Modular missile position adjustable wing connecting structure

Abstract

This invention discloses a modular missile wing connection structure with adjustable position. The structure includes a missile body to which wings are connected; four elongated rectangular planes of equal thickness are arranged at equal angles along the axial direction of the missile body, and several equally spaced rectangular grooves are formed on the elongated rectangular planes along their axial direction; a wing flange is provided at the wing root of each wing, and several equally spaced rectangular locking blocks are provided at the bottom of the wing flange; the rectangular locking blocks cooperate with the rectangular grooves to connect several wings to the missile body; the number of rectangular grooves is greater than the number of rectangular locking blocks, and the relative position of the wings is adjusted by adjusting the insertion position of the rectangular locking blocks; several wings are fixed to the missile body by binding circular retaining rings. The above-mentioned wing connection structure is easy to assemble and disassemble and is adjustable, and can adapt to different combat mission requirements.

Description

Technical Field

[0001] This invention belongs to the field of missile structure design technology, specifically relating to a modular missile wing connection structure with adjustable position. Background Technology

[0002] In missile design, the shape and connection method of the missile wing play a crucial role in the missile's system performance. In existing technologies, the wing is fixedly attached to the missile body. This design results in the wing position being non-adjustable, limiting the adjustment of the missile's aerodynamic performance and failing to meet the diverse needs of modern battlefields. Furthermore, many wing connection designs employ a large number of connectors or complex connection structures to ensure connection reliability, leading to difficulties or even impossibilities in wing disassembly, and also presenting manufacturing challenges. Summary of the Invention

[0003] In order to overcome the shortcomings of the prior art, the present invention aims to provide a modular missile wing connection structure with adjustable position, which enables rapid disassembly and reliable connection of modular missile wings, reduces the complexity of the connection structure, reduces disassembly and assembly time, ensures the interchangeability of wing modules, and enables the adjustment of wing position to change the aerodynamic performance of the missile.

[0004] To achieve the above objectives, the present invention employs the following technical solution:

[0005] The present invention provides a modular missile wing connection structure with adjustable position, including a missile body, wherein the missile body is connected to a wing;

[0006] Four long rectangular planes of equal thickness are arranged at equal angles along the axial direction of the projectile body, and several rectangular grooves are formed on the long rectangular planes at equal intervals along the axial direction of the long rectangular planes.

[0007] The wing root is provided with a wing flange, and the bottom of the wing flange is provided with a number of equally spaced rectangular locking blocks; the rectangular locking blocks cooperate with the rectangular grooves to connect the wing to the missile body; the number of rectangular grooves is greater than the number of rectangular locking blocks, and the relative position of the wing is adjusted by adjusting the insertion position of the rectangular locking blocks.

[0008] Several of the aforementioned fins are secured to the projectile body by binding circular retaining rings.

[0009] In practice, the distance between adjacent rectangular grooves is equal to the distance between adjacent rectangular blocks.

[0010] In the specific implementation process, the structure of the binding circular retaining ring is a quarter-circular ring structure.

[0011] In the specific implementation process, two adjacent missile wings are connected by two sets of binding circular retaining rings set at the front and rear.

[0012] In the specific implementation process, both sides of the wing root of the missile wing are provided with protruding connecting platforms, and several first connecting through holes are opened at both ends near the protruding connecting platforms.

[0013] The binding circular retaining ring has several second connecting through holes at both ends;

[0014] The first connecting through hole and the second connecting through hole are fixedly connected to connect several binding circular retaining rings to the projectile wing.

[0015] In the specific implementation process, the two ends of the binding circular retaining ring have connecting lugs.

[0016] In practice, the second connecting through hole is formed on the connecting lug.

[0017] In the specific implementation process, the first connecting through holes opened at both ends of the missile wing each correspond to a set of second connecting through holes on a set of binding circular retaining rings.

[0018] In practice, the front end of the raised connecting platform has a slope to reduce the impact of air resistance.

[0019] In practice, the raised connecting platform is aligned parallel to both sides of the missile wing flange.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] This invention provides a modular missile wing connection structure with adjustable position. This connection structure is simple, easy to manufacture, and requires no welding or excessive connecting parts during wing connection. It is easy to disassemble and has good interchangeability. Several wings are connected to a single unit with binding circular retaining rings. The wing offset is limited by the compression of rectangular retaining blocks, providing strong bending resistance and ensuring connection rigidity, thus effectively transferring the wing load to the missile body. Simultaneously, the wing's position is adjustable by selecting the position of the rectangular groove on the missile body to be inserted. This is convenient to operate, and the number of rectangular grooves can be increased to achieve a wider range of adjustment. The manufacturing process is relatively simple, with minimal weakening of the missile body's rigidity and strength. No through holes are required, ensuring the airtightness of the missile body section. The aforementioned wing connection structure is easy to assemble and disassemble and is adjustable, enabling flexible adjustment of the wing position and rapid replacement of wing modules, thereby adapting to different combat mission requirements. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the connection structure between the projectile wing and the projectile body of the present invention;

[0023] Figure 2 This is a schematic diagram of the main structure of the missile wing of the present invention;

[0024] Figure 3 This is a schematic diagram of the main structure of the projectile body of the present invention;

[0025] Figure 4 This is a schematic diagram of the binding circular retaining ring structure of the present invention;

[0026] Wherein: 1-wing; 2-body; 3-connecting bolt; 4-binding circular retaining ring; 5-wing flange; 6-protruding connecting platform; 7-first connecting through hole; 8-rectangular retaining block; 9-rectangular groove; 10-connecting lug; 11-second connecting through hole. Detailed Implementation

[0027] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. 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 should fall within the scope of protection of the present invention.

[0028] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover a non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0029] The present invention will now be described in further detail with reference to the accompanying drawings:

[0030] See Figure 1 The present invention provides a modular missile wing connection structure with adjustable position. The connection structure includes the missile body 2, the wing 1 connected to the missile body 2, the connecting bolt 3, and the binding circular retaining ring 4.

[0031] The projectile body 2 is connected to the projectile wing 1, and the projectile wing 1 is connected to the binding circular retaining ring 4. Several projectile wings 1 are fixed to the projectile body 2 by the binding circular retaining ring 4. The specific connection structure is as follows:

[0032] like Figure 3 As shown, the projectile body 2 has four long rectangular planes of equal thickness arranged at equal angles along the axial direction of the projectile body 2, and several rectangular grooves 9 are equally distributed on the long rectangular planes along the axial direction of the long rectangular planes.

[0033] like Figure 2 As shown, the missile 1 has a missile wing flange 5 at its wing root. The bottom of the missile wing flange 5 has several rectangular clips 8 that are evenly distributed. Both sides of the wing root of the missile 1 have a raised connecting platform 6. Several first connecting through holes 7 are opened at each end near the raised connecting platform 6.

[0034] like Figure 4 As shown, a circular retaining ring 4 is used for binding, and several second connecting through holes 11 are provided on both ends of the circular retaining ring 4; wherein, the first connecting through hole 7 is fixedly connected to the second connecting through hole 11, connecting several circular retaining rings 4 to the projectile wing 1; the rectangular retaining block 8 cooperates with the rectangular groove 9 to connect several projectile wings 1 to the projectile body 2.

[0035] Specifically, the connection between the wing 1 and the body 2 is achieved by inserting the rectangular clip 8 at the bottom of the wing 1 into the rectangular groove 9 on the body 2, and by coordinating the first connecting through hole 7 and the second connecting through hole 11, tightening the connecting bolt 3 to connect the wing root of the wing 1 to the connecting lugs 10 of the four binding circular clips 4, forming two binding clip structure at the front and rear, which presses and fixes the wing 1 to the body 2.

[0036] In practical implementation, the number of rectangular grooves 9 is greater than the number of rectangular locking blocks 8. The relative position of the missile wings 1 is adjusted by adjusting the insertion position of the rectangular locking blocks 8, and the distance between adjacent rectangular grooves 9 is equal to the distance between adjacent rectangular locking blocks 8. The squeezing fit of the rectangular locking blocks 8 restricts the offset of the missile wings 1, has strong bending resistance, ensures the rigidity of the connection, and effectively transfers the load of the missile wings 1 to the missile body 2. By selecting the position of the rectangular groove 9 on the missile body 2 to be inserted, the position of the missile wings 1 can be adjusted in a stop, which is convenient to operate. The number of rectangular grooves 9 can be increased to achieve a wider range of adjustment positions.

[0037] In the specific implementation process, the structure of the binding circular ring 4 is a quarter-circle structure. Two adjacent missile wings 1 are connected by two sets of binding circular rings 4 set in front and behind. There are 8 binding circular rings 4, and several missile wings are connected to the binding circular rings as one unit.

[0038] The two ends of the binding circular retaining ring 4 have connecting lugs 10, and the second connecting through holes 11 are opened on the connecting lugs 10. The first connecting through holes 7 opened at both ends of the wing 1 correspond to a set of second connecting through holes 11 on the binding circular retaining ring 4. The first connecting through holes 7 and the second connecting through holes 11 are connected by connecting bolts 3.

[0039] Specifically, the two ends of the binding circular retaining ring 4 have at least two connecting through holes on the connecting lugs 10, which is the same number as the first connecting through hole 7 at one end of the protruding connecting platform 6 of the wing 1.

[0040] In the specific implementation process, the front end of the raised connecting platform 6 has a slope to reduce the impact of air resistance; the raised connecting platform 6 is parallel and aligned with both sides of the missile wing flange 5.

[0041] This invention meets the connection stiffness requirements between the missile wing 1 and the missile body 2 under flight conditions. It features adjustable wing 1 with different levels of position, making connection and disassembly relatively convenient, and can meet the design requirements for rapid assembly of modular missiles.

[0042] Example 1

[0043] This embodiment provides a modular missile wing connection structure with adjustable position, including a wing 1, a missile body 2, and a binding circular retaining ring 4.

[0044] The missile wing 1 has a rectangular flange structure, namely the missile wing flange 5, at its wing root. The bottom of the missile wing flange 5 has several equidistantly distributed raised rectangular locking blocks 8. Raised connecting platforms 6 are located on both sides of the wing root of the missile wing 1, parallel and aligned with the sides of the missile wing flange 5. At least two connecting through holes are provided at both ends of the raised connecting platforms 6. The front end of the raised connecting platforms 6 is tapered to reduce the impact of air resistance. The missile body 2 has four long rectangular planes of equal thickness along the axial direction at equal angles. Multiple equidistant rectangular grooves 9 are provided on these planes along the axial direction, the number of which is greater than the number of rectangular locking blocks 8 at the bottom of the missile wing 1. The binding circular retaining ring 4 of the missile wing 1 is a quarter-circle structure. Each end of its connecting lugs 10 has at least two second connecting through holes 11, the same number as the number of first connecting through holes 7 at one end of the raised connecting platform 6 of the missile wing 1. Insert the rectangular clip 8 at the bottom of the wing 1 into the rectangular groove 9 of the body 2. Through the concentric fit of the connecting through hole, tighten the connecting bolt 3 to connect the wing root to the connecting lug 10 of the four binding circular clips 4, forming two binding clip structure at the front and rear, pressing and fixing the wing 1 to the body 2.

[0045] Specifically, the rectangular locking block 8 of the wing flange 5 at the bottom of one wing 1 is inserted into the rectangular groove 9 on the missile body 2. Through the concentric engagement of the first connecting through hole 7 and the second connecting through hole 11, the connecting bolt 3 is tightened to press and connect the protruding connecting platform 6 at the root of the wing 1 to the connecting lugs 10 of the four binding circular retaining rings 4. Similarly, the other three wings 1 are connected sequentially until all the wings 1 and the binding circular retaining rings 4 are connected together to form two front and rear binding retaining ring structures, thus fixing the wings 1 to the missile body 2. The close engagement between the protruding rectangular locking block 8 of the wing 1 and the rectangular groove 9 of the missile body 2 restricts the forward, backward, left, and right displacement of the wing 1, while the integrated retaining ring configuration effectively restricts the deflection and detachment of the wing 1, ensuring that the load of the wing 1 is effectively transferred to the missile body 2.

[0046] Example 2

[0047] Further, based on Embodiment 1, the bottom of the wing 1 has multiple raised rectangular locking blocks 8, and the missile body 2 has four rows of multiple rectangular grooves 9 arranged axially. The rectangular locking blocks 8 at the bottom of the four wings 1 are inserted into the rectangular grooves 9 of the missile body 2. The wing roots of the wings 1 are connected to the missile body 2 by connecting bolts 3, and are integrally fixedly connected to the missile body 2 with eight binding circular retaining rings 4, forming two binding ring-type structures at the front and rear. In addition, the number of rectangular grooves 9 on the missile body 2 is greater than the number of rectangular locking blocks 8 at the bottom of the wings 1, and the relative position of the wings 1 can be adjusted by selecting the position of the rectangular grooves 9 to be inserted on the missile body 2.

[0048] The above content is only for illustrating the technical concept of the present invention and should not be construed as limiting the scope of protection of the present invention. Any modifications made to the technical solution based on the technical concept proposed in this invention shall fall within the scope of protection of the claims of this invention.

Claims

1. A modular missile wing connection structure with adjustable position, characterized in that, Includes a projectile body (2), wherein the projectile body (2) is connected to a projectile wing (1); Four long rectangular planes of equal thickness are arranged at equal angles along the axial direction of the projectile body (2), and several rectangular grooves (9) are opened at equal intervals along the axial direction of the long rectangular planes. The wing (1) is provided with a wing flange (5) at the wing root, and the bottom of the wing flange (5) is provided with a number of rectangular locking blocks (8) evenly distributed; the rectangular locking blocks (8) cooperate with the rectangular grooves (9) to connect the wing (1) to the body (2); the number of rectangular grooves (9) is greater than the number of rectangular locking blocks (8), and the relative position of the wing (1) is adjusted by adjusting the insertion position of the rectangular locking blocks (8); Several of the aforementioned wings (1) are fixed to the projectile body (2) by binding circular clasps (4).

2. The modular missile wing connection structure with adjustable position according to claim 1, characterized in that, The distance between adjacent rectangular grooves (9) is equal to the distance between adjacent rectangular blocks (8).

3. The modular missile wing connection structure with adjustable position according to claim 1, characterized in that, The structure of the binding circular clasp (4) is a quarter-circular ring structure.

4. The modular missile wing connection structure with adjustable position according to claim 1, characterized in that, The two adjacent warp wings (1) are connected by two sets of binding circular retaining rings (4) set at the front and back.

5. The modular missile wing connection structure with adjustable position according to claim 1, characterized in that, The wing (1) has protruding connecting platforms (6) on both sides at the wing root, and several first connecting through holes (7) are opened at both ends near the protruding connecting platforms (6). The binding circular retaining ring (4) has several second connecting through holes (11) at both ends; The first connecting through hole (7) is fixedly connected to the second connecting through hole (11), and several binding circular retaining rings (4) are connected to the projectile wing (1).

6. The modular missile wing connection structure with adjustable position according to claim 5, characterized in that, The binding circular clasp (4) has connecting lugs (10) at both ends.

7. The modular missile wing connection structure with adjustable position according to claim 6, characterized in that, The second connecting through hole (11) is formed on the connecting ear piece (10).

8. The modular missile wing connection structure with adjustable position according to claim 5, characterized in that, The first connecting through holes (7) at both ends of the wing (1) correspond to the second connecting through holes (11) on a set of binding circular retaining rings (4).

9. The modular missile wing connection structure with adjustable position according to claim 5, characterized in that, The front end of the raised connecting platform (6) has a slope to reduce the impact of air resistance.

10. The modular missile wing connection structure with adjustable position according to claim 5, characterized in that, The raised connecting platform (6) is aligned parallel to both sides of the missile wing flange (5).

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