A missile tail cone separation device based on a strong magnetic array

Abstract

This invention discloses a missile tail cover separation device based on a strong magnetic array, comprising a launch tube, a missile body, and a tail cover main body. The missile body includes a bottom end, which includes an engine exhaust nozzle, a bottom wall surface, and a connected iron ring. The tail cover main body includes an open end, a tail cover wall surface, and a fixing groove. The open end includes a strong magnetic array, which comprises four parts, evenly and symmetrically distributed near the wall surface of the tail cover opening end. Each array contains a certain number of magnetic adsorption devices. The magnetic attraction between the strong magnetic array inside the tail cover main body and the iron ring inside the missile body achieves the connection between the tail cover main body and the missile body, providing protection during the initial launch phase. The tail cover separation device proposed in this invention uses a non-pyrotechnic method, based on a strong magnetic array device, to separate the tail cover main body from the missile body, offering advantages such as safety, controllability, simplicity, high efficiency, and reusability.

Description

Technical Field

[0001] This invention belongs to the field of missile separation technology, specifically relating to a missile tail cover separation device based on a strong magnetic array. Background Technology

[0002] The missile relies on the high-temperature, high-pressure gas at the bottom of the launch tube to provide initial power. During this process, the tail cover plays a role in protecting the first-stage engine and electromechanical system from damage caused by the high-temperature gas. After the missile leaves the tube, the tail cover should be separated in time, and the first-stage engine jet will generate power. At the same time, it is necessary to prevent the engine from igniting and creating a high-pressure area inside the tail cover, which would affect the engine jet state.

[0003] Currently, there are two main methods for separating the tail cover: 1) Side-thrust separation: After the explosive bolts detonate, the side-thrust engine ignites, pushing the tail cover to change its flight direction and avoid the missile's exhaust plume and ground launch tubes; 2) Rotational separation: The tail cover is connected to the missile body via a hinge mechanism. After the explosive bolts detonate, the tail cover rotates along a rotating device to a safe angle and separates from the missile body by inertia. Both methods use pyrotechnic separation, which means the explosive fragments cannot be reused after detonation. Furthermore, the random movement of the explosive fragments can easily damage the nozzle and internal electromechanical systems, creating safety hazards.

[0004] Patent document 1 (CN112361895A) discloses a residual missile tail cover. In the technical solution disclosed in this patent document, the tail cover is separated and retained in the launch tube, but this will increase the tail cover recovery and processing work in the launch tube. Patent document 2 (CN111189367A) discloses a cover body with a concave surface and a flow-blocking protrusion. In the technical solution disclosed in this patent document, the lateral power of the cover is provided by changing the direction of the exhaust plume of the missile's first-stage engine, but this method will undoubtedly have a certain impact on the missile's flight attitude. Summary of the Invention

[0005] The purpose of this invention is to provide a missile tail cover separation device based on a strong magnetic array, which provides a highly efficient and accurate missile tail cover side-throw separation device.

[0006] The technical solutions adopted in the present invention are as follows:

[0007] A missile tail cover separation device based on a strong magnetic array includes: a tail cover body, a missile body, and a launch tube.

[0008] The launch tube is a missile launch device;

[0009] The projectile body includes a bottom end, which includes an engine exhaust nozzle, a bottom wall, and an iron ring; the bottom wall is fixedly connected to the iron ring, and the engine exhaust nozzle is located at the center of the iron ring.

[0010] The tail cover body includes an open end, a tail cover wall, and a fixing groove;

[0011] The opening is located above the tail cover wall, which is an arc-shaped surface. The fixing groove is located inside the tail cover wall and is used to fix the stepper motor.

[0012] The opening end includes a strong magnetic array, comprising array ①, array ②, array ③, and array ④. These four arrays are symmetrically and evenly distributed near the tail cover wall, with the center of the opening end as the center point and the crosshair as the standard line. Arrays ①, ②, ③, and ④ each include a certain number of magnetic adsorption devices. The magnetic adsorption devices in each array have the same structure and parameters. Arrays ② and ④ are symmetrically distributed with the center of the tail cover opening end along the tail cover wall, each containing 4×1 magnetic adsorption devices. Arrays ① and ③ are symmetrically distributed with the center of the tail cover opening end along the tail cover wall, containing 8×1 and 4×1 magnetic adsorption devices respectively. The magnetic adsorption devices are used to attract the iron ring at the bottom of the projectile.

[0013] The magnetic adsorption device includes a permanent magnet, a metal frame, a top fixing groove, a lead screw shaft, a fixed bearing, a coupling, a stepper motor, a stepper motor output end, and a bottom groove. The permanent magnet is fixedly connected to the bottom groove of the metal frame, the top fixing groove of the metal frame is connected to the lead screw shaft, and the fixed bearing connects to the lead screw shaft. The stepper motor output end is fixedly connected to the coupling. When the stepper motor starts, it drives the coupling to rotate, and the coupling drives the lead screw shaft to rotate. The metal frame moves up and down under the rotation of the lead screw shaft, which in turn changes the position of the permanent magnet. The bottom end of the projectile and the opening end of the tail cover are connected by magnetic force generated between the permanent magnet in the magnetic adsorption device and the iron ring, achieving a protective function during the initial launch phase.

[0014] The permanent magnets are Alnico 9, which have higher operating temperatures (up to 550℃) under the same conditions of magnetic energy product, coercivity, and magnetic properties. To limit the interference of the permanent magnets rotating when the stepper motor starts on the permanent magnets in other magnetic adsorption devices, round magnets are selected. The metal frame is made of copper and has a cylindrical hollow shape with cylindrical Alnico permanent magnets embedded in the grooves. The stepper motor is a 57HB115-428 type motor with a torque of 1.95 N·m and a weight of 1.5 kg. All stepper motors in the strong magnetic array are fixedly connected to the fixing grooves inside the tail cover wall.

[0015] The stepper motors are controlled by a programmable logic controller (PLC). The stepper motors in arrays ①, ②, ③ and ④ inside the tail cover body are connected in parallel. When the command to separate the tail cover body from the projectile is issued, the PLC receives the original electrical signal and the processed output signal can control each stepper motor in the magnetic adsorption device inside the strong magnetic array to start simultaneously.

[0016] After all the stepper motors in the strong magnetic array start simultaneously, array ① completes the separation of the iron ring at the bottom of the projectile from the permanent magnet in the magnetic adsorption device inside the tail cover body later than arrays ②, ③, and ④. Under the action of inertial force and the gravity of the tail cover body, array ① will drive the tail cover body to move outward from the position of array ①. When the critical separation position of array ① is reached, under the action of the jet of the engine tail nozzle, the projectile and the tail cover body complete the complete separation and the tail cover body is thrown to the side according to the set attitude.

[0017] The beneficial effects of this invention are:

[0018] This invention discloses a missile tail cover separation device based on an array. Upon receiving a separation command, the stepper motors in the strong magnetic array within the tail cover body are all rapidly and synchronously started by PLC control. Through couplings and lead screws, they drive permanent magnets connected to a metal frame to move downwards, away from the iron rings adsorbed at the bottom of the missile body, achieving rapid, reliable, and controllable tail cover separation. During separation, when arrays ②, ③, and ④ reach the critical separation distance from the iron rings, due to the large number of magnetic adsorption devices in array ① and the strong magnetic attraction, the tail cover can be thrown outwards from array ① under the influence of inertia and the overall gravity of the tail cover, achieving side-throwing. Simultaneously, the symmetrical array position, arranged along a cross-shaped standard line, is variable, allowing for the rational selection of the side-throwing position according to separation requirements. In summary, the missile tail cover separation device disclosed in this invention does not employ pyrotechnic separation methods, is safe and efficient, and easy to control; the tail cover separation position can be designed independently, and side-throwing will not cause safety hazards to ground equipment; furthermore, the method is reusable, environmentally friendly, and reliable. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the structure of a missile tail cover separation device based on a strong magnetic array according to the present invention;

[0020] Figure 2 This is a schematic diagram showing the position of the magnetic adsorption device in the strong magnetic array of the present invention at the opening end of the tail cover;

[0021] Figure 3 This is a schematic diagram of the structure of a single magnetic adsorption device of the present invention;

[0022] Figure 4 This is a schematic diagram of the stepper motor control start-up structure of the present invention;

[0023] Figure 5 This is a schematic diagram of the structure for achieving side-throwing during the separation process of this invention;

[0024] Figure 6 This is a schematic diagram of the structure connecting a single magnetic adsorption device of the present invention to the tail cover wall.

[0025] In the diagram: 1. Projectile body, 2. Tail cover body, 3. Launch tube, 4. Bottom end of projectile body, 5. Opening end of tail cover, 6. Iron ring, 7. Array ①, 8. Array ②, 9. Array ③, 10. Array ④, 101. Magnetic adsorption device, 1010. Permanent magnet, 1011. Metal frame, 1012. Top fixing groove of metal frame, 1013. Lead screw shaft, 1014. Fixed bearing, 1015. Coupling, 1016. Stepper motor, 1017. Stepper motor output end, 1018. Bottom groove of metal frame, 11. Separation command, 12. Original electrical signal, 13. Programmable logic controller, 14. Output signal, 15. Strong magnetic array, 40. Bottom wall of projectile body, 41. Engine tail nozzle, 50. Tail cover wall, 51. Inner fixing groove of tail cover body.

[0026] Specific implementation

[0027] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. The following examples are only used to more clearly illustrate the technical solutions of the present invention and should not be construed as limiting the scope of protection of the present invention.

[0028] Example 1

[0029] This invention discloses a missile tail cone separation device based on a strong magnetic array, such as... Figure 1 As shown, the system includes a missile body 1, a tail cover body 2, and a launch tube 3. The missile body 1 includes a bottom end 4, which includes an engine exhaust nozzle 41, a bottom wall 40, and an iron ring 6 fixedly connected to it. The tail cover body 2 includes an open end 5, a tail cover wall 50, and a fixing groove 51. The open end 5 includes a strong magnetic array 15, which includes a number of magnetic adsorption devices 101. The magnetic adsorption devices 101 are used to adsorb and connect with the iron ring 6 in the bottom end 4 of the missile body. The launch tube 3 is a missile launch device. The connection between the tail cover body and the missile body is achieved through the magnetic attraction between the strong magnetic array in the tail cover body 2 and the iron ring in the missile body, thus achieving protection during the initial launch phase.

[0030] like Figure 2As shown, the strong magnetic array 15 further comprises array ①7, array ②8, array ③9, and array ④10. The four parts are symmetrically and evenly distributed at the tail cover opening 5 near the tail cover wall 50 with the center of the opening end as the center point and the cross center line as the standard line. Array ①7, array ②8, array ③9, and array ④10 each include a certain number of magnetic adsorption devices 101. The magnetic adsorption devices 101 contained in each arrangement mechanism have the same structure and parameters. Array ②8 and array ④10 are symmetrically distributed at the tail cover wall 50 with the center of the tail cover opening 5 as the center, and each contains 4×1 magnetic adsorption devices 101. Array ①7 and array ③9 are symmetrically distributed at the tail cover wall 50 with the center of the tail cover opening 5 as the center, and each contains 8×1 and 4×1 magnetic adsorption devices 101 respectively.

[0031] like Figure 3 As shown, the magnetic adsorption device 101 consists of a permanent magnet 1010, a metal frame 1011, a top fixing groove 1012, a lead screw shaft 1013, a fixed bearing 1014, a coupling 1015, a stepper motor 1016, a stepper motor output end 1017, and a bottom groove 1018. The permanent magnet 1010 is fixedly connected to the bottom groove 1018 of the metal frame 1011. The top fixing groove 1012 of the metal frame 1011 is connected to the lead screw shaft 1013. The fixed bearing 1014 connects to the lead screw shaft 1013. The stepper motor output end 1017 is fixedly connected to the coupling 1015. When the stepper motor 1016 starts, it drives the coupling 1015 to rotate, and the coupling 1015 drives the lead screw shaft 1013 to rotate. The metal frame 1011 adjusts its up-and-down movement under the rotation of the lead screw shaft 1013, thereby causing the permanent magnet 1010 to change its position. The permanent magnet 1010 is an Alnico 9 permanent magnet with higher operating temperature (up to 550℃) under the same conditions of magnetic energy product, coercivity, and magnetic properties. To limit the interference of the permanent magnet 1010's rotation on the permanent magnets 1010 in the other magnetic adsorption devices 101 when the stepper motor 1016 starts, a circular magnet is selected. The metal frame 1011 is made of copper and has a cylindrical hollow shape. The cylindrical Alnico permanent magnet 1010 is embedded in the groove 1018. The stepper motor 1016 is a 57HB115-428 type motor with a torque of 1.95 N·m and a weight of 1.5 kg. Figure 6 As shown, the stepper motors 1016 in the strong magnetic array 15 are all fixedly connected to the fixing grooves 51 inside the tail cover wall 50.

[0032] like Figure 4As shown, the stepper motor 1016 is further controlled by the programmable logic controller (PLC) 13. The stepper motors 1016 in arrays ①7, ②8, ③9 and ④10 inside the tail cover body 2 are connected in parallel. When the separation command 11 between the tail cover body 2 and the projectile 1 is issued, the PLC 13 receives the original electrical signal 12 and the processed output signal 14 can control the stepper motors 1016 in the magnetic adsorption device 101 inside the strong magnetic array 15 to start simultaneously.

[0033] After the stepper motors 1016 start simultaneously, array ①7 reaches the critical separation distance from the iron ring 6 when arrays ②8, ③9, and ④10 reach the same distance. Because array ①7 has a large number of magnetic adsorption devices 101 and a strong magnetic force, it reaches the critical separation distance later than arrays ②8, ③9, and ④10 within the same timeframe. Figure 5 As shown, under the action of inertia and gravity of the tail cover body 2, the array ①7 will drive the tail cover body 2 to move outward from the position of the array ①7. When the critical separation position of the array ①7 is reached, under the action of the jet of the engine tail nozzle 41, the projectile 1 and the tail cover body 2 will be completely separated and the tail cover body 2 will be side-thrown according to the set attitude.

[0034] In summary, the missile tail cover separation device disclosed in this invention, based on a strong magnetic array, utilizes the magnetic attraction force generated between the permanent magnet 1010 and the iron ring 6 to achieve separation using a non-pyrotechnic method. This method is reusable, environmentally friendly, and reliable. After the separation command 11 is issued, the stepper motors 1016 in the strong magnetic array 15 within the tail cover body 2 are all rapidly and synchronously started by the PLC 13. Through the coupling 1015 and the lead screw 1013, the permanent magnets 1010 connected to the metal frame 1011 move downwards, away from the iron ring 6 attracted to the bottom 4 of the missile body, achieving rapid, reliable, and controllable tail cover separation. The different numbers of magnetic attraction devices 101 within the strong magnetic array 15 result in different magnetic attraction force distributions, leading to different critical separation positions for each array. This allows for the side-throwing of the tail cover body 2, preventing any safety hazards to ground equipment.

[0035] Example 2

[0036] Furthermore, based on Example 1, the position of the strong magnetic array 15 symmetrically arranged with cross standard lines is variable. The position of the array with more magnetic adsorption devices 101 than the other three arrays in the four-part array of the strong magnetic array 15 is the side-throw position of the tail cover body 2. The side-throw position can be reasonably selected according to the separation requirements.

[0037] The embodiments described above are merely preferred embodiments of the present invention, and the scope of protection of the present invention is not limited thereto. Any simple changes or equivalent substitutions of the technical solutions that can be obviously obtained by those skilled in the art within the scope of the technology disclosed in the present invention shall fall within the scope of protection of the present invention.

Claims

1. A missile tail cone separation device based on a strong magnetic array, characterized in that, include: Tail cover body (2), projectile body (1) and launch tube (3); The launch tube (3) is a missile launch device; The projectile (1) includes a projectile bottom end (4), which includes an engine exhaust nozzle (41), a bottom wall (40), and an iron ring (6); the bottom wall (40) is fixedly connected to the iron ring (6), and the engine exhaust nozzle (41) is located at the center of the iron ring (6). The tail cover body (2) includes an open end (5), a tail cover wall (50), and a fixing groove (51). The opening end (5) is located above the tail cover wall (50), the tail cover wall (50) is an arc-shaped surface, the fixing groove (51) is located inside the tail cover wall (50), and the fixing groove (51) is used to fix the stepper motor (1016). The opening end (5) includes a strong magnetic array (15), which includes array ① (7), array ② (8), array ③ (9) and array ④ (10). The four arrays are symmetrically and evenly distributed at the position of the tail cover opening end (5) near the tail cover wall (50) with the center of the opening end (5) as the center point and the cross center line as the standard line. Array ① (7), array ② (8), array ③ (9) and array ④ (10) each include a certain number of magnetic adsorption devices (101). The magnetic adsorption devices (101) contained in each array have the same structure and parameters. Array ② (8) and array ④ (10) are symmetrically distributed at the tail cover wall (50) with the center of the tail cover opening end (5) as the center. Array ① and array ③ are symmetrically distributed at the tail cover wall (50) with the center of the tail cover opening end (5) as the center. The magnetic adsorption device (101) is used to adsorb with the iron ring (6) in the bottom end (4) of the projectile. The magnetic adsorption device (101) includes a permanent magnet (1010), a metal frame (1011), a top fixing groove (1012), a lead screw shaft (1013), a fixed bearing (1014), a coupling (1015), a stepper motor (1016), a stepper motor output end (1017), and a bottom groove (1018); the permanent magnet (1010) is fixedly connected to the bottom groove (1018) of the metal frame (1011), and the top fixing groove (1012) of the metal frame (1011) is connected to the lead screw shaft (1013); the fixed bearing (1014) connects to the lead screw shaft (1013); the stepper motor (1015) is connected to the lead screw shaft (1016). The output end (1017) of the stepper motor is fixedly connected to the coupling (1015). The stepper motor (1016) starts and outputs to drive the coupling (1015) to rotate. The coupling (1015) drives the lead screw shaft (1013) to rotate. The metal frame (1011) is adjusted up and down under the rotation of the lead screw shaft (1013), which drives the permanent magnet (1010) to change position up and down. The bottom end (4) of the projectile and the opening end (5) of the tail cover are connected by the magnetic force generated between the iron ring (6) and the permanent magnet (1010) in the magnetic adsorption device (101), so as to realize the protection function in the early stage of launch. Both array ② (8) and array ④ (10) contain 4×1 magnetic adsorption devices (101), and array ① and array ③ contain 8×1 and 4×1 magnetic adsorption devices (101) respectively.

2. The missile tail cover separation device based on a strong magnetic array as described in claim 1, characterized in that, The permanent magnet (1010) is an AlNiCo permanent magnet and is a round magnet.

3. The missile tail cover separation device based on a strong magnetic array as described in claim 1, characterized in that, The metal frame (1011) is made of copper and has a cylindrical hollow shape. A cylindrical aluminum nickel cobalt permanent magnet (1010) is embedded in the bottom groove (1018). The stepper motor (1016) is a 57HB115-428 type motor with a torque of 1.95 N·m and a weight of 1.5 kg. The stepper motors (1016) in the strong magnetic array (15) are all fixedly connected to the fixing groove (51) on the tail cover wall.

4. The missile tail cover separation device based on a strong magnetic array as described in claim 1, characterized in that, The stepper motor (1016) is controlled by a programmable logic controller (13). The stepper motors (1016) in arrays ① (7), ② (8), ③ (9) and ④ (10) inside the tail cover body (2) are connected in parallel. When the tail cover body (2) is separated from the projectile by the command (11), the programmable logic controller (13) receives the original electrical signal (12). The processed output signal (14) can control the stepper motors (1016) in the magnetic adsorption device (101) inside the strong magnetic array (15) to start simultaneously.

5. The operating method of a missile tail cone separation device based on a strong magnetic array according to any one of claims 1 to 4, characterized in that, After the stepper motor (1016) starts simultaneously, array ① (7) completes the separation of the iron ring (6) in the bottom end (4) of the projectile from the permanent magnet (1010) in the magnetic adsorption device (101) in the tail cover body (2) later than array ② (8), array ③ (9) and array ④ (10). Under the action of inertial force and gravity of the tail cover body (2), array ① (7) will drive the tail cover body (2) to move to the outside of the position of array ① (7). When the critical separation position of array ① is reached, under the action of the jet of the engine tail nozzle (41), the projectile (1) and the tail cover body (2) are completely separated and the tail cover body is thrown to the side according to the set posture.

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