Super-gravity field penetration simulation test device and method

Abstract

The invention discloses a hypergravity field penetration simulation test device, which comprises an air cannon, a launching bullet, a support mechanism, a penetration test mechanism and an acceleration mechanism, and is characterized in that the launching bullet is arranged in the air cannon, the air cannon is arranged in the support mechanism, the bottom of the support mechanism is connected with the top of the penetration test mechanism, and the acceleration mechanism is arranged in the support mechanism; high-pressure gas is filled into the air cannon to push the launching bomb to realize launching; the acceleration mechanism comprises a centrifugal machine and a hanging basket, and the acceleration mechanism provides a super-gravity field environment for the penetration simulation test through rapid rotation; the launching bomb intrudes into the test device to simulate the penetration process. According to the hypergravity field penetration simulation test device provided by the invention, the hypergravity field is applied to the test model through the centrifugal machine, and the test model and a prototype are similar in power, motion and energy, so that a more real penetration process is simulated, various parameters can be conveniently changed, multiple repeated tests can be carried out, and the test efficiency is improved. The test efficiency and the refinement degree are greatly improved, the cost is remarkably reduced, and damage is reduced.

Description

Technical Field

[0001] The invention relates to the technical field of penetration weapon testing, and in particular to a hypergravity field penetration simulation test device and method. Background Art

[0002] With the continuous development of military technology, new weapons such as precision-guided weapons and earth-penetrating bombs pose a serious threat to protective engineering. Penetration simulation research not only helps to improve the effectiveness of weapons and protective engineering capabilities, but also ensures the safety of infrastructure, promotes the development of new materials and technologies, deepens the understanding of physical phenomena, and promotes the advancement of experimental technology and numerical simulation methods.

[0003] At present, field tests for penetration simulation are complex, costly, and risky. In addition, it is difficult to adjust the launch device, and it is difficult to systematically study the effects of attack angle and velocity differences on penetration depth. Ground model tests have similarity issues. From the perspective of energy conservation, penetration is the process of converting the kinetic energy and gravitational potential energy of the missile into the deformation and crushing energy of concrete or rock and soil. During the penetration process, the friction between the missile and the medium is also an important way to dissipate energy. The energy consumed by friction is closely related to the stress and friction coefficient on the missile wall. Conventional scaled models are difficult to meet the similarity requirements of simulation tests, that is, the test results of scaled models cannot fully and truly reflect the results of the corresponding prototype real test.

[0004] Although the hypergravity field, the stress field of large-volume structures and the nonlinear properties of materials can basically meet the similarity, providing conditions for more accurate simulation of missile penetration effects, there is currently a lack of research on related devices and methods.

[0005] Therefore, there is an urgent need to develop a test device that can use a scaled model to conduct penetration weapon simulation tests and meet the similarity requirement, that is, it can truly reflect the results of prototype tests conducted on the ground. Summary of the invention

[0006] In order to solve the problems existing in the above-mentioned prior art, the present invention provides a hypergravity field penetration simulation test device and method. Specifically, the present invention includes the following contents.

[0007] The present invention provides a hypergravity field penetration simulation test device, comprising an air cannon (1000), a launcher (2000), a support mechanism (3000), a penetration test mechanism (4000) and an acceleration mechanism (5000), wherein:

[0008] The projectile (2000) is placed in the air cannon (1000), and the air cannon (1000) is arranged in the support mechanism (3000). The bottom of the support mechanism (3000) is connected to the top of the penetration test mechanism (4000). The air cannon (1000) comprises a barrel (1100), a piston (1200) and a launch tube (1300). The top end of the launch tube (1300) is connected to the bottom end of the barrel (1100). The barrel (1100) is provided with a main air chamber (1120) and a secondary air chamber (1130). The top surface of the secondary air chamber (1130) A first air inlet (1131) and an exhaust port (1132) are provided, the auxiliary air chamber (1130) is connected to an external air storage device via the first air inlet (1131) and is used to deliver high-pressure gas to the auxiliary air chamber (1130) and the main air chamber (1120), the main air chamber (1120) is connected to a launch tube (1300), the exhaust port (1132) discharges the high-pressure gas to drive the piston (1200) to move toward the auxiliary air chamber (1130), and the high-pressure gas in the main air chamber (1120) enters the launch tube (1300) to push the launch bullet (2000) to achieve launch;

[0009] The acceleration mechanism (5000) comprises a centrifuge (5100) and a hanging basket (5200), wherein the centrifuge (5100) comprises a base (5110) and a rotating arm (5120), wherein the rotating arm (5120) is mounted on the base (5110), wherein a driving motor is arranged in the base (5110), wherein the driving motor is used to provide power to the rotating arm (5120) so that the rotating arm (5120) rotates horizontally around the base (5110), wherein the hanging basket (5200) is arranged at both ends of the rotating arm (5120), wherein the air cannon (1000), the supporting mechanism (3000) and the penetration test mechanism (4000) are arranged in the hanging basket (5200) at one end, and wherein the acceleration mechanism (5000) provides a hypergravity field environment for a penetration simulation test through rapid rotation.

[0010] In certain embodiments, according to the hypergravity field penetration simulation test device described in the present invention, the barrel (1100) is cylindrical in shape, the piston (1200) is arranged in the barrel (1100), and the piston (1200) includes a piston plate (1210) and a piston rod (1220). Under the action of pressure difference, the piston (1200) is in a blocked or disengaged state with the entrance of the launch tube (1300). When the high-pressure gas in the main air chamber (1120) enters the launch tube (1300), it pushes the launch projectile (2000) to move along the launch tube (1300) to achieve launch.

[0011] In certain embodiments, according to the hypergravity field penetration simulation test device described in the present invention, the support mechanism (3000) includes a support frame (3100) and a support base (3200), and the support frame (3100) and the support base (3200) are frame structures. The support frame (3100) is provided with a rotating shaft (3110) for adjusting the firing angle of the air cannon (1000), and the rotating shaft (3110) is connected to the support frame (3100) through a nut.

[0012] In certain embodiments, according to the hypergravity field penetration simulation test device described in the present invention, a laser speed measurement system (1310) is provided on the launch tube (1300), and the laser speed measurement system (1310) includes two sets of laser transceiver devices, one set is close to the entrance of the launch tube (1300) as an entrance laser transceiver device (1311), and the other set is close to the exit of the launch tube (1300) as an exit laser transceiver device (1312), each set of laser transceiver devices includes a laser, and the laser is used to generate a pulse signal when a launch bullet (2000) passes through, and the launch speed of the launch bullet (2000) is calculated by recording the time interval and spacing of the pulse signals of the two sets of laser transceiver devices.

[0013] In certain embodiments, according to the hypergravity field penetration simulation test device described in the present invention, the penetration test mechanism (4000) includes a model box (4100) with an opening at the upper end, and a target model (4200) is arranged in the model box (4100). The target model (4200) is a scaled model of the protective structure, and the target model (4200) is placed at the bottom of the model box (4100) so that the air cannon (1000) can shoot at different incident angles.

[0014] In certain embodiments, according to the hypergravity field penetration simulation test device described in the present invention, a protective device (4300) is also provided in the model box (4100), and the protective device (4300) is placed on the bottom or side wall of the model box (4100) to prevent the projectile (2000) from penetrating the model box (4100) and ejecting out of the box.

[0015] In certain embodiments, according to the hypergravity field penetration simulation test device described in the present invention, the protective device (4300) is made of a material that can generate a buffer and has a certain elasticity, and the material includes a rubber pad, a silicone pad or compacted soil.

[0016] In certain embodiments, according to the hypergravity field penetration simulation test device described in the present invention, a one-way valve (1211) is provided at the connection between the piston (1200) and the barrel (1100), and the one-way valve (1211) is used to control the gas to flow only from the auxiliary air chamber (1130) to the main air chamber (1120) and not to flow in the opposite direction.

[0017] In certain embodiments, according to the hypergravity field penetration simulation test device described in the present invention, a pressure sensor for real-time monitoring of pressure changes in the main air chamber (1120) is provided on the side wall of the barrel (1100), and a first air inlet (1131), an exhaust port (1132) and a valve are provided on the top surface of the auxiliary air chamber (1130). By adjusting the valve, the pressure in the main air chamber (1120) can be adjusted, thereby controlling the firing speed of the projectile (2000).

[0018] The present invention also provides a hypergravity field penetration simulation test method, using the above-mentioned hypergravity field penetration simulation test device to conduct a test, the method comprising the following steps:

[0019] S1: placing the projectile (2000) in a launching tube (1300) of an air cannon;

[0020] S2: High-pressure gas is charged into the auxiliary air chamber (1130) of the air cannon, and the high-pressure gas pushes the piston (1200) downward to block the inlet of the launch tube (1300), and the valve at the exhaust port (1132) is opened, and the high-pressure gas in the auxiliary air chamber (1130) is quickly released from the exhaust port (1132). Under the action of the pressure difference, the piston (1200) quickly moves upward to separate from the inlet of the launch tube (1300), and the high-pressure gas in the main air chamber (1120) enters the launch tube (1300), pushing the launch bullet (2000) to be launched;

[0021] S3: performing a penetration test in a hypergravity field environment generated by the acceleration mechanism (5000);

[0022] S4: measuring the launch speed of the projectile (2000) by means of a laser speed measurement system (1310), and collecting penetration depth, crack shape and target damage data by means of a sensor;

[0023] S5: Perform penetration simulation analysis based on the obtained data.

[0024] The beneficial effects of the present invention include:

[0025] (1) More accurate simulation of weapon penetration effects under laboratory conditions: By applying a hypergravity field to the scaled model, the stress field and material nonlinear properties of the large-volume structure under the hypergravity field can basically meet the similarity and test similarity rate, which provides conditions for more accurate simulation of weapon penetration effects and achieves similarity in power, motion and energy. It can simulate the penetration effect of penetrating weapons under laboratory conditions and provide a basis for the study of the penetration effect of large-volume structures. The test results can provide an important basis for the verification of theoretical models, contribute to the continuous development of impact dynamics theory, and promote the establishment and development of new theoretical models.

[0026] (2) Improving the efficiency and refinement of the test: The present application uses a test device that applies a hypergravity field to conduct simulation tests on penetration weapons, which can provide a test method for the penetration and damage effects of different media and complex structures, calibrate the penetration depth under different penetration speeds, and conveniently change various parameters to conduct multiple repeated tests, thus avoiding the problem that it is difficult for real launch devices to flexibly adjust factors such as angles and speeds, thereby greatly improving the efficiency and refinement of the test;

[0027] (3) Reduce costs and damage: This application uses scaled models and test equipment to conduct tests, avoiding the serious damage and huge costs of real ground scene tests. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 Schematic diagram of an exemplary air cannon of the present invention.

[0029] Figure 2 It is a cross-sectional view of an exemplary support mechanism of the present invention.

[0030] Figure 3 It is a cross-sectional view of an exemplary penetration test mechanism, a support mechanism and an air cannon of the present invention.

[0031] Figure 4 It is a schematic diagram of an exemplary overall structure of the present invention.

[0032] Figure 5 It is a schematic diagram of the stress state of the exemplary scaled model and prototype of the present invention.

[0033] Figure 6 Schematic diagram of verification test of target models A and target models B of different sizes in different hypergravity environments according to the present invention.

[0034] Description of reference numerals:

[0035] 1000. air cannon; 1100. cannon barrel; 1110. baffle; 1120. main air chamber; 1121. second air inlet; 1122. third air inlet; 1130. auxiliary air chamber; 1131. first air inlet; 1132. exhaust port; 1200. piston; 1210. piston plate; 1211. check valve; 1220. piston rod; 1300. launch tube; 1310. laser test system; 1311. inlet laser transceiver; 1312. outlet laser transceiver; 2000 .launching projectile; 3000. supporting mechanism; 3100. supporting frame; 3110. rotating shaft; 3200. supporting base; 3210. cover plate; 4000. penetration test mechanism; 4100. model box; 4200. target model; 4210. target model A; 4220. target model B; 4300. protective device; 5000. accelerating mechanism; 5100. centrifuge; 5110. base; 5120. rotating arm; 5310. slip ring; 5200. hanging basket; 5300. instrument cabin. DETAILED DESCRIPTION

[0036] Various exemplary embodiments of the present invention will now be described in detail. This detailed description should not be considered as limiting the present invention, but should be understood as a more detailed description of certain aspects, features, and embodiments of the present invention.

[0037] It should be understood that the terms described in the present invention are only for describing special embodiments and are not intended to limit the present invention. In addition, for the numerical range in the present invention, it should be understood that the upper and lower limits of the scope and each intermediate value therebetween are specifically disclosed. Each smaller range between the intermediate value in any stated value or stated range and any other stated value or intermediate value in the described range is also included in the present invention. The upper and lower limits of these smaller ranges can be independently included or excluded in the scope.

[0038] Unless otherwise specified, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the art to which the invention belongs. Although the present invention describes only preferred structures and materials, any structures and materials similar or equivalent to those described herein may also be used in the implementation or testing of the present invention.

[0039] In addition, the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. in the specification and claims indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, terms such as "first", "second", etc. are also used to describe various elements, regions, parts, etc., and do not specifically refer to order or sequence, and should not be regarded as limiting. It should be understood that the terms used in this way are interchangeable under appropriate conditions, and the embodiments of the present invention described herein can be operated in other orientations than those described or exemplified herein.

[0040] The terms "fixed" and "fixed connection" of the present invention include detachable fixed connection or non-detachable fixed connection. The detachable fixed connection includes bolt connection, etc., and the non-detachable fixed connection includes welding, etc.

[0041] Example

[0042] Combine the following Figure 1-Figure 6 , various embodiments of the present invention are described in further detail.

[0043] The hypergravity field penetration simulation test device disclosed in the present invention comprises an air cannon 1000, a launch projectile 2000, a support mechanism 3000, a penetration test mechanism 4000 and an acceleration mechanism 5000, wherein the launch projectile 2000 is placed in the air cannon 1000, the air cannon 1000 is placed in the support mechanism 3000, the bottom of the support mechanism 3000 is connected to the top of the penetration test mechanism 4000, and the acceleration mechanism 5000 is used to provide a hypergravity field environment for the penetration simulation test by rapid rotation.

[0044] As a power source, the Air Cannon 1000 is a barrel-fired weapon that relies on the pressure difference between the compressed gas in the air chamber of the gun body and the outside world to push the projectile to move. Conventional air cannons are all diaphragm structures. When the pressure reaches the strength limit of the diaphragm, the diaphragm ruptures, and the high-pressure gas acts on the projectile in the launch tube, causing the projectile to move at high speed. The choice of diaphragm is a factor that is difficult to control. The diaphragm has high requirements for toughness. A diaphragm with too low toughness will cause the membrane to rupture too early and fail to reach sufficient pressure. A diaphragm with too high toughness may cause the diaphragm to fail to crack in time or crack insufficiently, and the gas release speed is not fast enough, which affects the acceleration of the projectile and wastes a lot of energy.

[0045] like Figure 1As shown, the air cannon 1000 of this embodiment includes a barrel 1100, a piston 1200, a launch tube 1300 and other components. Among them, the launch bullet 2000 is placed in the launch tube 1300, and the launch bullet 2000 includes projectiles of different materials and diameters, such as steel projectiles, alloy projectiles, etc., and existing products can be selected according to needs.

[0046] The barrel 1100 is cylindrical in shape, and the piston 1200 is arranged inside the barrel 1100. The piston 1200 can move smoothly in the barrel 1100 along the axial direction of the barrel. The top end of the barrel 1100 is closed, and a circular opening is arranged at the bottom end of the barrel. The top end of the launch tube 1300 is connected to the bottom end of the barrel 1100 where the circular opening is arranged, and the inner diameter of the launch tube 1300 is adapted to the size of the circular opening of the barrel 1100.

[0047] The piston 1200 includes a piston plate 1210 and a piston rod 1220. The piston plate 1210 and the piston rod 1220 are preferably an integrally formed structure. The piston plate 1210 and the piston rod 1220 are both cylindrical. The top surface of the piston rod 1220 vertically abuts against the bottom surface of the piston plate 1210, and the center lines of the two are consistent. A circular baffle 1110 is provided in the barrel 1100, dividing the inner cavity of the barrel 1100 into two chambers. The chamber close to the end of the launch tube 1300 is the main air chamber 1120, and the chamber away from the end of the launch tube 1300 is the auxiliary air chamber 1130. The main air chamber 1120 is larger than the auxiliary air chamber 1130. The top surface of the auxiliary air chamber 1130 is provided with a first air inlet 1131 and an exhaust port 1132. The first air inlet 1131 is connected to an external air storage device for inflating the barrel 1100.

[0048] Furthermore, a second air inlet 1121 is provided on the side wall of the barrel 1100 between the piston plate 1210 and the baffle 1110 to speed up the filling of air into the barrel 1100;

[0049] Furthermore, a third air inlet 1122 is provided on the side wall of the barrel 1100 near the end of the launch tube 1300 to further speed up the inflation speed into the main air chamber 1120;

[0050] Furthermore, valves are provided at the first air inlet 1131, the second air inlet 1121, the third air inlet 1122 and the exhaust port 1132 to control the charging and discharging speed of the high-pressure gas;

[0051] Furthermore, the shape of the barrel of the barrel 1100 can be a concentric cylindrical hollow structure with a small top and a large bottom. The smaller volume of the auxiliary air chamber can obtain a higher piston speed and make the connection between the auxiliary air chamber and the main air chamber more stable.

[0052] Furthermore, the high-pressure gas can be nitrogen, helium, hydrogen, etc., preferably nitrogen, which has stable chemical properties and is not easy to react with other substances. It is a commonly used gas in the high-pressure field;

[0053] Furthermore, a one-way valve 1211 is provided at the connection between the piston 1200 and the barrel 1100 so that the gas can only flow from the auxiliary air chamber 1130 to the main air chamber 1120 and cannot flow in the reverse direction;

[0054] Before the test begins, high-pressure gas is first filled into the auxiliary air chamber 1130 from the first air inlet 1131 through an external air storage device. The high-pressure gas pushes the piston 1200 downward, so that the piston rod 1220 blocks the inlet of the launch tube 1300. Under the action of pressure, nitrogen enters the main air chamber 1120 from the auxiliary air chamber 1130 through the one-way valve 1211 until the predetermined pressure is reached, and then the air inlet valve at the first air inlet 1131 is closed. When launching the projectile, the exhaust valve at the exhaust port 1132 is opened, and the high-pressure gas in the auxiliary air chamber 1130 is quickly released from the exhaust port 1132. Under the action of the pressure difference, the piston 1200 moves upward rapidly, the piston rod 1220 is separated from the inlet of the launch tube 1300, and the high-pressure gas in the main air chamber 1120 enters the launch tube 1300, pushing the projectile to move along the launch tube 1300, and finally launching the projectile.

[0055] Furthermore, a pressure sensor is installed on the side wall of the barrel 1100 near the third air inlet 1122 for real-time monitoring of the pressure changes in the main air chamber 1120. By adjusting the opening and closing of the air inlet valve, the pressure in the main air chamber 1120 can be adjusted. By adjusting the pressure in the main air chamber 1120, the projectile firing speed can be controlled.

[0056] The air cannon 1000 of the present application can be fired without rupturing the diaphragm due to its unique structural design, and can be reused, which reduces the test cost and improves the test efficiency. In addition, the air cannon device of the present application can safely and stably carry out experimental research in a hypergravity environment, expands the use environment of the air cannon device, and realizes a new impact and penetration test simulation method. It solves the problems of conventional air cannon devices in a hypergravity environment, such as structural instability, low safety, uncontrollable firing speed and angle, and unstable air pressure control.

[0057] Furthermore, a laser velocity measurement system 1310 is installed on the launch tube 1300. Preferably, the laser velocity measurement system 1310 includes two sets of laser transceivers, one set installed near the entrance of the barrel is an entrance laser transceiver 1311, and the other set installed near the exit of the barrel is an exit laser transceiver 1312. Each set of laser transceivers includes a laser. Every time the projectile passes through a laser, a pulse signal is generated. The interval time between the two pulse signals is the time required for the projectile to move between the two laser transceivers, so that the launch speed of the projectile can be calculated.

[0058] like Figure 2 As shown, the support mechanism 3000 includes a support frame 3100 and a support base 3200. The support frame 3100 is fixedly arranged on the upper surface of the support base 3200. The support frame 3100 and the support base 3200 are preferably a frame structure, which is a frame structure formed by connecting a number of support columns horizontally and longitudinally. The frame structure can be formed by welding angle steel, or can be welded by replacing angle steel with stronger channel steel, T-shaped steel or I-shaped steel. Square steel is preferably used. Square steel refers to steel with a square cross-section, and all four sides are straight lines. The force direction of square steel is equal in four directions. It has better stability and support capacity, increases strength and rigidity, and reduces weight, providing reliable support under a hypergravity field. Preferably, a cover plate 3210 with an opening in the middle is provided on the upper surface of the support base 3200. The opening is conducive to the rotation of the launch tube 1300 to adjust the launch angle. The support frame 3100 and various pipelines and valves of the air cannon can be installed on the cover plate 3210.

[0059] The air cannon 1000 is placed in the support frame 3100, and preferably, the end of the air cannon auxiliary air chamber 1130 extends to the upper part of the support frame 3100 to facilitate the connection of an external air storage device; preferably, the lower surface of the air cannon barrel 1100 is flush with the upper surface of the support frame 3100, so that the launch tube 1300 is placed in the support base 3200, which is convenient for rotating the launch tube 1300 to adjust the launch angle.

[0060] A rotating shaft 3110 is provided in the support frame 3100, preferably symmetrically provided with two horizontal rotating shafts of the same size, one end of the rotating shaft 3110 is fixed to the support frame 3100, and the air cannon 1000 is placed between the two rotating shafts. The barrel 1100 is fixed to the center of the support frame 3100 by clamping the two rotating shafts. The specific structure of the rotating shaft 3110 clamping the air cannon 1000 is not limited, and any structure that can clamp the air cannon and rotate the air cannon to adjust the air cannon launch angle is acceptable. The launch angle of the air cannon launch tube 1300 can be adjusted by rotating the rotating shaft 3110, so that the launch angle can be adjusted and controlled. Preferably, the launch tube 1300 can achieve a swing angle of ±90° in the vertical direction.

[0061] Furthermore, the rotating shaft 3110 and the air cannon 1000 may be fixedly connected or detachably connected. The fixed connection may be achieved by welding, and the detachable connection may be achieved by threaded connection.

[0062] Furthermore, a clamp is arranged between the two rotating shafts, and the air cannon barrel 1100 is clamped by the clamp to fix the air cannon; the clamp preferably adopts a structure in which two connecting pipes are symmetrically arranged on the side, and an internal thread is arranged on the inner wall of the connecting pipe, and a corresponding external thread is arranged at the connecting end of the rotating shaft 3110 and the clamp, and the rotating shaft 3110 and the clamp are connected by threads.

[0063] Furthermore, a nut is arranged between the rotating shaft 3110 and the supporting frame 3100 , and a corresponding external thread is arranged at one end of the rotating shaft 3110 on which the nut is installed, and the air cannon 1000 is loosened or tightened by tightening or loosening the nut.

[0064] As shown in the figure, the penetration test mechanism 4000 includes a model box 4100 with an upper opening, a target model 4200 and a protective device 4300 are placed in the model box 4100, and a support base 3200 is placed on the upper part of the model box 4100. The target model 4200 is a scaled model of the protective structure of the pre-strike of the penetration weapon, and the target model 4200 can be placed at the bottom of the model box. The protective device 4300 is placed at the lower part or rear part of the target model 4200 or the bottom and side wall of the model box 4100 to prevent the projectile 2000 from penetrating the model box 4100 and popping out of the box, causing damage to the model box 4100 or other damage.

[0065] The protective device 4300 can be made of thick rubber pads, silicone pads, compacted soil and other materials that can produce cushioning and have a certain elasticity. Industrial rubber blocks are preferably used, which have sufficient shock-absorbing and buffering capabilities and a small deformation amount, and can form a stable support for the target model 4200.

[0066] The shape of the target model 4200 is not limited and it can be a cube, a cuboid, a cylinder or other complex polyhedrons, as long as it can be adapted to the structure into which the projectile 2000 is shot and can be easily fixed. The material is preferably concrete to simulate the penetration test effect of a concrete dam.

[0067] Furthermore, a water tank filled with water is set behind the target model 4200 to simulate the reservoir effect after the penetrating weapon hits the concrete dam.

[0068] like Figure 4As shown, the acceleration mechanism 5000 is used to make the test device rotate quickly to generate centrifugal force, and simulate the gravity field environment of the structure with inertial force. In this embodiment, high-speed rotation is achieved by a centrifuge. The acceleration mechanism 5000 of this embodiment includes a centrifuge 5100 and a hanging basket 5200. The centrifuge 5100 includes a base 5110 and a rotating arm 5120. The center position of the rotating arm 5120 is installed on the base 5110. A driving motor is arranged in the base 5110. The driving motor is used to provide power for the rotating arm 5120 so that the rotating arm 5120 rotates horizontally around the base 5110. The hanging basket 5200 is arranged at both ends of the rotating arm 5120. The hanging basket 5200 is a matching accessory of the centrifuge 5100. The hanging basket 5200 is used to place a container or device therein. The hanging basket 5200 mainly provides support and protection for the container or device, and ensures that they remain stable and safe when rotating at high speed. The air cannon 1000, the support mechanism 3000 and the penetration test mechanism 4000 are all placed in the hanging basket 5200 at one end of the rotating arm, and a counterweight is set in the hanging basket 5200 at the other end of the rotating arm to keep the centrifuge 5100 balanced. When the centrifuge 5100 is running, the device in the hanging basket rotates with the rotating arm 5120, thereby providing a hypergravity field environment for the penetration simulation test.

[0069] Furthermore, an instrument cabin 5300 is arranged above the base 5110, and the control and test system of the penetration simulation test device is arranged in the instrument cabin 5300, and is wiredly connected to the central control room through the centrifuge slip ring 5310 to realize multi-channel data acquisition and automatic control of the system for the hypergravity field penetration simulation test. The centrifuge slip ring 5310 is an accessory of the centrifuge 5100. The slip ring, also known as a rotary connector, has the main function of transmitting electrical energy, signals or images, so that the rotating part can rotate freely while maintaining the continuous transmission of electrical signals or energy. The main functions of the control and test system in the instrument cabin 5300 include projectile release control, projectile initial velocity measurement, detonation control, synchronous acquisition, storage, analysis and callback of structural transient signals and images, etc.

[0070] During the test, the acceleration mechanism 5000 can provide different hypergravity environments, so that the air cannon 1000 can simulate the penetration of target models 4200 of different sizes at different incident speeds and different incident angles. The data obtained by the acceleration and other sensors set in the test device can be used to analyze the penetration process of the target from multiple aspects such as target vibration, penetration depth, crack shape, crack cause, target damage characteristics, etc. Based on the similarity theory, the penetration depth expression is established. On the basis of penetration and hole formation, explosives or detonators can be further placed in the hole to simulate the whole process of penetration explosion under the attack of weapons such as earth-penetrating bombs, so as to realize the simulation analysis of the composite damage effect of penetration explosion and structure.

[0071] Test method:

[0072] The test is carried out using the above-mentioned hypergravity field penetration simulation test device. The test method mainly includes the following steps:

[0073] S1: placing the projectile 2000 in the launch tube 1300 of the air cannon;

[0074] S2: High-pressure gas is charged into the auxiliary air chamber 1130 of the air cannon. The high-pressure gas pushes the piston 1200 downward to block the entrance of the launch tube 1300, opens the valve at the exhaust port 1132, and quickly releases the high-pressure gas in the auxiliary air chamber 1130 from the exhaust port 1132. Under the action of the pressure difference, the piston 1200 quickly moves upward to break away from the entrance of the launch tube 1300, and the high-pressure gas in the main air chamber 1120 enters the launch tube 1300, pushing the launch bullet 2000 to be launched;

[0075] S3: Penetration test is conducted in a hypergravity field environment generated by the acceleration mechanism 5000;

[0076] S4: measuring the launch speed of the projectile 2000 by means of the laser speed measurement system 1310, and collecting the penetration depth, crack shape and target damage data by means of sensors;

[0077] S5: Perform penetration simulation analysis based on the obtained data.

[0078] Experimental principle: Similarity between hypergravity field and penetration

[0079] The centrifuge 5100 generates centrifugal force by rotating rapidly, simulating the gravity field environment of the structure with inertial force. When the centrifuge 5100 is running, the test device in the basket rotates rapidly around the center of the base 5110, and the basket 5200 and the test device therein gradually tend to be horizontal. When the designed speed is reached, the centrifuge 5100 maintains uniform circular motion. At this time, in addition to the constant gravity acceleration on the ground, the test device will also be subjected to additional inertial force, namely the horizontal centrifugal acceleration. When the centrifuge 5100 rotates fast enough, the centrifugal force can reach dozens of times the gravity, and the earth's gravity can usually be ignored compared to it. At this time, a supergravity field environment is formed. Through the supergravity field, the test device as a small-scale scale model can maintain a similar gravity field environment as the prototype, such as Figure 5 The figure shows the stress state of the scaled model and the prototype. The triangular area is the vertical self-weight stress distribution of the scaled model. It can be seen that the stress at any point inside the scaled model is the same as that at the corresponding position of the prototype.

[0080] The accuracy of the scaled model test results can be determined by the similarity theory based on dimensional analysis. The dimensional analysis method determines the dimensional homogeneity of the mathematical equations between the test influencing factors by analyzing the test conditions, test process, and test results, thereby determining the similarity between the model and the prototype. For the penetration test, the physical parameters involved are as follows.

[0081] Projectile parameters: projectile radius R, projectile length L, warhead length L N , projectile density ρ m ;

[0082] Target parameters: target density ρ t , target compressive strengthσ ct ;

[0083] Launch parameters: projectile incident speed v0, incident angle θ,

[0084] Coupling parameters: friction characteristics between projectile and target φ,

[0085] Gravitational acceleration g,

[0086] Then the expression of the penetration depth D of the projectile is:

[0087]

[0088] According to dimensional analysis, the dimensionless expression of penetration depth is established as:

[0089]

[0090] Based on this formula, the proportional factors of various physical quantities in the hypergravity field penetration simulation can be obtained.

[0091] Table 1 Proportional factors of various physical quantities in hypergravity field penetration simulation

[0092]

[0093] n means that the physical quantity of the centrifuge test is n times that of the prototype.

[0094] Relationship between air pressure, projectile size, launch tube size, projectile density and initial penetration velocity

[0095] Through scaled model tests, in different hypergravity environments, using launch tubes of different sizes and different gas pressures, the projectile exit velocity under different gas pressures is calibrated, and a database or formula of parameters and speed is established for easy reference in experiments.

[0096] v0=f3(P,L,R,ρ m ).

[0097] Verification test: Hypergravity field penetration similarity verification

[0098] In order to ensure the reliability of the test, the penetration similarity can be verified by the following methods: for the prototype, the test is carried out at different scales, and the launch tube size and air pressure are adjusted to keep the exit velocity consistent. The size of the scaled model is also converted according to the table, and the thickness and size of the scaled model are consistent with the prototype. Figure 6 As shown, target models A 4210 and target models B 4220 of different sizes are set to conduct the test in different hypergravity environments and keep the prototype consistent. In order to ensure the consistency of the incident length on the prototype scale, protective devices 4300 of different heights can be added under the target model to prevent the model box 4100 from being hit by the projectile while ensuring the distance between the target model and the launch tube 1300, so as to ensure the safety of the test environment. On this basis, the consistency of the penetration depth, crack distribution and vibration velocity on the prototype scale can be compared and analyzed. At the same time, general simulation tests under conventional gravity environments can be carried out to verify the influence of the hypergravity field on the penetration simulation.

[0099] Although the present invention has been described with reference to exemplary embodiments, it should be understood that the present invention is not limited to the disclosed exemplary embodiments. Various adjustments or changes may be made to the exemplary embodiments of the present specification without departing from the scope or spirit of the present invention. The scope of the claims should be based on the broadest interpretation to cover all modifications and equivalent structures and functions.

Claims

1. A hypergravity field penetration simulation test device, characterized in that: The invention comprises an air cannon (1000), a launching projectile (2000), a supporting mechanism (3000), a penetration test mechanism (4000) and an accelerating mechanism (5000), wherein: The projectile (2000) is placed in the air cannon (1000), the air cannon (1000) is arranged in the support mechanism (3000), the bottom of the support mechanism (3000) is connected to the top of the penetration test mechanism (4000), the air cannon (1000) comprises a barrel (1100), a piston (1200) and a launch tube (1300), the top end of the launch tube (1300) is connected to the bottom end of the barrel (1100), the barrel (1100) is provided with a main air chamber (1120) and a secondary air chamber (1130), the top surface of the secondary air chamber (1130) is provided with A first air inlet (1131) and an exhaust port (1132) are provided, the auxiliary air chamber (1130) is connected to an external air storage device via the first air inlet (1131) and is used to deliver high-pressure gas to the auxiliary air chamber (1130) and the main air chamber (1120), the main air chamber (1120) is connected to the launch tube (1300), the exhaust port (1132) discharges the high-pressure gas to drive the piston (1200) to move toward the auxiliary air chamber (1130), and the high-pressure gas in the main air chamber (1120) enters the launch tube (1300) to push the launch bullet (2000) to achieve launch; The acceleration mechanism (5000) comprises a centrifuge (5100) and a hanging basket (5200), wherein the centrifuge (5100) comprises a base (5110) and a rotating arm (5120), wherein the rotating arm (5120) is mounted on the base (5110), wherein a driving motor is arranged in the base (5110), wherein the driving motor is used to provide power to the rotating arm (5120) so that the rotating arm (5120) rotates horizontally around the base (5110), wherein the hanging basket (5200) is arranged at both ends of the rotating arm (5120), wherein the air cannon (1000), the supporting mechanism (3000) and the penetration test mechanism (4000) are arranged in the hanging basket (5200) at one end, and wherein the acceleration mechanism (5000) provides a hypergravity field environment for a penetration simulation test by rapidly rotating.

2. The hypergravity field penetration simulation test device according to claim 1, characterized in that: The barrel (1100) is cylindrical in shape. The piston (1200) is disposed in the barrel (1100). The piston (1200) comprises a piston plate (1210) and a piston rod (1220). The piston rod (1220) is in a blocked or disengaged state from an entrance of a launch tube (1300) under the action of a pressure difference. When the high-pressure gas in the main air chamber (1120) enters the launch tube (1300), it pushes the launch bullet (2000) to move along the launch tube (1300) to achieve launch.

3. The hypergravity field penetration simulation test device according to claim 1, characterized in that: The support mechanism (3000) comprises a support frame (3100) and a support base (3200), wherein the support frame (3100) and the support base (3200) are frame structures, and a rotating shaft (3110) for adjusting the firing angle of the air cannon (1000) is provided on the support frame (3100), and the rotating shaft (3110) is connected to the support frame (3100) via a nut.

4. The hypergravity field penetration simulation test device according to claim 1, characterized in that: The transmitting tube (1300) is provided with a laser speed measurement system (1310), the laser speed measurement system (1310) comprising a laser transceiver, the laser transceiver comprising an entrance laser transceiver (1311) arranged near the entrance of the transmitting tube (1300) and an exit laser transceiver (1312) arranged near the exit of the transmitting tube (1300), the laser transceiver comprising a laser, the laser being used to generate a pulse signal when a transmitting bullet (2000) passes through, and the time interval and spacing of the pulse signals of the entrance laser transceiver (1311) and the exit laser transceiver (1312) are recorded, thereby calculating the launch speed of the transmitting bullet (2000).

5. The hypergravity field penetration simulation test device according to claim 1, characterized in that: The penetration test mechanism (4000) comprises a model box (4100) with an opening at the upper end, wherein a target model (4200) is arranged in the model box (4100), wherein the target model (4200) is a scaled model of a protective structure, and wherein the target model (4200) is arranged at the bottom of the model box (4100) so that the air cannon (1000) can shoot at different incident angles.

6. The hypergravity field penetration simulation test device according to claim 5, characterized in that: A protective device (4300) is also provided in the model box (4100). The protective device (4300) is provided at the bottom or side wall of the model box (4100) and is used to prevent the projectile (2000) from penetrating the model box (4100) and ejecting out of the box.

7. The hypergravity field penetration simulation test device according to claim 6, characterized in that: The protective device (4300) is made of a material that can generate a buffer and has elasticity, and the material includes a rubber pad, a silicone pad or compacted soil.

8. The hypergravity field penetration simulation test device according to claim 1, characterized in that: A one-way valve (1211) is provided at the connection between the piston (1200) and the barrel (1100), and the one-way valve (1211) is used to control the flow of gas from the auxiliary air chamber (1130) to the main air chamber (1120).

9. The hypergravity field penetration simulation test device according to claim 1, characterized in that: A pressure sensor for real-time monitoring of pressure changes in the main air chamber (1120) is provided on the side wall of the barrel (1100), and valves are provided at the first air inlet (1131) and the exhaust port (1132) of the auxiliary air chamber (1130). By adjusting the valves, the pressure in the main air chamber (1120) can be adjusted, thereby controlling the firing speed of the projectile (2000).

10. A hypergravity field penetration simulation test method, characterized in that: The method comprises the steps of using the hypergravity field penetration simulation test device as claimed in any one of claims 1 to 9, comprising: S1: placing the projectile (2000) in a launching tube (1300) of an air cannon; S2: High-pressure gas is charged into the auxiliary air chamber (1130) of the air cannon, and the high-pressure gas pushes the piston (1200) downward to block the inlet of the launch tube (1300), and the valve at the exhaust port (1132) is opened, and the high-pressure gas in the auxiliary air chamber (1130) is quickly released from the exhaust port (1132). Under the action of the pressure difference, the piston (1200) quickly moves upward to separate from the inlet of the launch tube (1300), and the high-pressure gas in the main air chamber (1120) enters the launch tube (1300), pushing the launch bullet (2000) to be launched; S3: performing a penetration test in a hypergravity field environment generated by the acceleration mechanism (5000); S4: measuring the launch speed of the projectile (2000) by means of a laser speed measurement system (1310), and collecting penetration depth, crack shape and target damage data by means of a sensor; S5: Perform penetration simulation analysis based on the obtained data.

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