Aerofoil structure and method of mounting same

Abstract

This invention discloses a missile wing structure and its installation method. The missile wing structure includes: two symmetrically arranged wing plates; a steel strip that passes through the two wing plates sequentially and is connected end to end; and a tightening structure including a first pin, a second pin, and connecting bolts. The first pin and the second pin are respectively installed at both ends of the steel strip and connected by the connecting bolts. According to the embodiment of the missile wing structure and its installation method, assembly is simple and reliable; the installation of the wing plates is achieved by tightening the steel strip at both ends, which allows for convenient and quick fastening of the wing plates. It requires less material, has a simple manufacturing method, low cost, and can quickly achieve large-scale production.

Description

Technical Field

[0001] This invention relates to the field of missile overall technology, and in particular to a missile wing structure and its installation method. Background Technology

[0002] Missiles or guided bombs typically employ an X-shaped wing configuration, with four wings fixed to the fuselage at 45° angles. Currently, wings are mostly constructed using either a fixed or strapped structure. Fixed wings are directly bolted to the fuselage; however, due to weight reduction requirements, the fuselage material is either composite material or thin-walled titanium alloy. Drilling holes in the fuselage increases the manufacturing difficulty of the section and also affects the fuselage's strength. Strapped structures often use welding processes, welding the ends of steel strips to the mounting base. This method has poor manufacturability, and welding defects can reduce strength. Summary of the Invention

[0003] This invention aims to solve at least one of the technical problems existing in the prior art. To this end, this invention proposes a wing structure and its installation method, which fixes the wing with steel strips and locating pins, resulting in low manufacturing cost, simple assembly, and high reliability.

[0004] According to a first aspect of the present invention, a wing structure includes: two wing plates arranged symmetrically; a steel strip passing through the two wing plates sequentially and connected end to end; and a tightening structure including a first pin, a second pin, and a connecting bolt, wherein the first pin and the second pin are respectively installed at both ends of the steel strip and connected by the connecting bolt.

[0005] The wing structure according to embodiments of the present invention has at least the following beneficial effects:

[0006] By tightening both ends of the structural steel strip to install the wingplate, the wingplate can be fastened quickly and easily. It requires less material, is simple to manufacture, has low cost, and can quickly achieve large-scale production. The tightening structure sets the first and second pins at the two ends of the steel strip respectively, and then uses connecting bolts to connect the first and second pins. The connection method is simple, ensuring performance without damaging the performance of the wing material.

[0007] According to some embodiments of the present invention, the first pin is provided with a first radial hole and a first locking hole communicating with the first radial hole, and a first locking screw is provided in the first locking hole; one end of the steel strip is provided in the first radial hole, and the first locking screw passes through the steel strip placed in the first radial hole to lock the first pin and the steel strip.

[0008] According to some embodiments of the present invention, the second pin is provided with a second radial hole through which the other end of the steel strip passes and a second locking hole communicating with the second radial hole, and the second locking hole is provided with a second locking bolt for connecting the second pin and the other end of the steel strip.

[0009] According to some embodiments of the present invention, the tightening structure further includes a stop block; the other end of the steel strip is bent and disposed in the second radial hole, and a stop hole for inserting the stop block is formed at the bend, the stop block is inserted into the stop hole and abuts against the second pin to connect the steel strip and the second pin.

[0010] According to some embodiments of the present invention, the stop block is provided with an insert portion protruding to one side, and a stop plate protruding towards the center is provided in the second radial hole. The insert portion is inserted into the second radial hole and abuts against the stop plate.

[0011] According to some embodiments of the present invention, the first pin is further provided with a first through hole that penetrates radially, the second pin is provided with a threaded hole, and the connecting bolt passes through the first through hole and is threadedly connected to the threaded hole.

[0012] According to some embodiments of the present invention, the wing plate is provided with through holes for the steel strip to pass through.

[0013] According to some embodiments of the present invention, the wingplate includes an arc-shaped plate and two winglets, the two winglets being respectively disposed on both sides of the arc-shaped plate; the through hole is disposed at the connection between the arc-shaped plate and the winglets.

[0014] According to some embodiments of the present invention, the arc-shaped plate has a square hole in the middle to reduce weight; the outer arc surface of the arc-shaped plate has a strip groove for the steel strip to be embedded.

[0015] A method for installing a missile wing structure according to a second aspect of the present invention includes the following steps:

[0016] S1: Install the wing plates on the outer circumference of the missile, and then pass the steel strip through the two wing plates in sequence;

[0017] S2: Install the first and second pins of the tightening structure at both ends of the steel strip, respectively;

[0018] S3: Adjust the position of the two wing plates to make them symmetrical, then use the auxiliary tooling to hold the first pin and the second pin and pull them closer together, and finally insert the connecting bolt to connect the first pin and the second pin to tighten the steel strip.

[0019] According to some embodiments of the present invention, the auxiliary tooling includes two intersecting and hinged first clamping members and second clamping members. One end of the first clamping member is provided with a first clamping groove for the first pin to be inserted. The second clamping member is provided with a second clamping groove at one end corresponding to the first clamping groove. The second clamping groove is used for the second pin to be inserted. The end of the first clamping member away from the first clamping groove and the end of the second clamping member away from the second clamping groove are far apart from each other, which can drive the first pin placed in the first clamping groove and the second pin placed in the second clamping groove to move closer to each other.

[0020] The method for installing a missile wing structure according to an embodiment of the present invention has at least the following beneficial effects:

[0021] The installation of the wing plate is achieved simply by tightening the steel strip through the tightening structure. The installation method is simple, can greatly improve installation efficiency, and is suitable for large-scale application.

[0022] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0023] The present invention will be further described below with reference to the accompanying drawings and embodiments, wherein:

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

[0025] Figure 2 This is an exploded view of the assembly structure of the steel strip and the tightening structure according to an embodiment of the present invention;

[0026] Figure 3 for Figure 2 Enlarged view of point A in the middle;

[0027] Figure 4 This is a cross-sectional view of the mounting structure of the second pin and the stop block according to an embodiment of the present invention;

[0028] Figure 5 This is a schematic diagram of the auxiliary tooling in an embodiment of the present invention.

[0029] Icon labels:

[0030] Wing plate 100, arc plate 110, square hole 111, wing 120, through hole 130;

[0031] Steel strip 200, stop hole 210;

[0032] Tightening structure 300, first pin 310, first radial hole 311, first locking hole 312, first through hole 313, second pin 320, second radial hole 321, second locking hole 322, abutment plate 323, threaded hole 324, connecting bolt 330, stop block 340, and embedded part 341;

[0033] Auxiliary fixture 400, first clamping component 410, first clamping groove 411, second clamping component 420, second clamping groove 421. Detailed Implementation

[0034] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0035] In the description of this invention, it should be understood that the orientation descriptions, such as up, down, etc., are based on the orientation or positional relationship shown in the drawings and are only for the convenience of describing this invention and simplifying the description, and are not intended to 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.

[0036] In the description of this invention, "multiple" refers to two or more. The use of "first" and "second" is for distinguishing technical features only and should not be construed as indicating or implying relative importance, or implicitly indicating the number of indicated technical features or their sequential relationship.

[0037] In the description of this invention, unless otherwise explicitly defined, terms such as "set up," "install," and "connect" should be interpreted broadly, and those skilled in the art can reasonably determine the specific meaning of the above terms in this invention in conjunction with the specific content of the technical solution.

[0038] Reference Figures 1 to 4 An embodiment of the present invention provides a wing structure comprising:

[0039] Two wing plates 100 are symmetrically mounted on the outer circumference of the missile. Each wing plate 100 includes an arc-shaped plate 110 and two winglets 120. The two winglets 120 are respectively disposed on both sides of the arc-shaped plate 110, and the included angle between the two winglets 120 is ninety degrees. (Refer to...) Figure 1 As shown, the angle between the two adjacent winglets 120 of the two wing plates 100 is also ninety degrees, that is, the four winglets 120 are installed on the outer periphery of the missile in a cross-shaped manner.

[0040] The steel strip 200 passes through the two wing plates 100 one after the other and is connected end to end to lock the wing plates 100 onto the missile.

[0041] The tightening structure 300 includes a first pin 310, a second pin 320, and a connecting bolt 330. The first pin 310 and the second pin 320 are respectively installed at both ends of the steel strip 200 and connected by the connecting bolt 330. The first pin 310 has a radially penetrating first through hole 313, and the second pin 320 has a threaded hole 324. The connecting bolt 330 passes through the first through hole 313 and is threadedly connected to the threaded hole 324. (Refer to...) Figure 2 , Figure 3 As shown, the first pin 310 is also provided with a slot, which abuts against the head of the connecting bolt 330 to facilitate a more secure connection between the first pin 310 and the second pin 320.

[0042] Furthermore, the first pin 310 is provided with two first through holes 313, which are respectively located at both ends of the first pin 310; the second pin 320 is provided with two threaded holes 324, which are respectively located at both ends of the second pin 320; and two connecting bolts 330 pass through the two second through holes and are connected to the two threaded holes 324.

[0043] In some embodiments of the present invention, the first pin 310 is provided with a first radial hole 311 and a first locking hole 312 communicating with the first radial hole 311, and a first locking screw is inserted into the first locking hole 312; one end of the steel strip 200 is inserted into the first radial hole 311, and the first locking screw passes through the steel strip 200 placed in the first radial hole 311 to lock the first pin 310 and the steel strip 200. Specifically, refer to Figure 3 As shown, the first radial hole 311 is an elongated hole, and the first locking hole 312 is a cylindrical hole. The first radial hole 311 and the first locking hole 312 are perpendicular to each other. The length of the first radial hole 311 should not be less than the width of the steel strip 200.

[0044] In some embodiments of the present invention, the second pin 320 is provided with a second radial hole 321 through which the other end of the steel strip 200 passes and a second locking hole 322 communicating with the second radial hole 321. A second locking bolt for connecting the second pin 320 and the other end of the steel strip 200 passes through the second locking hole 322. Specifically, the second pin 320 is substantially the same in shape as the first pin 310, the second radial hole 321 is the same in size and shape as the first radial hole 311, and the second locking hole 322 is the same in size and shape as the first latch, so as to facilitate the mass production of each component.

[0045] In some embodiments of the present invention, the tightening structure 300 further includes a stop block 340; the other end of the steel strip 200 is bent and disposed in the second radial hole 321, and a stop hole 210 for inserting the stop block 340 is formed at the bend. The stop block 340 is inserted into the stop hole 210 and abuts against the second pin 320 to connect the steel strip 200 and the second pin 320. Specifically, refer to Figure 3 , Figure 4 As shown, one end of the steel strip 200 is bent and installed in the first radial hole 311, and the other end of the steel strip 200 is bent and installed in the second radial hole 321. Bending the steel strip 200 means that either the first locking bolt or the second locking bolt passes through two layers of steel strip 200, which makes the connection between the first pin 310 or the second pin 320 and the steel strip 200 more secure.

[0046] In some embodiments of the present invention, the stop block 340 is provided with an insert portion 341 protruding to one side, and a stop plate 323 protruding towards the center is provided in the second radial hole 321. The insert portion 341 is inserted into the second radial hole 321 and abuts against the stop plate 323. (See reference...) Figure 3 , Figure 4 As shown, the overall cross-section of the stop block 340 is wedge-shaped, and the end of its embedded part 341 is embedded in the second radial hole 321 and abuts against the abutment plate 323; the second locking hole 322 is provided at the position of the abutment plate 323.

[0047] It should be understood that the second pin 320 and the steel strip 200 are connected by a stop block 340. The end of the abutment plate 323 facing the stop block 340 has inclined surfaces corresponding to both sides of the insertion portion 341 of the stop block 340. When the stop block 340 is inserted into the second radial hole 321, refer to... Figure 4 As shown, the steel strip 200 is pressed between the stop block 340 and the inner wall of the second radial hole 321. In particular, the end of the abutment plate 323 facing the stop block 340 has an inclined surface corresponding to the embedded part 341, which further ensures the stability of the connection between the second pin 320 and the steel strip 200. The second locking bolt passes through the second pin 320 and the steel strip 200 and is locked to provide reinforcement and effectively prevent the stop block 340 from disengaging from the second pin 320.

[0048] It should be noted that a stop plate 323 can also be provided in the first radial hole 311 of the first pin 310, and a stop block 340 can be installed, not limited to the second pin 320.

[0049] In some embodiments of the present invention, the wing plate 100 is provided with a through hole 130 for the steel strip 200 to pass through, and the through hole 130 is disposed at the connection between the arc-shaped plate 110 and the wing 120. Specifically, refer to Figure 1As shown, there are two steel strips 200, which are respectively installed at both ends of the wing plate 100 in the length direction. Therefore, a single wing plate 100 is provided with four through holes 130, and each steel strip 200 passes through two through holes 130.

[0050] In some embodiments of the present invention, the arc-shaped plate 110 has a square hole 111 in the middle to reduce weight; the outer arc surface of the arc-shaped plate 110 has a strip groove for the steel strip 200 to be embedded. Specifically, there are two square holes 111, which can greatly reduce the weight of the wing plate 100 and reduce production costs; the inner diameter of the inner arc surface of the arc-shaped plate 110 is the same as the outer diameter of the missile, and the outer surface of the arc-shaped plate 110 is provided with a strip groove with the same width as the steel strip 200 to facilitate the positioning of the steel strip 200 and further ensure the tightening of the steel strip 200.

[0051] A method for installing a missile wing structure according to a second aspect of the present invention includes the following steps:

[0052] S1: Install the wing plate 100 on the outer circumference of the missile, and then the steel strip 200 passes through the two wing plates 100 in sequence;

[0053] S2: Install the first pin 310 and the second pin 320 of the tightening structure 300 at both ends of the steel strip 200 respectively;

[0054] S3: Adjust the positions of the two wing plates 100 to make them symmetrical, then use the auxiliary tooling 400 to clamp the first pin 310 and the second pin 320 and pull them closer together. Finally, insert the connecting bolt 330 to connect the first pin 310 and the second pin 320 to tighten the steel strip 200.

[0055] Reference Figure 5 As shown, in some embodiments of the present invention, the auxiliary tooling 400 includes two intersecting and hinged first clamping members 410 and second clamping members 420. The middle part of the first clamping member 410 and the middle part of the second clamping member 420 are hinged to each other and intersecting. Driving one end of the first clamping member 410 to approach the second clamping member 420 can drive the other end of the first clamping member 410 away from the second clamping member 420.

[0056] The first clamping member 410 has a first clamping groove 411 at one end for the first pin 310 to be inserted, and the second clamping member 420 has a second clamping groove 421 at one end corresponding to the first clamping groove 411. The second clamping groove 421 is used for the second pin 320 to be inserted. The end of the first clamping member 410 away from the first clamping groove 411 and the end of the second clamping member 420 away from the second clamping groove 421 are far apart from each other, which can drive the first pin 310 placed in the first clamping groove 411 and the second pin 320 placed in the second clamping groove 421 to move closer to each other. Both the first clamping groove 411 and the second clamping groove 421 are arc-shaped grooves to facilitate the insertion of the first pin 310 or the second pin 320. Using the auxiliary tooling 400 to assist in the installation of the connecting bolt 330 can greatly improve work efficiency.

[0057] According to the wing structure and installation method of the present invention, the wing plate 100 is installed by tightening both ends of the steel strip 200 of the structure 300. This can achieve fastening of the wing plate 100 conveniently and quickly, requiring less material, with a simple manufacturing method and low cost, and enabling rapid large-scale production. The tightening structure 300 sets the first pin 310 and the second pin 320 at both ends of the steel strip 200 respectively, and then connects the first pin 310 and the second pin 320 with connecting bolts 330. The connection method is simple, ensuring performance without damaging the performance of the wing material.

[0058] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings. However, the present invention is not limited to the above embodiments. Within the scope of knowledge possessed by those skilled in the art, various changes can be made without departing from the spirit of the present invention.

Claims

1. A wing structure, characterized in that, include: Two wing plates (100) are symmetrically arranged; the wing plate (100) includes an arc-shaped plate (110) and two winglets (120), and the two winglets (120) are respectively arranged on both sides of the arc-shaped plate (110); A steel strip (200) passes through two of the wing plates (100) in sequence and is connected end to end; the connection between the arc plate (110) and the wing (120) is provided with a through hole (130) for the steel strip (200) to pass through. The tightening structure (300) includes a first pin (310), a second pin (320) and a connecting bolt (330). The first pin (310) and the second pin (320) are respectively installed at both ends of the steel strip (200) and connected by the connecting bolt (330). The first pin (310) has a first radial hole (311) and a first locking hole (312) communicating with the first radial hole (311). A first locking screw passes through the first locking hole (312). One end of the steel strip (200) passes through the first radial hole (311). The first locking screw passes through the steel strip (200) placed in the first radial hole (311) to lock the first pin (310) and the steel strip (200). The second pin (320) has a second radial hole (321) through which the other end of the steel strip (200) passes and a second locking hole (322) communicating with the second radial hole (321). A second locking bolt for connecting the second pin (320) and the other end of the steel strip (200) passes through the second locking hole (322). The tightening structure (300) further includes a stop block (340); the other end of the steel strip (200) is bent and disposed in the second radial hole (321), and a stop hole (210) is formed at the bend for the stop block (340) to be inserted. The stop block (340) is inserted into the stop hole (210) and abuts against the second pin (320) to connect the steel strip (200) and the second pin (320); the stop block (340) is provided with an insert portion (341) protruding to one side, and a stop plate (323) protruding towards the center is provided in the second radial hole (321). The insert portion (341) is inserted into the second radial hole (321) and abuts against the stop plate (323).

2. The wing structure according to claim 1, characterized in that: The first pin (310) is provided with a first through hole (313) that penetrates radially, and the second pin (320) is provided with a threaded hole (324). The connecting bolt (330) passes through the first through hole (313) and is threadedly connected to the threaded hole (324).

3. The wing structure according to claim 1, characterized in that: The arc plate (110) has a square hole (111) in the middle to reduce weight; the outer arc surface of the arc plate (110) has a strip groove for the steel strip (200) to be embedded.

4. A method for installing a wing structure according to any one of claims 1 to 3, characterized in that, Includes the following steps: S1: Install the wing plate (100) on the outer circumference of the missile, and then pass the steel strip (200) through the two wing plates (100) in sequence. S2: Install the first pin (310) and the second pin (320) of the tightening structure (300) at both ends of the steel strip (200); S3: Adjust the positions of the two wing plates (100) to make them symmetrical, then use the auxiliary tool (400) to clamp the first pin (310) and the second pin (320) and pull them closer together. Finally, insert the connecting bolt (330) to connect the first pin (310) and the second pin (320) to tighten the steel strip (200).

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