Bullet support structure

Abstract

The invention relates to the technical field of ultra-high-speed launching of light-gas guns, in particular to a sabot structure which comprises a sabot body, a gas generating device and a triggering device, a sabot groove is formed in the sabot body, the sabot body comprises at least two sub-supports, the sub-supports are annularly distributed around a preset axis, and the preset axis is the central axis of the sabot groove; the gas generating device is arranged on the side, close to the preset axis, of the sub-support. The triggering device is connected with the gas generating device and used for triggering the gas generating device to generate gas to push the sub-support to be away from the preset axis. The gas generating device can be triggered through the triggering device to generate gas, so that the sub-support is pushed by air pressure to be transversely away from the central axis, and active separation between the sub-support and the projectile is achieved. And the projectile and sabot separation effect is greatly improved while the influence on the projectile state is avoided, and projectile and sabot separation under the higher speed condition is achieved.

Description

Technical Field

[0001] The present application relates to the technical field of ultra-high velocity launching of light gas guns, and in particular to a sabot structure. Background Art

[0002] The light gas gun hypervelocity launch system is widely used in the field of space hypervelocity impact such as space debris and asteroid defense. Through the two-stage / three-stage light gas gun, spherical and other specific shapes of projectiles are launched to hypervelocity (above 3km / s), simulating the hypervelocity impact process of space debris, asteroids, etc. and analyzing the impact effect to achieve the corresponding scientific or engineering purposes. When launching a specific shape projectile with a light gas gun, the projectile needs to be supported and fixed by a sabot to ensure the self-sealing performance between the projectile and the launch tube, and to ensure the collimation and flight stability of the projectile during the accelerated motion in the launch tube. At the same time, it plays a certain protective role on the launch tube to prevent the accelerated motion of the projectile in the launch tube from causing damage to the launch tube. When the projectile sabot flies out of the launch tube, due to the test requirements, the sabot must be separated from the projectile in time to ensure that only the projectile hits the test target according to the predetermined parameters, so as to achieve the predetermined test purpose. Therefore, ensuring the effective separation of the sabot of the hypervelocity flying projectile at a limited flight distance is the key to the success of the test.

[0003] At present, passive separation technology based on external force is usually used for the separation of projectiles and sabots. However, with the increase of launch speed, especially under ultra-high-speed launch conditions above 8km / s, passive projectile and sabot separation technology based on aerodynamic drag and forced action is difficult to achieve effective separation of ultra-high-speed flying projectiles and sabots within a limited flight distance. Summary of the invention

[0004] The present application provides a sabot structure to solve the problem that the passive projectile-sabot separation technology based on aerodynamic resistance and forced action in the prior art is difficult to achieve effective separation of the sabot of an ultra-high-speed flying projectile within a limited flight distance.

[0005] The present application provides a support structure, comprising: A butt plate body, on which a bullet groove is formed, the butt plate body comprises at least two sub-butt plates, which are distributed in a ring shape around a preset axis, and the preset axis is the central axis of the bullet groove; The gas generating device is arranged on one side of the sub-support close to the preset axis; The trigger device is connected to the gas generating device and is used to trigger the gas generating device to generate gas to push the sub-support away from the preset axis.

[0006] In one possible design, the support body includes a first sub-support and a second sub-support that are arranged opposite to each other, a first groove is formed on the side of the first sub-support close to the second sub-support, and a second groove is formed on the side of the second sub-support close to the first sub-support, the notch of the first groove and the notch of the second groove are arranged opposite to each other so that the first groove and the second groove together form a receiving groove, and the gas generating device is arranged in the receiving groove.

[0007] In a possible design, the groove depth directions of the first groove and the second groove are respectively perpendicular to the contact surface between the first sub-holder and the second sub-holder.

[0008] In a possible design, the center point of the receiving groove is located on the center axis of the bullet groove.

[0009] In a possible design, the gas generating device is disposed at one end of the receiving groove close to the bullet groove.

[0010] In one possible design, the gas generating device includes: A first housing is disposed in the first groove; A second shell is disposed in the second groove, and an opening end of the first shell is disposed opposite to an opening end of the second shell; The gas product is filled in the first shell and the second shell respectively.

[0011] In a possible design, the cartridge body has a first end face and a second end face that are arranged opposite to each other, the cartridge slot is opened on the first end face, the notch of the receiving slot extends to the second end face, the trigger device is arranged in the receiving slot, and the trigger device includes: A piezoelectric sensor is disposed in the receiving groove; The lead wire is arranged in the receiving groove, one end of which is connected to the piezoelectric sensor and the other end of which is in contact with the gas product.

[0012] In a possible design, the trigger device further includes: A force transmission sheet, arranged on the second end surface; The buffer rod is arranged in the accommodating groove, one end of which is connected to the force transmission sheet, and the other end of which is connected to the piezoelectric sensor.

[0013] In one possible design, the accommodating groove includes a first groove section, a second groove section, a third groove section, a fourth groove section and a fifth groove section which are connected in sequence, the force transmission plate is arranged in the first groove section, the elastic rod is arranged in the second groove section, the piezoelectric sensor is arranged in the third groove section, the lead wire is arranged in the fourth groove section, and the gas generating device is arranged in the fifth groove section.

[0014] In a possible design, the axial length of the first slot segment is greater than the thickness of the force transmission plate, and the buffer rod can cause the force transmission plate to undergo axial displacement along the inner wall of the first slot segment by extending and retracting.

[0015] The beneficial effects of this application are as follows: The support structure of the present application includes a plurality of sub-supports distributed in a circular array along the central axis, and a gas generating device is arranged on the side of the sub-support close to the central axis. The trigger device can trigger the gas generating device to generate gas, thereby using gas pressure to push the sub-support away from the central axis, thereby realizing active separation between the sub-support and the projectile. While avoiding affecting the state of the projectile, the separation effect of the projectile and support is greatly improved, and the projectile and support separation under higher speed conditions is realized. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the specific implementation methods of the present application or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0017] Figure 1 A front view of the support structure provided in an embodiment of the present application; Figure 2 A top view of the support structure provided in an embodiment of the present application; Figure 3 A front view of the support structure provided in an embodiment of the present application; Figure 4 A rear view of the support structure provided in an embodiment of the present application; Figure 5 A schematic diagram of the structure of a trigger device of a support structure provided in an embodiment of the present application; Figure 6 A schematic diagram of the structure of a gas generating device of a support structure provided in an embodiment of the present application; Figure 7 A schematic diagram of generating the lateral separation force of the support structure provided in an embodiment of the present application; Figure 8 Schematic diagram of the projectile and support separation process of the support structure provided in an embodiment of the present application.

[0018] Reference numerals: 100, bullet support body; 110, first sub-support; 111, first groove; 120, second sub-support; 121, second groove; 130, accommodating groove; 131, first groove section; 132, second groove section; 133, third groove section; 134, fourth groove section; 135, fifth groove section; 140, bullet groove; 150, first end face; 160, second end face; 200, gas generating device; 210, first shell; 220, second shell; 230, gas product; 240, fuse; 300, trigger device; 310, piezoelectric sensor; 320, lead; 330, force transmission plate; 340, buffer rod; 400, launch tube; 500, bullet shield; 600, projectile. DETAILED DESCRIPTION

[0019] The technical solution of the present application will be described clearly and completely below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present application.

[0020] At present, passive projectile-suspension separation is mainly achieved in the following two ways: The first method is to achieve separation of the projectile and the sabot through aerodynamic resistance: by pre-maintaining a certain low air pressure between the launch tube and the target chamber, the sabot of the projectile flying out of the launch tube is affected by aerodynamic resistance, among which the sabot structure is affected by aerodynamic resistance more. At the same time, the special petal design of the sabot structure makes the sabot structure spread out in the direction of the vertical flight trajectory under the action of aerodynamic resistance. The spread sabot structure is separated from the projectile by a bullet-blocking plate through which the projectile can pass, thereby achieving the purpose of separating the projectile and the sabot. However, with the increase of the launch speed, the flight time of the projectile and the sabot is shortened at the same target distance, and the separation effect of the projectile and the sabot based on aerodynamic resistance is reduced, resulting in the failure of the separation of the projectile and the sabot. In order to improve the separation effect, the aerodynamic resistance can be increased by increasing the air pressure, but the increase in aerodynamic resistance will greatly reduce the speed of the projectile, resulting in a decrease in the speed of the projectile to the target, which cannot meet the test speed requirements.

[0021] The second method is to separate the projectile and the sabot through forced action: by setting a blocking device along the flight trajectory in front of the launch tube, and setting a through hole that is larger than the diameter of the projectile and smaller than the sabot along the flight trajectory of the blocking device, the projectile can pass through when the projectile and the sabot fly out of the launch tube and reach the blocking device along the flight trajectory, and the sabot is intercepted due to the blocking effect, thereby achieving the purpose of separating the projectile and the sabot. However, with the increase of the launch speed, the relative impact speed between the sabot and the blocking device is higher, and the impact force of the blocking device on the sabot is stronger. On the one hand, the strong impact may be transmitted to the projectile to interfere with the normal flight state of the projectile. On the other hand, the strong impact may cause the sabot structure to break. The broken sabot structure follows the projectile through the through hole and hits the test target, thereby causing a change in the test state, interfering with the normal test result analysis, and even causing the test failure.

[0022] In order to ensure that the sabot of the hyperspeed flying projectile 600 can be effectively separated in a limited flight distance, especially under the hyperspeed launch condition of more than 8km / s, the embodiment of the present application provides a sabot structure, which is combined with Figure 1-Figure 8 , describing the support structure provided in the embodiments of the present application.

[0023] Reference Figure 1 , Figure 3 As shown, the sabot structure provided in the embodiment of the present application includes a sabot body 100, a gas generating device 200 and a triggering device 300. The sabot body 100 is generally a cylindrical structure adapted to the shape of the launch tube 400, so that the sabot body 100 has a first end face 150 (i.e., the front end face of the sabot body 100) and a second end face 160 (i.e., the rear end face of the sabot body 100) arranged opposite to each other, and the bullet groove 140 is generally opened at the center of the front end face of the sabot body 100, and the bullet groove 140 is hemispherical, and the bullet groove 140 is used to place the projectile 600. The triggering device 300 is arranged near the rear end face of the sabot body 100, and the gas generating device 200 is arranged inside the sabot body 100.

[0024] Specifically, the support body 100 includes at least two sub-supports, for example, two, three, four, etc., all of which are distributed in a ring around a preset axis to form a support body 100 of a columnar structure, wherein the preset axis is the central axis of the bullet groove 140. The gas generating device 200 is arranged on the side of the sub-support close to the preset axis, that is, the inner side of the sub-support. The trigger device 300 is connected to the gas generating device 200, and the trigger device 300 generates gas by triggering the gas generating device 200, and uses the gas pressure to push the sub-support outward, so that each sub-support is separated from the projectile 600. In this way, there is no need to rely on an external mechanism, and the sub-support and the projectile 600 are actively separated, which can effectively avoid affecting the flight state of the projectile 600 during the separation process, greatly improve the separation effect of the projectile 600 support, and thus achieve the separation of the projectile 600 support under higher speed conditions.

[0025] Reference Figure 1 , Figure 2 As shown, in some embodiments provided by the present application, the main body 100 of the cartridge includes two oppositely arranged sub-carriers, namely, a first sub-carrier 110 and a second sub-carrier 120. The first sub-carrier 110 and the second sub-carrier 120 have the same shape, both of which are semi-cylinders. The contact surface between the first sub-carrier 110 and the second sub-carrier 120 is a plane. The first sub-carrier 110 and the second sub-carrier 120 of the two semi-cylinders are in contact with each other to form a complete cylindrical structure of the cartridge main body 100. Since the number of sub-carriers is only two, namely, the first sub-carrier 110 and the second sub-carrier 120, it is convenient to assemble before firing and to recover the sub-carriers after firing. Specifically, a first groove 111 is formed on a plane of the first sub-holder 110 close to the second sub-holder 120, and a second groove 121 is formed on a plane of the second sub-holder 120 close to the first sub-holder 110, and the notch of the first groove 111 and the notch of the second groove 121 are arranged opposite to each other, so that the first groove 111 and the second groove 121 form a receiving groove 130, and the gas generating device 200 is arranged in the receiving groove 130. In this way, when the gas generating device 200 starts to generate gas, as the gas pressure continues to increase, the gas pressure generates an outward thrust, so that the first sub-holder 110 and the second sub-holder 120 quickly move away from each other.

[0026] Reference Figure 2 As shown, in some preferred embodiments, the groove depth direction of the first groove 111 and the second groove 121 are respectively perpendicular to the contact surface between the first sub-holder 110 and the second sub-holder 120. For example, the first groove 111 and the second groove 121 are both cylindrical grooves, and the depth direction of the cylindrical grooves is perpendicular to the contact surface between the first sub-holder 110 and the second sub-holder 120. The notches of the two cylindrical grooves are opposite, so that when the gas generating device 200 starts to generate gas, as the gas pressure in the first groove 111 and the second groove 121 continues to increase, when the first sub-holder 110 and the second sub-holder 120 lose the constraint of the launch tube 400, the high-pressure gas will be ejected from the notch, thereby only generating a thrust perpendicular to the contact surface, so that the first sub-holder 110 and the second sub-holder 120 are simultaneously and rapidly away from each other in the direction perpendicular to the contact surface, and separated from the projectile 600.

[0027] Reference Figure 2 As shown, in some specific embodiments, the center point of the receiving groove 130 is located on the central axis of the bullet groove 140. In this way, the first sub-holder 110 and the second sub-holder 120 can be prevented from rotating at the moment of separation, and the accidental collision with the projectile 600 during rotation can be avoided, thereby ensuring the separation effect and separation speed of the first sub-holder 110, the second sub-holder 120 and the projectile 600.

[0028] Reference Figure 2As shown, in some embodiments provided in the present application, the gas generating device 200 is disposed at one end of the receiving groove 130 close to the bullet groove 140. Since the projectile 600 is mounted on the first end face 150, that is, the front end face, of the bullet support body 100, the gas generating device 200 is disposed at a position close to the front end face of the receiving groove 130. In this way, the lateral thrust generated by the gas generating device 200 will make the first sub-support 110 and the second sub-support 120 open at a greater angle at the head than at the tail, thereby smoothly disengaging from the projectile 600 at the head, avoiding the squeezing effect on the projectile 600 during the separation process of the first sub-support 110 and the second sub-support 120, and avoiding the disturbance of the state of the projectile 600 during the separation process.

[0029] Reference Figure 6 As shown, in some embodiments provided in the present application, the gas generating device 200 includes a first shell 210, a second shell 220 and a gas product 230. The first shell 210 and the second shell 220 have the same structure, and are both cylindrical shells matching the first groove 111 and the second groove 121. The first shell 210 is arranged in the first groove 111, and the second shell 220 is arranged in the second groove 121. The opening end of the first shell 210 is arranged opposite to the opening end of the second shell 220, and the gas product 230 is respectively filled in the first shell 210 and the second shell 220. Specifically, the first shell 210 and the second shell 220 are made of a metal material with high strength. The gas product 230 uses rocket engine solid fuel or low-intensity gunpowder and other materials. It can burn violently to produce high-pressure gas by triggering ignition. When the first sub-holder 110 and the second sub-holder 120 lose the constraint of the launch tube 400, the high-pressure gas is ejected from the opening ends of the first shell 210 and the second shell 220 respectively. The opening ends of the first shell 210 and the second shell 220 are the high-pressure gas ejection surfaces. In this way, except for the high-pressure gas ejection surface, the other surfaces are covered by the cylindrical first shell 210 and the second shell 220, thereby forming a high-strength protective layer to prevent the high-pressure gas from ejecting from other surfaces to damage the structure of the cartridge case, and ensure that the high-pressure gas is ejected only from the ejection surface. The reaction force generated by the high-pressure gas ejection pushes the first sub-holder 110 and the second sub-holder 120 laterally away from the flight trajectory, thereby achieving the purpose of separating the cartridge case from the projectile 600.

[0030] In some specific embodiments, the gas product 230 filled in the first shell 210 and the second shell 220 is also connected by a fuse 240, and the middle part of the fuse 240 is connected to the trigger device 300. In this way, it is ensured that the gas product 230 filled in the first shell 210 and the second shell 220 can be triggered and ignited at the same time, which is conducive to the gas product 230 filled in the first shell 210 and the second shell 220 to produce gas at the same time, balancing the air pressure on both sides, thereby balancing the thrust of pushing the ball away from the flight trajectory laterally.

[0031] Reference Figure 2 As shown, the slot of the receiving slot 130 extends to the second end surface 160, and the trigger device 300 is disposed in the receiving slot 130. Figure 5 As shown, the trigger device 300 includes a piezoelectric sensor 310 and a lead 320. The piezoelectric sensor 310 and the lead 320 are respectively arranged in the receiving groove 130. One end of the lead 320 is connected to the piezoelectric sensor 310, and the other end of the lead 320 is in contact with the gas product 230. When the light gas gun is fired, the high-pressure propulsion gas of the light gas gun acts on the piezoelectric sensor 310. The piezoelectric sensor 310 is subjected to force due to the piezoelectric effect, and a high-voltage electric spark will be generated. The high-voltage electric spark acts on the gas product 230 through the lead 320, thereby igniting the gas product 230, completing the triggering ignition of the gas product 230.

[0032] Considering that the force of the high-pressure propellant gas of the light gas gun is relatively large, in order to protect the piezoelectric sensor 310, the trigger device 300 also includes a force transmission sheet 330 and a buffer rod 340. The force transmission sheet 330 is arranged at the second end surface 160. The force transmission sheet 330 is made of a hard material and is used to directly bear the force of the high-pressure propellant gas of the light gas gun. The buffer rod 340 is arranged in the receiving groove 130. The buffer rod 340 has a certain elasticity, such as a spring rod. One end of the buffer rod 340 is connected to the force transmission sheet 330, and the other end of the buffer rod 340 is connected to the piezoelectric sensor 310. In this way, the high-pressure propellant gas of the light gas gun first acts on the force transmission sheet 330, and then the buffer rod 340 buffers a part of the impact force by contraction, and finally acts on the piezoelectric sensor 310, thereby protecting the piezoelectric sensor 310.

[0033] In some specific embodiments, the accommodating groove 130 includes a first groove section 131, a second groove section 132, a third groove section 133, a fourth groove section 134 and a fifth groove section 135 which are connected in sequence, and the force transmission piece 330 is arranged in the first groove section 131, and the axial length of the first groove section 131 is greater than the thickness of the force transmission piece 330. The elastic rod is arranged in the second groove section 132, and the second groove section 132 matches the shape of the elastic rod, and the axial length of the second groove section 132 is less than the length of the elastic rod in the natural state, so as to ensure that in the natural state of the buffer rod 340, there is a gap between the force transmission piece 330 and the right end of the first groove section 131, so that the force transmission piece 330 can move axially in the first groove section 131. When subjected to the high-pressure propellant gas of the light gas gun, the buffer rod 340 can cause the force transmission piece 330 to move axially along the inner wall of the first groove section 131 by telescoping, thereby absorbing part of the impact force. The piezoelectric sensor 310 is disposed in the third slot section 133, and the third slot section 133 matches the shape of the piezoelectric sensor 310. The lead wire 320 is disposed in the fourth slot section 134, and the fourth slot section 134 matches the shape of the lead wire 320. The gas generating device 200 is disposed in the fifth slot section 135, and the fifth slot section 135 matches the overall shape of the gas generating device 200.

[0034] Reference Figure 7 As shown, when the sabot body 100 in the launch tube 400 is subjected to the high-pressure gas load launched by the light gas gun, the force transmission piece 330 and the buffer rod 340 complete the triggering of the piezoelectric sensor 310, and the piezoelectric sensor 310 generates a high-voltage electric spark which is transmitted to the ignition wire 240 through the lead 320, and the ignition wire 240 completes the ignition of the gas product 230 such as the filled low-intensity gunpowder or solid rocket engine fuel. After the gas product 230 is ignited and burned, it generates high-pressure gas in a small space under the constraints of the first shell 210, the second shell 220, the sabot body 100 and the launch tube 400. When the constraints of the launch tube 400 disappear, the high-pressure gas is ejected from the open ends of the first shell 210 and the second shell 220, generating a lateral thrust perpendicular to the flight trajectory.

[0035] The active separation process of the support structure of this application refers to Figure 8As shown, the separation process is divided into three stages: I, II, and III. Stage I is the launch preparation stage, at which the trigger device 300, the gas generating device, and the projectile 600 are respectively installed and fixed in the sabot body 100, and the installed projectile 600 sabot structure is placed at the end of the launch tube 400. Stage II is the stage of flight in the launch tube 400 after triggering and ignition. Under the action of high-pressure gas emitted by the light gas gun, the trigger device 300 generates high-voltage electric sparks that are transmitted to the gas generating device through the lead 320 to complete the ignition of the gas generating device. During the flight of the launch tube 400, the gas generating device continuously reacts to generate a large amount of gas. Due to the constraints of the first shell 210, the second shell 220, the sabot body 100 and the launch tube 400, the generated gas is compressed in a small space, causing the gas pressure to rise rapidly, providing a power source for the lateral separation of the sabot of the projectile 600 after it flies out of the launch tube 400. Stage III is the separation stage of the sabot of the projectile 600 flying out of the launch tube 400. In this stage, the high-pressure gas generated in the sabot body 100 loses its lateral constraint, is ejected from the injection port, and generates a reaction force to push the first sub-suspension 110 and the second sub-suspension 120 to fly away from the flight trajectory. After the sabot of the projectile 600 is separated, the projectile 600 flies through the through hole of the bullet-blocking plate 500, which has a diameter slightly larger than that of the projectile 600, and the sabot body 100 is completely intercepted by the bullet-blocking plate 500, thereby avoiding sabot material flying through the through hole and causing test failure, and realizing the complete active separation of the sabot of the projectile 600.

[0036] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0037] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of this application, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0038] In this application, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0039] In the present application, the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0040] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and cannot be understood as limitations on the present application. Ordinary technicians in this field can change, modify, replace and modify the above embodiments within the scope of the present application.

Claims

1. A support structure, characterized in that: include: A buttstock body, wherein a bullet groove is formed on the buttstock body, the buttstock body comprises at least two sub-buttstocks, and the sub-buttstocks are distributed in a ring shape around a preset axis, and the preset axis is the central axis of the bullet groove; A gas generating device is arranged on a side of the sub-holder close to the preset axis; A trigger device is connected to the gas generating device and is used to trigger the gas generating device to generate gas to push the sub-support away from the preset axis.

2. The support structure according to claim 1, characterized in that: The support body includes a first sub-support and a second sub-support arranged opposite to each other, wherein the first sub-support is formed with a first groove on the side close to the second sub-support, and the second sub-support is formed with a second groove on the side close to the first sub-support, and the notch of the first groove and the notch of the second groove are arranged opposite to each other so that the first groove and the second groove together form a receiving groove, and the gas generating device is arranged in the receiving groove.

3. The support structure according to claim 2, characterized in that: The groove depth directions of the first groove and the second groove are respectively perpendicular to the contact surfaces of the first sub-holder and the second sub-holder.

4. The support structure according to claim 3, characterized in that: The center point of the accommodating groove is located on the central axis of the elastic groove.

5. The support structure according to any one of claims 2 to 4, characterized in that: The gas generating device is arranged at one end of the containing groove close to the elastic groove.

6. The support structure according to any one of claims 2 to 4, characterized in that: The gas generating device comprises: A first housing, disposed in the first groove; A second shell is disposed in the second groove, wherein an opening end of the first shell is disposed opposite to an opening end of the second shell; The gas product is filled in the first shell and the second shell respectively.

7. The support structure according to claim 6, characterized in that: The bullet support body has a first end face and a second end face that are arranged opposite to each other, the bullet groove is opened on the first end face, the notch of the receiving groove extends to the second end face, the trigger device is arranged in the receiving groove, and the trigger device includes: A piezoelectric sensor is disposed in the receiving groove; A lead wire is arranged in the receiving groove, one end of which is connected to the piezoelectric sensor, and the other end of which is in contact with the gas product.

8. The support structure according to claim 7, characterized in that: The trigger device also includes: A force transmission sheet, arranged on the second end surface; A buffer rod is arranged in the accommodating groove, one end of which is connected to the force transmission sheet, and the other end of which is connected to the piezoelectric sensor.

9. The support structure according to claim 8, characterized in that: The accommodating groove includes a first groove section, a second groove section, a third groove section, a fourth groove section and a fifth groove section which are connected in sequence, the force transmission plate is arranged in the first groove section, the elastic rod is arranged in the second groove section, the piezoelectric sensor is arranged in the third groove section, the lead wire is arranged in the fourth groove section, and the gas generating device is arranged in the fifth groove section.

10. The support structure according to claim 9, characterized in that: The axial length of the first slot section is greater than the thickness of the force transmission plate, and the buffer rod can cause the force transmission plate to undergo axial displacement along the inner wall of the first slot section by telescoping.

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