Empennage folding device and guided missile
By adopting a combination design of mount, flap, limit part and elastic parts on the missile tail, the problems of complex folding structure and poor stability of the tail wing are solved, the stable deployment and handling of the missile are improved, and the complex assembly is reduced degree and cost.
Patent Information
- Application Number
- CN202420924290.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-04-29
- Publication Date
- 2024-12-20
- Estimated Expiration
- Not applicable · inactive patent
AI Technical Summary
The folding structure of the existing missile tail wing is complex and cannot be stably maintained in a deployed state, especially when facing external forces, which easily folds partially or completely, resulting in poor handling of the rolling channel.
A tail wing folding device is designed, using components such as mounts, wings, elastic parts, limit parts and bearings. Through the plug-in fit of the limit parts and the compression potential energy of the elastic parts, the wings are kept stable during flight. and high temperature ablation is prevented by flange rings.
The tail wing folding structure is simplified, the handling and stability of the missile's rolling channel is improved, the assembly complexity and cost are reduced, and the high-temperature ablation is prevented, which enhances the missile's anti-jamming ability.
Smart Images
Figure CN222211425U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of missile control, in particular to a tail folding device and a missile. Background Art
[0002] The related technology can reduce the storage space and launch space occupied by the missile body by setting a folding tail fin at the tail of a small and medium diameter missile while stably controlling its rolling channel. However, the current missile body tail fin folding structure is relatively complex. In addition, since the tail fin is maintained in an unfolded state by the compression potential energy of the torsion spring, if the external force is greater than the force provided by the elastic compression potential energy of the torsion spring, the tail fin cannot maintain a stable unfolded state. Utility Model Content
[0003] In view of this, the utility model provides a tail folding device and a missile, aiming to solve the problem that the folding structure of the missile body tail fin is relatively complicated and the wing cannot be stably maintained in the unfolded state.
[0004] On the one hand, the utility model provides a tail folding device, including a mounting seat, a wing and an elastic member, wherein the first end of the wing is rotatably connected to the mounting seat around an axis parallel to a first linear direction, and the elastic member is installed between the wing and the mounting seat. The tail folding device also includes a first limiting portion and a second limiting portion, wherein at least one side of the first end of the wing is provided with a first limiting portion along the first linear direction, and a second limiting portion is provided at the mounting seat corresponding to a first limiting portion. The wing has a folded state and an unfolded state. When the wing is in the folded state, the second end of the wing is arranged close to the mounting seat, and the elastic member is in a compressed state. When the wing is in the unfolded state, the first limiting portion is inserted and arranged with the second limiting portion along the first linear direction to keep the wing in the unfolded state.
[0005] Beneficial effect: The wing has a folded state and an unfolded state. When the wing is in the folded state, the second end of the wing is arranged close to the mounting seat, that is, the second end of the wing rotates to a position close to the mounting seat, thereby reducing the radial space occupied by the wing, and the elastic member is in a compressed state at this time. When the wing is in the unfolded state, the second end of the wing rotates to a position away from the mounting seat, which is conducive to eliminating the interference torque of the rolling channel of the missile during flight, so as to improve the rolling channel controllability of the missile body.
[0006] When the wing rotates from the compressed state to the unfolded state at the preset position under the action of the elastic member, the first limiting portion and the second limiting portion are plugged and matched along the first straight line direction. The plugged first limiting portion and the second limiting portion can prevent the wing from continuing to unfold, and at the same time prevent the wing from rotating in the opposite direction toward the folded state, so that the wing can maintain a stable unfolded state. That is, the wing can maintain a stable unfolded state only by the plugging and matching of the first limiting portion and the second limiting portion in the first straight line direction, which has a simple structure and is easy to operate, and has the advantages of simple processing technology and low manufacturing cost.
[0007] In an optional embodiment, the first limiting portion is a limiting column, and one side of the first end of the wing is connected to the limiting column along the first straight line direction. The second limiting portion is a limiting groove, and when the wing is in the unfolded state, the limiting column is inserted into the limiting groove along the first straight line direction.
[0008] Beneficial effect: Through the plug-in cooperation between the limiting column and the limiting groove in the first straight line direction, the side wall of one side of the limiting groove can limit the wing from continuing to unfold through the limiting column, and the other side wall of the limiting groove arranged opposite to each other can simultaneously prevent the wing from rotating to the folded state through the limiting column, so that the wing can maintain a stable unfolded state. Compared with the scheme in which the wing is maintained in the unfolded state only by the elastic force of the elastic member. It can avoid a large external force (i.e., greater than the force of the elastic member) during flight to partially or completely fold the wing, so as to improve the rolling channel controllability of the projectile.
[0009] In an optional embodiment, along the first straight line direction, the first limiting portion and the second limiting portion are arranged on the leeward side of the airfoil.
[0010] Beneficial effect: When the tail folding device is flying along the first straight line, the wing will be subject to an air resistance directed from the windward side to the leeward side. Under the action of the air resistance, the wing moves along the first straight line direction so that the first limit portion approaches the second limit portion and maintains a plug-in fit state, so that the wing maintains a stable unfolded state.
[0011] In an optional embodiment, the elastic member is a torsion spring, and when the wing is in a folded state, the torsion spring is in a compressed state around an axis parallel to the first straight line direction.
[0012] Beneficial effect: When the wing is in a compressed state, the wing and the mounting seat exert a circumferential force on the torsion spring, so that the torsion spring is in a compressed state around an axis parallel to the first straight line (i.e., circumferential direction). When the wing is not acted upon by an external force, the compressed torsion spring exerts a force on the wing to rotate the wing from a folded state to an unfolded state, until the first limiting portion and the second limiting portion are plugged and matched along the first straight line, so that the wing remains in a stably unfolded state.
[0013] In an optional embodiment, when the wing is in a folded state, the torsion spring is in a compressed state along the first straight line direction. When the wing is in an unfolded state, the torsion spring causes the first limiting portion to approach the second limiting portion along the first straight line direction and maintain the plugged state.
[0014] Beneficial effect: By setting the torsion spring in an axially compressed state in the folded state and in an expanded state in which the first limiting portion and the second limiting portion are plugged in and matched, the torsion spring can apply a force along the first straight line direction to the first limiting portion through the wing, so that the first limiting portion and the second limiting portion maintain a stable plug-in state.
[0015] In an optional embodiment, there are multiple fins, and the multiple fins are distributed at intervals along the circumference of the mounting seat. A first limit portion is provided on at least one side of the first end of each fin along the first straight line direction.
[0016] Beneficial effect: The mounting seat is provided with a plurality of winglets along the circumferential direction, and a first limiting portion is provided on at least one side of the windward side and the leeward side of each winglet, so that each winglet can maintain a stable unfolded state during the flight of the projectile, which is beneficial to improving the control stability of the rolling channel of the projectile.
[0017] In an optional embodiment, the tail folding device further includes a third limiter, which is arranged at a position of the mounting seat close to the wing. When the first limiter is plugged and matched with the second limiter, the third limiter contacts the first end of the wing to prevent the wing from further unfolding.
[0018] Beneficial effect: Since the elastic member such as the torsion spring will continuously exert a force on the wing to continue to expand, the third limiter can prevent the wing from continuing to expand. Combined with the plug-in cooperation between the first limiter and the second limiter, the third limiter further improves the stability of the wing in the expanded state.
[0019] In an optional embodiment, the tail folding device also includes a flange ring, and along the first straight line direction, one end of the mounting seat close to the leeward side is connected to the flange ring, and the outer diameter of the flange ring is larger than the radial dimension of the mounting seat.
[0020] Beneficial effect: Since the leeward side of the mounting seat is arranged close to the engine injection port of the projectile during use, by providing a flange ring with a larger outer diameter, it is possible to prevent the high-temperature tail flame at the injection port from burning the components of the tail folding device.
[0021] In an optional embodiment, the mounting seat is provided with a mounting through hole along the first straight line direction, and the tail folding device further comprises at least two bearings. In the mounting through hole, at least two bearings are spaced apart and distributed along the first straight line direction and connected to the mounting seat.
[0022] Beneficial effect: The tail folding device installed on the missile body can be connected or interference-fitted with the outer wall of the missile body through the inner walls of at least two bearings. That is, through the arrangement of at least two bearings, the mounting seat can drive the wing to rotate more than the missile body and have a smaller rotation resistance, which is conducive to reducing or eliminating the interference torque of the rolling channel of the missile body during flight.
[0023] On the other hand, the utility model also provides a missile, comprising a missile body and the tail folding device in the above aspect, wherein the missile body and the tail folding device are detachably connected.
[0024] Beneficial effect: By setting the tail folding device as a modular structure, the missile body and the tail folding device can be conveniently and quickly assembled and disassembled through simple interface matching, which is conducive to improving production efficiency and reducing the complexity of the assembly process through modular production.
[0025] In addition, since the tooling assembly also includes the clamping tooling in the above aspect, the tooling assembly has all the beneficial effects of the above-mentioned clamping tooling, which will not be repeated here. BRIEF DESCRIPTION OF THE DRAWINGS
[0026] In order to more clearly illustrate the specific implementation methods of the utility model or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.
[0027] Figure 1 It is a three-dimensional structural schematic diagram of a tail wing folding device in an embodiment of the utility model, in which the wing is in a folded state;
[0028] Figure 2 for Figure 1 A three-dimensional structural schematic diagram showing that the wing of the tail folding device is in an unfolded state;
[0029] Figure 3 for Figure 1 A partial enlarged schematic diagram showing the wing of the tail folding device in a folded state;
[0030] Figure 4 for Figure 2 A partial enlarged schematic diagram showing the wing of the tail folding device in a folded state;
[0031] Figure 5 for Figure 2 A cross-sectional view of the tail folding device shown.
[0032] Description of reference numerals:
[0033] 100. Tail wing folding device;
[0034] 10. Mounting seat;
[0035] 20. Wings;
[0036] 30. Elastic parts;
[0037] 41. first limiting portion; 42. second limiting portion; 43. third limiting portion;
[0038] 50. Pin;
[0039] 61. First socket; 62. Second socket;
[0040] 71. Flange ring; 72. First bearing; 73. Second bearing. DETAILED DESCRIPTION
[0041] In order to make the purpose, technical solution and advantages of the embodiment of the utility model clearer, the technical solution in the embodiment of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiment of the utility model. Obviously, the described embodiment is a part of the embodiment of the utility model, not all the embodiments. Based on the embodiment of the utility model, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the utility model.
[0042] In the description of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they cannot be understood as limitations on the present invention.
[0043] The terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present utility model, unless otherwise specified, "plurality" means two or more.
[0044] Large missiles are heavier and have a larger body diameter. By setting a fixed tail fin, the rolling channel of the large missile can be stably controlled.
[0045] However, small and medium-sized missiles are more practical, and their advantages of being small, flexible and low-cost are becoming more and more prominent. As for small and medium-diameter missiles, due to their small diameter and weight, the moment of inertia along the roll channel is very small, resulting in very poor anti-interference ability of the roll channel to the outside world, which increases the difficulty of controlling the missile roll channel.
[0046] The related technology can reduce the storage space and launch space occupied by the missile body by setting a folding tail fin at the tail of a small and medium diameter missile while stably controlling its rolling channel. However, the current missile body tail fin folding structure is relatively complex. In addition, since the tail fin is maintained in an unfolded state by the compression potential energy of the torsion spring, if the external force is greater than the force provided by the elastic compression potential energy of the torsion spring, the tail fin cannot maintain a stable unfolded state.
[0047] Combine the following Figures 1 to 5 , describing the embodiments of the tail folding device and missile of the utility model.
[0048] On the one hand, according to an embodiment of the present utility model, as Figure 1 and Figure 2 As shown, a tail folding device 100 is provided, including a mounting seat 10, a wing 20 and an elastic member 30. The first end of the wing 20 is rotatably connected to the mounting seat 10 around an axis parallel to the first straight line direction, and the elastic member 30 is installed between the wing 20 and the mounting seat 10.
[0049] Taking the first straight line direction as the front-to-back direction (i.e., the axial direction or the X direction) as an example, the wing 20 can be rotated relative to the mounting seat 10 around an axis parallel to the front-to-back direction. When the tail folding device 100 is installed on the missile body, the missile flies or moves from the back to the front. Correspondingly, the front side of the tail folding device 100 is the windward side, and the rear side of the tail folding device 100 is the leeward side.
[0050] The wing 20 has a folded state and an unfolded state. Figure 1 In the folded state shown, the second end of the wing 20 is disposed close to the mounting seat 10, that is, the second end of the wing 20 is rotated to a position close to the mounting seat 10, thereby reducing the radial space occupied by the wing 20, and at this time the elastic member 30 is in a compressed state. Figure 2 In the deployed state shown, the second end of the wing 20 rotates to a position away from the mounting seat 10, which is beneficial to eliminate the interference torque of the rolling channel of the missile during flight, so as to improve the rolling channel controllability of the missile body.
[0051] It should be noted that the wing 20 can remain in a folded state under the action of external force to reduce space occupation. For example, when the projectile is in the transportation process or in the launch tube, the wing 20 is in a folded state. Moreover, under the action of external force, the wing 20 in the folded state can also compress the elastic member 30 so that the elastic member 30 accumulates elastic potential energy. When the external force or the external limiting structure disappears, under the action of the elastic member 30, the wing 20 can quickly rotate from the folded state to the unfolded state at the preset position.
[0052] Based on this, Figure 3 and Figure 4 As shown, the tail folding device 100 further includes a first limiting portion 41 and a second limiting portion 42. Along the first straight direction, at least one side of the first end of the wing 20 is provided with a first limiting portion 41, and one second limiting portion 42 is provided at the mounting seat 10 corresponding to one first limiting portion 41. When the wing 20 is in the unfolded state, the first limiting portion 41 is inserted and arranged with the second limiting portion 42 along the first straight direction, so that the wing 20 remains in the unfolded state.
[0053] In this way, when the wing 20 rotates from the compressed state to the unfolded state at the preset position under the action of the elastic member 30, the first limit portion 41 and the second limit portion 42 are plugged and matched along the first straight line direction. The plugged first limit portion 41 and the second limit portion 42 can prevent the wing 20 from continuing to unfold, and at the same time prevent the wing 20 from rotating in the opposite direction toward the folded state, so that the wing 20 can maintain a stable unfolded state. That is, the wing 20 can maintain a stable unfolded state only by the plugging and matching of the first limit portion 41 and the second limit portion 42 in the first straight line direction, which has a simple structure and is easy to operate, and has the advantages of simple processing technology and low manufacturing cost.
[0054] When the connecting wing 20 and the mounting seat 10 are rotated, as shown in FIG. Figure 2 and Figure 5 As shown, the tail folding device 100 further includes a pin 50. The wing 20 is provided with one or more first sockets 61 along the first straight line direction at the first end, and each first socket 61 is provided with a first plug hole along the first straight line direction. The mounting seat 10 is provided with one or more second sockets 62 along the corresponding first sockets 61, and each second socket 62 is provided with a second plug hole along the first straight line direction. The first plug hole and the second plug hole are aligned along the first straight line direction, so that the pin 50 is sequentially inserted into the first plug hole and the second plug hole along the first straight line direction, that is, the wing 20 is rotatably connected to the mounting seat 10 through the pin 50.
[0055] For example, if a first end of a wing 20 is provided with a first socket 61, a corresponding second socket 62 may be provided on one side of the first socket 61 along the first straight line direction. Alternatively, the second sockets 62 may be provided on opposite sides of the first socket 61.
[0056] If two first sockets 61 are provided at the first end of a wing 20 along the first straight line direction, one or more second sockets 62 may be connected between the two first sockets 61 via a pin shaft along the first straight line direction. Figure 2 As shown, a second socket 62 is provided between the two first sockets 61, and a second socket 62 is also provided on the other side of the first end along the first straight line direction away from the first limiting portion 41, and the side of the first end along the first straight line direction close to the first limiting portion 41 is used to set the second limiting portion 42.
[0057] A third second socket 62 may be provided at the position where the second limiting portion 42 is provided on the mounting seat 10, and the second limiting portion 42 is provided at the second socket 62. The second limiting portion 42 may also be provided directly here without providing a third second socket, which is not limited.
[0058] Thus, when the wing 20 is in a compressed state, the wing 20 and the mounting seat 10 exert a circumferential force on the torsion spring, so that the torsion spring is in a compressed state around an axis parallel to the first straight line direction (i.e., the circumferential direction). When the wing 20 is not acted upon by an external force, the compressed torsion spring exerts a force on the wing 20 to rotate the wing 20 from the folded state to the unfolded state, until the first limiting portion 41 and the second limiting portion 42 are plugged and matched along the first straight line, so that the wing 20 maintains a stable unfolded state.
[0059] In addition, the elastic member 30 may also be a metal or non-metal spring sheet, or an elastic rope, etc., which is not limited thereto.
[0060] In some embodiments, Figure 3 and Figure 4 As shown, the first limiting portion 41 is a limiting column. Along the first straight line direction, one side of the first end of the wing 20 is connected to the first limiting portion 41 of the limiting column structure. Correspondingly, the second limiting portion 42 is a limiting groove. When the wing 20 is in Figure 2 and Figure 4 In the unfolded state shown, the limiting post is inserted into the limiting groove along the first straight line direction.
[0061] Through the plug-in cooperation between the limiting column and the limiting groove in the first straight line direction, the side wall of one side of the limiting groove can limit the wing 20 from further unfolding through the limiting column, and the other side wall of the limiting groove opposite to the limiting groove can simultaneously prevent the wing 20 from rotating to the folded state through the limiting column, so that the wing 20 can maintain a stable unfolded state. For example, a limiting column is provided with a corresponding limiting groove structure at the mounting seat 10.
[0062] Compared with the scheme in which the wing 20 is maintained in the unfolded state only by the elastic force of the elastic member 30, a larger external force (i.e., greater than the force of the elastic member 30) during flight can be avoided to partially or completely fold the wing 20, thereby improving the rolling channel controllability of the missile body.
[0063] In some other embodiments, the first limiting portion 41 can also be set as a limiting groove structure, and the corresponding second limiting portion 42 can be a limiting column structure connected to the mounting seat 10, which can also meet the plug-in limiting effect of the first limiting portion 41 and the second limiting portion 42 along the first straight line direction.
[0064] It should be noted that, along the first straight line direction, a first limiting portion 41 may be provided on one side of the first end of the wing 20 , and a second limiting portion 42 adapted to match the first limiting portion 41 may be provided at the mounting seat 10 .
[0065] Alternatively, along the first straight line direction, two opposite first ends of the wing 20 are provided with a first limiting portion 41, and the mounting seat 10 is provided with one or two matching second limiting portions 42 corresponding to each wing, which is not limited thereto.
[0066] In some embodiments, Figure 5 As shown, along the first straight line direction, the first limiting portion 41 and the second limiting portion 42 are arranged on the leeward side of the wing 20 .
[0067] When the tail folding device 100 is flying along the first straight line, the wing 20 is subjected to an air resistance directed from the windward side to the leeward side. Under the action of the air resistance, the wing 20 moves the first limit portion 41 close to the second limit portion 42 along the first straight line and maintains a plug-in fit state, so that the wing 20 maintains a stable unfolded state.
[0068] In some embodiments, Figure 1 and Figure 3 As shown, when the wing 20 is in the folded state, the torsion spring is in a compressed state along the first straight line direction. Figure 2 and Figure 4 In the unfolded state shown, the torsion spring (ie, the elastic member 30 ) causes the first limiting portion 41 to approach the second limiting portion 42 along the first straight line direction and maintain the plugged state.
[0069] In the first straight direction, the first limiting portion 41 is a plug-in column located on the leeward side of the first end of the wing 20, and the second limiting portion 42 is a plug-in hole of the mounting seat 10 located on the leeward side of the wing 20. The rotatably connected wing 20 and the mounting seat 10 can slide forward and backward along the first straight direction at the pin 50, such as the windward side is the front side. When the wing 20 is in the folded state, the wing 20 moves forward along the first straight direction compared to the mounting seat 10, and the length of the torsion spring in the first straight direction is reduced to be in a compressed state. At this time, the first end and the second end of the torsion spring are close to each other in the circumferential direction and the torsion spring is in a circumferentially compressed state. When the wing 20 rotates to the expanded state in which the plug-in post and the plug-in hole are aligned along the first straight line direction under the drive of the torsion spring, the axially compressed torsion spring applies a backward force to the wing 20 to make the plug-in post insert backward into the plug-in hole, and restricts the wing 20 from continuing to expand and rotate or rotate in the folding direction through the two opposite side walls of the plug-in hole in the circumferential direction, that is, the wing 20 maintains a stable expanded state at the preset position.
[0070] By setting the torsion spring in an axially compressed state in the folded state and in an expanded state in which the first limiting portion 41 and the second limiting portion 42 are plugged in and matched, the torsion spring can apply a force along the first straight line direction to the first limiting portion 41 through the wing 20, so that the first limiting portion 41 and the second limiting portion 42 maintain a stable plug-in state.
[0071] Exemplarily, along the first straight line direction, the torsion spring is sleeved on the pin 50 and is located between a first socket 61 and a second socket 62. The second socket 62 is arranged in contact with the torsion spring and is located on the windward side of the torsion spring.
[0072] In some embodiments, there are multiple fins 20, which are spaced apart along the circumference of the mounting seat 10, and the first straight line direction is the circumference of the mounting seat 10. A first stopper 41 is provided on at least one side of the first end of each fin 20 along the first straight line direction.
[0073] The mounting seat 10 is provided with a plurality of winglets 20 along the circumferential direction, and a first limiting portion 41 is provided on at least one side of the windward side and the leeward side of each winglet 20, so that each winglet 20 can maintain a stable unfolded state during the flight of the projectile, which is beneficial to improving the control stability of the rolling channel of the projectile.
[0074] For example, the number of fins 20 may be Figure 2 As shown, the four fins 20 are distributed at intervals of 90° along the circumference of the mounting seat 10. Alternatively, the number of fins 20 may be three, and the three fins 20 are distributed at intervals of 120° along the circumference of the mounting seat 10. Alternatively, the number of fins 20 may be two, and the two fins 20 are distributed at intervals of 180° along the circumference of the mounting seat 10.
[0075] In some embodiments, Figure 2 As shown, the tail folding device 100 further includes a third limit portion 43. The third limit portion 43 may be a convex structure or a groove structure. The third limit portion 43 is disposed at a position of the mounting seat 10 close to the wing 20. When the first limit portion 41 and the second limit portion 42 are as shown in FIG. Figure 4 During the plug-in fitting, the third limiting portion 43 contacts the first end of the wing 20 to prevent the wing 20 from further unfolding.
[0076] Since the elastic member 30 such as the torsion spring will continuously exert a force to continue to expand the wing 20, the third limiter 43 can prevent the wing 20 from continuing to expand. Combined with the plug-in cooperation of the first limiter 41 and the second limiter 42, the third limiter 43 further improves the stability of the wing 20 in the expanded state.
[0077] It should be noted that, because the wing 20 can be quickly rotated from the folded state to the unfolded state under the action of the elastic member 30, the third limiter 43 can be provided to enable the wing 20 to stop rotating quickly when it is quickly rotated to the unfolded state at the preset position, and avoid causing a large impact force on the first limiter 41 and the second limiter 42 when the wing 20 stops suddenly.
[0078] Taking the third limiting portion 43 as an example, the third limiting portion 43 is located between two adjacent first sockets 61 along the first straight line direction, and a second socket 62 is provided at the third limiting portion 43. A torsion spring in an axial compression state is provided between the second socket 62 and a first socket 61 on its leeward side.
[0079] In some embodiments, the fin 20 may be a rectangular sheet-like structure with a simple structure.
[0080] Alternatively, the wing 20 may also be a curved structure bent from the first end to the second end. In this way, when the wing 20 is in the folded state, its second end may be arranged close to the mounting seat 10, thereby reducing the occupied space of the tail folding device 100 in the radial direction.
[0081] It should be noted that the first limit portion 41 and the first plug hole are arranged in different positions from the first end to the second end of the wing 20, or from the second end to the first end of the wing 20. For example, the first limit portion 41 is located on the side of the first plug hole close to the second end. Or the first limit portion 41 is located on the side of the first plug hole away from the second end. So that the plug-in cooperation between the first limit portion 41 and the second limit portion 42 in the axial direction can prevent the wing 20 from rotating clockwise and counterclockwise.
[0082] In some embodiments, the tail folding device 100 further includes a flange ring 71. Along the first straight line direction, one end of the mounting seat 10 close to the leeward side is connected to the flange ring 71, and the outer diameter of the flange ring 71 is larger than the radial dimension of the mounting seat.
[0083] Since the leeward side of the mounting seat 10 is arranged close to the engine injection port of the missile body during use, the high-temperature tail flame at the injection port can be prevented from burning the components of the tail folding device 100 by providing a flange ring 71 with a larger outer diameter.
[0084] For example, the flange ring 71 and the mounting seat 10 can be detachably connected to facilitate assembly and maintenance of the tail folding device 100. For example, the flange ring 71 and the mounting seat 10 can be detachably connected via a threaded structure.
[0085] The mounting seat 10 is approximately a cylindrical structure and has a mounting through hole. The mounting through hole is used to be sleeved on the tail of the projectile to connect the mounting seat 10 and the projectile.
[0086] Taking the wing 20 as a curved structure as an example, the overall outer diameter of the wing 20 and the mounting seat 10 in the folded state is less than or equal to the outer diameter of the flange ring 71, which is conducive to reducing the space occupied by the tail folding device 100 in the storage state, facilitating canister launch and reducing storage space.
[0087] In some embodiments, Figure 5 As shown, the mounting seat 10 is provided with a mounting through hole 11 along the first straight line direction. The tail folding device 100 further includes at least two bearings, in which the at least two bearings are spaced apart and connected to the mounting seat 10 along the first straight line direction in the mounting through hole 11 .
[0088] At least two bearings are Figure 5 Taking the first bearing 72 and the second bearing 73 as an example, in the mounting through hole 11, the first bearing 72 and the second bearing 73 are spaced apart along the first straight line direction, and the first bearing 72 is located on the windward side of the second bearing 73. The outer walls of the first bearing 72 and the second bearing 73 can be arranged in the mounting through hole 11 by interference fit to be connected with the mounting seat 10.
[0089] In this way, the tail folding device 100 installed on the missile body can be connected to or fitted with the outer wall of the missile body through the first bearing 72 and the inner wall of the second bearing. That is, by setting at least two bearings, the mounting seat 10 can drive the wing 20 to rotate compared with the missile body, and has a smaller rotation resistance, which is conducive to reducing or eliminating the interference torque of the rolling channel of the missile body during flight.
[0090] In some embodiments, the bearing can be configured as a high-speed bearing with a sealed structure. For example, the bearing uses a ceramic bearing with a sealed end cap as an inner sand-proof structure. The bearing has a self-lubricating effect and does not need to be lubricated for long-term storage, which facilitates the maintenance and repair of the rotating tail mechanism in the later stage, and has a low cost throughout the life cycle.
[0091] The inner diameter of the flange ring 71 is smaller than or equal to the inner diameter of the bearing, that is, the flange ring 71 on the leeward side can serve as an outer sand-proof structure and can prevent the high-temperature tail flame from ablating the bearing structure.
[0092] On the other hand, an embodiment of the present utility model further provides a missile, which includes a missile body and the tail folding device 100 in the above aspect, and the missile body and the tail folding device 100 are detachably connected.
[0093] That is, by setting the tail folding device 100 to a modular structure, the bomb body and the tail folding device 100 can be assembled and disassembled conveniently and quickly through simple interface matching, which is beneficial to improving production efficiency and reducing the complexity of the assembly process through modular production.
[0094] In addition, since the missile also includes the tail folding device 100 in the above aspect, the missile has all the beneficial effects of the above tail folding device 100, which will not be repeated here.
[0095] That is, in actual use, the wing 20 in the folded state can be quickly rotated and unfolded by the force of the elastic member 30 without external force. The first end of the wing 20 unfolded to the preset position can abut against the third limit portion 43, and the axial force of the elastic member 30 enables the first limit portion 41 to move backward along the first straight line direction and be plugged and matched with the second limit portion 42, and the wing 20 can maintain a stable unfolded state.
[0096] If the above process is the maintenance process of the tail folding device 100, then a forward force along the first straight line direction can be applied to the wing 20 to move the wing 20 forward and make the first limit portion 41 and the second limit portion 42 out of the plug-in matching state. Then, a circumferential force or a radial force is applied to the wing 20 to rotate the wing 20 in the same direction to the folded state. Then, a continuous external force is applied to the wing 20 through the sleeve structure or other limit members to keep the wing 20 in a stable folded state.
[0097] Although the embodiments of the present invention are described in conjunction with the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations are all within the scope defined by the appended claims.
Claims
1. A tail folding device, comprising a mounting seat (10), a wing (20) and an elastic member (30), wherein a first end of the wing (20) is rotatably connected to the mounting seat (10) around an axis parallel to a first straight line direction, and the elastic member (30) is installed between the wing (20) and the mounting seat (10); It is characterized in that The tail folding device (100) further comprises: A first limiting portion (41), wherein at least one side of the first end of the wing (20) is provided with the first limiting portion (41) along the first straight line direction; and a second limiting portion (42), wherein one second limiting portion (42) corresponds to one first limiting portion (41) and is arranged on the mounting seat (10); Wherein, the wing (20) has a folded state and an unfolded state; When the wing (20) is in the folded state, the second end of the wing (20) is arranged close to the mounting seat (10), and the elastic member (30) is in a compressed state; When the wing (20) is in the unfolded state, the first limiting portion (41) is inserted into and arranged with the second limiting portion (42) along the first straight line direction, so that the wing (20) maintains the unfolded state.
2. The tail folding device according to claim 1, characterized in that: The first limiting portion (41) is a limiting column, and along the first straight line direction, one side of the first end of the wing (20) is connected to the limiting column; The second limiting portion (42) is a limiting groove, and when the wing (20) is in an unfolded state, the limiting column is inserted into the limiting groove along the first straight line direction.
3. The tail folding device according to claim 1, characterized in that: Along the first straight line direction, the first limiting portion (41) and the second limiting portion (42) are arranged on the leeward side of the wing (20).
4. The tail folding device according to claim 1, characterized in that: The elastic member (30) is a torsion spring; When the wing (20) is in a folded state, the torsion spring is in a compressed state about an axis parallel to the first straight direction.
5. The tail folding device according to claim 4, characterized in that: When the wing (20) is in a folded state, the torsion spring is in a compressed state along the first straight line direction; When the wing (20) is in an unfolded state, the torsion spring causes the first limiting portion (41) to approach the second limiting portion (42) along the first straight line direction and maintain a plugged state.
6. The tail folding device according to any one of claims 1 to 5, characterized in that: The number of the fins (20) is multiple, and the multiple fins (20) are distributed at intervals along the circumference of the mounting seat (10); The first end of each wing (20) is provided with the first limiting portion (41) on at least one side along the first straight line direction.
7. The tail folding device according to any one of claims 1 to 5, characterized in that: The tail folding device (100) further comprises: a third limiting portion (43), the third limiting portion (43) being arranged at a position of the mounting seat (10) close to the wing (20); When the first limiting portion (41) is plugged and matched with the second limiting portion (42), the third limiting portion (43) contacts the first end of the wing (20) to prevent the wing (20) from further unfolding.
8. The tail folding device according to any one of claims 1 to 5, characterized in that: The tail folding device (100) further comprises: A flange ring (71), along the first straight direction, one end of the mounting seat (10) close to the leeward side is connected to the flange ring (71), and the outer diameter of the flange ring (71) is larger than the radial dimension of the mounting seat (10).
9. The tail folding device according to any one of claims 1 to 5, characterized in that: The mounting seat (10) is provided with a mounting through hole (11) along the first straight line direction, and the tail folding device (100) further comprises: At least two bearings are disposed in the mounting through hole (11), and at least two of the bearings are spaced apart and distributed along the first straight line direction and are connected to the mounting seat (10).
10. A missile, characterized in that: include: Projectile; And the tail folding device (100) according to any one of claims 1 to 9, wherein the bomb body is detachably connected to the tail folding device (100).