A wing outside rotary folding mechanism

Abstract

The utility model provides a wing outside rotation folding mechanism, including wing, wing seat, locking mechanism, torsional spring, the wing seat fixed mounting is in the rear of missile, its setting has the inner chamber, is installed with locking mechanism in the inner chamber, the wing includes the wing piece and with the torsional part that wing piece is connected, the torsional part inserts into the inner chamber of wing seat, outside setting has torsional spring, torsional spring is against the inner chamber side wall of wing seat, provides the force of turning over to wing piece, locking mechanism sets up the limit pin for wing piece to insert the wing clamping groove that sets up in the torsional part side after unfolding. The utility model discloses a wing is folded and is stored in the outer wall of missile body, to liberate the inside space of missile body, reduces the restriction to the inside layout of missile body, solves the situation of mutual check and balance between wing and missile body inside layout.

Description

Technical Field

[0001] This utility model relates to a projectile wing structure, and more particularly to a projectile wing external rotation and folding mechanism. Background Technology

[0002] Small tactical missiles are mostly launched from tubes, and their wings are mostly folding wing structures. When the missile is inside the tube, it is constrained by the inner wall of the tube. After the missile is launched from the tube, the wings are released to a fixed position and locked by the unfolding mechanism.

[0003] Traditional rotary-folding deployment mechanisms connect the wings to the missile body via a horizontally positioned pivot at the tail, perpendicular to the missile's axis. During folding, the wings rotate around this pivot until they are parallel to the missile body. When retracted into the missile body, the wings must penetrate deeply, dividing the internal space into four fan-shaped regions or two semi-circular regions. This severely impacts the internal structural layout of the missile, and when the central internal area is unavailable, the wing width is severely limited. Therefore, satisfying the wing length and width constraints severely restricts the internal structural layout of the missile body. Conversely, satisfying the internal structural layout constraints further severely limits the wing length and width. Utility Model Content

[0004] This utility model provides an externally mounted rotating and folding mechanism for projectile wings, which solves the problem of projectile wing storage and deployment. The technical solution is as follows:

[0005] An externally mounted rotating folding mechanism for missile wings includes a missile wing, a wing mount, a locking mechanism, and a torsion spring. The wing mount is fixedly installed at the rear of the missile and has an inner cavity in which the locking mechanism is installed. The missile wing includes a wing flap and a torsion section connected to the wing flap. The torsion section is inserted into the inner cavity of the wing mount, and a torsion spring is provided on its outer side. The torsion spring abuts against the inner cavity sidewall of the wing mount and provides a force for flipping the wing flap. The locking mechanism is provided with a limit pin for inserting the wing flap into a wing slot provided on the side of the torsion section after it is unfolded.

[0006] The wing mount includes a wing mount body, which is fixedly installed at the rear of the missile. A groove is provided on the outer side for receiving the front end of the wing blade when the missile wing is not deployed. An insertion hole is provided between the groove and the inner cavity of the wing mount for inserting the torsion part of the missile wing. A connecting part is provided in the inner cavity of the wing mount body, and the connecting part is rotatably connected to the torsion part.

[0007] The twisting part of the missile wing is obliquely and fixedly connected to the winglet.

[0008] The torsion section is divided into a connecting section, a torsion section, and a rotation section from the front end to the rear end. The connecting section is inserted into the connecting section and is rotatably connected to the connecting section through a bearing. A connecting piece is provided in the middle of the torsion section, and a torsion spring is provided on the outer side. The two ends of the torsion spring abut against the inner cavity sidewall of the wing body and the middle abut against the connecting piece. The rotation section passes through the insertion hole of the wing body and is provided with a wing slot. When the wing rotates into place, the limiting pin of the locking mechanism is inserted into the wing slot.

[0009] The locking mechanism includes a locking base, a limiting pin, and a limiting spring. The locking base is fixed to the inner wall of the wing seat by bolts, and a limiting pin and a limiting spring are provided inside it.

[0010] The limiting pin is cross-shaped, with its front end protruding from the opening of the locking base and abutting against the torsion part. A limiting spring is sleeved on its rear end, and the other end of the limiting spring abuts against the inner wall of the locking base, providing an outward force to the limiting pin.

[0011] The outer side of the wing base is provided with two pairs of missile wings, each pair of missile wings including two adjacent missile wings, which deploy synchronously in opposite directions.

[0012] The angle between the twisted part and the plane where the airfoil is located is 30 to 70 degrees.

[0013] The connector is made of bolts, which are fixed to the threaded holes in the middle of the torsion section.

[0014] The external rotating folding mechanism of the projectile wing frees up the internal space of the projectile by folding and storing the projectile wing on the outer wall of the projectile, reducing the restrictions on the internal layout of the projectile and solving the problem of mutual restraint between the projectile wing and the internal layout of the projectile. Attached Figure Description

[0015] Figure 1 This is a three-dimensional structural diagram of the external rotating and folding mechanism for the missile wing;

[0016] Figure 2 This is a cross-sectional schematic diagram of the external rotating and folding mechanism of the missile wing;

[0017] Figure 3 This is a schematic diagram of the structure of the said missile wing;

[0018] Figure 4 This is a schematic diagram of the connection between the twisted part of the missile wing and the wing mount. Figure 1 ;

[0019] Figure 5 This is a schematic diagram of the connection between the twisted part of the missile wing and the wing mount. Figure 2 ;

[0020] Figure 6 This is a schematic diagram of the connection between the twisted part of the missile wing and the wing mount. Figure 3 ;

[0021] Figure 7 This is a schematic diagram of the structure of the torsion spring;

[0022] Figure 8 This is a schematic diagram of the deployment of the aforementioned missile wings. Detailed Implementation

[0023] like Figure 1 and Figure 2 As shown, the external rotating folding mechanism of the missile wing includes a missile wing 1, a wing base 2, a locking mechanism 3, and a torsion spring 4. The wing base 2 is fixedly installed at the rear of the missile and has an inner cavity in which the locking mechanism 3 is installed. The missile wing 1 includes a wing piece 11 and a torsion part 12 connected to the wing piece 11. The torsion part 12 is inserted into the inner cavity of the wing base 2, and a torsion spring 4 is provided on the outer side. The torsion spring 4 abuts against the inner cavity sidewall of the wing base 2 and provides a force for flipping the wing piece 11. The locking mechanism 3 is provided with a limit pin 31 for inserting the wing piece 11 into the missile wing slot 13 provided on the side of the torsion part 12 after it is unfolded.

[0024] The wing mount 2 includes a wing mount body 21, which is cylindrical and fixedly installed at the rear of the missile. A groove 22 is provided on the outer side of the wing mount body 21. When the wing flap 11 of the missile wing 1 is not deployed, the front end of the flap 11 is located in the groove 22, ensuring that the flap 11 does not exceed the outer diameter of the wing mount body 21 when viewed from above. At this time, the end of the flap 11 faces downwards. An insertion hole 23 is provided between the groove 22 and the inner cavity of the wing mount 2, for inserting the torsion part 12 of the missile wing 1. A connecting part 24 is provided in the inner cavity of the wing mount body 21, and the connecting part 24 is rotatably connected to the connecting section of the torsion part 12.

[0025] Combination Figure 3 As shown, the end of the twisting part 12 of the wing 1 is fixedly connected to the front end of the wing 11, and the twisting part 12 is fixedly connected to the wing 11 at an angle, that is, there is an angle between the twisting part 12 and the plane where the wing 11 is located. In this embodiment, the angle is 30 to 70 degrees, and can be designed to be 45 degrees.

[0026] Combination Figures 4 to 6 As shown, the torsion section 12 is divided into a connecting section 14, a torsion section 15, and a rotating section 16 from front to back. The connecting section 14 is inserted into the connecting section 24 and is rotatably connected to the connecting section 24 via a bearing 17. A connecting member 5 is provided in the middle of the torsion section 15, and a torsion spring 4 is provided on its outer side. The torsion spring 4 is as follows... Figure 7As shown, the torsion spring 4 is in a pre-compressed state, with its two ends abutting against the inner cavity sidewall of the wing base body 21 and its middle abutting against the connecting piece 5. When the missile leaves the launch tube, the wing 1 loses its external constraint, and the torsion spring 4 releases potential energy to drive the torsion part 12 of the wing 1 to rotate, thereby realizing the deployment of the wing 11. The rotating section 16 passes through the insertion hole 23 of the wing base body 21, which is provided with a wing slot 13. When the wing 11 rotates into place, the limiting pin 7 of the locking mechanism 3 is inserted into the wing slot 13.

[0027] The locking mechanism 3 is installed in the inner cavity of the wing body 21. It includes a locking base, a limiting pin 31, and a limiting spring 32. The locking base is installed in the inner cavity of the wing body 21 and fixed to the inner wall of the wing 2 by bolts. The limiting pin 31 and the limiting spring 32 are installed inside the locking base. The limiting pin 31 is cross-shaped, with its front end protruding from the opening of the locking base and abutting against the rotating section 16 of the torsion part 12. The limiting spring 32 is sleeved on its rear end. The other end of the limiting spring 32 abuts against the inner wall of the locking base, providing an outward force to the limiting pin 31. When the wing flips into place, the front end of the limiting pin 31 is facing the wing slot 13. Under the action of the limiting spring 32, the limiting pin 31 inserts into the wing slot 13, thereby fixing the position of the wing 1. It can be seen that the locking mechanism 3 has a simple structure and is safe and reliable in operation.

[0028] like Figure 8 The diagram shows the missile wing 1 from folding to unfolding. As you can see, after the missile leaves the launch tube, the missile wing 1 loses its external constraint. The torsion spring 4 releases its potential energy to drive the missile wing 1 to rotate around the axis of rotation. Adjacent missile wings unfold synchronously in opposite directions (e.g., missile wing A rotates clockwise and missile wing B rotates counterclockwise). The rotational inertia cancels each other out, ensuring the stability of the missile body attitude. When the missile wing 1 unfolds to be perpendicular to the missile body, the limiting pin 7 is locked into the missile wing slot under the action of the limiting spring 6, achieving rigid locking, and the missile enters the flight state.

[0029] This invention uses a torsion spring as the power source for the deployment of the projectile wings, which can effectively achieve rapid and synchronous deployment of the projectile wings, with good synchronization and high reliability in the deployment process.

[0030] The deployment method adopts the adjacent wings facing each other. The two adjacent wings rotate in opposite directions around the axis of rotation. The rotational inertia generated during the deployment of the wings cancel each other out. After the missile leaves the tube, the deployment of the wings has little impact on the attitude of the missile body.

[0031] Compared with existing technologies, the advantage of this invention lies in its ability to fold and store the projectile wings on the outer wall of the projectile when the internal space is limited, thereby providing a complete space inside the projectile and reducing restrictions on the internal layout. This invention frees up internal space by folding and storing the projectile wings on the outer wall of the projectile, reducing restrictions on the internal layout and resolving the mutual constraints between the projectile wings and the internal layout.

Claims

1. A wing-external rotating folding mechanism, characterized in that: The missile includes a wing, a wing mount, a locking mechanism, and a torsion spring. The wing mount is fixedly installed at the rear of the missile and has an inner cavity in which the locking mechanism is installed. The wing includes a wing flap and a torsion part connected to the wing flap. The torsion part is inserted into the inner cavity of the wing mount, and a torsion spring is provided on its outer side. The torsion spring abuts against the inner cavity sidewall of the wing mount and provides a force for flipping the wing flap. The locking mechanism is provided with a limit pin for inserting into the wing slot provided on the side of the torsion part after the wing flap is deployed.

2. The externally mounted rotating folding mechanism for projectile wings according to claim 1, characterized in that: The wing mount includes a wing mount body, which is fixedly installed at the rear of the missile. A groove is provided on the outer side for receiving the front end of the wing blade when the missile wing is not deployed. An insertion hole is provided between the groove and the inner cavity of the wing mount for inserting the torsion part of the missile wing. A connecting part is provided in the inner cavity of the wing mount body, and the connecting part is rotatably connected to the torsion part.

3. The externally mounted rotating folding mechanism for projectile wings according to claim 1, characterized in that: The twisting part of the missile wing is obliquely and fixedly connected to the winglet.

4. The externally mounted rotating folding mechanism for projectile wings according to claim 1, characterized in that: The torsion section is divided into a connecting section, a torsion section, and a rotation section from the front end to the rear end. The connecting section is inserted into the connecting section and is rotatably connected to the connecting section through a bearing. A connecting piece is provided in the middle of the torsion section, and a torsion spring is provided on the outer side. The two ends of the torsion spring abut against the inner cavity sidewall of the wing body and the middle abut against the connecting piece. The rotation section passes through the insertion hole of the wing body and is provided with a wing slot. When the wing rotates into place, the limiting pin of the locking mechanism is inserted into the wing slot.

5. The externally mounted rotating folding mechanism for projectile wings according to claim 1, characterized in that: The locking mechanism includes a locking base, a limiting pin, and a limiting spring. The locking base is fixed to the inner wall of the wing seat by bolts, and a limiting pin and a limiting spring are provided inside it.

6. The externally mounted rotating folding mechanism for projectile wings according to claim 5, characterized in that: The limiting pin is cross-shaped, with its front end protruding from the opening of the locking base and abutting against the torsion part. A limiting spring is sleeved on its rear end, and the other end of the limiting spring abuts against the inner wall of the locking base, providing an outward force to the limiting pin.

7. The externally mounted rotating folding mechanism for projectile wings according to claim 1, characterized in that: The outer side of the wing base is provided with two pairs of missile wings, each pair of missile wings including two adjacent missile wings, which deploy synchronously in opposite directions.

8. The externally mounted rotating folding mechanism for projectile wings according to claim 3, characterized in that: The angle between the twisted part and the plane where the airfoil is located is 30 to 70 degrees.

9. The externally mounted rotating folding mechanism for projectile wings according to claim 4, characterized in that: The connector is made of bolts, which are fixed to the threaded holes in the middle of the torsion section.

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