A gun-launched test projectile and a method and apparatus for recovering the same

Abstract

This application discloses a gun-launched test projectile, comprising: a first housing having symmetrically arranged first and second slotted structures; an antenna disposed within the first and second slotted structures for receiving satellite signals; a projectile-borne receiver circuit box disposed within the first housing and connected to the antenna for determining the current position of the test projectile based on the satellite signals; a buffer structure connected to the projectile-borne receiver circuit box for reducing the overload effect on the projectile-borne receiver circuit box during launch; and a base assembly disposed at one end of the first housing, having an abutment portion and a connecting portion, the abutment portion abutting against the projectile-borne receiver circuit box, the connecting portion connecting to the first housing, and a cavity structure between the abutment portion and the connecting portion. This application also discloses a test projectile recovery device and method.

Description

Technical Field

[0001] This application relates to a test projectile for artillery firing and its recovery method and apparatus. Background Technology

[0002] Satellite-guided mortars are guided mortars that launch via a combination of satellite / geomagnetic and pulse rocket guidance. Due to their high first-shot hit probability, satellite-guided mortars can quickly and accurately destroy high-value targets such as enemy personnel, ground-based technical weapons, and command, control, and communication systems in various complex terrains, leading to their rapid development in recent years. During the initial launch phase, under chamber pressure, the onboard satellite signal receiver (hereinafter referred to as the "onboard receiver") in the satellite-guided mortar experiences axial overloads of up to tens of thousands of grams, posing a severe test to the overload resistance of the electronic components. To study the overload resistance of the onboard receiver at the moment of launch, artillery firing tests are needed to measure the dynamic mechanical response of the onboard receiver and provide verifiable experimental data for simulation analysis. Artillery firing can effectively simulate the overload environment during the launch of a satellite-guided mortar, ensuring the authenticity of the reproduced high overload (5000g–15000g) environment. Therefore, it is necessary to design a special test missile specifically for the structure and characteristics of the missile-borne receiver. Summary of the Invention

[0003] In view of this, the embodiments of this application aim to provide a gun-launched test projectile and its recovery method and apparatus.

[0004] The technical solution of this application is implemented as follows:

[0005] According to one aspect of this application, a gun-launched test projectile is provided, the test projectile comprising:

[0006] The first housing has a first groove-shaped structure and a second groove-shaped structure arranged symmetrically;

[0007] An antenna, disposed within the first slotted structure and the second slotted structure, is used to receive satellite signals;

[0008] The missile-borne receiver circuit box is located inside the first housing and connected to the antenna, used to determine the current position of the test missile based on the satellite signal;

[0009] A buffer structure, connected to the missile-borne receiver circuit box, is used to reduce the overload effect on the missile-borne receiver circuit box during the launch of the test missile;

[0010] A base assembly is disposed at one end of the first housing and has an abutment portion and a connecting portion. The abutment portion abuts against the missile-borne receiver circuit box, and the connecting portion is connected to the first housing. A cavity structure is formed between the abutment portion and the connecting portion.

[0011] In the above scheme, the buffer structure includes:

[0012] The first buffer is disposed between the missile-borne receiver circuit box and the first housing;

[0013] The second buffer is disposed between the missile-borne receiver circuit box and the base assembly;

[0014] The first buffer and the second buffer have different buffering performance.

[0015] In the above scheme, the different buffering performances of the first buffer and the second buffer are manifested in the following ways:

[0016] The first buffer is made of at least one material selected from elastic nylon, polyurethane, and pine block, wherein the elastic nylon material meets a preset elasticity condition;

[0017] The second buffer is made of polyurethane foam material with a density of 0.25 g - 0.32 g / cm3.

[0018] In the above scheme, there is a first gap between the missile-borne receiver circuit box and the first housing; the first buffer has a first thickness from one side of the missile-borne receiver circuit box to one side of the first housing, and the first thickness is greater than the first gap.

[0019] In the above scheme, the first thickness is 0.1-0.15 mm larger than the first gap.

[0020] In the above scheme, the base assembly includes:

[0021] The base body has the connecting portion and the recessed portion;

[0022] The base cover has a first end that abuts against the missile-borne receiver circuit box and a second end that is connected to the first end of the base body, forming the cavity structure.

[0023] The recessed portion is disposed opposite to the cavity structure, and the diameter of the recessed portion is greater than or equal to 40mm.

[0024] In the above scheme, the test missile also includes a protective cover that fits onto the first groove structure and the second groove structure to protect the antenna.

[0025] In the above scheme, the end of the first housing away from the base assembly is a frustum-shaped structure, and the cone angle of the frustum-shaped structure is 45°-75°.

[0026] In the above scheme, the first housing and the base assembly are made of rigid materials.

[0027] According to another aspect of this application, a test projectile recovery device is provided, the test projectile recovery device being used to recover any of the above-described gun-launched test projectiles; the recovery device comprising:

[0028] The second shell, disposed on the base, has a cavity structure, wherein the inner diameter parameter of the cavity structure is larger than the outer diameter parameter of the test projectile;

[0029] Baffles are movably disposed at the first end, the second end, and the middle of the second housing, respectively, to divide the cavity structure into at least two cavities, wherein the at least two cavities are coaxially arranged and the axial direction of the cavities is the same as the launch direction of the test projectile;

[0030] The filling structures are respectively disposed in the at least two cavities, and the density of the filling structures in the at least two cavities is different;

[0031] The base is connected to the second housing and is used to support the second housing.

[0032] In the above scheme, the baffle divides the cavity structure into three cavities, and the filling structures in the three cavities, from the launch direction of the test projectile, are, in order, a liquid filling structure, a mixed filling structure of solid and liquid, and a solid filling structure.

[0033] According to a third aspect of this application, a method for recovering a test projectile is provided, the method being applied to the test projectile recovery apparatus described in any of the preceding claims, the method comprising:

[0034] In response to the detection that the test missile has been fired, the middle baffle of the test missile recovery device is controlled to eject the second housing; in order to detect whether there is a bullet penetration hole on the middle baffle.

[0035] If the middle baffle has the bullet penetration hole, the rear baffle of the test bullet recovery device is controlled to pop out of the second housing to locate the test bullet on the rear baffle;

[0036] If there is no bullet penetration hole on the middle baffle, the front baffle of the test bullet recovery device is popped out of the second housing to locate the test bullet on the front baffle or in the cavity area near the front baffle.

[0037] The middle baffle is located between the front baffle and the rear baffle. The front baffle is located at the end of the test missile recovery device that is closer to the direction of launch of the test missile, and the rear baffle is located at the end of the test missile recovery device that is farther away from the direction of launch of the test missile.

[0038] The gun-launched test projectile and its recovery method and apparatus provided in this application can not only avoid the ablation effect of gunpowder gas on the onboard receiver circuit during the launch of the test projectile, but also reduce the overall mass of the test projectile, reduce the difficulty of recovering the test projectile, and improve the recovery efficiency and integrity of the test projectile. Attached Figure Description

[0039] Figure 1 This is a schematic cross-sectional view of the structural composition of the test projectile for artillery firing in this application;

[0040] Figure 2 This is a three-dimensional schematic diagram of the structural composition of the test projectile for artillery firing in this application;

[0041] Figure 3 This is a partial cross-sectional schematic diagram of the test projectile being loaded into the artillery in this application;

[0042] Figure 4 This is a schematic cross-sectional view of the structural components of the test missile recovery device in this application. Figure 1 ;

[0043] Figure 5 This is a schematic cross-sectional view of the structural components of the test missile recovery device in this application. Figure 2 ;

[0044] Figure 6 This is a schematic diagram illustrating the process of recovering the test projectile in this application;

[0045] Figure 7 This is a schematic diagram of the recovery scenario for the test missile in this application. Detailed Implementation

[0046] The technical solution of this application will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0047] The specific technical features described in the various embodiments in the detailed implementation can be combined in various ways without contradiction. For example, different implementation methods can be formed by combining different specific technical features. In order to avoid unnecessary repetition, the various possible combinations of the specific technical features in this application will not be described separately.

[0048] In the embodiments described in this application, it should be noted that, unless otherwise stated and limited, the term "connection" should be interpreted broadly. For example, it can be an electrical connection, or a connection between two internal components. It can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above term according to the specific circumstances.

[0049] It should be noted that the terms "first," "second," and "third" used in the embodiments of this application are merely used to distinguish similar objects and do not represent a specific ordering of objects. It is understood that "first," "second," and "third" can be interchanged in a specific order or sequence where permitted. It should be understood that the objects distinguished by "first," "second," and "third" can be interchanged where appropriate so that the embodiments of this application described herein can be implemented in an order other than those illustrated or described herein.

[0050] Figure 1 This is a schematic cross-sectional view of the structural components of the test projectile for artillery firing in this application. Figure 2 This is a three-dimensional schematic diagram of the structural composition of the test projectile for artillery firing in this application, as shown below. Figure 1 , Figure 2 As shown, the test projectile includes: a first housing 11, an antenna 12, a projectile-borne receiver circuit box 13, a buffer structure 14, and a base assembly 15. The first housing 11 has symmetrically arranged first groove-shaped structures 111 and second groove-shaped structures 112 for housing the antenna 12. The antenna 12 is disposed within the first groove-shaped structure 111 and the second groove-shaped structure 112 for receiving satellite signals. The projectile-borne receiver circuit box 13 is disposed within the first housing 11 and connected to the antenna 12 for determining the target location based on the satellite signals. The test missile's current position is described; the buffer structure 14 is connected to the missile-borne receiver circuit box 13 to reduce the overload effect on the missile-borne receiver circuit box 13 during the launch of the test missile; the base assembly 15 is disposed at one end of the first housing 11, and has an abutment part 1521 and a connecting part 1511. The abutment part 1521 abuts against the missile-borne receiver circuit box 13, and the connecting part 1511 is connected to the first housing 11. A cavity structure 153 is provided between the abutment part 1521 and the connecting part 1511.

[0051] In this application, the buffer structure 14 includes a first buffer 141 and a second buffer 142; wherein, the first buffer 141 is disposed between the missile-borne receiver circuit box 13 and the first housing 11, and is used to reduce the overload effect on the missile-borne receiver circuit box 13 during the launch of the test projectile; the second buffer 142 is disposed between the missile-borne receiver circuit box 13 and the base assembly 15, and is used to reduce the overload effect on the missile-borne receiver circuit box 13 during the launch of the test projectile, and to reduce the overload effect on the missile-borne receiver circuit box 13 during the recovery of the test projectile.

[0052] Here, the first buffer 141 and the second buffer 142 have different buffering performances, which can be manifested as follows: the first buffer 141 is made of at least one material selected from elastic nylon, polyurethane, and pine block, wherein the elastic nylon material meets a preset elasticity condition; this preset elasticity condition can refer to a flexural modulus of 2500 MPa, possessing both elasticity and durability. The second buffer 142 is made of polyurethane foam material with a density of 0.25 g - 0.32 g / cm3, and the thickness of the second buffer 142 can be 1.5~1.8 mm, with a preferred density of 0.28 g / cm3 and a preferred thickness of 1.5 mm. The second buffer 142, made of polyurethane foam material, exhibits increased yield stress under high strain rate conditions, and its deformation absorbs energy, providing better protection for the missile-borne receiver circuit box.

[0053] Here, the second buffer 142 can also be made of aluminum foam with a density of 0.25-0.27 g / cm3.

[0054] In this application, there may be a first gap between the missile-borne receiver circuit box 13 and the first housing 11; the first buffer 141 may have a first thickness from one side of the missile-borne receiver circuit box 13 to one side of the first housing 11, and the first thickness is greater than the first gap, so as to press the missile-borne receiver circuit box 134 tightly and improve the stability of the missile-borne receiver circuit box in the housing.

[0055] Here, the first thickness is greater than the first gap by a first threshold, which is between 0.1 and 0.15 mm. For example, the first gap is 8.5 mm and the first thickness is 8.6 mm.

[0056] Here, under the condition that the first thickness is greater than the first gap, the protective performance is optimal when the first thickness is 8-15mm.

[0057] In this application, the base assembly 15 includes a base body 151 and a base cover 152. The base body 151 has a connecting portion 1511 and a recessed portion 1512. The first end of the base cover 152 is the abutting portion 1521, which abuts against the missile-borne receiver circuit box 13. The second end of the base cover 152 is connected to the first end of the base body 151 to form the cavity structure 153. The recessed portion 1512 is disposed opposite to the cavity structure 153, and the diameter of the recessed portion 1512 is greater than or equal to 40 mm, so as to maximize the reduction of the mass of the test missile itself and reduce the difficulty of recovering the test missile.

[0058] like Figure 1As shown, when the diameter of the recess 1512 is 40mm, the corresponding diameter of the test projectile can be 86mm, with a tolerance of -0.3mm to -0.15mm. This test projectile can be fired from a standard 86mm artillery piece.

[0059] In this application, the thickness of the connecting portion 1511 is between 15-22 mm, preferably 20 mm.

[0060] In this application, the connection method between the connecting part 1511 of the base body 151 and the first housing 11 is not limited, including screwing, riveting, and welding. For example, high-strength screws of grade 12.9 can be used to connect the housing and the base body to ensure the structural strength of the test projectile and prevent the test projectile from breaking and disintegrating during launch.

[0061] Of course, the base body 151 and the first shell 11 can also be integrally formed to further improve the structural strength of the test projectile.

[0062] In this application, the test missile also includes a protective cover (not shown in the figure), which covers the first groove structure 111 and the second groove structure 112 to protect the antenna 12.

[0063] The material of the protective cover is not limited here; it can be a rigid material, glass, or carbon fiber.

[0064] In this application, the slot depth parameter of the first slot structure 111 and the second slot structure 112 is greater than the thickness parameter of the antenna 12, for example, the slot depth parameter is 1-2 mm greater than the antenna thickness parameter, so as to facilitate antenna installation. The slot inclination angle of the first slot structure 111 and the second slot structure 112 is between 8 degrees and 11 degrees, so as to simulate the installation effect of the antenna on the satellite-guided mortar, making the test results more realistic.

[0065] In this application, the first slotted structure 111 and the second slotted structure 112 are also provided with through holes (not shown in the figure), through which the wires for the antenna are connected to the circuit on the missile-borne receiver circuit box 13 to form a loop.

[0066] Here, the position of the through hole is matched with the position of the antenna wire.

[0067] In this application, the end of the first housing 11 furthest from the base assembly 15 is a frustum-shaped structure, and the cone angle of the frustum-shaped structure is 45°-75°, preferably 46.86 degrees, to increase the flight drag and recovery drag of the test missile.

[0068] In this application, both the first shell 11 and the base assembly 15 can be made of rigid materials, such as stainless steel. The wall thickness of the first shell 11 is 6-10 mm, and the total length from the end of the first shell 11 with a frustum-shaped structure to the end of the base body with a recess can be 178 mm. This not only ensures the strength of the test projectile itself but also reduces the mass of the test projectile and the difficulty of its recovery.

[0069] The gun-launched test projectile provided in this application, by placing the onboard receiver circuit box inside the casing, can avoid the ablation of the onboard receiver circuit box by the propellant gases generated during the launch of the test projectile and the collision damage to the onboard receiver circuit box during the recovery of the test projectile.

[0070] Figure 3 This is a partial cross-sectional schematic diagram of the test projectile being loaded into the artillery in this application, as shown below. Figure 3 As shown, the device includes a test projectile 10 and a gun body 20. The first end of the gun body 20 is a special cartridge case 201, and the second end is a receiving cavity for accommodating the test projectile 10. A bottom sabot 2021 can be provided in the receiving cavity to support the projectile and seal the propellant gas in the gun barrel. After the test projectile leaves the muzzle, the sabot 2021 can detach on its own due to air resistance.

[0071] Here, the gun body 20 is an 86mm standard gun. When the diameter of the test projectile 10 is less than 86mm, a lateral sabot 2022 can also be installed in the accommodating cavity to meet the usage requirements of test projectiles of different diameters.

[0072] Figure 4 This is a schematic cross-sectional view of the structural components of the test missile recovery device in this application. Figure 1 , Figure 5 This is a schematic cross-sectional view of the structural components of the test missile recovery device in this application. Figure 2 The test projectile recovery device is used to recover, for example, Figure 1 , Figure 2 The test shell shown; such as Figure 4 , Figure 5As shown, the recovery device includes: a second housing 31, a baffle 32, a filling structure 33, and a base 34. The second housing 31 is disposed on the base 34 and has a cavity structure. The inner diameter of the cavity structure is larger than the outer diameter of the test projectile to allow the test projectile to pass through. The baffle 32 is movably connected to the second housing 31 via a connecting structure and is respectively disposed at the first end, the second end, and the middle of the second housing 31 to divide the cavity structure into at least two cavities. The at least two cavities are coaxially arranged, and the axial direction of the cavities is the same as the launch direction of the test projectile. The filling structure 33 is disposed in the at least two cavities, and the density of the filling structure in the at least two cavities is different. The base 34 is connected to the second housing 31 and is used to support the second housing 31.

[0073] Here, the second housing 31 and the base 34 can be made of rigid materials, such as iron or steel. The cross-section of the second housing 31 can be rectangular or circular. When the cross-section of the second housing 31 is circular, the diameter of the second housing 31 can be 580 mm.

[0074] Here, the connection structure between the baffle 32 and the second housing 31 is not limited; for example, it can be screwed, riveted, welded, etc.

[0075] Here, the base 34 can be welded from angle steel. The base 34 can have a receiving groove 341 for receiving the second housing 31, and the outer wall of the second housing 31 contacts the inner wall of the receiving groove 341 to improve the stability of the recycling device.

[0076] Here, the receiving groove 341 can be made of wood.

[0077] Here, the baffle 32 can divide the cavity structure into three cavities. The filling structures 33 in the three cavities are, in order from the launch direction of the test projectile, a liquid filling structure (such as water), a mixed filling structure of solid and liquid (such as a mixture of sawdust, cotton yarn, sand and water), and a solid filling structure (such as sawdust and sand).

[0078] Here, the second housing 31 is also provided with a plurality of openings 311, each opening corresponding to a cavity and communicating with the corresponding cavity, so as to place a filling structure into the cavity.

[0079] like Figure 4 As shown, the area of ​​the opening is 0.6m x 0.3m. The baffles 32 are sequentially referred to as the front baffle, middle baffle, and rear baffle from the direction of the test missile launch. A first cavity is formed between the front and middle baffles, and a second cavity is formed between the middle and rear baffles. The first cavity is filled with a mixture of sawdust, cotton yarn, sand, and water, while the second cavity is filled with sawdust and / or sand.

[0080] Here, the thickness of the front and middle baffles can be 15-20mm, and the thickness of the rear baffle can be 3 to 5 times that of the front or middle baffles. The distance between the outer wall of the front baffle and the outer wall of the rear baffle is about 2 meters. The distance between the inner wall of the front baffle and the side wall of the middle baffle near the front baffle is about 930mm. The distance between the side wall of the middle baffle near the rear baffle and the inner wall of the rear baffle is about 930mm.

[0081] Here, the baffle 32 can be made of wood, preferably pine, to allow the test projectile to pass through or embed itself, thereby improving the efficiency and integrity of the test projectile's recovery.

[0082] The test projectile recovery device provided in this application, by arranging multiple coaxial cavities along the launch direction of the test projectile, with each cavity filled with a different density of filling structure, not only achieves low-damage recovery of gun-fired test projectiles but also minimizes impact on the test projectile structure and onboard receiver, thereby improving the integrity and recovery rate of the test videotape projectiles. Furthermore, the inclusion of wooden baffles facilitates the retrieval of the test projectiles, further enhancing recovery efficiency.

[0083] Figure 6 This is a schematic diagram illustrating the process of recovering the test missile in this application. The method is applied to... Figure 4 , Figure 5 The experimental projectile recovery device shown includes the following method:

[0084] Step 601: In response to detecting that the test missile has been fired, the middle baffle of the test missile recovery device is controlled to pop out of the second housing; to detect whether there is a bullet penetration hole on the middle baffle.

[0085] Step 602: If the middle baffle has the bullet penetration hole, control the rear baffle of the test bullet recovery device to pop out the second housing, so as to locate the test bullet on the rear baffle;

[0086] Step 603: If there is no bullet penetration hole on the middle baffle, control the front baffle of the test bullet recovery device to pop out the second housing, so as to locate the test bullet on the front baffle or locate the test bullet in the cavity area near the front baffle;

[0087] The middle baffle is located between the front baffle and the rear baffle. The front baffle is located at the end of the test missile recovery device that is closer to the direction of launch of the test missile, and the rear baffle is located at the end of the test missile recovery device that is farther away from the direction of launch of the test missile.

[0088] The test missile recovery method provided in this application can not only minimize the damage to the test missile during recovery, but also improve the recovery efficiency of the test missile.

[0089] Figure 7 This is a schematic diagram of the recovery scenario for the test missile in this application. Figure 2 ,like Figure 7 As shown:

[0090] The first step is to set up a test missile recovery device;

[0091] Here, the distance between the recovery device and the artillery is between 15 and 20 meters, which can achieve the separation of the lateral sabot, the bottom sabot, and the test projectile, as well as the recovery of the test projectile, within the minimum distance;

[0092] The second step is to set up the high-speed camera and the backdrop, and calibrate the relevant parameters of the high-speed camera.

[0093] Here, the high-speed camera is positioned to one side of the artillery and recovery device, near the center of the device. The parameters for calibrating the high-speed camera include, but are not limited to, exposure, sampling frequency, focus, and calibration parameters.

[0094] Here, the high-speed camera can also be equipped with a protective cover to protect it from damage during the test missile launch.

[0095] The third step is to load the installed test projectile into the gun barrel, and then fill the propellant cartridge case in the barrel with the calculated amount of propellant, thus putting the gun into a ready-to-fire state.

[0096] If a bottom sabot and a side sabot are required, then a bottom sabot and / or a side sabot must also be installed inside the gun barrel, depending on the type of test projectile.

[0097] The fourth step is to control the high-speed camera to start acquiring images and control the test missile to launch it towards the recovery device.

[0098] Here, with a sabot in place, the sabot separates from the test projectile, and the test projectile is fired toward the recovery device.

[0099] The fifth step is to retrieve the test missile by using images captured by a high-speed camera to confirm that it has successfully entered the recovery device.

[0100] The sixth step is to remove the test missile from the recovery device.

[0101] Here, the middle baffle of the recovery device can be removed first to check whether there is a test bullet puncture on the middle baffle. If there is, the rear baffle is removed to find the test bullet; if not, the front baffle is removed to find the test bullet.

[0102] The test projectile, test projectile recovery method, and recovery device provided in this application allow for the testing and recovery of test projectiles using a smaller target range, greatly improving the integrity and efficiency of the recovery. Moreover, the impact point of the test projectile is accurate and reliable, avoiding the situation where errors in ballistic calculations in traditional methods make it difficult to recover the test projectile. In addition, the gradually increasing impedance in multiple recovery stages minimizes the damage to the test projectile during recovery, and the high-speed camera can capture the entire process from the launch of the test projectile to its impact, which is helpful for the later analysis and improvement of the test.

[0103] The above description is merely a specific implementation of this application, but the scope of protection of this application is not limited thereto.

Claims

1. A method for recovering a test missile, characterized in that, The test missiles included: The first housing has a first groove-shaped structure and a second groove-shaped structure arranged symmetrically; An antenna, disposed within the first slotted structure and the second slotted structure, is used to receive satellite signals; The missile-borne receiver circuit box is located inside the first housing and connected to the antenna, used to determine the current position of the test missile based on the satellite signal; A buffer structure, connected to the missile-borne receiver circuit box, is used to reduce the overload effect on the missile-borne receiver circuit box during the launch of the test missile; A base assembly is disposed at one end of the first housing and has an abutment portion and a connecting portion. The abutment portion abuts against the missile-borne receiver circuit box, and the connecting portion is connected to the first housing. A cavity structure is provided between the abutment portion and the connecting portion. The recycling device includes: The second shell, disposed on the base, has a cavity structure, wherein the inner diameter parameter of the cavity structure is larger than the outer diameter parameter of the test projectile; Baffles are movably disposed at the first end, the second end, and the middle of the second housing, respectively, to divide the cavity structure into at least two cavities, wherein the at least two cavities are coaxially arranged and the axial direction of the cavities is the same as the launch direction of the test projectile; The filling structures are respectively disposed in the at least two cavities, and the density of the filling structures in the at least two cavities is different; The base is connected to the second housing and is used to support the second housing; The recycling method includes: In response to the detection that the test missile has been fired, the middle baffle of the test missile recovery device is controlled to eject the second housing; in order to detect whether there is a bullet penetration hole on the middle baffle. If the middle baffle has the bullet penetration hole, the rear baffle of the test bullet recovery device is controlled to pop out of the second housing to locate the test bullet on the rear baffle; If there is no bullet penetration hole on the middle baffle, the front baffle of the test bullet recovery device is popped out of the second housing to locate the test bullet on the front baffle or in the cavity near the front baffle. The middle baffle is located between the front baffle and the rear baffle. The front baffle is located at the end of the test missile recovery device that is closer to the direction of launch of the test missile, and the rear baffle is located at the end of the test missile recovery device that is farther away from the direction of launch of the test missile.

2. The method according to claim 1, characterized in that, The buffer structure includes: The first buffer is disposed between the missile-borne receiver circuit box and the first housing; The second buffer is disposed between the missile-borne receiver circuit box and the base assembly; The first buffer and the second buffer have different buffering performance.

3. The method according to claim 2, characterized in that, The difference in buffering performance between the first buffer and the second buffer is manifested in the following ways: The first buffer is made of at least one material selected from elastic nylon, polyurethane, and pine block, wherein the elastic nylon material satisfies a preset elasticity condition; The second buffer is made of polyurethane foam material with a density of 0.25 g - 0.32 g / cm3.

4. The method according to claim 2, characterized in that, There is a first gap between the missile-borne receiver circuit box and the first housing; the first buffer has a first thickness from one side of the missile-borne receiver circuit box to one side of the first housing, and the first thickness is greater than the first gap.

5. The method according to claim 4, characterized in that, The first thickness is 0.1-0.15 mm larger than the first gap.

6. The method according to claim 1, characterized in that, The base assembly includes: The base body has the connecting portion and the recessed portion; The base cover has a first end that abuts against the missile-borne receiver circuit box and a second end that is connected to the first end of the base body, forming the cavity structure. The recessed portion is disposed opposite to the cavity structure, and the diameter of the recessed portion is greater than or equal to 40mm.

7. The method according to claim 1, characterized in that, The test missile also includes a protective cover that fits over the first slotted structure and the second slotted structure to protect the antenna.

8. The method according to claim 1, characterized in that, The end of the first housing away from the base assembly is a frustum-shaped structure with a cone angle of 45°-75°.

9. The method according to any one of claims 1 to 8, characterized in that, The first housing and the base assembly are made of rigid materials.

10. The method according to claim 1, characterized in that, The baffle divides the cavity structure into three chambers, and the filling structures in the three chambers, from the launch direction of the test projectile, are, in order, a liquid filling structure, a mixed filling structure of solid and liquid, and a solid filling structure.

Images