A method for the production of a composite material for an aircraft longeron

Abstract

The application discloses a kind of preparation methods of composite material for aircraft longerons, it is related to aircraft longeron preparation technical field, comprising: first support component, for the parts used in assembling aircraft longeron;Second support component is located in the side of first support component and can be detached with first support component connection.The beneficial effects of the present application are: the card slot on the first longeron is aligned with the card block on the second longeron, then the second longeron is moved to one end of the first longeron, so that the card block on the second longeron can extend to the inside of the card slot on the first longeron, so that the butt joint between the first longeron and the second longeron can be realized, and the first jack and the second jack arranged on the end face of the first longeron and the second longeron can be directly used for reinforcing steel bars, for reinforcing and butt joint multiple groups of the first longeron and the second longeron, so that the contact area of the contact surface of the first longeron and the second longeron can be extended, the frictional resistance is increased, and the firmness is stronger.

Description

Technical Field

[0001] This invention relates to the field of aircraft stringer manufacturing technology, specifically a method for preparing composite materials for aircraft stringers. Background Technology

[0002] The stringer type is a type of semi-monocoque fuselage, consisting of stringers, skin, and bulkheads. The stringers and skin are relatively strong and have good compressive stability. The axial force caused by bending moment is entirely borne by the upper and lower skin and stringer panels under tension and compression. Because this type of fuselage does not have strong beams, it is not suitable for large hatches. If an opening is required, it must be reinforced with special components at the opening. The fuselage structure has high torsional stiffness and is suitable for high-speed aircraft.

[0003] However, during the assembly process of existing aircraft stringers, the contact area at the contact ends is relatively small, resulting in lower stability and frictional resistance at the contact ends, leading to poor docking performance and reduced docking stability. Furthermore, the irregular structure of the stringers makes their fabrication process more difficult, increasing the workload. Summary of the Invention

[0004] The purpose of this invention is to address the problems of existing aircraft stringers, such as the small contact area at the contact ends during assembly, resulting in low stability and frictional resistance at the contact ends, leading to poor docking performance and reduced docking stability. Furthermore, the irregular structure of the stringers makes their preparation difficult, increasing the workload. This invention provides a composite material for aircraft stringers, a preparation tool, and a preparation method thereof.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a method for preparing a composite material for an aircraft stringer, wherein the composite material comprises a first support component prepared by a second preparation component and a second support component prepared by the first preparation component.

[0006] The first support assembly is used to assemble components used in aircraft stringers;

[0007] The second support component is located on one side of the first support component and is detachably connected to the first support component;

[0008] The first support component includes a first stringer, with a first protruding plate at the top of each side of the first stringer, a slot at the bottom of each first protruding plate, and a plurality of first insertion holes extending to the other end of one end of the first stringer evenly distributed at the bottom of one end of the first stringer. The second support component includes a second stringer, with a second protruding plate at the bottom of each side of the second stringer, a locking block matching the slot at the top of each second protruding plate, and a plurality of second insertion holes extending to the other end of one end of the second stringer evenly distributed at the bottom of one end of the second stringer.

[0009] The preparation of the composite material for the stringer specifically includes the following methods:

[0010] Step 1: Select high-purity aluminum ingots with a purity greater than 99.996%, magnesium ingots with a purity greater than 99.95%, manganese additives, electrolytic copper, alloy blanks, titanium alloy materials, and aluminum materials as raw materials according to their elemental composition.

[0011] Step 2: Put the high-purity aluminum ingots, magnesium ingots and electrolytic copper prepared in Step 1 into a smelting furnace with a smelting temperature of 700-750℃ for smelting. When the smelting temperature reaches 710℃, add alloy blanks, titanium alloy materials and aluminum materials. When the smelting temperature reaches 730℃, add manganese additives to obtain aluminum alloy melt.

[0012] Step 3: When the second stringer needs to be prepared, firstly extend multiple sets of first pressure plates into the interior of the first preparation tank through the first movable holes on the end face of the first preparation tank. At the same time, place two sets of first pressure pieces on both sides inside the first preparation tank. Then, directly introduce the stringer into the interior of the first preparation tank using molten aluminum alloy. Then, let it stand for a period of time until it cools and solidifies. After it solidifies, simply pull the first connecting rod outward so that the first connecting rod carries multiple sets of first pressure plates and slowly moves them out of the first movable holes on the end face of the first preparation tank. This will allow the end face of the cooled and solidified second stringer to form a second insertion hole extending to the other end. Then, move the cooled and solidified second stringer and the first pressure pieces out of the interior of the first preparation tank at the same time. Then, move the first pressure pieces forward or backward along the locking block to obtain the complete second stringer.

[0013] Step four: When the first stringer needs to be prepared, the second pressing component and the second pressing plate are directly extended along the docking hole and the second movable hole to one end of the second preparation tank, respectively. Then, the pre-prepared stringer is introduced into the second preparation tank with aluminum alloy melt and left to stand for a period of time until it cools and forms. After it cools and forms, the second connecting rod can be pulled to move the second connecting rod, carrying the second pressing component and the second pressing plate out from the docking hole and the second movable hole, respectively. This allows the first insertion hole extending to the other end of the first stringer that has cooled and formed inside the second preparation tank to be obtained, and also allows the two sides of the bottom of the first stringer to form a slot structure. Then, the cooled and formed first stringer is moved out from the inside of the second preparation tank, making its preparation simpler.

[0014] Step 5: When connecting the first and second trusses, place them parallel to each other and align the slots on the first truss with the blocks on the second truss. Then, move the second truss towards one end of the first truss so that the blocks on the second truss extend into the slots on the first truss, thus achieving the connection between the first and second trusses. Simultaneously, the first insertion hole on the end face of the first truss and the second insertion hole on the end face of the second truss can be directly used to insert reinforcing bars, reinforcing and connecting multiple sets of first and second trusses. This extends the contact area between the first and second trusses, increases frictional resistance, and enhances their strength.

[0015] As a further embodiment of the present invention: the first preparation component includes a first preparation tank, and first pressing members extending to the inner sides of the first preparation tank are provided on both sides of the top of the first preparation tank. Multiple sets of first movable holes are uniformly provided at the bottom of one end of the first preparation tank. A first pressure plate is movably connected inside each of the first movable holes. A first connecting rod is provided at the end of each set of first pressure plates away from the first preparation tank.

[0016] As a further embodiment of the present invention: the second preparation component includes a second preparation tank, a plurality of second movable holes are uniformly arranged at the bottom of one end of the second preparation tank, and a second pressure plate is movably connected inside each of the second movable holes. Both sides of one end of the second preparation tank are provided with docking holes extending to one end of their interiors, and a second pressing member is movably connected inside each of the docking holes. A second connecting rod is provided on the end face of the second pressure plate and the second pressing member.

[0017] As a further embodiment of the present invention: the first connecting rod is movably connected to the first preparation tank through the first pressure plate and the first movable hole.

[0018] As a further embodiment of the present invention: the second pressure plate and the second pressure member are movably connected to the second preparation tank through the second movable hole and the docking hole, respectively.

[0019] As a further aspect of the present invention: the bottom of the first pressing member is consistent with the structure of the slot.

[0020] As a further aspect of the present invention: the first stringer is detachably connected to the second stringer through the cooperation of the slot and the block.

[0021] Compared with the prior art, the beneficial effects of the present invention are:

[0022] 1. With the first support component, second support component, first preparation component, and second preparation component set up, when the first and second trusses are to be connected, the first and second trusses are placed parallel to each other, and the slots on the first truss are aligned with the blocks on the second truss. Then, the second truss is moved to one end of the first truss, so that the blocks on the second truss extend into the slots on the first truss, thereby realizing the connection between the first and second trusses. At the same time, the first insertion hole on the end face of the first truss and the second insertion hole on the end face of the second truss can be directly used to insert reinforcing steel bars to reinforce and connect multiple sets of first and second trusses. This extends the contact area of ​​the contact surface between the first and second trusses, increases the frictional resistance, and makes them stronger, thus improving the connection effect at the connection end and improving the stability of the connection.

[0023] 2. Using the first support component, second support component, first preparation component, and second preparation component, when preparing the second stringer, multiple sets of first pressure plates are extended into the interior of the first preparation tank through the first movable holes on the end face of the first preparation tank. Simultaneously, two sets of first pressure members are placed on either side of the interior of the first preparation tank. Then, the stringer is directly introduced into the interior of the first preparation tank using molten aluminum alloy. It is then left to stand for a period of time until it cools and solidifies. Once solidified, the first connecting rod is pulled outwards, causing it to slowly move outwards along with multiple sets of first pressure plates from the first movable holes on the end face of the first preparation tank. This creates a second insertion hole extending to the other end of the cooled and solidified second stringer. The cooled and solidified second stringer and the first pressure members are then simultaneously moved outwards from the interior of the first preparation tank. Finally, the stringer is moved forward along the locking block or... The first pressing component is moved backward to obtain the complete second stringer. When the first stringer needs to be prepared, the second pressing component and the second pressure plate are extended directly along the docking hole and the second movable hole to one end of the second preparation tank. Then, the pre-prepared stringer is introduced into the second preparation tank with aluminum alloy melt and left to stand for a period of time until it cools and solidifies. After it cools and solidifies, the second connecting rod can be pulled to move the second connecting rod, carrying the second pressing component and the second pressure plate out of the docking hole and the second movable hole respectively. This allows the first insertion hole extending to the other end of the first stringer that has cooled and solidified inside the second preparation tank to be obtained, and also allows the two sides of the bottom of the first stringer to form a slot structure. Then, the cooled and solidified first stringer is moved out of the second preparation tank, making its preparation simpler and reducing the difficulty of the work. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the structure of the present invention;

[0025] Figure 2 This is a perspective view of the present invention;

[0026] Figure 3 This is a schematic diagram of the structure of the first preparation component of the present invention;

[0027] Figure 4 This is a schematic diagram of the structure of the second preparation component of the present invention.

[0028] In the figure: 1. First support assembly; 101. First stringer; 102. First protruding plate; 103. Slot; 104. First insertion hole; 2. Second support assembly; 201. Second stringer; 202. Second protruding plate; 203. Locking block; 204. Second insertion hole; 3. First preparation assembly; 301. First preparation groove; 302. First pressing element; 303. First movable hole; 304. First connecting rod; 305. First pressure plate; 4. Second preparation assembly; 401. Second preparation groove; 402. Docking hole; 403. Second movable hole; 404. Second connecting rod; 405. Second pressing element; 406. Second pressure plate. Detailed Implementation

[0029] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0030] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating orientation or positional relationships, are based on the orientation or positional relationships shown in the accompanying drawings and are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. In the description of this invention, it should be noted that unless otherwise explicitly specified and limited, the terms "installed," "connected," "linked," and "set up" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal communication of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances. The following describes embodiments of the invention based on its overall structure.

[0031] Please see Figures 1-4 In this embodiment of the invention, a method for preparing a composite material for an aircraft stringer is provided, wherein the composite material comprises a first support component 1 prepared by a second preparation component 4 and a second support component 2 prepared by a first preparation component 3.

[0032] First support component 1, used for assembling parts used in aircraft stringers;

[0033] The second support component 2 is located on one side of the first support component 1 and is detachably connected to the first support component 1;

[0034] The first support component 1 includes a first stringer 101, with a first protruding plate 102 at the top of both sides of the first stringer 101, and a slot 103 at the bottom of each of the first protruding plates 102. A plurality of first insertion holes 104 extending to the other end are evenly provided at the bottom of one end of the first stringer 101. The second support component 2 includes a second stringer 201, with a second protruding plate 202 at the bottom of both sides of the second stringer 201. A locking block 203 matching the slot 103 is provided at the top of each of the second protruding plates 202. A plurality of second insertion holes 204 extending to the other end are evenly provided at the bottom of one end of the second stringer 201.

[0035] The preparation of the composite material for the stringer specifically includes the following methods:

[0036] Step 1: Select high-purity aluminum ingots with a purity greater than 99.996%, magnesium ingots with a purity greater than 99.95%, manganese additives, electrolytic copper, alloy blanks, titanium alloy materials, and aluminum materials as raw materials according to their elemental composition.

[0037] Step 2: Put the high-purity aluminum ingots, magnesium ingots and electrolytic copper prepared in Step 1 into a smelting furnace with a smelting temperature of 700-750℃ for smelting. When the smelting temperature reaches 710℃, add alloy blanks, titanium alloy materials and aluminum materials. When the smelting temperature reaches 730℃, add manganese additives to obtain aluminum alloy melt.

[0038] Step 3: When the second stringer 201 needs to be prepared, firstly, multiple sets of first pressure plates 305 are extended into the interior of the first preparation tank 301 through the first movable hole 303 on the end face of the first preparation tank 301. At the same time, two sets of first pressure pieces 302 are placed on both sides inside the first preparation tank 301. Then, the stringer is directly introduced into the interior of the first preparation tank 301 with aluminum alloy molten material. Then, it is left to stand for a period of time until it cools and sets. After it sets, simply pull the first connecting rod 304 outward so that the first connecting rod 304 carries multiple sets of first pressure plates 305 and slowly moves them out of the first movable hole 303 on the end face of the first preparation tank 301. This will allow the end face of the cooled and set second stringer 201 to form a second insertion hole 204 extending to the other end. Then, the cooled and set second stringer 201 and the first pressure pieces 302 are moved out of the interior of the first preparation tank 301 at the same time. Then, the first pressure pieces 302 are moved forward or backward along the locking block 203 to obtain the complete second stringer 201.

[0039] Step four: When the first stringer 101 needs to be prepared, the second pressing member 405 and the second pressing plate 406 are directly extended along the docking hole 402 and the second movable hole 403 to one end of the second preparation tank 401, respectively. Then, the pre-prepared stringer is introduced into the interior of the second preparation tank 401 with aluminum alloy melt, and then left to stand for a period of time until it cools and forms. After it cools and forms, the second connecting rod 404 can be pulled directly to move the second connecting rod 404, carrying the second pressing member 405 and the second pressing plate 406 out from the interior of the docking hole 402 and the second movable hole 403, so that the first stringer 101, which is cooled and formed inside the second preparation tank 401, can obtain the first insertion hole 104 extending to the other end, and can also form a slot 103 structure on both sides of the bottom of the first stringer 101. Then, the cooled and formed first stringer 101 is moved out from the interior of the second preparation tank 401, making its preparation simpler.

[0040] Step 5: When connecting the first truss 101 and the second truss 201, place the first truss 101 and the second truss 201 parallel to each other, aligning the slot 103 on the first truss 101 with the locking block 203 on the second truss 201. Then, move the second truss 201 towards one end of the first truss 101, allowing the locking block 203 on the second truss 201 to extend into the slot 103 on the first truss 101, thus achieving the connection between the first truss 101 and the second truss 201. Simultaneously, the first insertion hole 104 on the end face of the first truss 101 and the second insertion hole 204 on the end face of the second truss 201 can be directly used to insert reinforcing bars, reinforcing and connecting multiple sets of first trusses 101 and second trusses 201, extending the contact area of ​​the contact surfaces of the first trusses 101 and the second trusses 201, increasing frictional resistance, and simultaneously strengthening their rigidity.

[0041] Please refer to this carefully. Figure 3 The first preparation component 3 includes a first preparation tank 301. Both sides of the top of the first preparation tank 301 are provided with first pressing members 302 extending into both sides of the interior of the first preparation tank 301. Multiple sets of first movable holes 303 are uniformly provided at the bottom of one end of the first preparation tank 301. A first pressure plate 305 is movably connected inside each of the first movable holes 303. A first connecting rod 304 is provided at the end of each set of first pressure plates 305 away from the first preparation tank 301.

[0042] Please refer to this carefully. Figure 4The second preparation component 4 includes a second preparation tank 401. Multiple sets of second movable holes 403 are evenly arranged at the bottom of one end of the second preparation tank 401. A second pressure plate 406 is movably connected inside each of the second movable holes 403. Both sides of one end of the second preparation tank 401 are provided with docking holes 402 extending to one end of their interiors. A second pressing member 405 is movably connected inside each of the docking holes 402. A second connecting rod 404 is provided on the end face of the second pressure plate 406 and the second pressing member 405.

[0043] Please refer to this carefully. Figure 3 The first connecting rod 304 is movably connected to the first preparation tank 301 through the first pressure plate 305 and the first movable hole 303.

[0044] Please refer to this carefully. Figure 4 The second pressure plate 406 and the second pressure member 405 are movably connected to the second preparation tank 401 through the second movable hole 403 and the docking hole 402, respectively.

[0045] Please refer to this carefully. Figure 1 , 2 Both 3 and 3, the bottom of the first pressing part 302 has the same structure as the slot 103.

[0046] Please refer to this carefully. Figure 1 and 2 The first stringer 101 is detachably connected to the second stringer 201 through the cooperation of the slot 103 and the block 203.

[0047] The above description is merely a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A method for preparing a composite material for aircraft strands, characterized in that, The composite material is the first support component (1) prepared by the second preparation component (4) and the second support component (2) prepared by the first preparation component (3): First support assembly (1), used for assembling components used in aircraft stringers; The second support component (2) is located on one side of the first support component (1) and is detachably connected to the first support component (1); The first support component (1) includes a first stringer (101), with a first protruding plate (102) at the top of both sides of the first stringer (101), a slot (103) at the bottom of the first protruding plate (102), and a plurality of first insertion holes (104) extending to the other end of the bottom of one end of the first stringer (101). The second support component (2) includes a second stringer (201), with a second protruding plate (202) at the bottom of both sides of the second stringer (201), a locking block (203) matching the slot (103) at the top of the second protruding plate (202), and a plurality of second insertion holes (204) extending to the other end of the bottom of one end of the second stringer (201). The preparation of the composite material for the stringer specifically includes the following methods: Step 1: Select high-purity aluminum ingots with a purity greater than 99.996%, magnesium ingots with a purity greater than 99.95%, manganese additives, electrolytic copper, alloy blanks, titanium alloy materials, and aluminum materials as raw materials according to their elemental composition. Step 2: Put the high-purity aluminum ingots, magnesium ingots and electrolytic copper prepared in Step 1 into a smelting furnace with a smelting temperature of 700-750℃ for smelting. When the smelting temperature reaches 710℃, add alloy blanks, titanium alloy materials and aluminum materials. When the smelting temperature reaches 730℃, add manganese additives to obtain aluminum alloy melt. Step 3: When it is necessary to prepare the second stringer (201), firstly, extend multiple sets of first pressure plates (305) through the first movable holes (303) on the end face of the first preparation tank (301) into the interior of the first preparation tank (301). At the same time, place two sets of first pressure pieces (302) on both sides inside the first preparation tank (301). Then, directly introduce the stringer into the interior of the first preparation tank (301) using molten aluminum alloy. Then, let it stand for a period of time until it cools and solidifies. After it is solidified, simply pull the first connecting rod (304) outward to make the second stringer... A connecting rod (304) simultaneously carries multiple sets of first pressure plates (305) and slowly moves them out of the first movable hole (303) on the end face of the first preparation tank (301), so that the end face of the cooled and shaped second stringer (201) forms a second insertion hole (204) extending to the other end. Then, the cooled and shaped second stringer (201) and the first pressure member (302) are simultaneously moved out of the interior of the first preparation tank (301). Then, the first pressure member (302) is moved forward or backward along the locking block (203) to obtain the complete second stringer (201). Step four: When the first stringer (101) needs to be prepared, the second pressing member (405) and the second pressing plate (406) are directly extended along the mating hole (402) and the second movable hole (403) to one end of the second preparation tank (401), respectively. Then, the pre-prepared stringer is introduced into the interior of the second preparation tank (401) using molten aluminum alloy. It is then left to stand for a period of time until it cools and solidifies. After it cools and solidifies, the second connecting rod (404) can be pulled directly to carry the stringer. The second pressing member (405) and the second pressing plate (406) are removed from the inside of the docking hole (402) and the second movable hole (403) respectively, so that the first stringer (101) located in the second preparation tank (401) can be cooled and formed to obtain the first insertion hole (104) extending to the other end, and the two sides of the bottom of the first stringer (101) can form a slot (103) structure. Then the cooled and formed first stringer (101) is removed from the inside of the second preparation tank (401), making its preparation simpler. Step 5: When docking the first stringer (101) and the second stringer (201), place the first stringer (101) and the second stringer (201) parallel to each other, aligning the slot (103) on the first stringer (101) with the locking block (203) on the second stringer (201). Then, move the second stringer (201) towards one end of the first stringer (101), so that the locking block (203) on the second stringer (201) extends into the interior of the slot (103) on the first stringer (101). This allows for the docking connection between the first truss (101) and the second truss (201). At the same time, the first insertion hole (104) on the end face of the first truss (101) and the second insertion hole (204) on the end face of the second truss (201) can be directly used to insert reinforcing bars, which can be used to reinforce and dock multiple sets of first trusses (101) and second trusses (201), extend the contact area of ​​the contact surface between the first truss (101) and the second truss (201), increase the frictional resistance, and at the same time make it stronger.

2. The method for preparing a composite material for an aircraft stringer according to claim 1, characterized in that, The first preparation component (3) includes a first preparation tank (301). Both sides of the top of the first preparation tank (301) are provided with first pressing members (302) extending to both sides inside the first preparation tank (301). Multiple sets of first movable holes (303) are uniformly provided at the bottom of one end of the first preparation tank (301). A first pressure plate (305) is movably connected inside the first movable hole (303). A first connecting rod (304) is provided at the end of the multiple sets of first pressure plates (305) away from the first preparation tank (301).

3. The method for preparing a composite material for an aircraft stringer according to claim 2, characterized in that, The second preparation component (4) includes a second preparation tank (401). Multiple sets of second movable holes (403) are uniformly arranged at the bottom of one end of the second preparation tank (401). A second pressure plate (406) is movably connected inside each of the second movable holes (403). A docking hole (402) extending to one end of the second preparation tank (401) is provided on both sides of one end. A second pressure member (405) is movably connected inside each of the docking holes (402). A second connecting rod (404) is provided on the end face of the second pressure plate (406) and the second pressure member (405).

4. The method for preparing a composite material for an aircraft stringer according to claim 3, characterized in that, The first connecting rod (304) is movably connected to the first preparation tank (301) through the first pressure plate (305) and the first movable hole (303).

5. A method for preparing a composite material for an aircraft stringer according to claim 4, characterized in that, The second pressure plate (406) and the second pressure member (405) are movably connected to the second preparation tank (401) through the second movable hole (403) and the docking hole (402), respectively.

6. A method for preparing a composite material for an aircraft stringer according to claim 5, characterized in that, The bottom of the first pressing member (302) is consistent with the structure of the slot (103).

7. A method for preparing a composite material for an aircraft stringer according to claim 6, characterized in that, The first stringer (101) is detachably connected to the second stringer (201) through the cooperation of the slot (103) and the block (203).

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