A tail skirt angle adjusting mechanism suitable for a hypersonic missile

Abstract

A tail skirt angle adjustment mechanism suitable for hypersonic missiles belongs to the field of variator vehicle technology. This invention solves the problem that existing tail skirt mechanisms capable of extending the tail skirt angle cannot be reused, thus failing to effectively improve the missile's maneuverability and combat efficiency. A torque motor is mounted on one end of the tail section, and a drive shaft ring is coaxially sleeved on the tail section and fixedly connected to the mover of the torque motor. Several skirts are circumferentially distributed on the outer side of the tail section, with one end of each skirt rotatably connected to one end of the tail section. Several deflectors are circumferentially distributed on the outer side of the tail section and positioned between the skirts and the tail section. The skirts and deflectors are staggered inwards and outwards, and each pair of adjacent deflectors is slidably connected by a scissor hinge. The device of this invention has a simple structure, and the core mechanism uses a spatial linkage combined with a ball joint drive, resulting in high transmission efficiency, strong load-bearing capacity, and the ability to achieve rapid and smooth stepless extension and retraction.

Description

Technical Field

[0001] This invention relates to a tail skirt angle adjustment mechanism suitable for hypersonic missiles, belonging to the field of variator technology. Background Technology

[0002] With the development of aerospace technology, missile flight missions are increasingly moving towards larger airspace, wider speed ranges, longer distances, and higher precision. Traditional fixed-shape missiles are mostly designed and analyzed for a specific flight mission profile, which significantly limits their flight environment range and maneuverability, making it difficult to meet the demands of increasingly complex flight missions. Therefore, a variant of the missile's deployable tail skirt mechanism, suitable for multiple flight mission profiles, is needed. By adjusting the angle of the tail skirt, the aerodynamic shape of the missile can be adjusted, thereby enhancing flight stability.

[0003] The tail skirt mechanisms in the existing technology that can realize the tail skirt extension angle are generally one-time deployment tail skirt angle adjustment mechanisms that cannot be reused. This makes it impossible to adjust aerodynamic parameters such as pressure coefficient and lift-drag ratio in real time during missile flight, and makes it impossible to adapt to the flight environment of high and low speed flow fields during cross-speed maneuvering flight. As a result, it cannot effectively improve the missile's flexible maneuverability and combat efficiency. Summary of the Invention

[0004] The present invention aims to solve the above-mentioned technical problems and thereby provide a tail skirt angle adjustment mechanism suitable for hypersonic missiles.

[0005] The technical solution adopted by the present invention to solve the above-mentioned technical problems is as follows:

[0006] A tail skirt angle adjustment mechanism suitable for hypersonic missiles includes a tail section, a torque motor, a drive shaft collar, a transmission mechanism, several skirts, and several deflectors. The torque motor is mounted on one end of the tail section. The drive shaft collar is coaxially sleeved on the tail section and fixedly connected to the mover of the torque motor. Several skirts are circumferentially distributed on the outer side of the tail section, with one end of each skirt rotatably connected to one end of the tail section. Several deflectors are circumferentially distributed on the outer side of the tail section and positioned between the skirts and the tail section. The skirts and deflectors are staggered inwards and outwards. Each pair of adjacent deflectors is slidably connected via a scissor hinge, the middle of which is rotatably connected to the outer skirt.

[0007] The transmission mechanism includes a sliding ring and several spatial connecting rods and several support rods arranged circumferentially along the tail section. The sliding ring is slidably arranged along the tail section. The two ends of each spatial connecting rod are respectively connected to the transmission shaft ring and the sliding ring through ball joints. One end of each of the several support rods is rotatably connected to the end of the sliding ring away from the spatial connecting rod, and the other end of each support rod is rotatably connected to the inner side of several skirt pieces.

[0008] Furthermore, a guide ring is coaxially and fixedly fitted on the tail section. Several slides are provided on the guide ring along its circumference. Several limiting blocks are integrally fixed on the inner circular surface of the sliding ring, and the limiting blocks are correspondingly slidably arranged in the several slides.

[0009] Furthermore, each of the slides is equipped with a planar bearing, and each limiting block is slidably disposed within the corresponding slide via the planar bearing.

[0010] Furthermore, the stator of the torque motor is fixed at one end of the tail section, the mover of the torque motor is fitted at one end of the tail section and a thrust bearing is installed between one end of the mover and the tail section, and a radial bearing is installed between the inner surface of the transmission shaft ring and the tail section.

[0011] Furthermore, each skirt piece is rotatably connected to one end of the tail section via a connecting assembly, wherein the connecting assembly includes a connector and a connecting block rotatably connected to the connector, the connector is fixedly connected to the tail section, and the connecting block is fixedly connected to one end of the skirt piece.

[0012] Furthermore, an ear plate is integrally fixed on the skirt piece, and the other end of the support rod is rotatably connected to the ear plate.

[0013] Furthermore, a protruding ridge is integrally fixed on one side of the skirt near the deflector along its length, and the ear plate is fixed on the protruding ridge.

[0014] Furthermore, the scissor hinge includes a limiting shaft fixed on the skirt and two first limiting strips arranged in an X shape. The middle parts of the two first limiting strips are rotatably fitted onto the limiting shaft and limited by limiting nuts threaded onto the limiting shaft. Each first limiting strip has two first limiting elongated holes along its length direction, and the two first limiting elongated holes are respectively located on both sides of the limiting shaft. Each pair of adjacent baffles is slidably arranged relative to each other along the first limiting elongated holes by a slider.

[0015] Furthermore, one end of each baffle plate abuts against the outside of the torque motor, and the other ends of every two adjacent baffle plates are slidably connected relative to each other by a second limiting strip, which is correspondingly fixed on the outer side of the skirt.

[0016] Furthermore, two first mounting blocks are fixedly installed in the middle of the inner side of the baffle and connected to the scissor hinge through the first mounting blocks. Two second mounting blocks are fixedly installed on the inner side of the baffle away from the torque motor and connected to the second limit strip through the second mounting blocks. Several retainers are fixedly installed on the outer side of the torque motor along its circumference, and one end of several baffles is placed on several retainers.

[0017] Compared with the prior art, the present invention has the following advantages:

[0018] 1. The tail skirt angle adjustment mechanism of the present invention differs from the traditional one-time unfolding tail skirt angle adjustment mechanism. It utilizes a high-power density ring torque motor for drive, giving the mechanism good repeatability; it uses a single drive source to simultaneously drive multiple skirt panels to unfold and retract, giving the mechanism good synchronization during the unfolding and retracting process; and it uses an internal closed-loop control system to position and control the transmission mechanism, enabling the tail skirt to unfold or retract at any angle.

[0019] 2. The tail skirt angle adjustment mechanism of the present invention comprises a skirt and a baffle plate stacked together, with the baffle plate slidably connected to the skirt via a cross-scissor hinge. In the retracted state, the baffle plate is hidden inside the skirt; in the extended state, the baffle plate fills the gaps between the skirts, saving internal space while ensuring that the tail skirt has a good aerodynamic shape under any extended angle.

[0020] 3. The tail skirt angle adjustment mechanism of the present invention uses multiple circumferentially distributed spatial connecting rods as a transmission mechanism to convert the rotational motion of the torque motor into the linear motion of the sliding ring. The multi-point synchronous drive effectively avoids problems such as asynchronous and uneven force transmission. At the same time, the ability of the mechanism to bear external loads can be improved by increasing the number of spatial connecting rods.

[0021] 4. The device of the present invention has a simple structure. The core mechanism adopts a spatial linkage combined with a ball joint transmission, which has high transmission efficiency and strong load-bearing capacity, and can realize rapid and smooth stepless extension and retraction. Attached Figure Description

[0022] Figure 1 This is a three-dimensional structural diagram of the tail skirt angle adjustment mechanism of the present invention in the retracted state;

[0023] Figure 2 This is a three-dimensional structural diagram of the tail skirt angle adjustment mechanism of the present invention in its unfolded state.

[0024] Figure 3 This is a three-dimensional structural diagram of the tail skirt angle adjustment mechanism of the present invention in the retracted state (skirt and baffle are not shown);

[0025] Figure 4 This is a front view schematic diagram of the tail skirt angle adjustment mechanism of the present invention in the retracted state (skirt and deflector not shown);

[0026] Figure 5 This is a front view schematic diagram of the tail skirt angle adjustment mechanism of the present invention in its retracted state;

[0027] Figure 6 This is a front view schematic diagram of the tail skirt angle adjustment mechanism of the present invention in its deployed state (skirt and deflector not shown);

[0028] Figure 7This is a front view schematic diagram of the tail skirt angle adjustment mechanism of the present invention in its unfolded state;

[0029] Figure 8 A schematic front sectional view of the tail section where the torque motor is installed;

[0030] Figure 9 This is a three-dimensional structural diagram of a scissor hinge (the limiting axis is not shown).

[0031] Figure 10 This is a schematic diagram of the connection structure between the skirt and the deflector;

[0032] Figure 11 This is a schematic diagram of the three-dimensional structure of the skirt piece;

[0033] Figure 12 This is a three-dimensional structural diagram of the baffle.

[0034] Figure 13 This is a schematic diagram of the three-dimensional structure of the tail section;

[0035] Figure 14 A three-dimensional structural diagram of the guide ring;

[0036] Figure 15 This is a schematic diagram of the three-dimensional structure of the sliding ring.

[0037] In the picture:

[0038] 1. Tail section; 2. Torque motor; 2-1. Stator; 2-2. Mover; 3. Drive shaft collar; 4. Sliding ring; 4-1. Limiting block; 5. Spatial connecting rod; 6. Support rod; 7. Ball joint; 8. Surface bearing; 9. Skirt; 10. Baffle plate; 11. Scissor hinge; 11-1. Limiting shaft; 11-2. First limiting strip; 12. Guide ring; 12-1. Slide rail; 13. Thrust bearing; 14. Radial bearing; 15. Connector; 16. Connecting block; 17. Second limiting strip; 17-1. Second limiting elongated hole; 18. Limiting post; 19. Cage; 20. First mounting block; 21. Second mounting block; 22. Ear plate; 23. Protruding ridge. Detailed Implementation

[0039] Specific implementation method one: Combining Figures 1-15 This description aims to clearly and completely illustrate the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0040] It should be noted that the descriptions of "left," "right," "left side," "right side," "upper part," "lower part," "top," and "bottom" in this invention are defined based on the orientation or positional relationships shown in the accompanying drawings. They are merely for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the described structure must be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0041] In the description of this invention, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0042] A tail skirt angle adjustment mechanism suitable for hypersonic missiles includes a tail section 1, a torque motor 2, a transmission shaft ring 3, a transmission mechanism, several skirts 9, and several deflectors 10. The torque motor 2 is mounted on one end of the tail section 1. The transmission shaft ring 3 is coaxially sleeved on the tail section 1 and fixedly connected to the mover 2-2 of the torque motor 2. Several skirts 9 are circumferentially distributed on the outer side of the tail section 1, with one end of each skirt 9 rotatably connected to one end of the tail section 1. Several deflectors 10 are circumferentially distributed on the outer side of the tail section 1 and positioned between the skirts 9 and the tail section 1. The skirts 9 and deflectors 10 are staggered inwards and outwards. Each pair of adjacent deflectors 10 is slidably connected by a scissor hinge 11, the middle of which is rotatably connected to the outer side of the skirt 9.

[0043] The transmission mechanism includes a sliding ring 4 and several spatial connecting rods 5 and several support rods 6 arranged circumferentially along the tail section 1. The sliding ring 4 is slidably arranged along the tail section 1. The two ends of each spatial connecting rod 5 are connected to the transmission shaft ring 3 and the sliding ring 4 respectively through ball joints 7. One end of each of the several support rods 6 is rotatably connected to the end of the sliding ring 4 away from the spatial connecting rod 5, and the other end of each of the several support rods 6 is rotatably connected to the inner side of several skirt pieces 9.

[0044] Several spatial connecting rods are evenly distributed in five directions.

[0045] The stator 2-1 of the torque motor 2 is fixedly connected to one end of the tail section 1 by a plurality of screws, and the mover 2-2 of the torque motor 2 is fixedly connected to the transmission shaft ring 3.

[0046] The ball joint 7 is fixed to the drive shaft ring 3 and the ball joint 7 is fixed to the sliding ring 4 by screws.

[0047] The end of the spatial connection that is connected to the transmission shaft ring 3 is the input end, and the end that is connected to the sliding ring 4 is the output end.

[0048] One end of the support rod 6 is rotatably connected to the sliding ring 4, and the other end is rotatably connected to the skirt 9 via connecting shafts.

[0049] The scissor hinge 11 is preferably installed in the middle section of the skirt piece 9, and the connection position between the other end of the support rod 6 and the skirt piece 9 is preferably set between the scissor hinge 11 and the other end of the skirt piece 9.

[0050] The skirt piece 9 is an arc-shaped rectangular plate structure, with multiple pieces evenly distributed on the outer side of the tail section 1. When closed, it can form a complete circumferential envelope.

[0051] The baffle plate 10 is an arc-shaped fan-shaped plate structure, which is slidably connected to the skirt 9 through the scissor hinge 11. During the deployment of the tail skirt, under the driving action of the scissor hinge 11, the baffle plate 10 will immediately deploy to fill the gap between the skirt 9, so as to ensure the continuity of the aerodynamic shape of the tail skirt during the deployment process.

[0052] This invention adopts a modular design. The torque motor 2 serves as the driving source, outputting torque to drive the transmission shaft ring 3 to rotate in an directional manner. This, in turn, drives the input ends of several spatial connecting rods 5 connected by the ball joint 7 to rotate. Ultimately, this drives the sliding ring 4, which is connected to the ball joint 7 at the output end of the spatial connecting rod 5, to move linearly along the axial direction of the tail section 1. Under the pushing action of the sliding ring 4, several support rods 6 move linearly at one end and move spatially at the other end to support and unfold several skirt pieces 9, thereby realizing the unfolding and retraction of the tail skirt at different angles.

[0053] By adjusting the angle of the tail skirt, the aerodynamic shape of the missile can be adjusted, thereby allowing for real-time regulation of aerodynamic parameters such as pressure coefficient and lift-to-drag ratio during missile flight. This enables the missile to adapt to high- and low-speed flow environments during cross-speed maneuvering flight, improving its maneuverability and combat effectiveness.

[0054] 1. The tail skirt angle adjustment mechanism of the present invention differs from the traditional one-time unfolding tail skirt angle adjustment mechanism. It is driven by a high-power density ring torque motor 2, which gives the mechanism good repeatability; it uses a single drive source to drive multiple skirt pieces 9 to unfold and retract simultaneously, which gives the mechanism good synchronization during the unfolding and retracting process; and it uses an internal closed-loop control system to position and control the transmission mechanism, so that the tail skirt can be unfolded or retracted at any angle.

[0055] 2. The tail skirt angle adjustment mechanism of the present invention comprises a skirt 9 and a baffle 10 arranged in a stacked manner, with the baffle 10 slidably connected to the skirt 9 via a cross-scissor hinge 11. In the retracted state, the baffle 10 is hidden inside the skirt 9; in the extended state, the baffle 10 fills the gaps between the skirt 9, saving internal space while ensuring that the tail skirt has a good aerodynamic shape under any extended angle.

[0056] 3. The tail skirt angle adjustment mechanism of the present invention uses multiple circumferentially distributed spatial connecting rods 5 as a transmission mechanism to convert the rotational motion of the torque motor 2 into the linear motion of the sliding ring 4. The multi-point synchronous drive effectively avoids problems such as asynchronous and uneven force transmission. At the same time, the ability of the mechanism to bear external loads can be improved by increasing the number of spatial connecting rods 5.

[0057] 4. The device of the present invention has a simple structure. The core mechanism adopts a spatial connecting rod 5 combined with a ball joint 7 for transmission, which has high transmission efficiency and strong load-bearing capacity, and can realize rapid and smooth stepless extension and retraction.

[0058] A guide ring 12 is coaxially and fixedly fitted onto the tail section 1. Several slide rails 12-1 are formed along the circumference of the guide ring 12. Several limiting blocks 4-1 are integrally fixed to the inner surface of the sliding ring 4, and these limiting blocks 4-1 are slidably disposed within the slide rails 12-1. In this design, the end of each slide rail 12-1 closest to the torque motor 2 is closed, and the end furthest from the torque motor 2 is open, facilitating the installation of bearings. The slide rails 12-1 are evenly distributed circumferentially, further ensuring the stability of the tail skirt angle adjustment process. The limiting blocks 4-1 correspond one-to-one with the slide rails 12-1, allowing the sliding ring 4 to achieve linear movement along the axial direction of the tail section 1 via the limiting blocks 4-1 and the slide rails 12-1. The guide ring 12 is fixed to the tail section 1 by several screws.

[0059] Each of the slide rails 12-1 is equipped with a flat bearing 8, and each limiting block 4-1 is slidably disposed within the corresponding slide rail 12-1 via the flat bearing 8. This design ensures that the sliding ring 4 is slidably connected to the guide ring 12 via the flat bearing 8, further guaranteeing the smooth unfolding and retraction of the tail skirt.

[0060] The stator 2-1 of the torque motor 2 is fixedly mounted at one end of the tail section 1. The mover 2-2 of the torque motor 2 is fitted onto one end of the tail section 1, and a thrust bearing 13 is installed between its end and the tail section 1. A radial bearing 14 is installed between the inner surface of the drive shaft ring 3 and the tail section 1. With this design, the outer surface of one end of the tail section 1 is machined with several stepped mounting surfaces for mounting the stator 2-1, the mover 2-2, the thrust bearing 13, the drive shaft ring 3, and the radial bearing 14 of the torque motor 2. The thrust bearing 13, installed between the mover 2-2 and one end of the tail section 1, provides axial support for the mover 2-2. The radial bearing 14, installed between the drive shaft ring 3 and one end of the tail section 1, provides radial support for the drive shaft ring 3.

[0061] Each skirt piece 9 is rotatably connected to one end of the tail section 1 via a connecting assembly. The connecting assembly includes a connector 15 and a connecting block 16 rotatably connected to the connector 15. The connector 15 is fixedly connected to the tail section 1, and the connecting block 16 is fixedly connected to one end of the skirt piece 9. With this design, several connectors 15 are evenly distributed circumferentially at one end of the tail section 1. The rotatable connection between the connecting block 16 and the connector 15 is achieved through a connecting shaft, and the skirt piece 9 is fixed to the connecting block 16 by several screws. The rotatable connection between the skirt piece 9 and the tail section 1 via the connecting assembly facilitates the unfolding and retracting of the tail skirt. The skirt piece 9 is circumferentially limited by the connecting assembly and the support rod 6.

[0062] An ear plate 22 is integrally fixed to the skirt piece 9, and the other end of the support rod 6 is rotatably connected to the ear plate 22. With this design, the support rod 6 and the ear plate 22 are rotatably connected via a connecting shaft.

[0063] A protruding rib 23 is integrally fixed along the length of one side of the skirt 9 near the deflector 10, and the ear plate 22 is fixedly mounted on the protruding rib 23. With this design, the side of the skirt 9 near the deflector 10 is the inner side, and the protruding rib 23 is integrally fixed along the length of the inner side. Each pair of adjacent deflectors 10 is respectively set on both sides of the protruding rib 23. By setting the protruding rib 23, the deflector 10 is further circumferentially limited, preventing interference between adjacent deflectors 10 during the tail skirt retraction process.

[0064] The scissor hinge 11 includes a limiting shaft 11-1 fixed to the skirt 9 and two first limiting strips 11-2 arranged in an X-shape. The middle portions of the two first limiting strips 11-2 are rotatably fitted onto the limiting shaft 11-1 and limited by limiting nuts threaded onto the limiting shaft 11-1. Each first limiting strip 11-2 has two first limiting elongated holes 11-21 along its length, and the two first limiting elongated holes 11-21 are respectively located on both sides of the limiting shaft 11-1. Each pair of adjacent baffles 10 are respectively slidably positioned relative to each other along the first limiting elongated holes 11-21 by sliders. This design limits the two first limiting strips 11-2 along the axial direction of the limiting shaft 11-1 by the limiting nuts, ensuring that the two limiting strips can only rotate relative to each other. The slider can be any structural component that can be fixed to the baffle plate 10 and slide within the first limiting elongated hole 11-21. For example, it can be a screw and nut structure or a cylindrical structure with a cap. When a screw and nut structure is selected, the screw and nut are loosely connected, making maintenance and disassembly easier. During the tail skirt deployment process, under the drive of the torque motor 2, multiple skirt pieces 9 expand and unfold simultaneously. Under the drive of multiple scissor hinges 11, multiple baffle plates 10 gradually unfold from the inside, filling the gaps between the skirt pieces 9 to form a complete conical envelope.

[0065] One end of each baffle 10 abuts against the outside of the torque motor 2. The other ends of every two adjacent baffles 10 are slidably connected by a second limiting strip 17, which is fixedly mounted on the outer side skirt 9. With this design, the second limiting strip 17 is fixed to the outer side skirt 9 by screws. Two second limiting holes 17-1 are formed along the length of the second limiting strip 17. The two baffles 10 are slidably positioned relative to each other through two limiting posts 18 and two second limiting holes 17-1, thus achieving relative sliding of the baffles 10 via the limiting posts 18 and the second limiting holes 17-1.

[0066] Two first mounting blocks 20 are fixedly installed in the middle of the inner side of the baffle 10 and connected to the scissor hinge 11 through the first mounting blocks 20. Two second mounting blocks 21 are fixedly installed on the inner side of the baffle 10 away from the torque motor 2 and connected to the second limiting strip 17 through the second mounting blocks 21. A retainer 19 is fixedly installed on the side of each connecting block 16 near the torque motor 2. One end of each baffle 10 is correspondingly placed on two adjacent retainers 19. With this design, the retainers 19 provide support for one end of the baffle 10, and the first mounting blocks 20, second mounting blocks 21, and retainers 19 prevent interference between the scissor hinge 11, skirt 9, and second limiting strip 17 during the deployment and retraction process, further ensuring a smooth deployment and retraction process.

[0067] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A tail skirt angle adjustment mechanism suitable for hypersonic missiles, characterized in that: The device includes a tail section (1), a torque motor (2), a transmission shaft collar (3), a transmission mechanism, several skirts (9), and several baffles (10). The torque motor (2) is mounted on one end of the tail section (1). The transmission shaft collar (3) is coaxially mounted on the tail section (1) and fixedly connected to the mover (2-2) of the torque motor (2). Several skirts (9) are circumferentially distributed on the outside of the tail section (1), and one end of each skirt (9) is rotatably connected to one end of the tail section (1). Several baffles (10) are circumferentially distributed on the outside of the tail section (1) and located between the skirts (9) and the tail section (1). The skirts (9) and the baffles (10) are staggered inside and outside. Each pair of adjacent baffles (10) is slidably connected to each other through a scissor hinge (11). The middle part of the scissor hinge (11) is rotatably connected to the skirt (9) on its outside. The transmission mechanism includes a sliding ring (4) and several spatial connecting rods (5) and several support rods (6) arranged circumferentially along the tail section (1). The sliding ring (4) is slidably arranged along the tail section (1). The two ends of each spatial connecting rod (5) are connected to the transmission shaft ring (3) and the sliding ring (4) respectively through ball joints (7). One end of each of the several support rods (6) is rotatably connected to the end of the sliding ring (4) away from the spatial connecting rod (5). The other end of each of the several support rods (6) is rotatably connected to the inner side of several skirt pieces (9). The skirt (9) is an arc-shaped rectangular plate structure that forms a complete circumferential envelope when closed. The baffle (10) is an arc-shaped fan-shaped plate structure that ensures the continuity of the aerodynamic shape of the tail skirt during the unfolding process. The stator (2-1) of the torque motor (2) is fixed at one end of the tail section (1), the mover (2-2) of the torque motor (2) is fitted at one end of the tail section (1) and a thrust bearing (13) is installed between one end of the mover and the tail section (1), and a radial bearing (14) is installed between the inner surface of the transmission shaft ring (3) and the tail section (1). The scissor hinge (11) includes a limiting shaft (11-1) fixed on the skirt (9) and two first limiting strips (11-2) arranged in an X shape. The middle parts of the two first limiting strips (11-2) are respectively rotatably fitted on the limiting shaft (11-1) and limited by the limiting nut threaded on the limiting shaft (11-1). Each first limiting strip (11-2) has two first limiting holes (11-21) along its length direction. The two first limiting holes (11-21) are respectively located on both sides of the limiting shaft (11-1). Each pair of adjacent baffles (10) are respectively slidably arranged relative to each other along the first limiting holes (11-21) by a slider.

2. The tail skirt angle adjustment mechanism for hypersonic missiles according to claim 1, characterized in that: The tail section (1) is coaxially and fixedly fitted with a guide ring (12). The guide ring (12) has several slides (12-1) along its circumference. The inner circular surface of the sliding ring (4) is integrally fixed with several limiting blocks (4-1), and the several limiting blocks (4-1) are correspondingly slidably arranged in the several slides (12-1).

3. The tail skirt angle adjustment mechanism for hypersonic missiles according to claim 2, characterized in that: Each of the slides (12-1) is equipped with a plane bearing (8), and each limiting block (4-1) is slidably disposed in the corresponding slide (12-1) via the plane bearing (8).

4. The tail skirt angle adjustment mechanism for hypersonic missiles according to claim 1, characterized in that: Each skirt piece (9) is rotatably connected to one end of the tail section (1) by a connecting assembly, wherein the connecting assembly includes a connector (15) and a connecting block (16) rotatably connected to the connector (15), the connector (15) is fixedly connected to the tail section (1), and the connecting block (16) is fixedly connected to one end of the skirt piece (9).

5. The tail skirt angle adjustment mechanism for hypersonic missiles according to claim 1, characterized in that: An ear plate (22) is integrally fixed on the skirt piece (9), and the other end of the support rod (6) is rotatably connected to the ear plate (22).

6. A tail skirt angle adjustment mechanism for hypersonic missiles according to claim 5, characterized in that: A protruding rib (23) is integrally fixed on one side of the skirt piece (9) near the baffle plate (10) along its length direction, and the ear plate (22) is fixed on the protruding rib (23).

7. The tail skirt angle adjustment mechanism for hypersonic missiles according to claim 1, characterized in that: One end of each baffle (10) is abutted against the outside of the torque motor (2), and the other ends of each pair of adjacent baffles (10) are slidably connected by a second limiting strip (17), which is fixedly mounted on the skirt (9) on its outer side.

8. A tail skirt angle adjustment mechanism for hypersonic missiles according to claim 4, characterized in that: Two first mounting blocks (20) are fixedly installed in the middle of the inner side of the baffle (10) and connected to the scissor hinge (11) through the first mounting blocks (20). Two second mounting blocks (21) are fixedly installed on the inner side of the baffle (10) away from the torque motor (2) and connected to the second limit strip (17) through the second mounting blocks (21). A retainer (19) is fixedly installed on the side of each connecting block (16) near the torque motor (2). One end of each baffle (10) is correspondingly mounted on the two adjacent retainers (19).

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