Missile wing structure and forming mold

Abstract

The utility model relates to the technical field of missile wing forming, and discloses a missile wing structure and a forming die, the missile wing structure comprises a main wing and an auxiliary wing, the main wing comprises a first skin and a first sandwich filled in the first skin; the aileron comprises a second skin and a second sandwich filled in the second skin; the main wing is flexibly hinged to the aileron through the flexible hinge piece, and a groove is formed in the bottom of the hinged position of the main wing and the aileron. The two ends of the flexible hinge piece are connected to the outer surfaces of the first skin and the second skin correspondingly. The problems that core materials in a main wing and an aileron of an existing missile wing are directly connected, the outer surfaces of the main wing and the aileron are coated with skin, and when the joint of the main wing and the aileron is broken or damaged, maintenance and repair are difficult are solved.

Description

TECHNICAL FIELD

[0001] The utility model relates to a wing structure and forming die, and particularly relates to a wing structure and forming die. BACKGROUND

[0002] In the related art, a wing is usually arranged on a flying bomb to stabilize the state of the flying bomb during falling or flying. The wing generally comprises a main wing and an auxiliary wing, and the core material inside the main wing and the auxiliary wing is directly connected and covered by a skin on the outer surface of the main wing and the auxiliary wing. When the connection part of the main wing and the auxiliary wing is broken or damaged, it is difficult to maintain and repair. SUMMARY

[0003] Therefore, the utility model provides a wing structure and forming die to solve the problem that the core material inside the main wing and the auxiliary wing of the existing wing is directly connected and covered by a skin on the outer surface of the main wing and the auxiliary wing, and it is difficult to maintain and repair when the connection part of the main wing and the auxiliary wing is broken or damaged.

[0004] In a first aspect, the utility model provides a wing structure, which comprises a main wing and an auxiliary wing, wherein the main wing comprises a first skin and a first sandwich filled in the first skin;

[0005] The auxiliary wing comprises a second skin and a second sandwich filled in the second skin;

[0006] The main wing is flexibly connected with the auxiliary wing through a flexible hinge, and a groove is formed at the bottom of the hinge part of the main wing and the auxiliary wing;

[0007] The two ends of the flexible hinge are connected to the outer surfaces of the first skin and the second skin.

[0008] The flexible hinge is used to flexibly connect the auxiliary wing with the main wing, and a groove is formed between the main wing and the auxiliary wing, which saves materials and provides a space for the swing of the auxiliary wing. The auxiliary wing can swing within a preset angle range to ensure the stability during flight. In addition, the groove can be used for positioning during the forming of the main wing and the auxiliary wing to improve the forming precision. The flexible hinge is directly connected to the outer surfaces of the first skin and the second skin, which facilitates the connection and maintenance and repair when the hinge is broken or damaged.

[0009] In an optional embodiment, the flexible hinge is an aramid fiber flexible hinge. The aramid fiber material is used for the flexible hinge to meet the angle requirement of the auxiliary wing, reduce the weight, and facilitate the co-curing connection with the first skin and the second skin.

[0010] In an alternative embodiment, the two ends of the flexible hinge are co-cured with the first skin and the second skin respectively. The flexible hinge is co-cured with the first skin and the second skin, which facilitates one-time forming of the whole wing structure, reduces the manufacturing cycle and cost, and improves the connection strength.

[0011] In an alternative embodiment, the first skin is a carbon fiber skin.

[0012] In an alternative embodiment, the second skin is a carbon fiber skin.

[0013] By using the carbon fiber skin in at least one of the first skin and the second skin, the overall structural strength is ensured while the weight is reduced, and the flight performance is improved.

[0014] In an alternative embodiment, the first core is a PMI foam core.

[0015] In an alternative embodiment, the second core is a PMI foam core.

[0016] By using the PMI foam core in at least one of the first core and the second core, the overall structural strength is ensured while the weight is reduced, and the flight performance is improved. In addition, the use of the PMI foam core can reduce the use of carbon fiber and save costs.

[0017] In an alternative embodiment, the thickness of the first skin gradually decreases from the wing root to the wing tip. By using the carbon fiber skin for the first skin, the overall structural strength is ensured while the weight is reduced, and the flight performance is improved.

[0018] In an alternative embodiment, the thickness of the second skin gradually decreases from the wing root to the wing tip. By using the carbon fiber skin for the second skin, the overall structural strength is ensured while the weight is reduced, and the flight performance is improved.

[0019] In a second aspect, the utility model also provides a forming die which is applied to the processing and forming of the wing structure of any one of the first aspect, the forming die includes first mould body and second mould body, the first mould body and the second mould body are detachable connection, the first mould body and the second mould body are clamped and form at least one forming cavity between them, the forming cavity includes the first forming cavity that is adapted to the main wing and the second forming cavity that is adapted to the aileron, the first forming cavity and the second forming cavity are communicated with the third forming cavity that is adapted to the flexible hinge, and the first forming cavity and the second forming cavity are provided with the boss that is adapted to the groove.

[0020] When the wing structure needs to be processed and formed, the first mold body and the second mold body can be separated first, the materials corresponding to the main wing and the aileron can be laid on the bottom of the first forming cavity and the second forming cavity respectively, and the flexible hinge is arranged at the position corresponding to the third forming cavity, the flexible hinge is positioned and supported by the boss to form a groove, after the laying is completed, the second mold body is clamped with the first mold body to press the laid materials, and the main wing and the aileron are processed and formed, the first mold body and the second mold body are used to facilitate one-time processing and forming of the wing structure, the manufacturing period and the cost are reduced, and a plurality of forming cavities can be arranged according to requirements to realize simultaneous processing and forming of a plurality of wing structures, for example, one-time forming of left wing and right wing, and the production efficiency is improved.

[0021] In an optional embodiment, a plurality of first positioning holes are arranged on the first mold body, and second positioning holes corresponding to the first positioning holes are arranged on the second mold body, and the first positioning holes and the second positioning holes are positioned by positioning pins.

[0022] By arranging the first positioning holes and the second positioning holes on the first mold body and the second mold body respectively, the first mold body and the second mold body are clamped, the positioning pins pass through the first positioning holes and the second positioning holes for positioning and correction, and the forming accuracy is ensured.

[0023] In an optional embodiment, inserts are arranged at the wing roots and wing tips of the main wing in the first forming cavity. The inserts are arranged for positioning, facilitating material laying, and facilitating demolding of the wing structure after forming.

[0024] In an optional embodiment, a positioning line is arranged on the side of the first mold body facing the second mold body. The positioning line is arranged to provide a reference for accurately laying materials and ensuring forming accuracy. BRIEF DESCRIPTION OF DRAWINGS

[0025] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the following will briefly introduce the drawings needed to be used in the specific embodiments or the prior art description. Obviously, the drawings described below are some embodiments of the present application, and those skilled in the art can also obtain other drawings according to these drawings without creative labor.

[0026] Figure 1 FIG. 1 is a structural schematic view of a wing structure according to an embodiment of the present application;

[0027] Figure 2 FIG. 2 is a partial cross-sectional view of the wing structure shown in FIG. 1; Figure 1

[0028] Figure 3 ​A structure schematic view of the first mold body of the embodiment of the utility model;

[0029] Figure 4 For Figure 3 The sectional view of the first mold body shown in the figure.

[0030] Mark explanation:

[0031] 1, main wing;101, first skin;102, first sandwich;2, aileron;201, second skin;202, second sandwich;3, groove;4, flexible hinge;5, first mold body;6, first forming cavity;7, second forming cavity;8, boss;9, positioning pin. Specific implementation

[0032] The technical scheme of the utility model will be described clearly and completely below in combination with the drawings, obviously, the described embodiment is a part of the embodiment of the utility model, rather than all the embodiments. Based on the embodiment in the utility model, all other embodiments obtained by the person skilled in the art without making creative labor belong to the protection scope of the utility model.

[0033] In the description of the utility model, it needs to be explained that the orientation or position relation indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like is the orientation or position relation based on the drawing shown, only for the convenience of describing the utility model and simplifying the description, and cannot be understood as indicating or implying that the device or element indicated must have a particular orientation, be constructed and operated in a particular orientation, therefore, cannot be understood as the limitation of the utility model. In addition, the terms "first", "second", "third" are only for the purpose of description, and cannot be understood as indicating or implying relative importance.

[0034] In the description of the utility model, it needs to be explained that unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connection" should be understood broadly, for example, can be fixed connection, can also be detachable connection, or integrally connected;Can be mechanical connection, can also be electrical connection;Can be directly connected, can also be indirectly connected through an intermediate medium, can be the communication inside two elements. For the person skilled in the art, the specific meaning of the above terms in the utility model can be understood according to the specific situation.

[0035] In addition, the technical features involved in different embodiments of the utility model described below can be combined with each other as long as there is no conflict.

[0036] The embodiments of the utility model will be described below in combination with Figures 1 to 4 .

[0037] According to the embodiment of the utility model, on the one hand, a wing structure is provided, which comprises a main wing 1 and an aileron 2, the main wing 1 comprises a first skin 101 and a first sandwich 102 filled in the first skin 101, the aileron 2 comprises a second skin 201 and a second sandwich 202 filled in the second skin 201, the main wing 1 is flexibly hinged with the aileron 2 through a flexible hinge 4, and a groove 3 is formed at the bottom of the hinge of the main wing 1 and the aileron 2, and the two ends of the flexible hinge 4 are connected to the outer surfaces of the first skin 101 and the second skin 201 respectively.

[0038] It should be noted that the flexible hinge 4, the main wing 1 and the aileron 2 jointly form the groove 3, and the flexible hinge 4 is above the groove 3.

[0039] In the embodiment, the aileron 2 is flexibly hinged with the main wing 1 through the flexible hinge 4, and the groove 3 is formed between the main wing 1 and the aileron 2, which not only saves materials, but also provides a space for the swing of the aileron 2, so that the aileron 2 can swing within a preset angle range, ensuring the stability during flight. In addition, the groove 3 can be positioned and used when the main wing 1 and the aileron 2 are formed, improving the forming precision, and the flexible hinge 4 is directly connected to the outer surfaces of the first skin 101 and the second skin 201, facilitating connection, and facilitating maintenance and repair when fracture or damage occurs, simple and convenient, improving efficiency.

[0040] In one embodiment, the flexible hinge 4 is an aramid fiber flexible hinge.

[0041] In the embodiment, the flexible hinge 4 adopts an aramid fiber flexible hinge, which is made of aramid fiber material, so that the strength and toughness of the flexible hinge 4 meet the angle requirements of the aileron 2, reduce the weight, and facilitate co-curing connection with the first skin 101 and the second skin 201.

[0042] In one embodiment, as shown in Figure 2 the two ends of the flexible hinge 4 are co-cured and connected with the first skin 101 and the second skin 201 respectively.

[0043] In the embodiment, the flexible hinge 4 is connected with the first skin 101 and the second skin 201 in a co-curing connection mode, facilitating one-time molding of the whole wing structure, reducing the manufacturing cycle and cost, and improving the connection strength.

[0044] Specifically, as shown in Figure 2 the flexible hinge 4 is in a plate structure with a preset thickness, so as to facilitate co-curing connection with the first skin 101 and the second skin 201.

[0045] Specifically, the flexible hinge 4 is provided with a hinge groove in the gap along the length direction of the first skin 101 and the second skin 201, so as to realize the swing of the aileron 2 within the preset angle range, and the depth of the hinge groove can be set according to the required angle.

[0046] In one embodiment, the first skin 101 is a carbon fiber skin.

[0047] In this embodiment, the first skin 101 is a carbon fiber skin, which can reduce the weight and improve the flight performance while ensuring the overall structural strength.

[0048] In one embodiment, the second skin 201 is a carbon fiber skin.

[0049] In this embodiment, the second skin 201 is a carbon fiber skin, which can reduce the weight and improve the flight performance while ensuring the overall structural strength.

[0050] In one embodiment, the first core 102 is a PMI foam core.

[0051] In this embodiment, the first core 102 is a PMI foam core, which has the advantages of light weight and high strength, can reduce the weight and improve the flight performance while ensuring the overall structural strength, and can reduce the use of carbon fiber and save costs.

[0052] In one embodiment, the second core 202 is a PMI foam core.

[0053] In this embodiment, the second core 202 is a PMI foam core, which has the advantages of light weight and high strength, can reduce the weight and improve the flight performance while ensuring the overall structural strength, and can reduce the use of carbon fiber and save costs.

[0054] In one embodiment, the thickness of the first skin 101 gradually decreases from the wing root to the wing tip.

[0055] In this embodiment, the thickness of the first skin 101 gradually decreases from the wing root to the wing tip, which can reduce the weight and save materials and costs while ensuring the structural strength.

[0056] In one embodiment, the thickness of the second skin 201 gradually decreases from the wing root to the wing tip.

[0057] In this embodiment, the thickness of the second skin 201 gradually decreases from the wing root to the wing tip, which can reduce the weight and save materials and costs while ensuring the structural strength.

[0058] The specific working principle of the wing structure provided by the embodiment is that the first skin 101 of the main wing 1 and the second skin 201 of the auxiliary wing 2 are connected by co-curing the flexible hinge 4 in a plate-shaped structure, so that the main wing 1 and the auxiliary wing 2 are flexibly hinged, and the groove 3 is formed between the main wing 1 and the auxiliary wing 2, which saves materials and provides a space for the swing of the auxiliary wing 2, so that the auxiliary wing 2 can swing within a preset angle range, ensuring stability during flight. In addition, the groove 3 can be positioned and used when the main wing 1 and the auxiliary wing 2 are formed, improving the forming precision, and the flexible hinge 4 is directly connected to the outer surfaces of the first skin 101 and the second skin 201, facilitating connection, and facilitating maintenance and repair when the flexible hinge 4 is broken or damaged, simple and convenient, improving efficiency. In addition, the flexible hinge 4 is made of aramid fiber, the first skin 101 and the second skin 201 are made of carbon fiber material, and the first core 102 and the second core 202 are made of PMI foam material, which ensures the overall structural strength while making the overall lightweight, improves flight performance, and solves the problem that the core material of the main wing 1 and the auxiliary wing 2 is directly connected and covered by the skin on the outer surface of the main wing 1 and the auxiliary wing 2. When the connection between the main wing 1 and the auxiliary wing 2 is broken or damaged, it is difficult to maintain and repair.

[0059] In a specific application, the formed wing structure is divided into zones and each zone is subjected to a predetermined constraint and a limited pressure load, and it is concluded that the wing tip displacement of the wing structure under the limited load is less than 30mm, and the overall torsion angle of the wing under the limited load is less than 0.3 degrees. The wing structure meets the strength and stiffness index requirements.

[0060] According to the embodiment of the utility model, as shown in Figure 3 and Figure 4 On the other hand, a forming die is also provided, which is applied to the processing and forming of the wing structure of any one of the first aspect, and the forming die comprises a first die body 5 and a second die body, the first die body 5 and the second die body are detachably connected, at least one forming cavity is formed by clamping the first die body 5 and the second die body, the forming cavity comprises a first forming cavity 6 matched with the main wing 1 and a second forming cavity 7 matched with the auxiliary wing 2, and the first forming cavity 6 and the second forming cavity 7 are communicated with a third forming cavity matched with the flexible hinge 4. The first forming cavity 6 and the second forming cavity 7 are provided with a boss 8 matched with the groove 3.

[0061] In this embodiment, when the wing structure needs to be processed and formed, the first mold body 5 and the second mold body can be separated first, the materials corresponding to the formation of the main wing 1 and the aileron 2 can be laid on the bottom of the first forming cavity 6 and the second forming cavity 7 respectively, and the flexible hinge 4 is arranged at the position corresponding to the third forming cavity. The flexible hinge 4 is positioned and supported by the boss 8 to form the groove 3. After the laying is completed, the second mold body is clamped with the first mold body 5 to press the laid materials and process and form the main wing 1 and the aileron 2. The first mold body 5 and the second mold body are used to process and form the wing structure at one time, reduce the manufacturing cycle and cost, and multiple forming cavities can be arranged according to the needs to realize the simultaneous processing and forming of multiple wing structures, for example, left wing and right wing are formed at one time, and the production efficiency is improved.

[0062] In one embodiment, as shown in Figure 3 and Figure 4 The first mold body 5 is provided with a plurality of first positioning holes, and the second mold body is provided with a second positioning hole corresponding to the first positioning hole. The first positioning hole and the second positioning hole are positioned by the positioning pin 9.

[0063] In this embodiment, the first positioning hole and the second positioning hole are respectively arranged on the first mold body 5 and the second mold body, which is convenient for positioning and correcting by the positioning pin 9 when the first mold body 5 and the second mold body are clamped, and ensures the forming precision.

[0064] In one embodiment, the first forming cavity 6 is provided with an insert block corresponding to the wing root and the wing tip of the main wing 1.

[0065] In this embodiment, the insert block is used for positioning, which is convenient for laying materials and demolding of the formed wing structure.

[0066] In one embodiment, the side of the first mold body 5 facing the second mold body is provided with a positioning line.

[0067] In this embodiment, the positioning line is provided to provide a reference for accurately laying materials and ensure the forming precision.

[0068] Specifically, the side of the first mold body 5 facing the second mold body is provided with a laying direction line to facilitate the laying of materials and improve the forming precision.

[0069] Specifically, the forming cavity is provided with two forming cavities to facilitate the one-time processing and forming of the left wing and the right wing.

[0070] Specifically, the first mold body 5 and the second mold body are steel molds to ensure the structural strength.

[0071] Specifically, the first mold body 5 is provided with a first forming groove matched with the lower part of the main wing 1 and a second forming groove matched with the lower part of the auxiliary wing 2 on the side facing the second mold body; the second mold body is provided with a third forming groove matched with the upper part of the main wing 1, a fourth forming groove matched with the upper part of the auxiliary wing 2 and a fifth forming groove matched with the flexible hinge 4 on the side facing the first mold body 5; the first forming groove and the third forming groove form a first forming cavity 6, and the second forming groove and the fourth forming groove form a second forming cavity 7, so as to facilitate the laying of the main wing 1 and the auxiliary wing 2 materials.

[0072] The process of the forming mold provided by the embodiment for processing and forming the missile wing structure is as follows:

[0073] First, the first mold body 5 and the second mold body are separated, then the lower skins of the first skin 101 and the second skin 201 are laid in the first forming groove and the second forming groove respectively according to the positioning lines and the laying direction lines, then the first core 102 and the second core 202 are laid, then the wing root filler, the upper skins of the first skin 101 and the second skin 201 and the flexible connecting piece are laid in sequence, then the second mold body is positioned with the first mold body 5 through the positioning pin 9 and is closed and cured, after curing, the mold is removed and cleaned, then the formed missile wing structure is machined, then assembled and inspected.

[0074] Although the embodiments of the utility model are described in combination with the drawings, various modifications and changes can be made by those skilled in the art without departing from the spirit and scope of the utility model, and such modifications and changes all fall within the scope defined by the appended claims.

Claims

1. A wing structure, characterized by, The wing structure comprises a main wing (1) and a sub wing (2), the main wing (1) comprises a first skin (101) and a first sandwich (102) filled in the first skin (101); The sub wing (2) comprises a second skin (201) and a second sandwich (202) filled in the second skin (201); The main wing (1) is flexibly connected with the sub wing (2) through a flexible hinge (4), and a groove (3) is formed at the bottom of the hinge of the main wing (1) and the sub wing (2); Both ends of the flexible hinge (4) are connected to the outer surfaces of the first skin (101) and the second skin (201) respectively.

2. The projectile wing structure of claim 1, wherein The flexible hinge (4) is an aramid fiber flexible hinge.

3. The wing structure according to claim 1 or 2, characterized in that Both ends of the flexible hinge (4) are co-cured with the first skin (101) and the second skin (201) respectively.

4. The projectile wing structure of claim 1, wherein The first skin (101) is a carbon fiber skin; And / or, the second skin (201) is a carbon fiber skin.

5. The projectile wing structure of claim 1, wherein The first sandwich (102) is a PMI foam sandwich; And / or, the second sandwich (202) is a PMI foam sandwich.

6. The projectile wing structure of claim 1, wherein The thickness of the first skin (101) gradually decreases from the wing root to the wing tip; And / or, the thickness of the second skin (201) gradually decreases from the wing root to the wing tip.

7. A forming mold characterized by, The forming mold applied to the wing structure of any one of claims 1-6 comprises a first mold body (5) and a second mold body, the first mold body (5) and the second mold body are detachably connected, at least one forming cavity is formed between the first mold body (5) and the second mold body, the forming cavity comprises a first forming cavity (6) matched with the main wing (1) and a second forming cavity (7) matched with the sub wing (2); a third forming cavity matched with the flexible hinge (4) is communicated between the first forming cavity (6) and the second forming cavity (7); a boss (8) matched with the groove (3) is arranged between the first forming cavity (6) and the second forming cavity (7).

8. The forming mold of claim 7, wherein, A plurality of first positioning holes are arranged on the first mold body (5), and second positioning holes corresponding to the first positioning holes are arranged on the second mold body, and the first positioning holes and the second positioning holes are positioned by a positioning pin (9).

9. The forming mold of claim 7, wherein, In the first forming cavity (6), an inlay block is arranged at the wing root and the wing tip of the main wing (1) respectively.

10. The forming mold of claim 7, wherein, The first mold body (5) is provided with a positioning line on the side facing the second mold body.

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