control time of the product, increasing the reliability of the fuselage structure, and in general, increases the efficiency of the fuselage with a power set in the form of a truss filler in terms of reducing the weight of the structure and increasing the strength characteristics of the fuselage.

Claims (1)

The fuselage of an aircraft made of truss filler, which is a volumetric structure consisting of a load-bearing set of transverse and longitudinal elements, external and internal skins, characterized in that a truss filler is located between the external and internal skins, and the filler is made of rod elements that are located in the longitudinal , replacing the spar, and transverse, replacing the frame, the directions of the power set, and is a structure made of composite material in the form of zigzag bar elements that are located throughout the volume between the inner and outer skins, interconnected with the help of grooves and spikes, forming in place connections of longitudinal and transverse zigzag rod elements of the apex, which are directed in opposite directions and are connected to the outer and inner skins, and the lower part of the tops of the frames is reinforced by the inner skin, and the upper part of the tops of the spars along reinforced by an outer skin, the skins have holes for connecting to the tops of the frames and side members, and the grooves and tops of the frames and side members are connected to each other using adhesive elements, while the rods located between the tops in the longitudinal and transverse directions and in the bases of the transverse members give the shape of a circle the outer and inner skins, forming a cylindrical shape, and between the zigzag bar elements, open cavities are formed for laying cables and pipelines.

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