Integrated annular locking and unlocking device for folding empennage

Abstract

The invention relates to the technical field of locking and unlocking devices, and discloses an integrated annular locking and unlocking device for a folding empennage. The locking and unlocking device comprises a mounting seat, a locking ring and an inertia body, the inertia body comprises a cylinder part, one end of the cylinder part extends outwards in the radial direction of the cylinder part to form an annular skirt edge, a first limiting groove is formed in the outer circumferential wall of the cylinder part, a thrust pin is elastically connected into the first limiting groove, and a locking groove is formed in the inner circumferential wall of the locking ring; when overload is emitted in an ammunition chamber, the inertia body moves in the direction close to the empennage in the axial direction under the inertia effect, the shear pin is cut off, the thrust pin stretches out of the first limiting groove and enters the locking groove, and the inertia body drives the locking ring to move till the end, away from the annular skirt edge, of the locking ring is connected with the groove in the empennage in a clamped mode. And after the ammunition is discharged from the chamber, the inertia body automatically resets, and the locking ring is driven by the thrust pin to move in the direction deviating from the empennage to be separated from the empennage. Reliable locking in the chamber of the empennage and timely unlocking when the empennage goes out of the chamber are realized, and harsh working environments such as high temperature and high pressure are met.

Description

Technical Field

[0001] The present invention relates to the technical field of locking and unlocking devices, and in particular to an integrated annular locking and unlocking device for a folding tail wing. Background Art

[0002] At present, artificial rainfall and other application scenarios will use rockets or artillery to spread dry ice, silver iodide, salt powder and other catalysts into the clouds to promote precipitation or increase precipitation artificial rainfall. The intelligent ammunition fired by artillery (loaded with dry ice, silver iodide, salt powder and other catalysts), that is, smart ammunition, is becoming more and more a research hotspot. As an important component of smart ammunition, the tail stabilization device is usually set to fold to adapt to the artillery launch platform. During the in-bore firing process, the tail needs to be kept locked to avoid scratching the barrel due to its deployment; after the ammunition is discharged, the tail needs to be unlocked in time and quickly deployed to keep the ammunition in the correct aerodynamic shape. Therefore, the tail stabilization device is directly related to the safety of in-bore firing and the stability after discharge. At present, most tail folding, unfolding and locking are achieved by motor action or gunpowder actuator. These two methods are costly, complex in structure and cumbersome in unlocking. The aircraft cabin needs to be disassembled and even cannot be reused. In addition, open tail compartments are gradually being used in long-range artillery-fired intelligent ammunition. The open tail compartment is located behind the ammunition belt, and each component is directly exposed to the high-temperature and high-pressure gas in the chamber. The current tail stabilization device cannot meet the harsh working environments such as high pressure and high temperature.

[0003] Therefore, there is an urgent need for an integrated annular locking and unlocking device for folding tail fins, which can be used in open tail fin compartments to meet the needs of reliable locking of the tail fin chamber and timely unlocking of the tail fin chamber during the firing process and in harsh working environments of gun-fired intelligent ammunition. Summary of the invention

[0004] Based on the above, the purpose of the present invention is to provide an integrated annular locking and unlocking device for a folding tail wing, so as to achieve reliable locking of the tail wing in the chamber and timely unlocking when out of the chamber, and meet the harsh working environment of high temperature, high pressure, etc.

[0005] To achieve the above object, the present invention adopts the following technical solutions:

[0006] An integrated annular locking and unlocking device for a folding tail wing, comprising:

[0007] A mounting seat is installed in the tail wing compartment shell and is spaced apart at the tail of the tail wing, wherein a mounting groove is provided in the mounting seat;

[0008] A locking ring, movably disposed in the mounting groove, with one end of the locking ring extending out of the mounting groove;

[0009] The inertia body is elastically resettable and connected to the mounting groove along its axial direction, and has a tendency to move in the direction away from the tail wing along its axial direction. The inertia body includes a barrel, one end of the barrel extends radially outward to form an annular skirt, the barrel is movably sleeved in the locking ring and connected and fixed by a shear pin, a first limiting groove is formed on the outer peripheral wall of the barrel, a thrust pin is elastically connected in the first limiting groove, the thrust pin has a tendency to move toward the locking ring, and a locking groove is formed on the inner peripheral wall of the locking ring;

[0010] When the ammunition chamber is overloaded during firing, the inertial body moves along its axial direction toward the tail fin under the action of inertia and cuts off the shear pin, the thrust pin extends out of the first limiting groove and enters the locking groove, the inertial body moves to the annular skirt and abuts against one end of the locking ring, and drives the locking ring to move until the end of the locking ring away from the annular skirt is engaged with the groove on the tail fin;

[0011] After the ammunition is ejected from the chamber, the inertial body automatically resets and drives the locking ring to move in a direction away from the tail fin through the thrust pin until the locking ring is separated from the tail fin.

[0012] As a preferred solution of an integrated annular locking and unlocking device for a folding tail wing, it also includes a reset component, which includes a guide cylinder and a reset spring. The cylinder is provided with a receiving groove, and the notch of the receiving groove is facing the direction of the tail wing. The guide cylinder is fixedly arranged in the installation groove and movably inserted in the receiving groove. The reset spring is arranged in the guide cylinder, and one end abuts against the bottom of the receiving groove. After the ammunition is discharged from the chamber, under the elastic force of the reset spring, the inertial body moves along its axial direction away from the tail wing.

[0013] As a preferred solution of an integrated annular locking and unlocking device for a folding tail wing, the reset assembly also includes a guide rod, which is fixedly connected to the guide cylinder, the reset spring is sleeved outside the guide rod, and a guide hole is opened at the bottom of the accommodating groove, and one end of the guide rod can pass through the guide hole as the inertial body moves.

[0014] As a preferred solution of an integrated annular locking and unlocking device for a folding tail wing, the mounting seat includes a mounting body and an annular baffle, the mounting body is provided with an annular mounting groove, the notch of the mounting groove is facing the direction of the tail wing, the annular baffle is connected to the notch of the mounting groove, and the guide cylinder is fixedly connected to the annular baffle.

[0015] As a preferred solution of an integrated annular locking and unlocking device for a folding tail wing, the annular baffle extends radially outward to form an ear plate, and the guide cylinder is fixedly connected to the ear plate.

[0016] As a preferred solution of an integrated annular locking and unlocking device for a folding tail wing, the mounting seat also includes an annular pressure plate, a first boss is convexly provided on the outer periphery of the locking ring, the annular pressure plate is connected to the outer edge of the slot of the mounting groove, the annular baffle is connected to the inner edge of the slot of the mounting groove, a first annular space is formed between the annular baffle and the annular pressure plate, one end of the locking ring moves through the first annular space, and as the locking ring moves along its axial direction toward the tail wing, the first boss can abut against the annular pressure plate.

[0017] As a preferred solution for an integrated annular locking and unlocking device for a folding tail wing, a limiting platform is formed on the inner wall of the installation groove, and as the locking ring moves along its axial direction away from the tail wing, the first boss can abut against the limiting platform.

[0018] As a preferred solution of an integrated annular locking and unlocking device for a folding tail wing, a second boss is provided on the inner wall of the locking ring, a locking groove is provided on the side of the second boss facing the inertial body, and the locking groove passes through the side of the second boss facing the tail wing.

[0019] As a preferred solution of an integrated annular locking and unlocking device for a folding tail wing, an elastic member is provided at one end of the thrust pin facing away from the locking ring. When the thrust pin is opposite to the locking groove, under the elastic force of the elastic member, the thrust pin extends out of the first limiting groove and enters the locking groove.

[0020] As a preferred solution of an integrated annular locking and unlocking device for a folding tail wing, a vent hole is provided at the bottom of the installation groove, and the vent hole is arranged opposite to the guide hole.

[0021] The beneficial effects of the present invention are:

[0022] The present invention provides an integrated annular locking and unlocking device for a folding tail wing, the locking and unlocking device comprises a mounting seat, a locking ring and an inertial body. When the ammunition chamber is overloaded and reaches the shearing threshold of the shear pin, the inertial body moves toward the tail wing under the action of inertia and shears the shear pin. With the movement of the inertial body, the thrust pin extends out of the first limiting groove and enters the locking groove. The annular skirt of the inertial body abuts against one end of the locking ring and drives the locking ring to move together until the locking ring is engaged with the groove on the tail wing, thereby realizing reliable locking of the tail wing in the chamber and preventing the tail wing from scratching the gun chamber when it is unfolded. After the ammunition is discharged from the chamber, When the overload disappears, the inertial body automatically resets and drives the locking ring to move away from the tail fin through the thrust pin. The locking ring moves to disengage from the tail fin, unlocking the tail fin and allowing it to quickly deploy, making it easier for the ammunition to maintain the correct aerodynamic shape during flight, thereby meeting the safety of in-bore firing and the stability after firing. In addition, the locking and unlocking device is a purely mechanical structure with a simple structure and easy operation. It can meet the harsh working environments such as high temperature and high pressure. At the same time, it is formed as a separate component and is connected to the inner wall of the tail fin compartment shell by threads, which can adapt to the harsh in-bore high temperature, high pressure, high rotation and high overload launching environment. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments of the present invention. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the contents of the embodiments of the present invention and these drawings without paying any creative work.

[0024] Figure 1 1 is a schematic structural diagram of an integrated annular locking and unlocking device for a folding tail wing provided by an embodiment of the present invention (folded state);

[0025] Figure 2 1 is a schematic structural diagram of an integrated annular locking and unlocking device for a folding tail wing provided by an embodiment of the present invention (when the shear pin is not disconnected);

[0026] Figure 3 is a side view of the annular locking and unlocking device provided by an embodiment of the present invention;

[0027] Figure 4 yes Figure 3 Medium AA perspective image;

[0028] Figure 5 is a schematic diagram of a partial structure of a mounting base provided by an embodiment of the present invention;

[0029] Figure 6 is a schematic diagram of the locking ring structure provided by an embodiment of the present invention;

[0030] Figure 7It is a schematic diagram of the inertial body structure provided by an embodiment of the present invention.

[0031] In the figure:

[0032] 1. Mounting seat; 11. Mounting groove; 111. Limiting platform; 112. Ventilation hole; 12. Annular baffle; 121. Ear plate; 13. Annular pressure plate;

[0033] 2. Locking ring; 21. Locking groove; 22. First boss; 23. Second boss;

[0034] 3. Inertia body; 31. Cylinder; 311. First limiting groove; 312. Accommodating groove; 32. Annular skirt;

[0035] 4. Reset assembly; 41. Guide cylinder; 42. Reset spring; 43. Guide rod;

[0036] 101. Shear pin; 102. Thrust pin. DETAILED DESCRIPTION

[0037] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only parts related to the present invention, rather than all structures, are shown in the accompanying drawings.

[0038] In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0039] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0040] In the description of the present embodiment, the terms "upper", "lower", "left", "right" and other directions or positional relationships are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of description and simplification of operation, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation of the present invention. In the description of the present invention, unless otherwise specified, the meaning of "plurality" is two or more. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0041] like Figures 1 to 7 As shown, this embodiment provides an integrated annular locking and unlocking device for a folding tail, the locking and unlocking device comprises a mounting seat 1, a locking ring 2 and an inertial body 3, the mounting seat 1 is mounted in the tail compartment shell and is spaced at the tail of the tail, a mounting groove 11 is arranged in the mounting seat 1, the locking ring 2 is movably arranged in the mounting groove 11, one end of the locking ring 2 extends out of the mounting groove 11, the inertial body 3 is elastically resettable and connected to the mounting groove 11 along its axial direction, and has a tendency to move in the direction away from the tail along its axial direction, the inertial body 3 comprises a barrel 31, one end of the barrel 31 extends radially outward to form an annular skirt 32, the barrel 31 is movably sleeved in the locking ring 2, and is connected and fixed by the shear pin 101, the outer peripheral wall of the barrel 31 is provided with a first limiting groove 311, and a thrust pin 102 is elastically connected in the first limiting groove 311, and the thrust pin 102 has a tendency to move toward the locking ring 2, and a locking groove 21 is formed on the inner peripheral wall of the locking ring 2; when the overload in the ammunition chamber is fired and the shearing threshold of the shear pin 101 is reached, the inertial body 3 moves along its axis under the action of inertia The inertial body 3 moves toward the direction close to the tail fin and cuts off the shear pin 101. With the movement of the inertial body 3, the thrust pin 102 extends out of the first limiting groove 311 and enters the locking groove 21. The inertial body 3 moves to the annular skirt 32 to abut against one end of the locking ring 2, and drives the locking ring 2 to move together, until the end of the locking ring 2 away from the annular skirt 32 is engaged with the groove on the tail fin, so as to realize reliable locking in the bore of the tail fin and prevent the tail fin from scratching the barrel when it is unfolded; after the ammunition is discharged from the barrel, the overload disappears, the inertial body 3 automatically resets, and is driven by the thrust pin 102 The dynamic locking ring 2 moves in the direction away from the tail fin, and the locking ring 2 moves to disengage from the tail fin, thereby unlocking the tail fin when it is ejected from the barrel, allowing the tail fin to quickly unfold, making it easier for the ammunition to maintain a correct aerodynamic shape during flight, and meeting the safety of in-barrel firing and stability after ejecting from the barrel; in addition, the locking and unlocking device is a purely mechanical structure with a simple structure and easy operation, which can meet the harsh working environments such as high temperature and high pressure, and at the same time, it is formed as a separate component and is connected to the inner wall of the tail fin compartment shell by threads, which can adapt to the harsh in-barrel high temperature, high pressure, high rotation and high overload firing environment.

[0042] Exemplarily, the locking ring 2 is an annular structure with no quadrant requirement during installation, and can adapt to the consistent locking and unlocking of different numbers of tail wings, with better applicability; in other embodiments, the locking ring 2 may also be provided with multiple protrusions in addition to the engagement with the tail wing groove, and can also adapt to the consistent locking and unlocking of different numbers of tail wings, which is determined according to actual conditions.

[0043] Specifically, the locking and unlocking device also includes a reset component 4, which includes a guide cylinder 41 and a reset spring 42. The cylinder portion 31 is provided with a receiving groove 312, and the notch of the receiving groove 312 faces the direction of the tail wing. The guide cylinder 41 is fixedly arranged in the mounting groove 11 and movably inserted in the receiving groove 312. The reset spring 42 is arranged in the guide cylinder 41, and one end abuts against the bottom of the receiving groove 312. After the ammunition is discharged from the chamber, under the action of the elastic force of the reset spring 42, the inertial body 3 moves along its axial direction away from the tail wing. When the ammunition is overloaded during firing in the chamber, the inertial body 3 moves along its axial direction toward the tail fin under the action of inertia, and the bottom of the accommodating groove 312 abuts against the return spring 42 and is gradually compressed. The movement of the inertial body 3 causes the return spring 42 to compress and store energy. When the ammunition is fired, the overload disappears, and the return spring 42 is reset and releases energy, pushing the inertial body 3 and the locking ring 2 to move along their axial direction away from the tail fin, and the locking ring 2 is separated from the tail fin, so that the tail fin is unlocked after being fired. In addition, the return spring 42 is installed in the guide tube 41 to prevent the gunpowder gas from burning the return spring 42 during the firing process, which affects the use of the locking and unlocking device.

[0044] Preferably, the reset assembly 4 further comprises a guide rod 43, which is fixedly connected to the guide cylinder 41, and the reset spring 42 is sleeved outside the guide rod 43. A guide hole is provided at the bottom of the receiving groove 312, and one end of the guide rod 43 can pass through the guide hole as the inertial body 3 moves. The setting of the guide rod 43 can prevent the reset spring 42 from bending during the compression and extension process, which affects the driving of the inertial body 3; the aperture size of the guide hole is limited to the passing of the guide rod 43, which facilitates the bottom of the receiving groove 312 to compress the reset spring 42, and prevents the reset spring 42 from passing through the guide hole, which is unable to store energy and thus unable to generate driving force for the inertial body 3; in addition, the setting of the guide hole can balance the internal and external pressures of the locking and unlocking device, which is convenient for the ammunition to be fired.

[0045] More preferably, a vent hole 112 is provided at the bottom of the installation groove 11, and the vent hole 112 is arranged opposite to the guide hole. The vent hole 112 is arranged to balance the internal and external pressures of the locking and unlocking device to facilitate the firing of ammunition.

[0046] Further, the mounting seat 1 includes a mounting body and an annular baffle 12, the mounting body is provided with an annular mounting groove 11, the notch of the mounting groove 11 faces the tail direction, the annular baffle 12 is connected to the notch of the mounting groove 11, and the guide cylinder 41 is fixedly connected to the annular baffle 12. The annular baffle 12 is used to fix the guide cylinder 41, and at the same time, axially limit the inertial body 3 to maintain the stability of the locking and unlocking device. Exemplarily, the mounting body is an annular structure, the mounting groove 11 opened inside it is U-shaped, and the U-shaped opening faces the tail direction. The mounting body has an inner ring wall, an outer ring wall and a bottom wall, and a U-shaped mounting groove is formed between the inner ring wall, the outer ring wall and the bottom wall. The center of the annular structure is a hollow structure, which is connected to the inside of the tail compartment shell, providing a flow channel for the engine gas, and will not cause the thrust loss of the engine. In other embodiments, the mounting body can also be in other annular structures to meet the flow of the engine gas, which is determined according to actual conditions.

[0047] Preferably, the annular baffle 12 extends radially outward to form an ear plate 121, and the guide tube 41 is fixedly connected to the ear plate 121. By providing the ear plate 121 to connect the guide tube 41, the negative mass of the annular baffle 12 is reduced, the requirement of reducing the negative mass of the tail locking and unlocking device is met, and the stability and safety of ammunition launch are increased.

[0048] Specifically, the mounting seat 1 further comprises an annular pressure plate 13, a first boss 22 is convexly provided on the outer periphery of the locking ring 2, the annular pressure plate 13 is connected to the outer edge of the notch of the mounting groove 11, the annular baffle 12 is connected to the inner edge of the notch of the mounting groove 11, a first annular interval is formed between the annular baffle 12 and the annular pressure plate 13, one end of the locking ring 2 moves through the first annular interval, and as the locking ring 2 moves along its axial direction toward the tail wing, the first boss 22 can abut against the annular pressure plate 13. The annular pressure plate 13 is connected to the notch of the outer ring wall of the mounting groove 11, the annular baffle 12 is connected to the notch of the outer ring wall of the mounting groove 11, the annular pressure plate 13 abuts against the first boss 22, thereby radially limiting the locking ring 2, and when one end of the locking ring 2 moves through the first annular interval, the annular pressure plate 13 and the annular baffle 12 abut against the inner and outer sides of the locking ring 2, respectively, and both can maintain the stability of the locking and unlocking device.

[0049] Furthermore, a limiting platform 111 is formed on the inner wall of the installation groove 11, and as the locking ring 2 moves in the direction away from the tail wing along its axial direction, the first boss 22 can abut against the limiting platform 111. The limiting platform 111 is convexly arranged on the side of the outer ring wall of the installation groove 11 facing the inner ring wall, and the limiting platform 111 radially limits the first boss 22, thereby radially limiting the locking ring 2, reducing the impact force generated on the annular skirt 32 when the locking ring 2 moves in the direction away from the tail wing along its axial direction, and maintaining the stability of the locking and unlocking device.

[0050] Furthermore, a second boss 23 is provided on the inner wall of the locking ring 2, and a locking groove 21 is provided on the side of the second boss 23 facing the inertial body 3, and the locking groove 21 penetrates the side of the second boss 23 facing the tail wing. Since the locking groove 21 is provided through, it is convenient for the thrust pin 102 to move in the locking groove 21, and prevents the thrust pin 102 from being disconnected due to excessive inertia force when the locking groove 21 is a closed groove, thereby reducing the inertia force brought by the second boss 23 borne by the thrust pin 102. The second boss 23 is arranged opposite to the first limiting groove 311, and when the locking and unlocking device structure is in a folded state, the thrust pin 102 abuts against the second boss 23. When an overload is fired in the ammunition chamber, the inertial body 3 moves along its axial direction toward the tail wing under the action of inertia, driving the thrust pin 102 to move relative to the second boss 23 until the thrust pin 102 extends out of the first limiting groove 311, enters the locking groove 21 and abuts against the side of the second boss 23 facing the tail wing. When the ammunition is ejected from the chamber, since the thrust pin 102 abuts against the groove wall of the locking groove 21 facing the tail wing, the thrust pin 102 can drive the locking ring 2 to move in the direction away from the tail wing, thereby unlocking the tail wing when it is ejected from the chamber.

[0051] Preferably, an elastic member is provided at one end of the thrust pin 102 away from the locking ring 2. When the thrust pin 102 is directly opposite to the locking groove 21, under the elastic force of the elastic member, the thrust pin 102 extends out of the first limiting groove 311 and enters the locking groove 21. The elastic member is sleeved on one end of the thrust pin 102 close to the first limiting groove 311, and the elastic member is fixedly connected to the bottom of the first limiting groove 311 to prevent the thrust pin 102 from falling off. The length of the elastic member is less than the groove depth of the first limiting groove 311 to prevent the elastic member from being stuck outside the first limiting groove 311 when it is reset and extended. Exemplarily, the elastic member can be configured as a compression spring. When the thrust pin 102 is located in the first limiting groove 311, the compression spring stores force and energy. When the thrust pin 102 is directly opposite to the locking groove 21, the compression spring resets and releases energy, driving the thrust pin 102 to extend out of the first limiting groove 311 and enter the locking groove 21, so that the inertial body 3 and the locking ring 2 are connected as one, which is convenient for reliable locking in the bore of the tail wing and timely unlocking when out of the bore.

[0052] The above are only preferred embodiments of the present invention and the technical principles used. Those skilled in the art will understand that the present invention is not limited to the specific embodiments described herein, and that various obvious changes, readjustments and substitutions can be made by those skilled in the art without departing from the scope of protection of the present invention. Therefore, although the present invention has been described in more detail through the above embodiments, the present invention is not limited to the above embodiments, and may include more other equivalent embodiments without departing from the concept of the present invention, and the scope of the present invention is determined by the scope of the appended claims.

Claims

1. An integrated annular locking and unlocking device for a folding tail wing, characterized in that: include: A mounting seat is installed in the tail wing compartment shell and is spaced apart at the tail of the tail wing, wherein a mounting groove is provided in the mounting seat; A locking ring, movably disposed in the mounting groove, with one end of the locking ring extending out of the mounting groove; The inertia body is elastically resettable and connected to the mounting groove along its axial direction, and has a tendency to move in the direction away from the tail wing along its axial direction. The inertia body includes a barrel, one end of the barrel extends radially outward to form an annular skirt, the barrel is movably sleeved in the locking ring and connected and fixed by a shear pin, a first limiting groove is formed on the outer peripheral wall of the barrel, a thrust pin is elastically connected in the first limiting groove, the thrust pin has a tendency to move toward the locking ring, and a locking groove is formed on the inner peripheral wall of the locking ring; When the ammunition chamber is overloaded during firing, the inertial body moves along its axial direction toward the tail fin under the action of inertia and cuts off the shear pin, the thrust pin extends out of the first limiting groove and enters the locking groove, the inertial body moves to the annular skirt and abuts against one end of the locking ring, and drives the locking ring to move until the end of the locking ring away from the annular skirt is engaged with the groove on the tail fin; After the ammunition is ejected from the chamber, the inertial body automatically resets and drives the locking ring to move in a direction away from the tail fin through the thrust pin until the locking ring is separated from the tail fin.

2. The integrated annular locking and unlocking device for a folding tail wing according to claim 1, characterized in that: It also includes a reset component, which includes a guide cylinder and a reset spring. The cylinder is provided with a receiving groove, and the notch of the receiving groove faces the direction of the tail wing. The guide cylinder is fixedly arranged in the installation groove and movably inserted in the receiving groove. The reset spring is arranged in the guide cylinder, and one end abuts against the bottom of the receiving groove. After the ammunition is discharged from the chamber, under the elastic force of the reset spring, the inertial body moves along its axial direction away from the tail wing.

3. The integrated annular locking and unlocking device for a folding tail wing according to claim 2, characterized in that: The reset assembly also includes a guide rod, which is fixedly connected in the guide cylinder. The reset spring is sleeved outside the guide rod. A guide hole is opened at the bottom of the accommodating groove. One end of the guide rod can pass through the guide hole as the inertial body moves.

4. The integrated annular locking and unlocking device for a folding tail wing according to claim 2, characterized in that: The mounting seat includes a mounting body and an annular baffle, the mounting body is provided with an annular mounting groove, the notch of the mounting groove faces the direction of the tail wing, the annular baffle is connected to the notch of the mounting groove, and the guide cylinder is fixedly connected to the annular baffle.

5. The integrated annular locking and unlocking device for a folding tail wing according to claim 4, characterized in that: The annular baffle plate extends radially outward to form an ear plate, and the guide cylinder is fixedly connected to the ear plate.

6. The integrated annular locking and unlocking device for a folding tail wing according to claim 4, characterized in that: The mounting seat also includes an annular pressure plate, a first boss is convexly provided on the outer periphery of the locking ring, the annular pressure plate is connected to the outer edge of the slot of the mounting groove, the annular baffle is connected to the inner edge of the slot of the mounting groove, a first annular space is formed between the annular baffle and the annular pressure plate, one end of the locking ring moves through the first annular space, and as the locking ring moves along its axial direction toward the tail wing, the first boss can abut against the annular pressure plate.

7. The integrated annular locking and unlocking device for a folding tail wing according to claim 6, characterized in that: A limiting platform is formed on the inner wall of the installation groove, and as the locking ring moves along its axial direction in a direction away from the tail wing, the first boss can abut against the limiting platform.

8. The integrated annular locking and unlocking device for a folding tail wing according to claim 1, characterized in that: A second boss is arranged on the inner wall of the locking ring, and a locking groove is formed on a side of the second boss facing the inertial body, and the locking groove penetrates a side of the second boss facing the tail wing.

9. The integrated annular locking and unlocking device for a folding tail wing according to claim 1, characterized in that: An elastic member is provided at one end of the thrust pin away from the locking ring. When the thrust pin is directly opposite to the locking groove, under the elastic force of the elastic member, the thrust pin extends out of the first limiting groove and enters the locking groove.

10. The integrated annular locking and unlocking device for a folding tail wing according to claim 1, characterized in that: A vent hole is provided at the bottom of the installation groove, and the vent hole is arranged opposite to the guide hole.

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