Initial locking mechanism of missile folding rudder and missile folding rudder

Abstract

The invention relates to an initial locking mechanism of a missile folding rudder and the missile folding rudder, and the initial locking mechanism comprises an initial locking pin which is suitable for moving along the Z-axis direction, one end of the initial locking pin is provided with a pin head, and the other end of the initial locking pin is provided with a pin tail; the lock pin spring is arranged on the initial lock pin in a sleeving manner; the sliding lock bolt is suitable for moving in the Y-axis direction and comprises a bolt body and an abutting head, an abutting face is arranged on one side of the abutting head, a lock lug is arranged on the other side of the abutting head, the abutting face abuts against the inclined face of the pin tail, and the sliding lock bolt is suitable for rotating along the axis of the sliding lock bolt or translating in the X-axis direction, so that the lock lug is deviated from or aligned to a check block on the missile; the sliding lock bolt is installed on the limiting guide seat, and a lock bolt limiting structure is arranged on the limiting guide seat and used for guiding the moving path of the sliding lock bolt. The initial locking mechanism is simple in structure, and the folding rudder can be directly installed and locked on the missile through cooperation of the initial locking pin, the sliding lock bolt and the limiting guide seat.

Description

Technical Field

[0001] This invention relates to the field of missile structural design technology, and in particular to an initial locking mechanism for a missile folding rudder and a missile folding rudder. Background Technology

[0002] With the development of missile technology, in order to improve the combat effectiveness and maneuverability of the carrier platform and reduce the size of the missile to adapt to the space constraints of the carrier platform and launch device, the adoption of a folding rudder design has become an inevitable choice. The folding rudder must meet the functions of folding and storing inside the launch box and quickly unfolding and locking after takeoff, while also adapting to the efficient operation requirements of multiple tests, maintenance, and actual combat scenarios.

[0003] Folding rudder structure, such as Figure 1 As shown, during the installation of the folding rudder, the stop block 7 (a fixed limiting structure used to limit excessive deployment of the rudder surface and ensure the stability of the rudder surface's working position) on the missile body interferes with the movement path of the initial locking mechanism, causing the initial locking mechanism to fail to enter the locking state normally after the rudder surface is installed in the deployed state. To solve this problem, the existing installation process requires a cumbersome step-by-step operation: first, fix the lower rudder surface 9, manually fold the upper rudder surface 8 to a specific angle, then temporarily fix the folded upper rudder surface 8 with special tooling, and finally install the upper rudder surface 8 as a whole into the preset position on the missile body. This not only increases the installation steps and tooling dependence but also significantly reduces assembly efficiency. In addition, during missile body testing, if the upper rudder surface 8 already installed on the missile body is accidentally deployed due to test requirements (such as rudder surface deployment function testing), the upper rudder surface 8 must be completely removed from the missile body before the folding operation can be performed again. This process further prolongs the test cycle and seriously affects test efficiency.

[0004] In summary, existing technologies have technical pain points in the design of folding rudders: the interference problem with the inherent blocks of the missile body has not been effectively solved, which makes it difficult to complete the folding or locking operation directly on the missile when restoring the folded state on the missile. It often requires disassembly and special tooling to complete the operation outside the missile, which is cumbersome and inefficient in scenarios such as multiple tests, and cannot meet the needs of efficient combat and testing. Summary of the Invention

[0005] In view of the shortcomings of the existing technology, the present invention aims to solve the problem that the folding rudder cannot be directly installed, folded and restored on the missile due to interference from the missile body block, and requires special tooling, which is cumbersome and inefficient.

[0006] To solve the above-mentioned technical problems, the present invention provides an initial locking mechanism for a missile folding rudder, comprising: An initial locking pin is adapted to move along the Z-axis direction. One end of the initial locking pin is provided with a pin head, and the other end is provided with a pin tail. The end face of the pin tail is a plane inclined relative to the Z-axis direction. A locking spring is sleeved on the initial locking pin; A sliding bolt, adapted to move along the Y-axis, includes a bolt body and an abutment. One side of the abutment has an abutment surface, and the other side has a locking lug. The abutment surface abuts against the inclined surface of the pin tail. The sliding bolt is adapted to rotate along its own axis or translate along the X-axis, so that the locking lug is offset from or aligned with the stop on the missile. A limiting guide seat is provided, and the sliding bolt is installed on the limiting guide seat. The limiting guide seat is provided with a bolt limiting structure to guide the movement path of the sliding bolt. The initial locking mechanism includes a locked state and an unlocked state. In the locked state, the pin head is inserted into the locking hole of the upper rudder surface, and the lock lug abuts against the stop block to lock the initial locking pin and the sliding bolt. In the unlocked state, the lock lug is separated from the stop block, and the initial locking pin and the sliding bolt are movable.

[0007] The initial locking mechanism of this invention has a simple structure. Through the cooperation of the initial locking pin, the sliding bolt and the limiting guide seat, it can be directly installed and locked on the folding rudder missile, eliminating the need for additional tooling. The sliding bolt avoids the original block of the missile body by rotating / translating, without the need to modify the missile body. Moreover, the components are simplified and adapted to the internal space of the rudder, reducing structural complexity and manufacturing costs.

[0008] As a preferred or optional solution, the bolt limiting structure is a bolt limiting groove provided on the surface of the limiting guide seat. The bolt body is plate-shaped and enters the bolt limiting groove. In the X-axis direction, the size of the bolt limiting groove is larger than the size of the bolt body, making the sliding bolt suitable for translation along the X-axis direction. The plate-shaped bolt body combined with the large-sized bolt limiting groove provides X-axis translation space for the sliding bolt to avoid the projectile block, and also guides it to move precisely along the Y-axis, avoiding deviation and ensuring smooth engagement with the initial locking pin.

[0009] As a preferred or optional solution, the initial locking mechanism includes at least one bolt positioning screw, which abuts against the side of the bolt body to define the position of the sliding bolt in the X-axis direction. The bolt positioning screw can fix the X-axis position of the sliding bolt in the locked state, prevent vibration-induced displacement, and also assist in quick position calibration during installation.

[0010] As a preferred or optional embodiment, the portion where the bolt body connects to the abutment is provided with a clearance groove. This clearance groove allows the stop block to pass through, and in the Y-axis direction, the opening size of the clearance groove is larger than the size of the stop block. The larger opening of the clearance groove allows the stop block to pass through, avoids interference between the sliding bolt and the stop block in the Y-axis direction, and ensures that the sliding bolt moves smoothly to the locking position.

[0011] As a preferred or optional solution, the abutment surface is an inclined plane that fits against the end face of the pin. The abutment surface fitting against the end face of the pin increases the force transmission area, making force transmission more uniform, and simultaneously helps to limit the initial offset of the locking pin, ensuring its precise movement along the Z-axis.

[0012] As a preferred or optional solution, the bolt limiting structure is a bolt limiting hole provided on the limiting guide seat. The bolt limiting hole extends along the Y-axis, and a spiral groove is provided on the hole wall. The bolt body is cylindrical, and a spiral rib is provided on the surface of the bolt body. The bolt body is inserted into the bolt limiting hole, and the spiral rib engages with the spiral groove, so that the sliding bolt rotates synchronously along its own axis when moving along the Y-axis. The bolt limiting hole extending along the Y-axis guides the sliding bolt to move precisely along the Y-axis, and the engagement of the spiral rib with the spiral groove allows the sliding bolt to rotate synchronously along its own axis when moving along the Y-axis, eliminating the need for an independent drive mechanism and enabling quick alignment or avoidance of stops.

[0013] As a preferred or optional embodiment, the limiting guide seat has a notch on the side near the abutment. When the abutment moves towards the limiting guide seat, it enters the notch. The notch of the limiting guide seat can accommodate the abutment, preventing the guide seat from interfering with the movement of the sliding bolt.

[0014] As a preferred or optional solution, the abutment surface is an inclined curved surface that fits against the end face of the pin. The inclined curved abutment surface that fits against the pin end adapts to the angle changes during the rotation of the sliding bolt, maintaining continuous force transmission and preventing jamming.

[0015] As a preferred or optional embodiment, the initial locking pin includes a limiting boss located between the pin head and the pin tail. One end of the locking pin spring is fixed, and the other end abuts against the limiting boss. The limiting boss positions the locking pin spring, stabilizing the initial locking pin and preventing it from vibrating. The locking pin spring also applies a force in the Z-axis direction to the initial locking pin, causing it to automatically enter the locking state.

[0016] As a preferred or optional solution, one side of the limiting boss is provided with a locking pin guide groove extending along the Z-axis, and a guide pin is provided in the locking pin guide groove. The locking pin guide groove and the guide pin cooperate to ensure that the initial locking pin moves linearly along the Z-axis, avoiding misalignment between the pin head and the locking hole.

[0017] As a preferred or optional solution, the initial locking mechanism further includes a bolt spring, one end of which is fixed and the other end abuts against the bolt body. The bolt spring applies a Y-axis preload to the sliding bolt, causing it to automatically enter the locked state and also suppressing vibrations in the unlocked state.

[0018] This invention also provides a missile folding rudder, including an upper rudder surface, a lower rudder surface, and the aforementioned initial locking mechanism, wherein the initial locking mechanism is mounted on the lower rudder surface. Through the aforementioned initial locking mechanism, this invention enables direct folding and locking of the missile folding rudder, eliminating the need for disassembly and refolding or additional tooling, shortening the installation and testing cycle, improving efficiency, and reducing costs.

[0019] In summary, compared with the prior art, the present invention has the following beneficial effects: (1) The present invention designs an initial locking pin to initially lock the upper rudder surface, and designs a locking pin spring, sliding bolt, limit guide seat and other structures to realize the direct installation of the folding rudder surface on the projectile body without the need for additional lower rudder fixing tooling, which greatly simplifies the installation process and improves the installation efficiency.

[0020] (2) The initial locking mechanism of the present invention is ingeniously designed. By cooperating with the sliding bolt and the stop, the interference of the projectile stop on the unfolding process of the folding control surface is effectively avoided, thereby improving the unfolding reliability and stability of the folding control surface.

[0021] (3) The initial locking mechanism of the present invention allows the folding rudder surface to be folded immediately after installation without disassembly, which greatly improves the test efficiency and saves the test time.

[0022] (4) The initial locking mechanism of the present invention is reasonably designed, makes use of the space inside the rudder, has fewer parts, and has a simple manufacturing process, which reduces production costs while ensuring the reliability and durability of the product. Attached Figure Description

[0023] Figure 1 This is a structural diagram of the missile's folding rudder in an embodiment of the present invention.

[0024] Figure 2 This is a schematic diagram of the installation position of the missile folding rudder in an embodiment of the present invention.

[0025] Figure 3 This is an assembly diagram of the initial locking mechanism in an embodiment of the present invention.

[0026] Figure 4 This is a structural diagram of the initial locking pin and the locking pin spring in an embodiment of the present invention.

[0027] Figure 5 This is a structural diagram of the sliding bolt and the limiting guide seat in an embodiment of the present invention.

[0028] Figure 6 This is a state diagram of the initial unlocked state of the locking mechanism in an embodiment of the present invention.

[0029] Figure 7 This is a state diagram of the initial locking state of the locking mechanism in an embodiment of the present invention.

[0030] Figure 8 This is an assembly diagram of the initial locking mechanism in another embodiment of the present invention.

[0031] Figure 9 This is an exploded view of the sliding bolt and the limiting guide seat in another embodiment of the present invention.

[0032] Figure 10 This is a state diagram of the initial unlocked state of the locking mechanism in an embodiment of the present invention.

[0033] Figure 11 This is a state diagram of the initial locking state of the locking mechanism in another embodiment of the present invention.

[0034] Explanation of reference numerals in the attached figures: 1-Initial locking pin, 11-Pin head, 12-Pin tail, 13-Limiting boss, 14-Locking pin guide groove, 15-Guide pin, 2-Locking pin spring, 3-Sliding bolt, 31-Bolt body, 32-Abutting joint, 33-Abutting surface, 34-Locking lug, 35-Leaning groove, 4-Limiting guide seat, 41-Locking bolt limiting groove, 42-Locking bolt limiting hole, 43-Notch, 5-Locking bolt positioning screw, 6-Locking bolt spring, 7-Stop block, 8-Upper rudder surface, 9-Lower rudder surface. Detailed Implementation

[0035] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0036] It should be noted that similar symbols and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0037] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "setting," "connection," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0038] Combination Figures 1 to 11 As shown in the figure, the specific embodiment of the present invention provides an initial locking mechanism for a missile folding rudder and a missile folding rudder including the mechanism. It aims to solve the technical problems of traditional folding rudders being unable to be directly installed, folded and restored on the missile due to interference from the missile body block, and requiring special tooling and cumbersome operation. The following describes in detail the structural design, assembly logic and state transition of the technical solution of the present invention with reference to the structural details and component matching relationships of each figure, so as to ensure that those skilled in the art can fully understand and reproduce the core structure and working process of the initial locking mechanism based on this embodiment.

[0039] like Figure 1 and Figure 2 As shown, the missile folding rudder assembly includes an upper rudder surface 8, a lower rudder surface 9, and an initial locking mechanism. The upper rudder surface 8 is rotatably connected to the lower rudder surface 9 via a folding hinge, enabling folding and unfolding actions. The lower rudder surface 9 is fixed to the missile body. The initial locking mechanism is embedded in the internal mounting cavity of the lower rudder surface 9, and its position corresponds to the locking hole of the folding hinge of the upper rudder surface 8, ensuring that the upper rudder surface 8 can be locked through the initial locking mechanism after folding.

[0040] The initial locking mechanism is the core component for the mounting and folding of the folding rudder missile, such as... Figures 2 to 7 As shown, the initial locking mechanism mainly consists of an initial locking pin 1, a locking pin spring 2, a sliding bolt 3, and a limit guide seat 4. A bolt positioning screw 5 and a bolt spring 6 can also be added as needed. These components form a system capable of switching between locked and unlocked states through a specific assembly structure: the initial locking pin 1 is movable along the Z-axis, with a pin head 11 at one end and a pin tail 12 at the other. The pin head 11 is used to insert into the locking hole of the upper rudder surface 8, achieving folding and locking of the upper rudder surface 8. The end face of the pin tail 12 is a plane inclined relative to the Z-axis; the locking pin spring 2 is sleeved on the initial locking pin 1, providing the locking force required for the initial locking pin 1; the sliding bolt 3... The sliding bolt 32 is movable along the Y-axis and includes a bolt body 31 and an abutment 32. The abutment 32 has an abutment surface 33 on one side and a locking lug 34 on the other side. The abutment surface 33 abuts against the inclined surface of the pin tail 12. When the initial locking pin 1 moves in the opposite direction along the Z-axis, it applies a force to the sliding bolt 3, pushing the sliding bolt 3 to move in the opposite direction along the Y-axis. The locking lug 34 is used to cooperate with the stop block 7 on the missile to achieve locking. The limiting guide seat 4 is provided with a bolt limiting structure. The sliding bolt 3 is installed on the limiting guide seat 4. The bolt limiting structure is used to guide the movement path of the sliding bolt 3, so that the sliding bolt 3 can move in the Y-axis direction and also translate in the X-axis direction.

[0041] The structural details of the initial locking pin 1 are as follows: Figure 4As shown, a limiting boss 13 is provided in the middle. The limiting boss 13 is located between the pin head 11 and the pin tail 12. One end of the locking pin spring 2 abuts against the limiting boss 13, and the other end is fixed in the mounting cavity of the lower rudder surface 9. The limiting boss 13 can position the locking pin spring 2 to prevent the locking pin spring 2 from shifting, and at the same time help stabilize the initial locking pin 1 to avoid unnecessary vibration.

[0042] A locking pin guide groove 14 extending along the Z-axis is also provided on one side of the limiting boss 13. A guide pin 15 is provided in the locking pin guide groove 14 and is fixedly mounted on the lower rudder surface 9. The guide pin 15 cooperates with the locking pin guide groove 14 to restrict the movement direction of the initial locking pin 1, ensuring that the initial locking pin 1 always moves in a straight line along the Z-axis without deviation or rotation, avoiding misalignment between the pin head 11 and the locking hole of the upper rudder surface 8, and ensuring the accuracy of locking and unlocking actions.

[0043] Combination Figure 5 As shown, in this embodiment, the limiting guide seat 4 is flat, and its surface is provided with a bolt limiting groove 41 as a bolt limiting structure; the bolt body 31 of the sliding bolt 3 is plate-shaped, and the plate-shaped bolt body 31 enters the bolt limiting groove 41. The dimension of the bolt limiting groove 41 in the X-axis direction is larger than the dimension of the bolt body 31, providing space for the sliding bolt 3 to translate along the X-axis direction, so that the sliding bolt 3 can achieve the deviation or alignment of the locking lug 34 and the stop block 7 through X-axis translation, avoiding interference from the bullet stop block 7.

[0044] In this embodiment, the abutment surface 33 of the abutment joint 32 of the sliding bolt 3 is an inclined plane, which matches the end face of the pin tail 12. The two can fit tightly together to ensure uniform force transmission, while also helping to limit the offset of the initial locking pin 1, further ensuring that the initial locking pin 1 moves accurately along the Z-axis. Furthermore, a clearance groove 35 is also provided at the connection between the bolt body 31 and the abutment joint 32. The clearance groove 35 is used for the stop block 7 to pass through. Its opening size in the Y-axis direction is larger than the size of the stop block 7, ensuring that when the sliding bolt 3 moves along the Y-axis direction, the stop block 7 can smoothly pass through the clearance groove 35, avoiding interference between the sliding bolt 3 and the stop block 7 in the Y-axis direction, and ensuring that the sliding bolt 3 can move smoothly to the locking position.

[0045] Combination Figure 7 As shown, to fix the position of the sliding bolt 3 in the X-axis direction, this embodiment uses two bolt positioning screws 5. The bolt positioning screws 5 pass through the screw holes of the lower rudder surface 9, with one end abutting against the side of the bolt body 31, thereby restricting the position of the sliding bolt 3 in the X-axis direction and preventing it from shifting due to vibration. During installation and debugging, the position of the sliding bolt 3 can be adjusted by loosening the screws, simplifying the calibration operation. In other embodiments, the number of bolt positioning screws 5 can be one or more, adjusted according to the actual situation.

[0046] In this embodiment, the initial locking mechanism also includes a bolt spring 6, one end of which is fixed to the lower rudder surface 9 or spring seat (not shown in the figure), and the other end abuts against the bolt body 31 of the sliding bolt 3. It can apply a pre-pressure along the Y-axis to the sliding bolt 3 so that it automatically reaches the locking position. In the unlocked state, it can also suppress the vibration of the sliding bolt 3.

[0047] The initial locking mechanism provided in the above embodiments has an unlocked state and a locked state, and the component cooperation relationships in the two states are as follows: Figure 6 and Figure 7 As shown, the specific switching method is as follows: When the control surface is installed, it is generally in the deployed state, and the initial locking mechanism is in the unlocked state at this time, as shown. Figure 6 As shown, the locking lug 34 of the sliding bolt 3 is offset from the stop block 7 in the X-axis direction, and the sliding bolt 3 can move freely in the Y-axis direction. The locking pin spring 2 and the bolt spring 6 are in a pre-compressed state, and the upper rudder surface 8 can rotate around the folding hinge. When the upper rudder surface 8 rotates to the preset folding angle, the initial locking pin 1 moves along the positive Z-axis under the action of the locking pin spring 2, and the pin head 11 is inserted into the locking hole of the upper rudder surface 8. The sliding bolt 3 is subjected to the force of the bolt spring 6 and moves along the positive Y-axis to the locking position under the guidance of the limit guide seat 4. At this time, the bolt positioning screw 5 pushes the sliding bolt 3 to translate along the X-axis direction, so that the locking lug 34 is aligned with the stop block 7, and the position of the sliding bolt 3 can be locked by the stop block 7. The sliding bolt 3 supports the pin tail 12 through the abutment surface 33, restricting the movement of the initial locking pin 1, and finally achieving the locking of the initial locking pin 1 and the sliding bolt 3, as shown in the figure. Figure 7 As shown, ensure that the upper control surface 8 remains stably folded. When unlocking is required, the servo motor drives the rudder shaft to rotate a small angle, causing the stop 7 and the sliding bolt 3 to move relative to each other in the X-axis direction, thus releasing the restriction. The initial locking pin 1 can move in the opposite direction along the Z-axis under the pressure of the upper control surface 8. Once the pin head 11 is completely disengaged from the locking hole of the upper control surface 8, the unlocking is complete.

[0048] Combination Figures 8 to 11 As shown, the present invention provides another embodiment of the initial locking mechanism, wherein the sliding bolt 3 can move along the Y-axis and rotate along its own axis. The rotation of the sliding bolt 3 is used to avoid the stop block 7, thereby further reducing the number of parts in the initial locking mechanism.

[0049] For details on the structure of the initial locking mechanism, please refer to [link / reference needed]. Figure 8 and Figure 9As shown, the limiting guide seat 4 is block-shaped, and the bolt limiting structure is a bolt limiting hole 42 extending along the Y-axis. The bolt body 31 of the sliding bolt 3 is cylindrical and is inserted into the bolt limiting hole 42, thereby guiding the sliding bolt 3 to move along the Y-axis. Furthermore, the bolt limiting hole 42 has a spiral groove (not shown in the figure) on its wall, and a spiral rib (not shown in the figure) on the surface of the cylindrical bolt body 31. The spiral rib engages with the spiral groove. This engagement allows the sliding bolt 3 to rotate synchronously along its own axis when moving along the Y-axis, achieving a combined movement and rotation action without an additional drive mechanism, quickly switching between unlocked and locked states. The bolt spring 6 is installed in the bolt limiting hole 42, with one end fixed to the hole and the other end abutting against the bolt body 31, providing force for the sliding bolt 3 to move to the locked state.

[0050] The contact surface 33 of the contact joint 32 is an inclined curved surface, which can adapt to the angle change when the sliding bolt 3 rotates, and always maintains a close fit with the end face of the pin tail 12, avoiding interruption of force transmission or jamming of action due to angle deviation, and ensuring the continuity of force transmission and smoothness of action.

[0051] Furthermore, the limiting guide seat 4 has a notch 43 on the side near the abutment 32. When the abutment 32 of the sliding bolt 3 moves towards the limiting guide seat 4, the abutment 32 can enter the notch 43, preventing interference between the abutment 32 and the limiting guide seat 4, and ensuring that the sliding bolt 3 can move to... Figure 10 The unlock location is shown.

[0052] In this embodiment, the unlocked and locked states of the initial locking mechanism are as follows: Figure 10 and Figure 11 As shown, the specific switching method is as follows: When the control surface installation is complete, the initial locking mechanism is as follows: Figure 10 In the unlocked state shown, the locking lug 34 of the sliding bolt 3 is offset from the stop block 7 by a certain angle. The sliding bolt 3 can move freely in the Y-axis direction. The locking pin spring 2 and the locking bolt spring 6 are in a pre-compressed state, and the upper rudder surface 8 can rotate around the folding hinge. When the upper rudder surface 8 rotates to the preset folding angle, the initial locking pin 1 moves along the positive Z-axis under the action of the locking pin spring 2, and the pin head 11 is inserted into the locking hole of the upper rudder surface 8. The sliding bolt 3 moves along the positive Y-axis under the force of the locking bolt spring 6, and rotates along its own axis. When it moves to the locked position, the locking lug 34 is aligned with the stop block 7, forming a lock as shown in the figure. Figure 11 The locked state shown ensures that the upper control surface 8 remains stably folded. To unlock, the servo motor powers the rudder shaft to rotate a small angle, causing the stop 7 to deviate from the sliding bolt 3, thus releasing the restriction.

[0053] The initial locking mechanism provided in the above embodiments is ingeniously designed. Through the coordinated cooperation of the initial locking pin, the sliding bolt, and the limiting guide seat, the folding rudder can be directly installed and locked on the missile body without relying on additional folding and fixing fixtures. Moreover, if the installed rudder surface is accidentally unfolded due to testing or other reasons, it can be directly refolded on the missile without disassembly, greatly simplifying the installation process and improving testing and combat efficiency. The initial locking mechanism, with the motion design of the sliding bolt 3 rotating along the axis or translating along the X-axis, can actively avoid the stop block 7 on the missile without redesigning or modifying the structure of the stop block 7, thus avoiding the cost and technical risks of missile body modification. At the same time, the initial locking mechanism simplifies the number of parts, can fully adapt to the internal space layout of the rudder, reduce the overall structural complexity and manufacturing cost, and balance the reliability and economy of locking.

[0054] While the present invention has been disclosed above, its scope of protection is not limited thereto. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of this disclosure, and all such changes and modifications will fall within the scope of protection of this invention.

Claims

1. An initial locking mechanism for a missile folding fin, characterized in that, include: An initial locking pin (1) is adapted to move along the Z-axis direction. One end of the initial locking pin (1) is provided with a pin head (11) and the other end is provided with a pin tail (12). The end face of the pin tail (12) is a plane that is inclined relative to the Z-axis direction. A locking spring (2) is sleeved on the initial locking pin (1); A sliding bolt (3) is adapted to move along the Y-axis. The sliding bolt (3) includes a bolt body (31) and an abutment (32). The abutment (32) has an abutment surface (33) on one side and a locking lug (34) on the other side. The abutment surface (33) abuts against the inclined surface of the pin tail (12). The sliding bolt (3) is adapted to rotate along its own axis or translate along the X-axis, so that the locking lug (34) is offset from or aligned with the stop block (7) on the missile. Limiting guide seat (4), the sliding bolt (3) is installed on the limiting guide seat (4), the limiting guide seat (4) is provided with a bolt limiting structure, which is used to guide the movement path of the sliding bolt (3); The initial locking mechanism includes a locked state and an unlocked state. In the locked state, the pin (11) is inserted into the locking hole of the upper rudder surface (8), and the lock lug (34) abuts against the stop (7) to lock the initial locking pin (1) and the sliding bolt (3). In the unlocked state, the lock lug (34) is separated from the stop (7), and the initial locking pin (1) and the sliding bolt (3) are movable.

2. The initial locking mechanism for the missile folding rudder according to claim 1, characterized in that, The bolt limiting structure is a bolt limiting groove (41) provided on the surface of the limiting guide seat (4). The bolt body (31) is plate-shaped and enters the bolt limiting groove (41). In the X-axis direction, the size of the bolt limiting groove (41) is larger than the size of the bolt body (31), so that the sliding bolt (3) is suitable for translation along the X-axis direction.

3. The initial locking mechanism for the missile folding rudder according to claim 2, characterized in that, Includes at least one bolt positioning screw (5) for abutting against the side of the bolt body (31) to define the position of the sliding bolt (3) in the X-axis direction.

4. The initial locking mechanism for the missile folding rudder according to claim 2, characterized in that, The part where the bolt (31) connects to the abutment (32) is provided with a relief groove (35), which is used for the stop (7) to pass through. In the Y-axis direction, the opening size of the relief groove (35) is larger than the size of the stop (7).

5. The initial locking mechanism for the missile folding rudder according to claim 2, characterized in that, The contact surface (33) is an inclined plane that fits against the end face of the pin (12).

6. The initial locking mechanism for the missile folding rudder according to claim 1, characterized in that, The bolt limiting structure is a bolt limiting hole (42) provided on the limiting guide seat (4). The bolt limiting hole (42) extends along the Y-axis direction. The bolt limiting hole (42) has a spiral groove on its hole wall. The bolt body (31) is cylindrical. The surface of the bolt body (31) is provided with spiral ribs. The bolt body (31) is inserted into the bolt limiting hole (42). The spiral ribs engage with the spiral grooves, so that the sliding bolt (3) rotates synchronously along its own axis when it moves along the Y-axis direction.

7. The initial locking mechanism for the missile folding rudder according to claim 6, characterized in that, The limiting guide seat (4) has a notch (43) on the side near the abutment (32). When the abutment (32) moves toward the limiting guide seat (4), the abutment (32) enters the notch (43).

8. The initial locking mechanism for the missile folding rudder according to claim 6, characterized in that, The contact surface (33) is an inclined curved surface that fits against the end face of the pin (12).

9. The initial locking mechanism for the missile folding rudder according to any one of claims 1-8, characterized in that, The initial locking pin (1) includes a limiting boss (13), which is located between the pin head (11) and the pin tail (12). One end of the locking pin spring (2) is fixed, and the other end abuts against the limiting boss (13).

10. The initial locking mechanism for the missile folding rudder according to claim 9, characterized in that, The limiting boss (13) has a locking pin guide groove (14) extending along the Z-axis on one side, and a guide pin (15) is provided in the locking pin guide groove (14).

11. The initial locking mechanism for the missile folding rudder according to claim 9, characterized in that, It also includes a locking spring (6), one end of which is fixed and the other end abuts against the bolt body (31).

12. A missile folding rudder, characterized in that, It includes an upper control surface (8), a lower control surface (9), and an initial locking mechanism as described in any one of claims 1-11, wherein the initial locking mechanism is mounted on the lower control surface (9).

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