Tail wing opening and locking device

Abstract

The application discloses a tail wing opening and locking device, which comprises a tail wing shell, three or more tail wing assemblies installed in the tail wing shell and an opening driving device, the tail wing shell is fixed at the tail of a projectile, the three or more tail wing assemblies are fixed and arranged uniformly in the tail wing shell along the circumference, the opening driving device is installed in the tail wing shell and used for driving the tail wing to open to a limit position, each tail wing assembly comprises a locking pin, the tail wing can be automatically opened to the limit position and locked after the projectile is separated from a launching barrel, the tail wing can be kept in the opened state, the tail wing can be prevented from swinging back and forth due to external factors, and the stability of the projectile in flight is ensured.

Description

Technical Field

[0001] This invention belongs to the field of projectile launching technology, specifically relating to a tail fin deployment and locking device. Background Technology

[0002] The main purpose of tail fins on a projectile is to provide aerodynamic support during launch, thus ensuring good flight stability, similar to the feathers on the tail of an arrow used in shooting competitions. Due to the limitations of the launch tube, tail fins are generally folded within the projectile body and need to deploy after leaving the launch tube. Once deployed, the free tail fins are highly susceptible to external factors such as maneuvering overload and wind resistance, which may cause them to oscillate back and forth, thus affecting the stability of the projectile's flight. Summary of the Invention

[0003] In view of this, the present invention provides a tail fin opening and locking device, which can ensure that after the projectile leaves the launch tube, the tail fin quickly and automatically opens to the limit position and locks, so that the tail fin can be kept in the opened state, avoiding the tail fin from swinging back and forth due to external factors, and ensuring the stability of the projectile flight.

[0004] This invention is achieved through the following technical solution:

[0005] A tail fin deployment and locking device includes: a tail fin housing, three or more tail fin assemblies installed inside the tail fin housing, and a deployment drive device;

[0006] The peripheral components are: the launch tube;

[0007] The tail fin housing is fixed to the tail of the projectile and is integrally installed inside the launch tube along with the projectile. The side wall of the tail fin housing is machined with tail fin grooves in the same number as the tail fin assembly along the axial direction.

[0008] Three or more tail fin assemblies are evenly fixed inside the tail fin housing along the circumference, and the tail fin of each tail fin assembly is opposite to three or more tail fin slots. In the initial state, the tail fins are retracted into the tail fin housing under the action of the side wall of the launch tube.

[0009] The opening drive device is installed inside the tail fin housing and is used to drive the tail fins in three or more tail fin assemblies to pass through the tail fin slot and open radially to the limit position.

[0010] Each tail fin assembly includes a tail fin, a tail fin mount, a pin, a spring, and a locking pin. The tail fin mount is fixed to the tail fin housing, and the tail fin is pinned to the tail fin mount via the pin. The spring and locking pin are both mounted on the tail fin mount. The spring and locking pin work together to limit the retraction direction of the tail fin after it leaves the launch tube and the tail fin rotates around the axis of the pin to its limit position under the action of the opening drive device.

[0011] Furthermore, the deployment drive device includes a compression spring and a compression spring seat. The compression spring seat is installed at the end of the tail fin housing where the tail fin is located. The compression spring is installed inside the tail fin housing. One end of the compression spring is fixedly connected to the compression spring seat. When the tail fin housing is located inside the launch tube, the other end of the compression spring abuts against the end faces of three or more tail fins, and the compression spring is in a compressed state. When the projectile is launched and leaves the launch tube, the tail fins are deployed to their limit position under the action of the compression spring force.

[0012] Furthermore, one side of the tail fin seat is an arc surface that can mate with the inner circumferential surface of the tail fin shell. Let the side where the arc surface is located on the tail fin seat be the outer side, the side opposite the arc surface be the inner side, the two ends along the axial direction be end a and end b respectively, and the other two sides be the first side and the second side.

[0013] The tail fin mount has pin holes machined along the direction from the first side to the second side, and a groove is also machined on the middle part of the b end face of the tail fin mount.

[0014] A semi-circular boss is provided at one end of the tail fin, and concentric shaft holes are provided on the semi-circular boss.

[0015] The semi-circular boss of the tail fin is fitted into the groove, and the pin passes through the pin hole on the tail fin seat and the shaft hole on the tail fin to connect the tail fin and the tail fin seat.

[0016] Furthermore, a stepped through hole is machined on the tail fin seat along the direction from the first side to the second side. The stepped through hole is closer to end b than the pin hole. The stepped through hole is divided into a large diameter section, a medium diameter section, and a small diameter section along the direction from the first side to the second side. The large diameter section is threaded. The groove divides the stepped through hole into two parts: one part is the small diameter section, and the other part is the medium diameter section and the large diameter section. The medium diameter section and the large diameter section together serve as a locking hole.

[0017] The diameter of the locking pin is smaller than the inner diameter of the middle diameter section of the locking hole, but larger than the inner diameter of the small diameter section.

[0018] One side of the semi-circular boss is provided with a stepped surface as a limiting surface; when the tail fin is deployed, the limiting surface of the tail fin reaches the limit position when it contacts the tail fin shell; the transition connection surface between the other side of the semi-circular boss and the end face of the tail fin is a locking surface.

[0019] When the tail fin is not deployed to its limit, the locking pin is installed in the middle diameter section of the locking hole, the locking screw is threaded to the large diameter section of the locking hole, and the spring is installed between the locking pin and the locking screw. One end of the spring abuts against the locking screw, and the other end abuts against one end of the locking pin. The spring is in a compressed state, and the other end of the locking pin abuts against the side of the tail fin under the action of the spring.

[0020] After the tail wing is deployed to its limit position, the tail wing releases its constraint on the locking pin. Under the action of the spring, the locking pin enters the groove and abuts against the end face of the process hole. The side of the locking pin limits the locking surface of the tail wing, thereby limiting the tail wing to retract and locking the deployed tail wing.

[0021] Furthermore, the tail fin seat is a hexahedron, and one side of the tail fin seat is an arc surface that can mate with the inner circumferential surface of the tail fin shell. A radially threaded hole is machined on the arc surface; the radially threaded hole is located between the stepped through hole and the pin hole.

[0022] The outer surface of the tail fin housing has mounting holes along the circumference, which are used to connect the tail fin assembly to the radial screw holes one by one by screws.

[0023] Furthermore, the small-diameter hole segment is used as a process hole;

[0024] Unlocking process holes are provided along the circumference on the outer surface of the tail fin housing, and the unlocking process holes are aligned with the process holes on the tail fin mount.

[0025] Furthermore, one end of the compression spring seat is provided with a stepped surface, and one end of the compression spring is bonded to the stepped surface of the compression spring seat by an adhesive.

[0026] Beneficial effects:

[0027] (1) The tail fin housing of the present invention is fixed to the tail of the projectile and is integrally disposed inside the launch tube along with the projectile; three or more tail fin assemblies are uniformly fixedly disposed inside the tail fin housing along the circumference; the tail fin is connected to the tail fin seat pin by a pin shaft; the deployment drive device is installed inside the tail fin housing to drive the tail fins of the three or more tail fin assemblies to pass through the tail fin slot of the tail fin housing and deploy radially to the limit position; the spring and the locking pin cooperate to limit the retraction direction of the tail fin after the projectile leaves the launch tube and the tail fin rotates around the pin shaft to the limit position under the action of the deployment drive device. By setting the spring and the locking pin, the present invention can limit the retraction of the tail fin after the tail fin is deployed, thereby locking the tail fin in the limit position, so that the tail fin can be kept in the deployed state continuously, avoiding the tail fin from swinging back and forth or rebounding back to the tail fin slot due to external factors, and ensuring the stability of the projectile flight.

[0028] Furthermore, by providing tail wing grooves on the outer surface of the tail wing housing in the same number as the tail wing assembly, the present invention can ensure the smooth deployment of the tail wing, thus solving the problem that the tail wing housing must both fix the tail wing assembly and not hinder the deployment of the tail wing.

[0029] Meanwhile, the separate design of the tail fin assembly reduces the processing and assembly difficulty of the device's tail fin body, making it applicable to different small-diameter projectiles.

[0030] (2) The deployment drive device of the present invention includes a compression spring and a compression spring seat. The compression spring seat is installed at the end of the tail fin housing where the tail fin is located. The compression spring is installed inside the tail fin housing, and one end of the compression spring is fixedly connected to the compression spring seat. When the tail fin housing is located inside the launch tube, the other end of the compression spring abuts against the end faces of three or more tail fins, and the compression spring is in a compressed state. After the projectile is launched and leaves the launch tube, the tail fins are deployed to their limit position under the action of the compression spring force. By setting the compression spring and the compression spring seat, it is possible to ensure that the tail fins are successfully deployed to their limit position under the action of the compression spring force after the projectile is launched.

[0031] (3) In this invention, when the tail fin is not fully deployed, the locking pin is installed in the middle diameter section of the locking hole, and the locking screw is threadedly connected to the large diameter section of the locking hole. The spring is installed between the locking pin and the locking screw, with one end of the spring abutting against the locking screw and the other end abutting against one end of the locking pin. The spring is in a compressed state, and the other end of the locking pin abuts against the side of the tail fin under the action of the spring. By compressing the spring with the locking screw, it is possible to install the spring and locking pin from the first side of the tail fin seat, which is simple to operate and convenient to install.

[0032] (4) The other side of the semi-circular boss of the present invention is provided with a stepped surface as a limiting surface. When the tail fin is deployed, the limiting surface of the tail fin reaches the limit position when it contacts the tail fin shell. The present invention limits the deployment of the tail fin by setting a limiting surface on the tail fin and using the contact between the limiting surface and the tail fin shell; and limits the retraction direction of the tail fin with the locking pin, so that the deployed tail fin can be fixed in the limit position, so that the tail fin can be kept in the deployed state continuously, avoiding the tail fin from swinging back and forth or rebounding back to the tail fin groove due to external factors, and ensuring the stability of the projectile flight.

[0033] (5) In this invention, the small-diameter hole section on the tail fin seat is used as a process hole; an unlocking process hole is provided along the circumference on the outer surface of the tail fin housing, and the unlocking process hole is one-to-one with the process hole on the tail fin seat. By setting the process hole and the unlocking process hole, not only can the locking device be unlocked during assembly to meet assembly requirements, but the device can also be used multiple times by unlocking to meet the requirements of multiple non-destructive tests before testing. Attached Figure Description

[0034] Figure 1 This is an overall schematic diagram of the tail fin opening and locking device of the present invention;

[0035] Figure 2 This is a schematic diagram of the tail fin assembly;

[0036] Figure 3 This is a schematic diagram of the tail fin mount;

[0037] Figure 4 Here is a detailed image of the tail fin;

[0038] Figure 5This is a cross-section of the tail fin not deployed. Figure I ;

[0039] Figure 6 This is a cross-section view with the tail fin not deployed. Figure II ;

[0040] Figure 7 yes Figure 6 A magnified view of part A;

[0041] Figure 8 This is a cross-section of the tail fin with the tail fin deployed. Figure I ;

[0042] Figure 9 This is a cross-section of the tail fin with the tail fin deployed. Figure II ;

[0043] Figure 10 yes Figure 9 A magnified view of part B;

[0044] Figure 11 This is a detailed image of the tail fin casing;

[0045] Among them, 1-tail wing assembly, 1-1-tail wing, 1-1-1-shaft hole, 1-1-2-locking surface, 1-1-3-limiting surface, 1-2-tail wing seat, 1-2-1-process hole, 1-2-2-pin hole, 1-2-3-locking hole, 1-2-4-screw hole, 1-2-5-groove, 1-3-pin shaft, 1-4-locking screw, 1-5-spring, 1-6-locking pin, 2-compression spring, 3-compression spring seat, 4-tail wing housing, 4-1-unlocking process hole, 4-2-tail wing groove, 4-3-mounting hole. Detailed Implementation

[0046] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0047] This embodiment provides a tail fin deployment and locking device; see attached document. Figure 1 It includes a tail fin housing 4, three or more tail fin assemblies 1 installed inside the tail fin housing 4, and a deployment drive device; the number of tail fin assemblies 1 is preferably four sets.

[0048] The peripheral components are: the launch tube;

[0049] The tail fin casing 4 is fixed to the tail of the projectile and is integrally mounted inside the launch tube along with the projectile.

[0050] The tail fin housing 4 is a cylindrical housing with openings at both ends. The side wall of the tail fin housing 4 is machined with tail fin grooves 4-2 in the same number as the tail fin assembly 1 along the axial direction.

[0051] See appendix Figure 1 and 2Three or more tail fin assemblies 1 are evenly fixed inside the tail fin housing 4 along the circumference; and each tail fin assembly 1 has a tail fin that is one-to-one opposite to three or more tail fin slots 4-2. In the initial state, the tail fins are retracted into the tail fin housing 4 under the action of the side wall of the launch tube.

[0052] The opening drive device is installed inside the tail fin housing 4 and is used to drive the tail fin 1-1 in three or more tail fin assemblies 1 to pass through the tail fin slot 4-2 and open radially to the limit position.

[0053] Each tail fin assembly 1, in addition to the tail fin 1-1, also includes a tail fin seat 1-2, a pin 1-3, a spring 1-5, and a locking pin 1-6. The tail fin seat 1-2 is fixed on the tail fin housing 4, and the tail fin 1-1 is pinned to the tail fin seat 1-2 via the pin 1-3. The spring 1-5 and the locking pin 1-6 are both mounted on the tail fin seat 1-2. The spring 1-5 and the locking pin 1-6 cooperate to limit the retraction direction of the tail fin 1-1 after it has rotated around the axis of the pin 1-3 to its limit position under the action of the opening drive device after the projectile leaves the launch tube.

[0054] For further details, please see the appendix. Figure 2 and 3 The tail fin seat 1-2 is a hexahedron. One side of the tail fin seat 1-2 is an arc surface that can mate with the inner circumferential surface of the tail fin shell 4. A radially arranged screw hole 1-2-4 is machined on the arc surface. Let the side containing the arc surface on the tail fin seat 1-2 be the outer side, and the side opposite the arc surface be the inner side. The two ends along the axial direction are end a and end b, respectively. The other two sides are the first side and the second side. A stepped through hole and a pin hole 1-2-2 are machined on the tail fin seat 1-2 along the direction from the first side to the second side. The stepped through hole is relatively... The pin hole 1-2-2 is closer to end b, and the radial screw hole 1-2-4 is located between the stepped through hole and the pin hole 1-2-2. The stepped through hole consists of a large-diameter section, a medium-diameter section, and a small-diameter section along the direction from the first side to the second side. The large-diameter section is threaded. A groove 1-2-5 is also machined on the middle part of the end face of end b on the tail fin seat 1-2. The groove 1-2-5 divides the stepped through hole into two parts: one part is the small-diameter section, which serves as the process hole 1-2-1; the other part consists of the medium-diameter section and the large-diameter section, which serve as the locking hole 1-2-3.

[0055] See appendix Figure 4 A semi-circular boss extends from one end of the tail fin 1-1, and concentric shaft holes 1-1-1 are provided on the semi-circular boss; one side of the semi-circular boss ( Figure 4 The transition surface between the right side of the semi-circular boss and the end face of the tail fin 1-1 is the locking surface 1-1-2; the other side of the semi-circular boss ( Figure 4 A stepped surface (1-1-3) is provided on the left side of the semi-circular boss as a limiting surface;

[0056] The diameter of locking pin 1-6 is smaller than the inner diameter of the middle diameter section of locking hole 1-2-3, but larger than the inner diameter of process hole 1-2-1;

[0057] The connection relationships of the components of tail fin assembly 1 are as follows:

[0058] The semi-circular boss of the tail fin 1-1 is fitted into the groove 1-2-5. The pin 1-3 passes through the pin hole 1-2-2 on the tail fin seat 1-2 and the shaft hole 1-1-1 on the tail fin 1-1, thereby connecting the tail fin 1-1 and the tail fin seat 1-2.

[0059] See appendix Figure 5-7 When the tail fin 1-1 is not fully deployed, the locking pin 1-6 is installed in the middle diameter section of the locking hole 1-2-3, the locking screw 1-4 is threadedly connected to the large diameter section of the locking hole 1-2-3, and the spring 1-5 is installed between the locking pin 1-6 and the locking screw 1-4. One end of the spring 1-5 abuts against the locking screw 1-4, and the other end abuts against one end of the locking pin 1-6. The spring 1-5 is in a compressed state, and the other end of the locking pin 1-6 abuts against the side of the tail fin 1-1 under the action of the spring 1-5.

[0060] See appendix Figure 8-10 After the tail wing 1-1 is deployed, the limiting surface 1-1-3 of the tail wing 1-1 reaches its limit position when it contacts the tail wing housing 4. The tail wing housing 4 limits the deployment of the tail wing. The constraint of the tail wing 1-1 on the locking pin 1-6 is released. Under the action of the spring 1-5, the locking pin 1-6 enters the groove 1-2-5 and abuts against the end face of the process hole 1-2-1. The side of the locking pin 1-6 limits the locking surface 1-1-2 of the tail wing 1-1, thereby limiting the retraction of the tail wing 1-1 and locking the deployed tail wing 1-1.

[0061] Furthermore, the deployment drive device includes a compression spring 2 and a compression spring seat 3. The compression spring seat 3 is installed at the end of the tail fin seat 1-2 inside the tail fin housing 4. The compression spring 2 is installed inside the tail fin housing 4, and one end of the compression spring 2 is fixedly connected to the compression spring seat 3. When the tail fin housing 4 is located inside the launch tube, the other end of the compression spring 2 abuts against the end face of three or more tail fins 1-1, and the compression spring 2 is in a compressed state. When the projectile is launched and leaves the launch tube, the tail fins 1-1 are deployed to their limit position under the action of the spring force of the compression spring 2.

[0062] Furthermore, the outer circumferential surface of the compression spring seat 3 is provided with threads, and one end is provided with a stepped surface; the compression spring seat 3 is threadedly installed with the tail wing housing 4, and one end of the compression spring 2 is bonded to the stepped surface of the compression spring seat 3 by adhesive.

[0063] For further details, please see the appendix. Figure 11The outer surface of the tail fin housing 4 is provided with mounting holes 4-3 along the circumference, which are used to connect with the radial threaded holes 1-2-4 of the tail fin assembly 1 one by one by screws.

[0064] An unlocking process hole 4-1 is also provided along the circumference on the outer surface of the tail fin housing 4. The unlocking process hole 4-1 is opposite to the process hole 1-2-1 on the tail fin seat 1-2.

[0065] Working principle:

[0066] When the projectile is not fired, the launch tube limits the opening of the tail fin 1-1; the locking pin 1-6 abuts against the tail fin 1-1 under the action of the spring 1-5;

[0067] The tail fin deployment and locking device is fixed to the tail of the projectile. After the projectile is launched and leaves the launch tube, the launch tube releases the limit on the deployment of the tail fin 1-1. The tail fin 1-1 is deployed to its limit position, and the locking pin 1-6 extends under the action of the spring 1-5 to limit and lock the retraction of the tail fin 1-1, so that the tail fin 1-1 can remain in the deployed state, preventing the tail fin 1-1 from swinging back and forth due to external factors and ensuring the stability of the projectile's flight.

[0068] Installation steps:

[0069] Step S1: Assemble tail wing assembly 1: Insert tail wing 1-1 into the groove 1-2-5 of tail wing seat 1-2. The shaft hole 1-1-1 on tail wing 1-1 and the pin hole 1-2-2 on tail wing seat 1-2 are coaxially set. Insert pin 1-3 to pin tail wing 1-1 and tail wing seat 1-2.

[0070] Then, retract the tail fin 1-1 to keep it in an unopened state. Insert the locking pin 1-6 and spring 1-5 sequentially from the end of the large diameter section of the locking hole 1-2-3. Then install the locking screw 1-4 to fix the spring 1-5 and locking pin 1-6 in the locking hole 1-2-3.

[0071] Step S2: Fix the compression spring 2 onto the compression spring seat 3, and fix the compression spring seat 3 to the end of the tail fin housing 4 by means of threaded connection;

[0072] Step S3: Assemble the tail wing assembly 1 and tail wing housing 4: Each tail wing assembly 1 is in the open and locked state. When each tail wing assembly 1 is installed into the tail wing housing 4, first make the tail wing 1-1 protrude from the tail wing groove 4-2 on the tail wing housing 4, then align the screw hole 1-2-4 on the tail wing seat 1-2 with the mounting hole 4-3 on the tail wing housing 4, and fix the connection with screws.

[0073] Then, use a special tool to compress the compression spring 2, and at the same time use a special unlocking tool to press the locking pin 1-6 through the unlocking process hole 4-1 on the tail wing housing 4 and the process hole 1-2-1 on the tail wing seat 1-2. At this time, the spring 1-5 is compressed, the locking pin 1-6 retracts into the locking hole 1-2-3, the tail wing assembly 1 is unlocked, the tail wing 1-1 is folded back into the tail wing housing 4 and abuts against the compression spring 2. After all tail wing assemblies 1 are unlocked, remove the special tool and tie the tail wing housing 4 with a rope.

[0074] Step S5: Load the tail fin housing 4 into the launch tube. During loading, after a portion of the tail fin housing 4 has entered the launch tube, remove the rope and then load the projectile.

[0075] In summary, the above are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A tail fin deployment and locking device, characterized in that, include: Tail fin housing, three or more tail fin assemblies installed inside the tail fin housing, and deployment drive mechanism; The peripheral components are: the launch tube; The tail fin housing is fixed to the tail of the projectile and is integrally installed inside the launch tube along with the projectile. The side wall of the tail fin housing is machined with tail fin grooves in the same number as the tail fin assembly along the axial direction. Three or more tail fin assemblies are evenly fixed inside the tail fin housing along the circumference, and the tail fin of each tail fin assembly is opposite to three or more tail fin slots. In the initial state, the tail fins are retracted into the tail fin housing under the action of the side wall of the launch tube. The opening drive device is installed inside the tail fin housing and is used to drive the tail fins in three or more tail fin assemblies to pass through the tail fin slot and open radially to the limit position. Each tail fin assembly includes, in addition to the tail fin, a tail fin mount, a pin, a spring, and a locking pin. The tail fin mount is fixed to the tail fin housing, and the tail fin is pinned to the tail fin mount via the pin. The spring and locking pin are both mounted on the tail fin mount. The spring and locking pin work together to limit the retraction direction of the tail fin after it has rotated around the pin axis to its limit position under the action of the deployment drive device after the projectile leaves the launch tube. The deployment drive device includes a compression spring and a compression spring seat. The compression spring seat is installed at the end of the tail fin housing where the tail fin is located. The compression spring is installed inside the tail fin housing. One end of the compression spring is fixedly connected to the compression spring seat. When the tail fin housing is located inside the launch tube, the other end of the compression spring abuts against the end faces of three or more tail fins, and the compression spring is in a compressed state. When the projectile is launched and leaves the launch tube, the tail fins are deployed to their limit position under the action of the compression spring force.

2. The tail fin deployment and locking device as described in claim 1, characterized in that, One side of the tail fin mount is an arc surface that can mate with the inner circumferential surface of the tail fin shell. Let the side on the tail fin mount where the arc surface is located be the outer side, and the side opposite the arc surface be the inner side. The two ends along the axial direction are end a and end b, respectively. The other two sides are the first side and the second side. The tail fin mount has pin holes machined along the direction from the first side to the second side, and a groove is also machined on the middle part of the b end face of the tail fin mount. A semi-circular boss is provided at one end of the tail fin, and concentric shaft holes are provided on the semi-circular boss. The semi-circular boss of the tail fin is fitted into the groove, and the pin passes through the pin hole on the tail fin seat and the shaft hole on the tail fin to connect the tail fin and the tail fin seat.

3. The tail fin deployment and locking device as described in claim 2, characterized in that, The tail fin mount has a stepped through hole machined along the direction from the first side to the second side. The stepped through hole is closer to end b than the pin hole. The stepped through hole has a large diameter section, a medium diameter section and a small diameter section along the direction from the first side to the second side. The large diameter section is threaded. The groove divides the stepped through hole into two parts: one part is the small diameter section, and the other part is the medium diameter section and the large diameter section. The medium diameter section and the large diameter section together serve as a locking hole. The diameter of the locking pin is smaller than the inner diameter of the middle diameter section of the locking hole, but larger than the inner diameter of the small diameter section. One side of the semi-circular boss is provided with a stepped surface as a limiting surface; when the tail fin is deployed, the limiting surface of the tail fin reaches the limit position when it contacts the tail fin shell; the transition connection surface between the other side of the semi-circular boss and the end face of the tail fin is a locking surface. When the tail fin is not deployed to its limit, the locking pin is installed in the middle diameter section of the locking hole, the locking screw is threaded to the large diameter section of the locking hole, and the spring is installed between the locking pin and the locking screw. One end of the spring abuts against the locking screw, and the other end abuts against one end of the locking pin. The spring is in a compressed state, and the other end of the locking pin abuts against the side of the tail fin under the action of the spring. After the tail wing is deployed to its limit position, the tail wing releases its constraint on the locking pin. Under the action of the spring, the locking pin enters the groove and abuts against the end face of the process hole. The side of the locking pin limits the locking surface of the tail wing, thereby limiting the tail wing to retract and locking the deployed tail wing.

4. The tail fin deployment and locking device as described in claim 3, characterized in that, The tail fin seat is a hexahedron, and one side of the tail fin seat is an arc surface that can mate with the inner circumferential surface of the tail fin shell. A radially threaded hole is machined on the arc surface; the radially threaded hole is located between the stepped through hole and the pin hole. The outer surface of the tail fin housing has mounting holes along the circumference, which are used to connect the tail fin assembly to the radial screw holes one by one by screws.

5. The tail fin deployment and locking device as described in claim 3, characterized in that, The small-diameter hole section is used as a process hole; Unlocking process holes are provided along the circumference on the outer surface of the tail fin housing, and the unlocking process holes are aligned with the process holes on the tail fin mount.

6. The tail fin deployment and locking device as described in claim 1, characterized in that, One end of the compression spring seat has a stepped surface, and one end of the compression spring is bonded to the stepped surface of the compression spring seat with an adhesive.

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