A device for ejecting a rod-shaped projectile after high-speed impact

Abstract

This invention relates to a projectile ejection device suitable for high-speed impact experiments with rod-shaped projectiles, comprising a sabot system and an ejection system. The sabot system is used to mount the rod-shaped projectile and allow it to be positioned along the axial direction of the gun barrel. The ejection system includes a collection bucket, a buffer pad, and an interceptor. The end of the collection bucket away from the sabot system has a baffle with a first through hole in its center. The buffer pad is disposed inside the collection bucket and abuts against the baffle, and has a second through hole. The first and second through holes are coaxially aligned and continuous. One end of the interceptor is embedded in the second and first through holes, and the other end has at least two spaced buffer layers along its axial direction. The interceptor has a through-channel for the rod-shaped projectile to pass through. This design allows the sabot system to completely separate from the rod-shaped projectile without affecting its original flight attitude, ensuring the projectile is ideally isolated when passing through the magnetic velocity measurement test area and impacting the target.

Description

Technical Field

[0001] This invention relates to the field of ejection technology in high-speed impact experiments of rod-shaped projectiles, and in particular to an ejection device suitable for high-speed impact experiments of rod-shaped projectiles. Background Technology

[0002] Lightweight gas cannons are important experimental devices used in laboratories to simulate hypersonic impact phenomena or to obtain high-temperature and high-pressure conditions through high-speed impacts. When firing small or metal projectiles from a large-caliber lightweight gas cannon, a plastic sabot is used to protect the projectile. During firing, the plastic sabot directly rubs against the gas cannon's barrel, propelling the projectile into acceleration. Upon exiting the muzzle, the sabot and projectile separate, and the projectile impacts the target plate at a certain velocity. Due to the effects of vibration and sabot separation, the projectile's flight attitude changes, thus affecting the experimental results. Therefore, researching attitude-stabilized sabots and ejection mechanisms is of great significance for high-speed impact experiments.

[0003] Current ejection mechanisms are divided into two types: forced separation and aerodynamic separation. Forced separation refers to using an interceptor to impede the sabot and forcibly separate the projectile from the sabot. However, current designs not only affect the projectile's original flight attitude but also result in incomplete sabot detachment. Aerodynamic separation utilizes the combined effect of the high-pressure gas shock wave at the launch tube exit and the surrounding flow field on the sabot to separate it from the projectile. While this method avoids the problems of current forced separation mechanisms, the projectile needs to travel a relatively long distance through the impeded gas medium, leading to complex ejection mechanisms, low stability, and high cost.

[0004] As for the two-stage light gas gun, it can fire projectiles of various shapes and sizes according to experimental needs, achieving loading velocities from 1 km / s to 7 km / s. For specially shaped rod-shaped projectiles, the corresponding ejection device needs to be specially designed and studied to ensure that the projectile flies along its original trajectory after passing through the ejection device, and to avoid interference from the sabot to the impact experiment. Summary of the Invention

[0005] The purpose of this invention is to provide a projectile ejection device suitable for high-speed impact experiments with rod-shaped projectiles, addressing the problems that existing ejection devices are not suitable for rod-shaped projectiles, have incomplete ejection of the sabot, and affect the original flight attitude of the projectile.

[0006] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0007] A projectile ejection device suitable for high-speed impact experiments with rod-shaped projectiles includes a projectile sabot system and a projectile ejection system;

[0008] The sabot system is used to mount the rod-shaped projectile and to enable the rod-shaped projectile to be positioned along the axial direction of the gun barrel.

[0009] The ejection system includes a collection bucket, a buffer pad, and an interceptor. The end of the collection bucket away from the ejection system has a baffle, and the baffle has a first through hole in the middle. The buffer pad is disposed inside the collection bucket and abuts against the baffle. The buffer pad has a second through hole. The first through hole and the second through hole are coaxially arranged and continuous. One end of the interceptor is embedded in the second through hole and the first through hole, and the other end has at least two buffer layers spaced apart along its axial direction. The interceptor has a through channel inside for the rod-shaped projectile to pass through.

[0010] The sabot system and the ejection system can be set on the same firing axis, that is, they can be aligned with the central axis of the gun barrel, so that the ejection system can intercept the sabot system and separate the rod-shaped projectile from the sabot system.

[0011] The ejection device of this invention, applicable to high-speed impact experiments of rod-shaped projectiles, forms a projectile system by installing the rod-shaped projectile into a sabot system. That is, the rod-shaped projectile and the sabot system are integrated, and it can ensure that the rod-shaped projectile can be arranged along the axial direction of the gun barrel. After the projectile system is placed inside the gun barrel, the rod-shaped projectile can be accelerated by the acceleration of the sabot system. After the projectile system is accelerated as a whole, it can be ejected from the muzzle of the gun barrel and reach the collection bucket of the ejection system.

[0012] When the projectile system impacts the interceptor, the sabot system is intercepted, while the rod-shaped projectile continues into the interceptor's internal penetration channel due to inertia, achieving separation between the projectile and the sabot system. During the projectile's entry into the interceptor's penetration channel, a buffer pad cushions the interceptor, preventing it from directly impacting the collection container's baffle and causing interception failure, as well as collection failure. At least two spaced buffer layers along the interceptor's axial direction gradually dissipate the sabot's kinetic energy, ensuring complete separation of the sabot system and the projectile without affecting the projectile's original flight attitude. This ensures the projectile maintains a stable flight attitude after leaving the muzzle and remains ideally isolated during the magnetic velocity measurement test area and at the moment of impact, unaffected by the sabot system. This makes the experimental structure more accurate and valuable for reference.

[0013] Preferably, the sabot system includes a sabot, a base, and a radial support. The sabot, base, and radial support are all rotating bodies and are arranged coaxially. The sabot includes an axial support and a mounting groove located at different positions along its axial direction. The base is disposed at the bottom of the mounting groove and abuts against the axial support. The radial support is mounted on the side wall of the mounting groove. The radial support has a third through hole along its axial direction at its radial center. The base has an abutment groove at its radial center near the end of the radial support. The abutment groove and the third through hole are used to install the rod-shaped projectile.

[0014] The sabot, base, and radial support are all rotating bodies, enabling stable and rapid acceleration of the entire projectile system after the rod-shaped projectile is installed in the sabot system. In this design, by setting up the base, the base directly abuts against the rod-shaped projectile during acceleration, preventing the projectile from directly acting on the sabot and penetrating its axial support. Furthermore, the mounting slot of the sabot is used to install the base and radial support, ensuring that the rod-shaped projectile remains coaxial with the gun barrel during acceleration. This allows for rapid and stable acceleration of the projectile, maintaining a stable flight attitude upon exiting the muzzle. The absence of a cavity between the base and radial support effectively reduces the weight of the entire sabot system, further increasing the projectile velocity.

[0015] Preferably, the radial support has a first conical surface at the end away from the base, and the diameter of the radial support at the end away from the base is smaller than the diameter of the other end.

[0016] The first conical surface ensures that the rod-shaped projectile completely enters the penetration channel. When the sabot system is intercepted by the interceptor, the radial support is the first to collide with the end of the interceptor with the buffer layer, and it is also the first to be destroyed. By setting the first conical surface, the interceptor can perform gradual shearing on the radial support, with the initial shearing size being smaller and the subsequent shearing size being larger, making the shearing process more gentle and the separation of the rod-shaped projectile from the radial support more stable.

[0017] Preferably, the end of the through channel near the buffer layer is a ejection port, and the outer wall of the ejection port has a second conical surface, which is disposed opposite to the first conical surface.

[0018] The first cone surface of the radial support gradually shears the second cone surface of the interceptor, and the second cone surface impacts the first cone surface to form an impact strain closure, which denies passage to the rear of the sabot system and can prevent the micro-spray particles formed by the destruction of the interceptor from entering the penetration channel. It also allows the sabot system to be completely separated from the rod-shaped projectile without affecting the original flight attitude of the rod-shaped projectile.

[0019] Preferably, the end of the through channel near the baffle is the ejection port, and the ejection port has a gradually changing inner diameter structure, with the inner diameter of the ejection port being larger than the inner diameter of the ejection port.

[0020] The exit port uses a gradually expanding aperture, which helps the micro-spray particles formed by the impact at the ejection port to diffuse in advance, increasing the efficiency of subsequent secondary interception.

[0021] Preferably, the base is frustoconical, and the diameter of the end of the base near the radial support is smaller than the diameter of the other end.

[0022] Considering that the force is greatest at the center of the base and decreases towards the periphery, the base is designed as a frustum. This reduces the overall weight of the projectile system and increases the projectile speed, while ensuring that the rod-shaped projectile does not penetrate the base.

[0023] Preferably, the base has a third conical surface, and the outer contour of the third conical surface is an arc shape that is concave inward along the axial direction of the base.

[0024] The concave arc design of the axial support can further reduce the overall mass of the projectile and increase its velocity while ensuring resistance to the force exerted during the acceleration of the rod-shaped projectile.

[0025] Preferably, the ratio of the distance from the bottom of the abutment groove to the end of the radial support away from the abutment groove to the length of the rod-shaped projectile is 1.9:3 to 2.1:3. With the above setting, the weight can be reduced as much as possible and the projectile speed can be increased without affecting the launch stability.

[0026] Preferably, the base is a high-strength metal component, the sabot is a polyetheretherketone component, which can withstand greater forces, enabling high-speed launch; the collection bucket and the interceptor are steel components.

[0027] Preferably, the ejection system further includes a docking structure and a splash guard. The splash guard is installed inside the collection bucket. One end of the splash guard abuts against the buffer pad, and the other end has a splash guard end plate. The splash guard end plate has a fourth through hole in the middle. One end of the docking structure is embedded in the collection bucket and abuts against the splash guard end plate. The docking structure has a fifth through hole. The fifth through hole, the fourth through hole, the second through hole, and the first through hole are all arranged coaxially. The fifth through hole and the fourth through hole are greater than or equal to the inner diameter of the gun barrel.

[0028] The docking structure allows for the positioning and installation of the ejection system and the gun barrel. The fifth and fourth through holes enable the entire projectile system to pass sequentially through the docking structure and the splash guard, and the projectile is intercepted by the sabot system between the splash guard and the buffer pad. This prevents the interceptor and the sabot system from colliding and causing splashing, and reduces the possibility of damage to other sensitive parts in the target chamber, such as magnetic velocity measuring devices.

[0029] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are:

[0030] 1. The ejection device for high-speed impact experiments of rod-shaped projectiles described in this invention, after the rod-shaped projectile is installed in the sabot system to form a projectile system, can ensure that the rod-shaped projectile can be arranged along the axial direction of the gun barrel. After the projectile system is placed in the gun barrel, the rod-shaped projectile can be accelerated by the acceleration of the sabot system. After the projectile system is accelerated as a whole, it can be fired from the gun barrel and reach the collection bucket of the ejection system. When the projectile system impacts the interceptor, the sabot system is intercepted by the interceptor, and the rod-shaped projectile continues to enter the penetrating channel through the interior of the interceptor under the action of inertia, realizing the separation of the rod-shaped projectile from the sabot system. The interceptor has at least two spaced buffer layers on its outer side along its axis to gradually dissipate the sabot's kinetic energy, thereby allowing the sabot system to completely separate from the rod-shaped projectile without affecting the original flight attitude of the projectile. This ensures that the projectile maintains a stable flight attitude after leaving the muzzle and is in an ideal isolated state when passing through the magnetic velocity test area and hitting the target, without being interfered with by the sabot system. This makes the experimental structure more accurate and more meaningful for reference.

[0031] 2. The ejection device of the present invention, which is suitable for high-speed impact experiments of rod-shaped projectiles, effectively reduces the mass of the projectile system and further improves the launch speed of the projectile.

[0032] 3. The ejection device of the present invention, which is suitable for high-speed impact experiments of rod-shaped projectiles, has a simple structure and processing method, low cost, and effectively improves experimental efficiency and quality. Attached Figure Description

[0033] Figure 1 This is a cross-sectional schematic diagram of the ejection device for high-speed impact experiments of rod-shaped projectiles according to the present invention;

[0034] Figure 2 This is a schematic diagram of the end face of the ejection system equipped with an interceptor;

[0035] Figure 3 yes Figure 2 Schematic diagram of the cross section at point AA;

[0036] Figure 4 This is a cross-sectional view of the collection bucket and the cushioning pad;

[0037] Figure 5 This is a cross-sectional view of the interceptor;

[0038] Figure 6 This is a side view of the sabot system installed inside the gun barrel;

[0039] Figure 7 yes Figure 6 Schematic diagram of the cross section at point BB;

[0040] Figure 8 This is a cross-sectional schematic diagram of the sabot system;

[0041] Figure 9 This is a cross-sectional view of the sabot;

[0042] Figure 10 This is a cross-sectional view of the base;

[0043] Figure 11 This is a cross-sectional view of the radial support;

[0044] Figure 12 This is a cross-sectional schematic diagram of the ejection device for high-speed impact experiments of rod-shaped projectiles according to the present invention, in its usage state.

[0045] Icons: 0-Cannon barrel; 1-Rod-shaped projectile; 21-Ship sabot; 211-Axial support; 212-Mounting groove; 213-Annular step; 22-Base; 221-Abutting groove; 222-Third conical surface; 23-Radial support; 231-Third through hole; 232-First conical surface; 3-Butt joint; 31-Fifth through hole; 4-Collection tube; 41-Baffle; 42-First through hole; 5-Splash shield; 51-Splash shield end plate; 52-Fourth through hole; 6-Buffer pad; 61-Second through hole; 7-Interceptor; 71-Ejection port; 72-Buffer layer; 73-Ejection port; 74-Through passage; 75-Second conical surface; 8-Magnetic velocity measuring baffle; 9-Magnetic velocity measuring device. Detailed Implementation

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

[0047] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0048] Example 1

[0049] This embodiment provides a projectile release device suitable for high-speed impact experiments with rod-shaped projectiles. See [link to documentation]. Figure 1 and Figure 12 This includes sabot systems and ejection systems;

[0050] The sabot system is used to mount the rod-shaped projectile 1 and to enable the rod-shaped projectile 1 to be positioned along the axial direction of the gun barrel 0, such as... Figure 12 As shown; in this embodiment, the design of the sabot system can be consistent with... Figure 12 Although they differ, they all require that after the rod-shaped projectile 1 is installed on the sabot system to form the entire projectile system, the entire projectile system is installed inside the gun barrel 0. The rod-shaped projectile 1 and the gun barrel 0 need to be arranged coaxially so that the entire projectile system can accelerate stably and quickly inside the gun barrel 0.

[0051] like Figures 2-5 As shown, the ejection system includes a collection bucket 4, a buffer pad 6, and an interceptor 7. The end of the collection bucket 4 away from the ejection system has a baffle 41. The baffle 41 has a first through hole 42 in the middle. The buffer pad 6 is disposed inside the collection bucket 4 and abuts against the baffle 41. The buffer pad 6 has a second through hole 61. The first through hole 42 and the second through hole 61 are coaxially arranged and continuous, so that one end of the interceptor 7 can be embedded into the second through hole 61 and the first through hole 42 to form a fixed connection. The other end of the interceptor 7 has at least two layers of buffer layers 72 arranged at intervals along the axial direction of the interceptor 7. The interceptor 7 has a through channel 74 for the rod-shaped projectile 1 to pass through.

[0052] The sabot system and the ejection system can be arranged on the same firing axis, such as... Figure 12 As shown, it can be aligned with the central axis of the gun barrel 0, enabling the ejection system to intercept the sabot system and achieve separation of the rod-shaped projectile 1 from the sabot system.

[0053] The ejection device described in this embodiment, applicable to high-speed impact experiments of rod-shaped projectiles, forms a projectile system by installing the rod-shaped projectile 1 into the sabot system. That is, the rod-shaped projectile 1 and the sabot system form an integral whole, and can ensure that the rod-shaped projectile 1 can be arranged along the axial direction of the gun barrel 0. After the projectile system is placed inside the gun barrel 0, the rod-shaped projectile 1 can be accelerated by accelerating the sabot system. After the projectile system is accelerated as a whole, it can be fired from the nozzle of the gun barrel 0 and reach the collection bucket 4 of the ejection system.

[0054] When the projectile system enters the collection tank 4 and impacts the interceptor 7, the sabot system is intercepted by the interceptor 7. The rod-shaped projectile 1 continues to enter through the penetration channel 74 inside the interceptor 7 due to inertia, thus separating the rod-shaped projectile 1 from the sabot system. During the process of the rod-shaped projectile 1 entering the penetration channel 74 inside the interceptor 7, the sabot system collides with the interceptor 7. The buffer pad 6 cushions the impact of the interceptor 7, preventing it from directly impacting the baffle 41 of the collection tank 4 during the interception of the sabot system, which would cause the baffle 41 to be punctured, leading to interception failure and the collection tank 4's failure to collect the sabot system. The interceptor 7 has at least two spaced buffer layers 72 on its outer side along its axial direction, which gradually dissipate the sabot's kinetic energy, thereby allowing the sabot system to completely separate from the rod-shaped projectile 1 without affecting the original flight attitude of the rod-shaped projectile. This ensures that the rod-shaped projectile maintains a stable flight attitude after leaving the muzzle and is in an ideal isolated state when passing through the magnetic velocity test area and hitting the target, without being interfered with by the sabot system. This makes the experimental structure more accurate and more meaningful for reference.

[0055] like Figure 1 and Figure 5 As shown, the end of the through-channel 74 near the buffer layer 72 is a ejection port 71. The outer wall of the ejection port 71 has a second conical surface 75. The solid portion containing the second conical surface 75 is larger at the end near the buffer pad 6 and smaller at the end away from the buffer pad 6, which allows for better interception of the sabot system. In this embodiment, a total of three annular buffer layers 72 are provided, which are spaced apart along the axial direction of the interceptor 7, and the buffer layer 72 near the buffer pad 6 is in contact with the buffer layer 72. The thickness of the buffer layer 72 along the axial direction of the interceptor 7 is the same as the distance between two buffer layers 72, which allows the kinetic energy of the sabot system to be dissipated gradually. That is, after the first buffer layer 72 is destroyed by impact, the second buffer layer 72 begins to function, allowing the sabot system to completely separate from the rod-shaped projectile 1 without affecting the original flight attitude of the rod-shaped projectile. During the experiment, the sabot, base, and radial support 23 were sheared off due to the impact, thereby dissipating kinetic energy and reducing the possibility of damage to other more sensitive parts in the target chamber, such as the magnetic velocity measuring device.

[0056] like Figure 2 , Figure 3 and Figure 5As shown, the end of the penetrating channel 74 near the buffer layer 72 is the ejection port 71, which is the interception port of the interceptor 7 against the sabot system and also the entrance of the rod-shaped projectile 1. The end of the penetrating channel 74 near the baffle 41 is the exit port 73, which is the exit of the rod-shaped projectile 1. In this embodiment, the exit port 73 has a gradually changing inner diameter structure. The inner diameter of the exit port 73 is larger than the inner diameter of the ejection port 71. That is, the exit port 73 adopts a gradually expanding hole, which can help the micro-spray particles formed by the impact at the ejection port 71 to diffuse in advance, increasing the efficiency of subsequent secondary interception.

[0057] In this embodiment, the collection bucket 4 and the interceptor 7 are preferably made of steel, and the buffer pad 6 is preferably made of high-pressure polyethylene. In addition to high-pressure polyethylene, the buffer pad 6 can also be made of polymers with similar properties to achieve buffering.

[0058] In this embodiment, as Figure 1 and Figure 2 As shown, the ejection system may also include a docking structure 3 and a splash guard 5. The docking structure 3 may be made of steel, and the splash guard may be made of high-pressure polyethylene. The splash guard 5 is installed inside the collection tank 4. The open end of the splash guard 5 abuts against the buffer pad 6, that is, one end of the splash guard 5 abuts against the buffer pad 6 and the other end has a splash guard end plate 51. The splash guard end plate 51 has a fourth through hole 52 in the middle. One end of the docking structure 3 is embedded in the collection tank 4 and abuts against the splash guard end plate 51. The docking structure 3 has a fifth through hole 31. The fifth through hole 31, the fourth through hole 52, the second through hole 61 and the first through hole 42 are all arranged coaxially. The fifth through hole 31 and the fourth through hole 52 are greater than or equal to the inner diameter of the gun barrel 0, so that the entire projectile system can pass through the docking structure 3 and the splash guard end plate 51 in sequence, and be intercepted by the sabot system between the splash guard end plate 51 and the buffer pad 6. This can avoid the interceptor 7 and the sabot system from colliding and splashing, and reduce the possibility of damage to other sensitive parts in the target chamber. Sensitive parts can be magnetic velocity measuring devices, etc.

[0059] Based on this, this embodiment designs a projectile ejection device suitable for high-speed impact experiments with rod-shaped projectiles. After the projectile system leaves the muzzle, it enters a uniform motion phase. Subsequently, the ejection system separates the sabot system from the rod-shaped projectile. The rod-shaped projectile flies at a uniform speed past the magnetic ring and coil within the magnetic velocity measuring device 9. When the rod-shaped projectile 1 passes through the magnetic ring, eddy currents and secondary magnetic fields are formed on its surface. The rod-shaped projectile 1, which has induced electromagnetic properties, generates an induced electromotive force in the receiving coil. The oscilloscope records the history of the electromotive force changes throughout the process. By reading the induced electrical signal pulses generated when the rod-shaped projectile 1 passes through the coil sequentially from the oscilloscope, the projectile velocity can be measured. This device ensures that the rod-shaped projectile 1 maintains a stable flight attitude when leaving the muzzle, achieving complete separation of the sabot system and the rod-shaped projectile 1 over a short distance, while also preserving the original flight attitude of the rod-shaped projectile 1. Furthermore, it maintains an ideal isolated state when passing through the magnetic velocity measuring test area and impacting the target, without interference from the sabot system. Moreover, the ejection device is simple in design, stable, reliable, and inexpensive.

[0060] Example 2

[0061] This embodiment provides a projectile ejection device suitable for high-speed impact experiments with rod-shaped projectiles. Based on Embodiment 1, it not only features a special design for the projectile ejection system, but also a special design for the projectile ejection system.

[0062] See Figures 6-12 The sabot system includes a sabot 21, a base 22, and a radial support 23. All three components—sabot 21, base 22, and radial support 23—are rotating bodies and are coaxially aligned. This allows for stable and rapid acceleration of the entire projectile system after the rod-shaped projectile 1 is mounted on it. The sabot 21 includes axial supports 211 and mounting grooves 212 positioned at different points along its axis. Specifically, the sabot 21 also adopts a barrel-shaped structure, with the axial supports 211 forming the bottom of the barrel and the mounting groove 212 forming the sidewalls of the barrel-shaped structure.

[0063] First, due to the rod-shaped projectile, a specially designed sabot system is required to accommodate the force exerted by the rod-shaped projectile 1 on the axial support 211 of the sabot during its acceleration. In this embodiment, polyetheretherketone (PEEK) is used as the main material of the sabot 21. To prevent the projectile 1 from penetrating the sabot 21 during acceleration, a high-strength metal base 22 is also designed. The high-strength metal base 22 and the PEEK sabot 21 can withstand significant forces, enabling high-speed launch of the rod-shaped projectile 1; alternatively, lower launch speeds can be achieved, where other similar materials can be used. The base 22 is positioned at the bottom of the mounting groove 212 and abuts against the axial support 211. The radial support 23 is mounted on the groove wall of the mounting groove 212 and spaced apart from the base 22, with a cavity between them. Figure 8 and Figure 9 As shown, the right end of the mounting groove 212 has an annular step 213 coaxial with the mounting groove 212, and the radial support 23 can be embedded in the annular step 213 to form a fixed structure. The radial support 23 has a third through hole 231 along its axial direction at its radial center, and the base 22 has an abutment groove 221 at its radial center near the radial support 23. The abutment groove 221 and the third through hole 231 are used to install the rod-shaped projectile 1, that is, the rod-shaped projectile 1 passes through the third through hole 231 of the radial support 23 and abuts against the abutment groove 221 of the base 22.

[0064] In this embodiment, by setting a base 22, which is preferably made of high-strength metal components, such as T4 metal components, when the rod-shaped projectile 1 accelerates, the base 22 directly abuts against the rod-shaped projectile 1, avoiding the rod-shaped projectile 1 from directly acting on the sabot 21 during acceleration, and avoiding penetration of the axial support 211 of the sabot 21. The sabot 21 is preferably made of polyetheretherketone (PEEK) components, which can accelerate the entire projectile system through friction within the gun barrel 0; and the mounting groove 212 of the sabot 21 is used to install the base 22 and the radial support 23, so that after the rod-shaped projectile 1 is installed on the base 22 and the radial support 23, it can be ensured that the rod-shaped projectile 1 always remains coaxial with the gun barrel 0 during acceleration. Figure 6 and Figure 7 As shown, this allows for rapid and stable acceleration of the rod-shaped projectile 1, ensuring the projectile maintains a stable flight attitude upon exiting the muzzle. Furthermore, the portion between the base 22 and the radial support 23 is a cavity, effectively reducing the weight of the entire sabot system and further increasing the projectile velocity.

[0065] In this embodiment, as Figure 8 and Figure 11 As shown, the radial support 23 has a first conical surface 232 at the end away from the base 22, and the diameter of the end of the radial support 23 away from the base 22 is smaller than the diameter of the other end. The first conical surface 232 ensures that the rod-shaped projectile 1 completely enters the penetration channel 74. When the sabot system is intercepted by the interceptor 7, the radial support 23 is the first to collide with the end of the interceptor 7 with the buffer layer 72, and the radial support 23 is also the first to be damaged. By setting the first conical surface 232, the interceptor 7 performs a gradual shearing action on the radial support 23, with the initial shearing being smaller and the subsequent shearing being larger, making the shearing process more gradual and the separation of the rod-shaped projectile 1 from the radial support 23 more stable.

[0066] In this embodiment, as Figure 1 and Figure 3As shown, the outer wall of the ejection port 71 of the interceptor 7 is appropriately provided with a second conical surface 75, and the second conical surface 75 is arranged opposite to the first conical surface 232. The first conical surface 232 of the radial support 23 gradually shears the second conical surface 75 of the interceptor 7. The second conical surface 75 impacts the first conical surface 232 to form an impact strain closure, which prevents passage to the rear of the sabot system and avoids the micro-spray particles formed by the destruction of the interceptor 7 from entering the penetration channel 74. This allows the sabot system to be completely separated from the rod-shaped projectile 1 without affecting the original flight attitude of the rod-shaped projectile. The cone angle of the first conical surface 232 ensures that after the long rod projectile 1 has completely entered the ejection port 71, the second conical surface 75 impacts the first conical surface 232 to form an "impact strain closure", which prevents passage to the rear of the sabot.

[0067] To achieve a higher launch velocity, the overall weight of the projectile system needs to be reduced. This is achieved by making the base 22 a frustum shape and appropriately hollowing out the tail section of the projectile system to reduce weight and increase velocity without affecting launch stability. Figure 8 and Figure 10 As shown, considering that the force is greatest at the center of the base and decreases towards the periphery, the base 22 is designed as a frustum-shaped cone. The diameter of the end of the base 22 closest to the radial support 23 is smaller than the diameter of the other end. This reduces the overall weight of the projectile system while ensuring that the rod-shaped projectile 1 will not penetrate the base, thus increasing the projectile speed. Furthermore, the base 22 has a third conical surface 222. The outer contour of the third conical surface 222 is an arc shape that is concave inward towards the axial support 211 along the axial direction of the base 22. This concave arc design further reduces the overall projectile mass and increases the projectile speed while ensuring resistance to the force exerted during the acceleration of the rod-shaped projectile 1. The curvature of the third conical surface 222 ensures that its support performance for the rod-shaped projectile 1 is not affected while minimizing weight, and that the base 22 does not undergo plastic deformation at maximum acceleration. Except, as... Figure 7 As shown, the ratio of the distance from the bottom of the abutment groove 221 to the end of the radial support 23 away from the abutment groove 221 to the length of the rod-shaped projectile 1 is 1.9:3 to 2.1:3, such as 2:3. This ensures that the ratio of the supported length of the rod-shaped projectile 1 to the protruding length of the front end is 2:1. With the above settings, the weight can be reduced as much as possible and the projectile speed can be increased without affecting the launch stability.

[0068] The ejection device described in this embodiment, applicable to high-speed impact experiments of rod-shaped projectiles, utilizes a specially designed sabot system and ejection system to ensure that the rod-shaped projectile 1 maintains a stable flight attitude after detaching from the sabot system. Specifically, the rod-shaped projectile 1 is mounted on the sabot system and placed inside the gun barrel 0. Inside the gun barrel 0, the sabot directly rubs against the barrel, propelling the rod-shaped projectile 1 to accelerate. After detaching from the muzzle, the projectile system, consisting of the rod-shaped projectile 1 and the sabot system, passes sequentially through the fifth through hole 31 of the docking 3 and the fourth through hole 52 of the splash guard 5 before entering the collection chamber. Inside the tube 4, the rod-shaped projectile 1 enters the interceptor 7's through-passage 74 from the ejection port 71. The radial support 23 of the sabot system is intercepted by the interceptor 7. The interceptor 7 gradually dissipates the sabot's kinetic energy through the spaced buffer layers 72, thus allowing the sabot system to completely separate from the rod-shaped projectile 1. After exiting the interceptor 7's ejection port 73, the rod-shaped projectile 1 passes through the magnetic velocity measuring baffle 8 and enters the magnetic velocity measuring device 9. This ensures that the rod-shaped projectile 1 is in an ideal isolated state when passing through the magnetic velocity measuring test area and impacting the target, without being interfered with by the sabot system. In addition, this embodiment effectively reduces the mass of the projectile system, further improving the projectile's launch velocity. Moreover, the ejection device has a simple structure and manufacturing method, is low in cost, and effectively improves experimental efficiency and quality.

[0069] Using the ejection device described in this embodiment, which is suitable for high-speed impact experiments of rod-shaped projectiles, when the length-to-diameter ratio of the rod-shaped projectile 1 is 15 (e.g., 60mm in length and 4mm in diameter), the thickness of the axial support 211 can be 6mm, and the base 22 is made of T4 metal components with a center thickness of 4mm. After testing, no projectile penetration occurs when the projectile is fired at a muzzle velocity of 4km / s, allowing the projectile sabot system to be completely separated from the rod-shaped projectile 1. This ensures that the rod-shaped projectile 1 is in an ideal isolated state when passing through the magnetic velocity measurement test area and impacting the target, and is not interfered with by the projectile sabot system.

[0070] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A projectile release device suitable for high-speed impact experiments with rod-shaped projectiles, characterized in that, Including sabot systems and ejection systems; The sabot system is used to mount a rod-shaped projectile (1) and enable the rod-shaped projectile (1) to be arranged along the axial direction of the gun barrel (0); the sabot system includes a sabot (21), a base (22) and a radial support (23), the sabot (21), the base (22) and the radial support (23) are all rotating bodies, the sabot (21), the base (22) and the radial support (23) are all arranged along the coaxial line, the sabot (21) includes an axial support (211) and a mounting groove (212) arranged at different positions in its axial direction, the base (22) is arranged at the bottom of the mounting groove (212) and abuts against the axial support (211), the radial support (23) is installed on the side wall of the mounting groove (212), and the radial support (23) has a third radial support at its radial center along its axial direction. A through hole (231) is provided. The base (22) has an abutment groove (221) at one end of its radial center near the radial support (23). The abutment groove (221) and the third through hole (231) are used to install the rod-shaped projectile (1). The radial support (23) has a first conical surface (232) at one end away from the base (22). The diameter of the radial support (23) at one end away from the base (22) is smaller than the diameter of the other end. The base (22) is frustoconical. The diameter of the base (22) at one end near the radial support (23) is smaller than the diameter of the other end. The base (22) has a third conical surface (222). The outer contour of the third conical surface (222) is an arc shape that is concave towards the axial support (211) along the axial direction of the base (22). The ejection system includes a collection bucket (4), a buffer pad (6), and an interceptor (7). The collection bucket (4) has a baffle (41) at one end away from the ejection system. The baffle (41) has a first through hole (42) in its center. The buffer pad (6) is disposed inside the collection bucket (4) and abuts against the baffle (41). The buffer pad (6) has a second through hole (61). The first through hole (42) and the second through hole (61) are coaxially aligned and continuous. One end of the interceptor (7) is embedded in the second through hole (61) and the first through hole (42), and the other end has at least two spaced buffer layers (72) on its outer side along its axial direction. The thickness of layer (72) along the axial direction of interceptor (7) is the same as the distance between the two buffer layers (72). The interceptor (7) is provided with a through channel (74) for the rod-shaped projectile (1) to pass through. One end of the through channel (74) near the buffer layer (72) is a ejection port (71). The outer wall of the ejection port (71) has a second conical surface (75). The second conical surface (75) is arranged opposite to the first conical surface (232). The first conical surface (232) with radial support gradually shears the second conical surface (75) of the interceptor (7). The second conical surface (75) impacts the first conical surface (232) to form an impact strain closure, which forms a denial of passage to the rear of the sabot system.

2. The ejection device for high-speed impact experiments of rod-shaped projectiles according to claim 1, characterized in that, The end of the through channel (74) near the baffle (41) is the ejection port (73), which has a gradually changing inner diameter. The inner diameter of the ejection port (73) is larger than the inner diameter of the ejection port (71).

3. The ejection device for high-speed impact experiments of rod-shaped projectiles according to claim 1, characterized in that, The ratio of the distance from the bottom of the abutment groove (221) to the end of the radial support (23) away from the abutment groove (221) to the length of the rod-shaped projectile (1) is 1.9:3 to 2.1:

3.

4. The ejection device for high-speed impact experiments of rod-shaped projectiles according to claim 1, characterized in that, The base (22) is a high-strength metal component, the ejector (21) is a polyetheretherketone component, and the collection bucket (4) and the interceptor (7) are steel components.

5. The ejection device for high-speed impact experiments of rod-shaped projectiles according to any one of claims 1-4, characterized in that, The ejection system also includes a docking structure (3) and a splash guard (5). The splash guard (5) is installed inside the collection bucket (4). One end of the splash guard (5) abuts against the buffer pad (6), and the other end has a splash guard end plate (51). The splash guard end plate (51) has a fourth through hole (52) in the middle. One end of the docking structure (3) is embedded in the collection bucket (4) and abuts against the splash guard end plate (51). The docking structure (3) is provided with a fifth through hole (31). The fifth through hole (31), the fourth through hole (52), the second through hole (61), and the first through hole (42) are all arranged in the same axis. The fifth through hole (31) and the fourth through hole (52) are greater than or equal to the inner diameter of the gun barrel (0).

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