Multi-projectile super-high-speed launching gas gun shell carrier and unshell device structure

Abstract

The present application relates to a kind of gas shell and dehuller structure, especially to a kind of multi-shell super-high-speed launch gas shell and dehuller structure, solve the problem that existing shell and dehuller structure cannot meet the application requirement of test scene of simultaneously launching multiple heavy metal long rod shells by gas gun.The shell and dehuller structure includes shell and dehuller;The shell includes barrel-shaped outer holder and support washer, support ring and fixed pressure ring arranged in the inner cavity of outer holder in turn along the direction from barrel bottom to barrel mouth;Expansion tail is arranged on the barrel bottom of outer holder, and inclined angle recessed surface is arranged on the end face outside barrel bottom;Multiple recesses with the radial dimension of shell are uniformly distributed on the end face of support washer away from barrel bottom;Multiple through holes with the same number as recesses and coaxial with them are arranged on support ring;Fixed pressure ring is fixedly connected with outer holder;The front end of dehuller is conical frustum, and through hole with diameter smaller than the diameter of outer holder outside cylindrical surface is arranged on it;Dehuller is sleeved on the outer extension end of shell after fixed pressure ring.

Description

Technical Field

[0001] This invention relates to a gas projectile sabot and discarding device structure, and particularly to a multi-projectile ultra-high-speed gas projectile sabot and discarding device structure. Background Technology

[0002] Gas cannons are an important means of hypersonic launch and hypersonic impact damage. Gas cannons, especially two-stage gas cannons, can load the projectile to several kilometers or more before impacting the target at hypersonic speed, causing damage. During the launch process, the projectile and sabot operate in harsh launch environments such as high temperature, high pressure, high overload, and high stress. The sabot needs to be able to withstand these harsh launch environments and support the accelerated launch of the projectile, while also protecting the inner bore of the cannon barrel from scratches caused by the projectile during high-speed movement.

[0003] During hypersonic launch, the projectile is loaded from a static state to a hypersonic state, generating a significant reaction force on the sabot. This is especially true for small-diameter, heavy metal projectiles, which may penetrate the sabot during hypersonic launch. Therefore, it is usually necessary to reinforce the sabot or use lateral loading to distribute the reaction force. However, lateral loading is not directly applicable in multi-projectile launch configurations due to its complex structure and high precision requirements.

[0004] Furthermore, after launch, the sabot, being a high-speed moving mass, also possesses a certain destructive capability against the target. To ensure a clear assessment of the projectile's damage capability against the target plate after testing, the projectile and sabot need to be separated during launch. The projectile's impact attitude significantly affects its penetration depth. Traditional forced discarding designs carry a high risk of discarding failure and are prone to causing projectile trajectory deflection, thus affecting the damage effect on the target plate. In contrast, aerodynamic separation design has less impact on the projectile's trajectory. The key to aerodynamic separation design lies in the fit and airtightness design between the sabot and the projectile; the quality of this design also influences the projectile's penetration depth against the target plate to some extent. Existing conventional small-caliber light gas cannons use barrel-shaped sabots. Because these existing structures fail to adequately address the fit and airtightness design between the sabot and the projectile, most conventional small-caliber light gas cannons can only fire low-area-density projectiles (i.e., projectiles with low density and small length-to-diameter ratio), and cannot fire high-area-density, high-length-to-diameter-ratio long-rod projectiles. While small-caliber light gas cannons offer the advantage of high velocity, their application is limited to areas such as space debris protection and fragmentation protection, making it difficult to play a significant role in fields where the required damage effect is equivalent to that of a high-area-density, high-length-to-diameter-ratio long-rod projectile impacting a target at ultra-high speed. The high-area-density, high-length-to-diameter-ratio long-rod projectile in this invention refers to a projectile with an area density greater than or equal to 100 g / m³. 2Projectiles with a length-to-diameter ratio greater than or equal to 10. Furthermore, existing aerodynamic separation designs often use a center-mounted projectile method, which cannot effectively separate multiple projectiles.

[0005] Therefore, designing a multi-projectile ultra-high-speed gas cannon projectile holder and discarding sabot structure to meet the application requirements of experimental scenarios where gas cannons simultaneously fire multiple heavy metal long rod projectiles is an urgent problem to be solved. Summary of the Invention

[0006] The purpose of this invention is to provide a multi-projectile hypersonic launch gas cannon sabot and discarding sabot structure to solve the technical problems of existing gas cannon sabot and discarding sabot structures, which are prone to bottom penetration during hypersonic launch, can only meet the launch of a single projectile with low surface density and small length-to-diameter ratio and the separation of a single projectile from the sabot, and cannot meet the requirements of simultaneous launch of multiple high surface density and high length-to-diameter ratio long rod projectiles and effective separation of multiple projectiles from the sabot, thus failing to meet the application requirements of gas cannons for simultaneous launch of multiple heavy metal long rod projectiles in experimental scenarios.

[0007] To solve the above-mentioned technical problems, the technical solution adopted by the present invention is as follows:

[0008] A multi-body ultra-high-speed gas cannon projectile sabot and discarding sabot structure, characterized by:

[0009] Includes sabot and discarding sabot;

[0010] The sabot includes an outer support, a support pad, a support collar, and a fixing pressure ring;

[0011] The outer support is cylindrical, with an flared tail at one end of the cylindrical bottom surface and a flared concave surface with a flared opening facing the bottom at the center of the outer end face of the bottom surface.

[0012] The supporting pad, supporting collar, and fixing pressure ring are coaxially arranged in sequence along the direction from the bottom to the opening of the outer support in the inner cavity of the outer support. The radial dimensions of the three are adapted to the radial dimensions of the inner cavity of the outer support, and the end faces of adjacent ones are in contact. The compressive strength of the outer support, supporting collar, and fixing pressure ring is not less than 1000MPa. The compressive strength of the supporting pad is not less than 800MPa.

[0013] The support pad is located at the very bottom of the outer support barrel. On its end face away from the barrel bottom, there are multiple grooves evenly distributed circumferentially, with radial dimensions that match the radial dimensions of the projectile. The thickness between the bottom of the groove and the end face of the support pad near the bottom of the outer support barrel is greater than or equal to 5mm. The support pad is used to support and position the rear end of the projectile, prevent changes in the projectile's attitude, bear and disperse the reaction force generated during the projectile's high-speed acceleration, and bear the pressure of launch overload on the bottom of the outer support.

[0014] The support collar is provided with a plurality of through holes, which are equal in number to the grooves and are coaxially arranged in a one-to-one correspondence with the grooves; the radial dimensions of the through holes are all adapted to the radial dimensions of the projectile; the support collar is used to support the projectile and limit its vibration.

[0015] The fixing ring is fixedly connected to the outer support, and its inner diameter is larger than the diameter of the smallest circle that can cover all the through holes; the fixing ring is used to press the support collar and the support gasket, and to limit their axial movement.

[0016] The front end of the discarding device is a frustoconical shape, smaller at the front and larger at the back; a through hole is centrally located on the discarding device, the diameter of which is larger than the diameter of the smallest circle that can cover all the through holes, and smaller than the diameter of the outer cylindrical surface of the outer support; the compressive strength of the discarding device is not less than 1000MPa; the discarding device is used to fit onto the extended end of multiple projectiles after the front end of the fixing pressure ring, and removes the sabot during the firing process.

[0017] Furthermore, in order to generate a certain amount of drag without affecting the direction of the missile's flight, the angle between the generatrix of the tail divergence and the axis is 3° to 5°.

[0018] Furthermore, to improve balance and strength during flight, the angle between the angled concave generatrix and the axis is 45° to 70°.

[0019] Furthermore, the end face of the support collar away from the support pad is a flat surface or a spherical concave surface. When the end face of the support collar away from the support pad is a spherical concave surface, the airflow is more stable and the vibration of the projectile is smaller.

[0020] Furthermore, in order to prevent bottom penetration and save materials, the thickness between the bottom of the groove and the end face of the support pad near the bottom of the outer support bucket is 5mm to 10mm.

[0021] Furthermore, in order for the projectile to pass smoothly through the discarding device in various attitudes and reduce the coaxiality requirement, the diameter of the through hole is more than 1.5 times the diameter of the smallest circle that can cover all the through holes.

[0022] The sheller has a hollow stepped shaft shape at the rear end, which is thicker at the front and thinner at the back. The front end face of the hollow stepped shaft shape and the rear end face of the frustum-shaped sheller share the same base circle. The sheller is a one-piece molded part.

[0023] The shelling device has a specific strength of 200 MPa / (g / cm²). 3 )~400MPa / (g / cm 3 It is made of high-strength steel material between 1 and 2.

[0024] Furthermore, the outer support is made of polycarbonate or polyetheretherketone material.

[0025] Furthermore, the support pad has a specific strength of 200 MPa / (g / cm²). 3 )~400MPa / (g / cm 3 High-strength steel with a specific strength between 300 MPa / (g / cm²) 3 )~500MPa / (g / cm 3 It is made of aerospace-grade titanium alloy material between 1 and 2.

[0026] Furthermore, the support collar is made of material with a specific strength of 200 MPa / (g / cm²). 3 )~400MPa / (g / cm 3 It is made of high-strength steel material between 1 and 2.

[0027] Furthermore, the fixing ring is made of a material with a density of 0.9 g / cm³. 3 ~1.1g / cm 3 Made of lightweight plastic materials;

[0028] The fixing ring and the outer support are detachably fixed together;

[0029] On the end face of the fixed pressure ring away from the supporting collar, two radially penetrating U-shaped grooves are centrally symmetrically arranged. These grooves serve as process grooves for tightening the fixed pressure ring when it is fixed to the outer support. This design makes assembly easier.

[0030] The beneficial effects of this invention are:

[0031] (1) In the structure of the multi-body hypersonic launching gas projectile sabot and discarding device of the present invention:

[0032] First, by providing a breech flare at one end of the outer cylindrical barrel of the outer sabot and an angled concave surface on the outer end face of the barrel bottom, the projectile and sabot are loaded into the gun barrel together. Under the action of the aforementioned breech flare, the projectile will not undergo structural displacement due to the pressure difference caused by the vacuum in the firing tube. At the same time, under the combined action of the aforementioned breech flare and the aforementioned angled concave surface, the rapidly released driving gas can be sealed and closed, resulting in better airtightness. Therefore, the sabot in this invention can meet the airtightness requirements when firing long rod projectiles with large surface density and high length-to-diameter ratio.

[0033] Secondly, by setting a support pad at the bottom of the outer support barrel, limiting the thickness between the bottom of the groove on the support pad and the end face of the support pad near the bottom of the outer support barrel, and limiting the compressive strength of the support pad, it can not only meet the requirements of supporting and positioning the rear end of multiple projectiles and prevent changes in projectile attitude caused by launch vibration, but also effectively withstand and disperse the reaction force generated during the high-speed acceleration of multiple large-area-density, high-length-to-diameter-ratio long rod projectiles when they are launched simultaneously, bear the pressure of launch overload on the bottom of the outer support, prevent the bottom penetration phenomenon, ensure the integrity of the projectile sabot structure, and thus ensure launch safety.

[0034] Furthermore, by setting multiple grooves on the end face of the support pad away from the bottom of the barrel and setting multiple through holes on the support collar, not only can multiple projectiles be launched simultaneously, but the vibration of the projectiles under strong action conditions can also be limited by the support collar.

[0035] Furthermore, by setting the front end of the discarding device to a frustum shape with a smaller front and a larger rear, and by setting a through hole in the center of the discarding device and limiting the diameter of the through hole, the discarding device is naturally connected and fixed to the sabot by air resistance during its forward movement. It can withstand greater air resistance than the projectile, which in turn makes the air resistance on the sabot greater than the friction between the sabot and the projectile. This results in relative acceleration between the projectile and the sabot. When the relative movement distance between the projectile and the sabot is greater than the assembly length, the friction between the projectile and the sabot disappears, and the relative speed between the projectile and the sabot increases. The projectile passes through the through hole on the discarding device, achieving smooth and effective separation between the projectile and the sabot. The projectile impacts the test target plate alone, which can clearly distinguish the damage capability of the projectile to the target plate and meet the requirements of the test application.

[0036] In summary, this invention solves the technical problems of existing gas cannon sabot and discarding sabot structures, which are prone to bottom penetration during ultra-high-speed firing, can only meet the firing of a single projectile with low surface density and small length-to-diameter ratio, and can only separate a single projectile from the sabot. They cannot meet the requirements for simultaneous firing of multiple long rod projectiles with high surface density and large length-to-diameter ratio, and the effective separation of multiple projectiles from the sabot. They also cannot meet the application requirements of gas cannons for simultaneous firing of multiple heavy metal long rod projectiles in experimental scenarios.

[0037] (2) In the multi-projectile hypersonic launching gas projectile sabot and discarding device structure of the present invention, the sabot is capable of simultaneously loading multiple test projectiles, which can launch multiple test projectiles at hypersonic speed at the same time, realizing the function of launching multiple projectiles in one test; then, through the action of the discarding device, multiple test projectiles can be smoothly and effectively separated from the sabot, realizing that the test projectiles impact the test target plate independently, and the damage capability of the test projectiles to the test target plate can be clearly distinguished, which can be used in the study of the coupled damage effect of multiple test projectiles impacting the test target plate at the same time.

[0038] (3) In the multi-projectile ultra-high speed launching gas gun projectile sabot and discarding device structure of the present invention, the projectile sabot and discarding device structure is simple, easy to process and assemble, and can reduce the experimental difficulty and experimental cost. Moreover, the projectile sabot of this structure has high strength under the same material conditions, which reduces the risk of gun firing.

[0039] (4) In the multi-projectile ultra-high-speed launching gas cannon shell holder and discarding device structure of the present invention, by changing the size and material of the support pad and the support collar, the number and size of the grooves on the support pad, and the number and size of the through holes on the support collar, it can adapt to projectiles of various diameters, lengths and masses, and has good versatility and scalability. Attached Figure Description

[0040] Figure 1 This is a schematic diagram of the external structure of the projectile mounted on the sabot in an embodiment of the present invention;

[0041] Figure 2 This is an internal sectional view of the projectile mounted on the sabot in an embodiment of the present invention;

[0042] Figure 3 This is a schematic diagram of the structure of the support pad in an embodiment of the present invention;

[0043] Figure 4 This is a schematic diagram of the structure of the support collar when the end face of the support collar away from the support pad is a spherical concave surface in an embodiment of the present invention;

[0044] Figure 5 This is a schematic diagram of the structure of the fixing ring in an embodiment of the present invention;

[0045] Figure 6 This is a schematic diagram of the shelling device in an embodiment of the present invention.

[0046] The labels in the diagram are explained as follows:

[0047] 1-Sabot, 11-Outer support, 111-Expanding tail, 112-Angled concave surface, 12-Support pad, 121-Groove, 13-Support collar, 131-Through hole, 132-Spherical concave surface, 14-Fixing pressure ring, 141-U-groove, 2-Ejector, 21-Through hole, 3-Projectile body. Detailed Implementation

[0048] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments.

[0049] See Figure 1 , Figure 2 as well as Figure 6 The present invention discloses a multi-projectile ultra-high-speed gas projectile sabot and a discarding device structure, comprising a sabot 1 and a discarding device 2.

[0050] See Figure 2 The aforementioned sabot 1 includes an outer support 11, a support pad 12, a support collar 13, and a fixing pressure ring 14.

[0051] See Figure 1 and Figure 2 The aforementioned outer support 11 is cylindrical, with a flared tail 111 at one end of its outer cylindrical bottom. A flared concave surface 112, with its flared opening facing the bottom, is centrally located on the outer end face of the bottom. The inner cavity of the outer support 11 is primarily used to house the projectile 3. To create sufficient drag without affecting the flight direction of the projectile 3, the angle between the generatrix of the flared tail 111 and the axis is preferably 3°–5°, with 3° used in this embodiment. For better balance and strength during flight, the angle between the generatrix of the flared concave surface 112 and the axis is preferably 45°–70°, with 45° used in this embodiment. With this configuration, after the projectile 3, along with the sabot 1, is loaded into the gun barrel, the projectile 3 will not experience structural displacement due to the pressure difference caused by the vacuum in the launch tube, thanks to the flared tail 111. Simultaneously, the combined action of the flared tail 111 and the flared concave surface 112 effectively seals off the rapidly released propulsion gas. The outer support 11 is made of materials such as polycarbonate or polyetheretherketone. In this embodiment, polycarbonate is selected. It is heated to a molten state and then injected into a pre-formed mold to solidify and form the required shape. In terms of strength design, the outer support 11 needs to have a certain structural strength, usually requiring a compressive strength of not less than 1000 MPa, in order to withstand the thrust during hypersonic launch.

[0052] See Figure 2 The aforementioned support pad 12, support collar 13, and fixing pressure ring 14 are arranged coaxially in the inner cavity of the outer support 11 along the direction from the bottom of the barrel to the opening of the barrel. The radial dimensions of the three are adapted to the radial dimensions of the inner cavity of the outer support 11, and the end faces of adjacent two are in contact.

[0053] See Figure 2 and Figure 3The aforementioned support pad 12 is located at the very bottom of the outer support 11. On its end face away from the bottom, multiple grooves 121 with radial dimensions matching the radial dimensions of the projectile 3 are evenly distributed circumferentially. In this embodiment, the support pad 12 is tightly fixed to the very bottom of the outer support 11. The number of grooves 121 is determined by the number of projectiles 3 to be launched simultaneously; in this embodiment, three grooves are used. To ensure that bottom penetration does not occur when launching long-rod projectiles with high surface density and high aspect ratio, and to maintain the structural integrity of the sabot 1, thereby ensuring launch safety, the thickness between the bottom of the groove 121 and the end face of the support pad 12 near the bottom of the outer support 11 is typically required to be greater than or equal to 5mm, preferably 5mm to 10mm. A value within this range avoids bottom penetration and saves material; in this embodiment, the thickness is 5mm. The aforementioned support pad 12 is made of material with a specific strength of 200MPa / (g / cm²). 3 )~400MPa / (g / cm 3 High-strength steel with a specific strength between 300 MPa / (g / cm²) 3 )~500MPa / (g / cm 3 It is made of aerospace-grade titanium alloy with high specific strength through molding. In this embodiment, high-strength steel is used for molding. The support pad 12 needs to have a certain structural strength, usually requiring a compressive strength of not less than 800MPa. The support pad 12 is used to support and position the rear end of the projectile 3, prevent changes in the attitude of the projectile 3, bear and disperse the reaction force generated during the high-speed acceleration of the projectile 3, and bear the pressure on the bottom of the outer support 11 during launch overload.

[0054] See Figure 2 , Figure 3 and Figure 4 The aforementioned support collar 13 is provided with a plurality of through holes 131, which are equal in number to the aforementioned grooves 121 and are coaxially arranged in a one-to-one correspondence with them; the radial dimensions of the aforementioned through holes 131 are all adapted to the radial dimensions of the projectile 3; the end face of the aforementioned support collar 13 away from the support pad 12 is preferably a planar or spherical concave surface 132. Figure 2 The end face of the middle support collar 13 away from the support pad 12 is a plane. Figure 4 This is a schematic diagram of the structure of the support collar 13 when the end face of the support collar 13 away from the support pad 12 is a spherical concave surface. When the end face of the support collar 13 away from the support pad 12 is a spherical concave surface, the airflow is more stable and the vibration of the projectile 3 is smaller. In this embodiment, the support collar 13 is placed on the end face of the support pad 12. The aforementioned support collar 13 is typically made of a material with a specific strength of 200 MPa / (g / cm²). 3 )~400MPa / (g / cm 3The high-strength steel material between 1000 MPa and 1300 MPa is manufactured through casting. In terms of strength design, considering the accelerated load, the compressive strength of the support ring 13 is typically required to be no less than 1000 MPa. The support ring 13 is used to support the projectile 3 and limit its vibration under strong conditions.

[0055] See Figure 1 and Figure 2 The aforementioned fixing ring 14 is fixedly connected to the outer support 11, and its inner diameter is larger than the diameter of the smallest circle that can cover all the aforementioned through holes 131; in this embodiment, the aforementioned fixing ring 14 and the outer support 11 are detachably fixedly connected by threads. See also Figure 1 and Figure 5 On the end face of the aforementioned fixing ring 14 away from the supporting collar 13, two radially penetrating U-shaped grooves 141 are centrally symmetrically arranged. These grooves serve as process grooves for tightening the fixing ring 14 when it is fixed to the outer support 11. This arrangement facilitates assembly. The aforementioned fixing ring 14 is typically made of material with a density of 0.9 g / cm³. 3 ~1.1g / cm 3 Made of lightweight plastics or similar materials, this embodiment uses high molecular weight polyethylene plastic. The fixing ring 14 has a certain amount of deformability and is tightly placed inside the cylindrical cavity of the outer support 11, tightly wrapping and fixing the projectile 3. In terms of strength design, the compressive strength of the fixing ring 14 is usually required to be not less than 1000MPa. The fixing ring 14 is used to press the support collar 13 and the support pad 12, axially limiting them and constraining the position of the support collar 13, the support pad 12, and the projectile 3.

[0056] See Figure 6 The aforementioned ejector 2 has a front end shaped like a frustum-shaped cone, smaller at the front and larger at the rear. A through-hole 21 is centrally located on the ejector 2, with a diameter larger than the diameter of the smallest circle that can cover all the aforementioned through-holes 131, and smaller than the diameter of the outer cylindrical surface of the outer support 11. To ensure the projectile can pass smoothly through the ejector in various attitudes and reduce coaxiality requirements, the diameter of the through-hole 21 is preferably at least 1.5 times the diameter of the smallest circle that can cover all the aforementioned through-holes 131; in this embodiment, it is 1.5 times. In this embodiment, the rear end of the ejector 2 is a hollow stepped shaft, thicker at the front and thinner at the rear, with the front end face of the hollow stepped shaft sharing a common base circle with the rear end face of the aforementioned frustum-shaped ejector 2. The ejector 2 is a one-piece molded part. The ejector 2 is typically made of a material with a specific strength of 200 MPa / (g / cm²). 3 )~400MPa / (g / cm 3It is made of high-strength steel material between 1000 MPa and 2000 MPa. In terms of strength design, the compressive strength of the discarding device 2 is usually required to be not less than 1000 MPa. The discarding device 2 is used to be fitted onto the extended end of multiple projectiles 3 after the fixed pressure ring 14 is extended from the front end through the aforementioned through hole 21. The axis of the through hole 21 on the discarding device 2 is aligned with the axis of the sabot 1 through the projectile, so that the sabot 1 is removed during the firing process.

[0057] When the projectile is launched using the multi-projectile ultra-high-speed gas cannon sabot and discarding device structure of the present invention, the discarding device 2 is naturally connected and fixed to the sabot 1 by air resistance during its forward movement, and bears greater air resistance than the projectile 3. As a result, the air resistance on the sabot 1 is greater than the friction between the sabot 1 and the projectile 3, and a relative acceleration motion is generated between the projectile 3 and the sabot 1. When the relative movement distance between the projectile 3 and the sabot 1 is greater than the assembly length, the friction between the projectile 3 and the sabot 1 disappears, and then the relative movement speed between the projectile 3 and the sabot 1 is greater. The projectile 3 passes through the through hole 21 on the discarding device 2, realizing the smooth and effective separation of the projectile 3 and the sabot 1.

[0058] The present invention relates to a multi-projectile hypersonic launching gas cannon sabot and discarding sabot structure. The sabot can simultaneously load multiple test projectiles, enabling the simultaneous launching of multiple test projectiles at hypersonic speeds, thus achieving the function of launching multiple projectiles in a single test. Through the action of the discarding sabot, multiple test projectiles can be smoothly and effectively separated from the sabot, allowing each test projectile to impact the test target plate independently. This clearly distinguishes the destructive capability of the test projectiles on the test target plate and can be used in the study of the coupled damage effect of multiple test projectiles impacting the test target plate simultaneously.

Claims

1. A structure for a multi-body, high-speed gas cannon projectile sabot and discarding device, characterized in that: Includes a sabot (1) and a discarding sabot (2); The sabot (1) includes an outer support (11), a support pad (12), a support collar (13), and a fixing pressure ring (14); The outer support (11) is cylindrical, with an expanded tail (111) at one end of the cylindrical bottom of the outer side, and a flared concave surface (112) with a flared mouth facing the bottom is provided in the center on the outer end face of the bottom of the barrel. The support pad (12), support collar (13), and fixing ring (14) are coaxially arranged in the inner cavity of the outer support (11) along the direction from the bottom to the opening of the outer support (11). The radial dimensions of the three are adapted to the radial dimensions of the inner cavity of the outer support (11), and the end faces of adjacent ones are in contact. The compressive strength of the outer support (11), support collar (13), and fixing ring (14) is not less than 1000MPa. The compressive strength of the support pad (12) is not less than 800MPa. The support pad (12) is located at the bottom of the outer support (11) barrel. On the end face away from the barrel bottom, there are multiple grooves (121) with radial dimensions that match the radial dimensions of the projectile (3) evenly distributed along the circumference. The thickness between the bottom of the groove (121) and the end face of the support pad (12) near the bottom of the outer support (11) barrel is greater than or equal to 5mm. The support pad (12) is used to support and position the rear end of the projectile (3), prevent the attitude of the projectile (3) from changing, bear and disperse the reaction force generated during the high-speed acceleration of the projectile (3), and bear the pressure of the launch overload on the bottom of the outer support (11). The support collar (13) is provided with a plurality of through holes (131) that are equal in number to the grooves (121) and are coaxially arranged in a one-to-one correspondence with them; the radial dimensions of the through holes (131) are all adapted to the radial dimensions of the projectile (3); the support collar (13) is used to support the projectile (3) and limit its vibration; The fixing ring (14) is fixedly connected to the outer support (11), and its inner diameter is larger than the diameter of the smallest circle that can cover all the through holes (131); the fixing ring (14) is used to press the support collar (13) and the support pad (12) and to limit their axial movement. The front end of the ejector (2) is a frustoconical shape with a smaller front and a larger rear. A through hole (21) is provided in the center of the ejector (2), and the diameter of the through hole (21) is larger than the diameter of the smallest circle that can cover all the through holes (131), and smaller than the diameter of the outer cylindrical surface of the outer support (11). The compressive strength of the ejector (2) is not less than 1000MPa. The ejector (2) is used to be fitted onto the extended end of multiple projectiles (3) after the front end extends out of the fixing ring (14), and removes the sabot (1) during the firing process.

2. The multi-body hypersonic gas cannon sabot and discarding sabot structure according to claim 1, characterized in that: The angle between the generatrix of the tail (111) and the axis is 3° to 5°.

3. The multi-body hypersonic gas cannon sabot and discarding sabot structure according to claim 1, characterized in that: The angle between the generatrix of the oblique concave surface (112) and the axis is 45° to 70°.

4. The multi-projectile hypersonic gas cannon sabot and discarding sabot structure according to claim 1, characterized in that: The end face of the support collar (13) away from the support pad (12) is a plane or a spherical concave surface (132).

5. The multi-body hypersonic gas cannon sabot and discarding sabot structure according to claim 1, characterized in that: The thickness between the bottom of the groove (121) and the end face of the support pad (12) near the bottom of the outer support (11) is 5mm to 10mm.

6. The multi-body hypersonic gas cannon sabot and discarding sabot structure according to claim 1, characterized in that: The diameter of the via (21) is more than 1.5 times the diameter of the smallest circle that can cover all the through holes (131); The shelling device (2) has a hollow stepped shaft shape with a thicker front and a thinner rear end. The front end face of the hollow stepped shaft shape and the rear end face of the frustum-shaped shelling device (2) share the same bottom circle. The shelling device (2) is an integrally formed part. The shelling device (2) is made of a material with a specific strength of 200 MPa / (g / cm). 3 )~400MPa / (g / cm 3 It is made of high-strength steel material between 1 and 2.

7. The multi-body hypersonic gas cannon sabot and discarding sabot structure according to claim 1, characterized in that: The outer support (11) is made of polycarbonate or polyetheretherketone material.

8. The multi-body hypersonic gas cannon sabot and discarding sabot structure according to claim 1, characterized in that: The support pad (12) is made of material with a specific strength of 200 MPa / (g / cm). 3 )~400MPa / (g / cm 3 High-strength steel with a specific strength between 300 MPa / (g / cm²) 3 )~500MPa / (g / cm 3 It is made of aerospace-grade titanium alloy material between 1 and 2.

9. The multi-body hypersonic gas cannon sabot and discarding sabot structure according to claim 1, characterized in that: The support collar (13) is made of a material with a specific strength of 200 MPa / (g / cm). 3 )~400MPa / (g / cm 3 It is made of high-strength steel material between 1 and 2.

10. The multi-body hypersonic gas cannon sabot and discarding sabot structure according to claim 1, characterized in that: The fixing ring (14) is made of material with a density of 0.9 g / cm³. 3 ~1.1g / cm 3 Made of lightweight plastic materials; The fixed pressure ring (14) and the outer support (11) are detachably fixed together; On the end face of the fixed pressure ring (14) away from the support ring (13), there are two radially penetrating U-shaped grooves (141) symmetrically arranged. These grooves are used to tighten the fixed pressure ring (14) when it is fixed to the outer support (11).

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