Main beam structure, paddle structure and aircraft structure

Abstract

The utility model discloses a main beam structure, blade structure and aircraft structure, the main beam structure is used for the blade structure, the main beam structure comprises an upper edge strip, a lower edge strip and a web plate, the upper edge strip and the lower edge strip respectively extend along the left-right direction, and the upper edge strip and the lower edge strip are arranged at intervals along the up-down direction; the web plate is arranged between the upper edge strip and the lower edge strip, the two ends of the web plate are connected with the upper edge strip and the lower edge strip respectively, and the web plate is made of chopped fiber reinforced composite materials.

Description

Technical Field

[0001] The utility model relates to the field of aviation technology, in particular to a main beam structure, a blade structure and an aircraft structure. Background Art

[0002] In the aircraft's rotor system, the blade is an important component that provides lift. Due to the particularity of the blade's working environment and the particularity of the blade's structure itself, the blade's structure design must meet requirements in terms of strength, stiffness, dynamics, and fatigue life.

[0003] The blade skin in the prior art uses a main beam with a large cross-section change along the length direction due to the irregular shape of the blade. The main beam of a traditional composite blade is made of continuous fiber fabric or prepreg, where a single layer is made of multiple fabrics or prepregs spliced ​​and overlapped. Due to the large change in the cross-section of the main beam, the cutting design and laying of the fabric or prepreg are more difficult, and the design freedom of the main beam shape is also limited.

[0004] The above contents are only used to assist in understanding the technical solution of the present utility model and do not constitute an admission that the above contents are prior art. Utility Model Content

[0005] The main purpose of the utility model is to provide a main beam structure, a blade structure and an aircraft structure, aiming to solve the problem that the main beam of a traditional composite blade is made of continuous fiber fabric or prepreg, wherein a single layer is made of multiple fabrics or prepregs spliced ​​and overlapped. Due to the large change in the cross section of the main beam, the cutting design and laying difficulty of the fabric or prepreg is increased, and the design freedom of the main beam shape is also limited.

[0006] In order to achieve the above object, the utility model provides a main beam structure for a blade structure, the main beam structure comprising:

[0007] An upper edge bar and a lower edge bar, the upper edge bar and the lower edge bar are respectively extended in the left-right direction, and the upper edge bar and the lower edge bar are arranged at intervals in the up-down direction;

[0008] The web is arranged between the upper edge strip and the lower edge strip, and the two ends are respectively connected to the upper edge strip and the lower edge strip, and the web is made of short-cut fiber reinforced composite material.

[0009] The preferred main beam structure is characterized in that the number of the webs is one or more.

[0010] Preferably, in the main beam structure, an installation space is formed between the upper edge bar and the lower edge bar, and the web has a first end and a second end located at opposite ends, the first end is installed on the upper edge bar, and the second end is installed on the lower edge bar; wherein,

[0011] The first end is not mounted on the edge of the upper edge strip; or,

[0012] The second end is not mounted on the edge of the lower edge strip; or,

[0013] The first end is installed at the edge of the upper edge bar, the second end is installed at the edge of the lower edge bar, and the first end and the second end are respectively located at different sides of the upper edge bar and the lower edge bar in the left-right direction.

[0014] Preferably, in the main beam structure, the first end and the second end are located at the middle of the upper edge bar and the lower edge bar, respectively.

[0015] Preferably, in the main beam structure, the material of the upper edge strip and the lower edge strip is a combination of one or more of woven fabric, warp knitted multi-axial fabric, and woven fabric.

[0016] In order to achieve the above object, the utility model also provides a blade structure, the blade structure comprising:

[0017] Inner skin;

[0018] The main beam structure is arranged in the inner skin, and the upper edge strip and the lower edge strip of the main beam structure are respectively arranged to abut against the upper end and the lower end of the inner skin;

[0019] A trailing edge is disposed adjacent to the inner skin in the left-right direction; and

[0020] The outer skin is respectively sleeved on the outer periphery of the trailing edge and the inner skin to combine the separate modules into a whole.

[0021] Preferably, in the blade structure, the outer skin comprises a plurality of layers of single-layer woven fabrics, and the plurality of layers of single-layer woven fabrics are reciprocatingly woven.

[0022] Preferably, in the blade structure, the inner skin comprises one or more of a woven fabric, a warp-knitted multi-axial fabric, and a woven fabric.

[0023] Preferably, in the blade structure, the inner skin comprises a first single-layer woven fabric, a first multi-layer uniaxial fabric, a second single-layer woven fabric, a second multi-layer uniaxial fabric, and a third single-layer woven fabric which are sequentially stacked together in an up-and-down direction.

[0024] In order to achieve the above object, the utility model provides an aircraft structure, which includes the above main beam structure or the above blade structure.

[0025] The utility model has at least the following beneficial effects:

[0026] The main beam structure provided by the utility model includes an upper edge strip and a lower edge strip, as well as a web, which are arranged in modules, reducing the difficulty of laying in the manufacturing process. In addition, the web adopts short-cut fiber reinforced composite materials, which can better meet the requirements of compression and shear stiffness when subjected to compression and shear force, and meet the overall bending and torsion resistance of the main beam structure, solving the problem that the main beam of the traditional composite blade is made of continuous fiber fabric or prepreg, in which a single layer is made of multiple pieces of fabric or prepreg spliced ​​and overlapped. Due to the large change in the cross section of the main beam, the difficulty of cutting, designing and laying the fabric or prepreg is increased, and the design freedom of the main beam shape is also limited.

[0027] Furthermore, the utility model adopts chopped fiber reinforced composite materials through the web, and the web is arranged between the upper edge strip and the lower edge strip, so that the web has a greater degree of freedom and can freely withstand compression and shear forces, so that the structural stability is higher.

[0028] Furthermore, the upper edge strips and the lower edge strips are modularly arranged with the web and the material of the upper edge strips and the lower edge strips is a combination of one or more of woven fabrics, warp-knitted multi-axial fabrics, and woven fabrics. In this way, the width of the upper edge strips and the lower edge strips can be freely adjusted to meet the performance and force transmission requirements, and the thickness can be freely adjusted to adjust the bending stiffness of the main beam structure; similarly, the upper edge strips and the lower edge strips are modularly arranged with the web and the web is a short-fiber reinforced composite material. The height of the web can also be freely adjusted to adapt to changes in the cross-section of the main beam structure, and the thickness can be freely adjusted to meet the requirements of its compressive and shear stiffness, thereby meeting the overall bending and torsional performance of the main beam structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 A schematic diagram of the structure of an embodiment of a blade structure provided by the utility model;

[0030] Figure 2 for Figure 1 The enlarged schematic diagram of point A in the middle;

[0031] Figure 3 A schematic diagram of an embodiment of a main beam structure;

[0032] Figure 4 A schematic diagram of another embodiment of the main beam structure.

[0033] 100-blade structure, 1-main beam structure, 11-web, 111-first end, 112-second end, 12-upper edge strip, 13-lower edge strip, 2-inner skin, 3-trailing edge, 4-outer skin.

[0034] The purpose, features and advantages of the present invention will be further described in conjunction with the embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0035] The technical solution of the utility model will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the utility model, rather than all of the embodiments. The utility model will be described in detail below with reference to the accompanying drawings and in conjunction with the embodiments. It should be noted that the embodiments of the utility model and the features in the embodiments can be combined with each other without conflict.

[0036] In the embodiments of the present invention, the term "and / or" describes the association relationship of the associated objects, indicating that three relationships may exist. For example, A and / or B may represent: A exists alone, A and B exist at the same time, and B exists alone. The character " / " generally indicates that the associated objects before and after are in an "or" relationship.

[0037] It should be noted that the terms "first", "second", etc. in the specification and claims of the utility model and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence.

[0038] The term "plurality" in the embodiments of the present invention refers to two or more than two, and other quantifiers are similar thereto.

[0039] In the present invention, unless otherwise specified, the directional words used, such as "up, down, top, bottom", usually refer to the directions shown in the drawings, or to the components themselves in the vertical, perpendicular or gravity directions; similarly, for ease of understanding and description, "inside and outside" refer to the inside and outside relative to the outline of each component itself, but the above-mentioned directional words are not used to limit the present invention.

[0040] In order to solve the above problems, the present embodiment relates to a main beam structure, such as Figure 1 and Figure 2 As shown, for a blade structure 100, the main beam structure 1 includes an upper edge bar 12 and a lower edge bar 13, and a web 11, wherein the upper edge bar 12 and the lower edge bar 13 are respectively extended in the left-right direction, and the upper edge bar 12 and the lower edge bar 13 are arranged at intervals in the up-down direction; the web 11 is arranged between the upper edge bar 12 and the lower edge bar 13, and the two ends are respectively connected to the upper edge bar 12 and the lower edge bar 13, and the web 11 is a chopped fiber reinforced composite material.

[0041] The blade skin in the prior art uses a main beam with a large cross-section change along the length direction due to the irregular shape of the blade. The main beam of a traditional composite blade is made of continuous fiber fabric or prepreg, where a single layer is made of multiple fabrics or prepregs spliced ​​and overlapped. Due to the large change in the cross-section of the main beam, the cutting design and laying of the fabric or prepreg are more difficult, and the design freedom of the main beam shape is also limited.

[0042] The main beam structure 1 of the utility model includes an upper edge bar 12, a lower edge bar 13, and a web 11, which are arranged in modules, thereby reducing the difficulty of laying during the manufacturing process. In addition, the web 11 adopts short-fiber reinforced composite materials, which can better meet the requirements of compressive and shear stiffness when subjected to compression and shear force, and meet the overall bending and torsional performance of the main beam structure 1.

[0043] Furthermore, compared with the traditional web 11 which is made of steel plate and cannot withstand compression and shear forces, the utility model adopts chopped fiber reinforced composite materials through the web 11, and the web 11 is arranged between the upper edge bar 12 and the lower edge bar 13, so that the web 11 has a greater degree of freedom and can freely withstand compression and shear forces, so that the structural stability is higher.

[0044] The number of the webs 11 is one or more. The webs 11 may be arranged in various forms, for example, in a Z-shape, an I-shape, etc. Specifically, an installation space is formed between the upper edge bar 12 and the lower edge bar 13, and the web 11 has a first end 111 and a second end 112 located at opposite ends, respectively, the first end 111 is installed on the upper edge bar 12, and the second end 112 is installed on the lower edge bar 13; wherein the first end 111 is not installed on the edge of the upper edge bar 12; or, the second end 112 is not installed on the edge of the lower edge bar 13; or,

[0045] The first end 111 is installed on the edge of the upper edge bar 12 , the second end 112 is installed on the edge of the lower edge bar 13 , and the first end 111 and the second end 112 are respectively located on different sides of the upper edge bar 12 and the lower edge bar 13 in the left-right direction.

[0046] It should be noted that the first end 111 is not installed on the edge of the upper edge strip 12, which can be understood as the first end 111 is installed in the middle of the upper edge strip 12, which can be the center position of the upper edge strip 12, or the area of ​​the upper edge strip 12 that is not the center position. If the first end 111 is not installed on the edge of the upper edge strip 12, then the second end 112 can be installed on the edge of the lower edge strip 13, or it can be installed in the non-edge area of ​​the lower edge strip 13 (for example, the center position of the lower edge strip 13). The edge of the upper edge strip 12 mentioned in the utility model is the two end edges of the upper edge strip 12, and the edge of the lower edge strip 13 is the two end edges of the lower edge strip 13.

[0047] The fact that the second end 112 is not installed on the edge of the lower edge bar 13 can be understood as the second end 112 being installed in the middle of the lower edge bar 13, which can be the center position of the lower edge bar 13 or a non-center position area of ​​the lower edge bar 13. If the second end 112 is not installed on the edge of the lower edge bar 13, the first end 111 can be installed on the edge of the upper edge bar 12 or a non-edge area of ​​the upper edge bar 12 (for example, the center position of the upper edge bar 12).

[0048] like Figure 3 As shown, the first end 111 is installed on the edge of the upper edge bar 12, the second end 112 is installed on the edge of the lower edge bar 13, and the first end 111 and the second end 112 are respectively located on different sides of the upper edge bar 12 and the lower edge bar 13 along the left-right direction. It can be understood that the upper edge bar 12, the lower edge bar 13 and the web 11 are arranged in a "Z" shape.

[0049] like Figure 4 As shown, when the main beam structure 1 is subjected to stress, the upper edge bar 12 and the lower edge bar 13 are mainly subjected to tension, and the web 11 located between the upper edge bar 12 and the lower edge bar 13 is mainly subjected to compression and shear force. Compared with the two ends of the web 11 connected to the edges on the same side of the upper edge bar 12 and the lower edge bar 13, the two ends of the web 11 connected to the middle of the upper edge bar 12 and the lower edge bar 13 have a better load-bearing effect. In this embodiment, the first end 111 and the second end 112 are respectively located in the middle of the upper edge bar 12 and the lower edge bar 13.

[0050] The material of the upper edge strip 12 and the lower edge strip 13 is a combination of one or more of woven fabrics, warp knitted multiaxial fabrics, and woven fabrics. The upper edge strip 12 and the lower edge strip 13 can be cut as a single layer, which greatly reduces the difficulty of laying in the manufacturing process. In addition, the upper edge strip 12 and the lower edge strip 13 are arranged in modules with the web 11, and the material of the upper edge strip 12 and the lower edge strip 13 is a combination of one or more of woven fabrics, warp knitted multiaxial fabrics, and woven fabrics. In this way, the upper edge strip 12 and the lower edge strip 13 can freely adjust the width to meet the performance and force transmission requirements, and the thickness can be freely adjusted to adjust the bending stiffness of the main beam structure 1; similarly, the upper edge strip 12 and the lower edge strip 13 are arranged in modules with the web 11, and the web 11 is a short-cut fiber reinforced composite material. The web 11 can also freely adjust the height to adapt to the changes in the cross section of the main beam structure 1, and the thickness can be freely adjusted to meet its compression and shear stiffness requirements, thereby meeting the overall bending and torsion resistance of the main beam structure 1.

[0051] The utility model provides a blade structure 100, which includes an inner skin 2, the main beam structure 1, a trailing edge 3, and an outer skin 4. The main beam structure 1 is arranged in the inner skin 2, and the upper edge strip 12 and the lower edge strip 13 of the main beam structure 1 are respectively abutted against the upper end and the lower end of the inner skin 2; the trailing edge 3 is adjacent to the inner skin 2 in the left and right directions; the outer skin 4 is respectively sleeved on the outer periphery of the trailing edge 3 and the inner skin 2 to combine the separated modules into a whole.

[0052] In the prior art, the blades are formed by woven fabrics, uniaxial fabrics or prepreg paving, and the skin and main beam are spliced ​​or overlapped by cut fabric or prepreg sheets. The splicing and overlapping process is cumbersome, requires high precision and has low efficiency. In addition, due to the large changes in the geometric shape of the blades, the cutting design of the fabric or prepreg is difficult, and the material utilization rate is low, resulting in great difficulty in blade manufacturing, poor product consistency, low production capacity and high production cost.

[0053] The utility model splits the blade structure 100 into different functional areas such as the main beam structure 1, the inner skin 2, the trailing edge 3, and the outer skin 4, so that each module of the blade structure 100 can be preformed, and then flexibly combined to build the entire blade structure 100, thereby solving the problems of difficulty in large-scale mass production of high-performance composite blades, poor product consistency, and high production costs. In addition, after the utility model is modularized, different modules can also be made of different materials according to their performance requirements, which can be more suitable for the stress of the module itself and the material performance can be better exerted.

[0054] Furthermore, compared with traditional webs made of laminates made of woven fabrics and unidirectional fabrics or prepregs, the main load-bearing direction of the laminates is inconsistent with the compression and shear directions of the webs, and the performance utilization rate of the laminates is low. The utility model uses short fiber reinforced composite materials to form the webs, and the material has balanced performance in all directions, which can all be used as the main load-bearing direction.

[0055] Furthermore, each split module can be further split according to needs, for example, the trailing edge 3 can also be made of more suitable materials according to needs, such as short-cut fibers. Furthermore, the trailing edge 3 can also be further modularized, for example, one material is used for the regular part, and multiple materials can be used for the irregular part, and finally assembled together to form a whole. More specifically, the area A part of the trailing edge is irregular in shape, difficult to make, and very thin, and the area B part is regular, so the area A part can be separated and made separately, and the area B part can be made separately, and finally the two parts can be assembled together to form a whole. Furthermore, the area A part can be made in multiple modules according to the situation, and so on.

[0056] In other embodiments, the C region of the trailing edge may also bear greater load, and the C region may be separated and manufactured separately.

[0057] It should be noted that other modules can also be further modularized. The principle is as mentioned above and will not be described in detail here.

[0058] Specifically, the outer skin 4 includes several layers of single-layer woven fabrics, which are woven back and forth, thereby ensuring the integrity, uniformity, and manufacturing efficiency of the blade skin while improving the ability of the skin to bear and transmit the torque, flapping, and shimmy bending moments of the blade. The outer skin 4 may include one layer of single-layer woven fabric or two layers of single-layer woven fabrics, which are not specifically limited here.

[0059] The inner skin 2 includes one or more of a woven fabric, a warp knitted multi-axial fabric, and a woven fabric. For example, the inner skin 2 can be a combination of a woven fabric and a warp knitted multi-axial fabric, and there can be multiple combinations, and the specific combination is not specifically limited here. In this embodiment, the inner skin 2 includes a first single-layer woven fabric, a first multi-layer uniaxial fabric, a second single-layer woven fabric, a second multi-layer uniaxial fabric, and a third single-layer woven fabric stacked in sequence along the up and down direction.

[0060] The utility model provides an aircraft structure, which includes the main beam structure 1 or the blade structure 100. An embodiment of the aircraft structure includes an embodiment of the main beam structure 1 or an embodiment of the blade structure 100. The beneficial effects of the main beam structure 1 or the blade structure 100 can be applied to the aircraft structure.

[0061] Obviously, the above described embodiments are only a part of the embodiments of the utility model, not all of them. Based on the embodiments of the utility model, ordinary technicians in this field can make other different forms of changes or modifications without creative work, which should fall within the scope of protection of the utility model.

Claims

1. A main beam structure for a blade structure, characterized in that: include: An upper edge bar and a lower edge bar, the upper edge bar and the lower edge bar are respectively extended in the left-right direction, and the upper edge bar and the lower edge bar are arranged at intervals in the up-down direction; The web is arranged between the upper edge strip and the lower edge strip, and the two ends are respectively connected to the upper edge strip and the lower edge strip, and the web is made of short-cut fiber reinforced composite material.

2. The main beam structure according to claim 1, characterized in that: The number of the webs is one or more.

3. The main beam structure according to claim 2, characterized in that: An installation space is formed between the upper edge bar and the lower edge bar, the web has a first end and a second end respectively located at opposite ends, the first end is installed on the upper edge bar, and the second end is installed on the lower edge bar; wherein, The first end is not mounted on the edge of the upper edge strip; or, The second end is not mounted on the edge of the lower edge strip; or, The first end is installed at the edge of the upper edge bar, the second end is installed at the edge of the lower edge bar, and the first end and the second end are respectively located at different sides of the upper edge bar and the lower edge bar in the left-right direction.

4. The main beam structure according to claim 3, characterized in that: The first end and the second end are respectively located at the middle of the upper edge strip and the lower edge strip.

5. The main beam structure according to claim 1, characterized in that: The material of the upper edge strip and the lower edge strip is a combination of one or more of woven fabric, warp-knitted multi-axial fabric, and woven fabric.

6. A blade structure, characterized in that: include: Inner skin; The main beam structure according to any one of claims 1 to 5 is arranged in the inner skin, and the upper edge strip and the lower edge strip of the main beam structure are respectively arranged to abut against the upper end and the lower end of the inner skin; A trailing edge is disposed adjacent to the inner skin in the left-right direction; and The outer skin is respectively sleeved on the outer periphery of the trailing edge and the inner skin to combine the separate modules into a whole.

7. The blade structure according to claim 6, characterized in that: The outer skin comprises a plurality of layers of single-layer woven fabrics, and the plurality of layers of single-layer woven fabrics are reciprocatingly woven.

8. The blade structure according to claim 6, characterized in that: The inner skin includes one or more of a braided fabric, a warp knitted multi-axial fabric, and a woven fabric.

9. The blade structure according to claim 8, characterized in that: The inner skin includes a first single-layer woven fabric, a first multi-layer uniaxial fabric, a second single-layer woven fabric, a second multi-layer uniaxial fabric, and a third single-layer woven fabric which are sequentially stacked together in an up-and-down direction.

10. An aircraft structure, characterized in that It comprises the main beam structure as described in any one of claims 1 to 5, or the blade structure as described in any one of claims 6 to 9.

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