Fragment recovery apparatus for ballistic disintegration test

Abstract

The application relates to the technical field of space debris capture, in particular to a device for recovering debris in a hypervelocity impact experiment, which comprises a target chamber and a capture structure, the target chamber is internally formed with a target cavity for placing a simulation target; the capture structure is arranged on the inner wall of the target cavity and comprises a first capture layer and a second capture layer, the second capture layer covers the inner wall of the target cavity, the first capture layer covers one side of the second capture layer away from the inner wall of the target cavity, the density of the first capture layer is smaller than that of the second capture layer, and the first capture layer is a transparent structure. Small-sized and low-energy micro debris are captured by the first capture layer, large-sized and high-energy debris pass through the first capture layer and are captured by the second capture layer, the number of micro debris entering the second capture layer is reduced, thereby facilitating the positioning and extraction of large debris in the second capture layer based on X-ray and sectioning methods, the debris recovery rate is improved, and the difficulty of extracting micro debris is reduced due to the transparent structure of the first capture layer.

Description

Technical Field

[0001] This application relates to the field of space debris capture technology, and in particular to a device for recovering debris from impact disintegration experiments. Background Technology

[0002] The purpose of space debris impact disintegration experiments is to obtain the disintegration threshold, characteristic dimensions, surface-to-mass ratio, and quantity distribution of disintegration debris, providing technical support for the establishment and improvement of space debris environment models. The impact velocities in disintegration experiments typically fall within the ultra-high-speed impact range. Modern typical satellites have complex structures and diverse materials; under strong impact, material and structural fracture failures are irregular. The characteristics of spacecraft model disintegration debris are extremely complex, not only in their sheer quantity but also in the variety of materials, complex shapes, and wide scale ranges, posing significant challenges to the recovery and extraction of disintegration debris.

[0003] Currently, the primary method used in impact disintegration tests is soft recovery using foam boards. Specifically, a foam layer is attached to the plywood lining the target chamber. The foam layer employs two to three density designs to capture debris at different velocities. After the test, X-ray scanning is used to determine the spatial distribution of debris within the foam board.

[0004] First, this method primarily addresses the recovery of fragments larger than 2mm; fragments smaller than 2mm are too difficult to recover and are largely not considered. Second, after recovering the fragments, this method uses X-ray scanning to precisely locate the disintegrated fragments within the foam board. However, X-rays, due to their inherent characteristics, have certain limitations during scanning. On one hand, information about some fragments that are transmissive to X-rays is lost, resulting in some fragments not being detected and causing a loss in the quality of the recovered fragments. On the other hand, the foam board contains numerous tiny fragments, making X-ray scanning, location, and extraction extremely time-consuming and labor-intensive. Using a foam board dissection method would also lead to excessively time-consuming fragment recovery and difficulty in detecting tiny fragments. Therefore, the foam board recovery method has shortcomings and difficulties in extracting tiny fragments, and it is essentially unable to recover fragments smaller than 2mm. Summary of the Invention

[0005] This application provides a fragment recovery device for impact disintegration tests, which solves the problem of difficulty in extracting and low recovery rate of tiny fragments generated by impact disintegration tests in the prior art.

[0006] This application provides a fragment recovery device for impact disintegration tests, comprising:

[0007] The target chamber contains a target cavity inside, which is used to place the simulated target.

[0008] A capture structure is disposed on the inner wall of the target cavity. The capture structure includes a first capture layer and a second capture layer. The second capture layer covers the inner wall of the target cavity, and the first capture layer covers the side of the second capture layer away from the inner wall of the target cavity. The density of the first capture layer is less than that of the second capture layer, and the first capture layer is a transparent structure.

[0009] In one possible design, the first capture layer is a multilayer membrane structure.

[0010] In one possible design, the first capture layer includes a flexible membrane, which has at least two layers, with an enclosing portion formed between adjacent flexible membrane layers.

[0011] In one possible design, air bubbles are uniformly formed between two adjacent flexible membrane layers through spaced bonding.

[0012] In one possible design, the bubble is round.

[0013] In one possible design, the distance between two adjacent bubbles is smaller than the diameter of the bubble.

[0014] In one possible design, the bubble diameter is 6mm-25mm; and / or, the bubble thickness is 2mm-12mm.

[0015] In one possible design, the density of the flexible membrane is 0.015 g / cm³. 3 -0.045g / cm 3 .

[0016] In one possible design, the density of the second trapping layer is 2-4 times that of the flexible membrane.

[0017] In one possible design, the second trapping layer is a foam board structure.

[0018] The beneficial effects of this application are as follows:

[0019] The impact disintegration test debris recovery device of this application comprises a first capture layer and a second capture layer on the inner wall of the target chamber. The first capture layer is close to the simulated target. After the projectile impacts the simulated target, the target disintegrates under the impact force, producing debris of varying sizes. The debris rushes towards the surrounding first and second capture layers. Since the density of the first capture layer is lower than that of the second capture layer, on the one hand, smaller debris with lower kinetic energy is directly captured by the first capture layer. Because the first capture layer is transparent, it is convenient to directly locate and extract the debris within it, thus improving the recovery rate of the debris. On the other hand, larger debris with higher kinetic energy passes through the first capture layer and enters the second capture layer, where it is captured. Since the debris is basically intercepted by the first capture layer, the number of debris entering the second capture layer is effectively reduced. This facilitates the location and extraction of larger debris in the second capture layer based on X-ray and profiling methods, greatly improving the debris recovery rate, significantly reducing the difficulty of debris extraction, and improving the debris extraction efficiency. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the specific embodiments of this application or the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the impact disintegration test debris recovery device provided in the embodiments of this application;

[0022] Figure 2 This is a schematic diagram of the structure of the first capture layer of the impact disintegration test debris recovery device provided in the embodiments of this application.

[0023] Figure label:

[0024] 100, Target chamber; 110, Target cavity; 200, Simulated target; 310, First capture layer; 311, Flexible membrane; 312, Bubble; 320, Second capture layer. Detailed Implementation

[0025] The technical solutions of this application will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0026] The following is combined Figures 1-2This application describes the impact disintegration test debris recovery device provided in the embodiments of this application.

[0027] Reference Figure 1 As shown in the embodiment of this application, the impact disintegration test debris recovery device includes a target chamber 100 and a capture structure. The target chamber 100 has a target cavity 110 inside, which simulates a vacuum environment and is used to place a simulated target 200 during the test. For example, the simulated target 200 is a spacecraft model, which is placed in the middle of the target cavity 110. By launching projectiles at the spacecraft model, the model disintegrates under the impact force of the projectiles, and the fragments of the disintegrated spacecraft model will impact the inner wall of the target chamber 100. After the test, it is necessary to recover as many fragments of the spacecraft model as possible. By obtaining the disintegration threshold, characteristic dimensions, surface-to-mass ratio, and quantity distribution of the disintegrated fragments, technical support data is provided for the establishment and improvement of the space debris environment model. The capture structure is used to capture these spacecraft model fragments.

[0028] The capture structure covers the inner wall of the target cavity 110, excluding the test window. Specifically, the capture structure includes a first capture layer 310 and a second capture layer 320, each with a clearance window for avoiding the test window. The second capture layer 320 covers the inner wall of the target cavity 110 and is in direct contact with it. The first capture layer 310 covers the side of the second capture layer 320 away from the inner wall of the target cavity 110, i.e., the side closer to the simulated target 200. The fragments after disintegration first reach the first capture layer 310 and then the second capture layer 320. The density of the first capture layer 310 is less than that of the second capture layer 320, and the first capture layer 310 is a transparent structure, such as a transparent film. In this way, small fragments with low kinetic energy are directly captured by the first capture layer 310. Since the first capture layer 310 is a transparent structure, it is convenient to observe the position of the small fragments inside, reducing the difficulty of locating and extracting the small fragments and improving the recovery rate of the small fragments. Larger fragments with high kinetic energy are able to pass through the first capture layer 310 and enter the second capture layer 320, where they are captured. Since the small fragments are basically intercepted by the first capture layer 310, the number of small fragments entering the second capture layer 320 is effectively reduced, which facilitates the location and extraction of larger fragments in the second capture layer 320 based on X-ray and profiling methods. This improves the overall fragment recovery rate, reduces the difficulty of fragment extraction, and improves the fragment extraction efficiency.

[0029] In some specific embodiments provided in this application, the first capture layer 310 is a multilayer membrane structure. The number of membrane layers is set according to the test parameters of the projectile or simulated target 200. For example, the number of membrane layers can be two, three, four, etc. By designing the first capture layer 310 as a multilayer membrane, with each layer being a transparent membrane, the multilayer membrane structure retains the transparency of the membrane while also possessing a certain degree of impact resistance. This allows small, low-kinetic-energy fragments to be intercepted, while large, high-kinetic-energy fragments can penetrate and successfully reach the second capture layer 320. Furthermore, due to the relatively soft texture of the membrane, the multilayer membrane can trap the intercepted small fragments on the multilayer membrane, facilitating extraction and recovery.

[0030] In some specific embodiments provided in this application, the first capturing layer 310 includes a flexible membrane 311, which is at least two layers, for example, two, three, four, etc. Specifically, the flexible membrane 311 is a transparent polyethylene film, which is lightweight, transparent, and has excellent impact absorption performance. The number and thickness of the flexible membrane 311 can be determined based on the impact parameters of the impact test and the parameters of the spacecraft model, such as the diameter and velocity of the projectile and the original mass of the projectile and spacecraft, so that the first capturing layer 310 can capture as many millimeter-sized and smaller fragments as possible. An enclosing portion is formed between adjacent flexible membrane layers 311. The enclosing portion has a large porosity. For example, the enclosing portion is a hollow structure formed between adjacent flexible membrane layers 311. The hollow structure is used to create a certain gap between adjacent flexible membrane layers to accommodate the fragments intercepted by the flexible membrane 311, and also to facilitate the fragments to detach from the hollow structure.

[0031] Reference Figure 2As shown, in some specific embodiments provided in this application, the containing portion can also be a bubble 312. Specifically, multiple bubbles 312 are uniformly formed between two adjacent flexible membrane layers 311 through spaced bonding. The shape of the bubble 312 can be circular, rectangular, irregular, etc. Preferably, the bubble 312 is circular. Circular bubbles 312 can avoid sharp corners around the bubble 312, which helps the flexible membrane 311 maintain a certain impact resistance and can intercept debris. At the same time, with a fixed area of ​​flexible membrane, the number of circular bubbles 312 formed will be greater, which helps to increase the effective capture area of ​​the flexible membrane 311. Thus, by bonding adjacent flexible membrane layers 311 together at intervals to form multiple bubbles 312, firstly, without adding other materials, the distance between adjacent flexible membrane layers 311 can be increased, allowing fragments that penetrate or are embedded in the previous flexible membrane layer 311 to be temporarily stored in the corresponding bubbles 312; secondly, since the bubbles 312 contain only air, they will not cause secondary damage to the fragments and can more realistically restore the original shape of the fragments; thirdly, the bubbles 312 are hollow, thereby maintaining a high degree of transparency in the first capture layer 310 as a whole, making it easier to observe the position of fragments embedded in the flexible membrane 311 or in the bubbles 312 when recovering fragments, thus facilitating extraction.

[0032] In some specific embodiments, the spacing between two adjacent bubbles 312 is smaller than the diameter of the bubble 312. This maximizes the effective capture area of ​​the entire flexible membrane 311. Specifically, the diameter of the bubble 312 is 6mm-25mm, for example, the diameters of the bubble 312 are 6mm, 10mm, 15mm, 50mm, 25mm, etc. The thickness of the bubble 312 is 2mm-12mm, for example, the thickness of the bubble 312 is 2mm, 4mm, 6mm, 8mm, 10mm, 12mm, etc. The density of the flexible membrane 311 is 0.015g / cm³. 3 -0.045g / cm 3 For example, the density of flexible membrane 311 is 0.015 g / cm³. 3 0.025g / cm 3 0.035g / cm 3 0.045g / cm 3 wait.

[0033] In some specific embodiments provided in this application, the second trapping layer 320 is a foam board structure. The density of the second trapping layer 320 is 2-4 times the density of the flexible membrane 311. For example, the density of the second trapping layer 320 is 0.135 g / cm³. 3 This prevents large, high-kinetic-energy fragments from passing through the second capture layer 320, thus avoiding damage to the target chamber 100.

[0034] Before conducting the experiment, it is necessary to determine the density and number of layers of the flexible membrane 311, the thickness and diameter of the bubble 312, and the density and thickness of the second trapping layer 320. The specific design method is as follows:

[0035] Based on the impact parameters and spacecraft model parameters designed for the experiment, the impact kinetic energy to the mass ratio of the impacted object, EMR, is calculated, where EMR = E / M, E is the impact kinetic energy, M is the mass of the impacted object, and the impacted object is the spacecraft model.

[0036] Based on the calculated EMR, the impact disintegration situation is preliminarily determined, and the density and number of layers of the flexible membrane 311, as well as the diameter and thickness of the bubble 312, are designed; the density and thickness of the second trapping layer 320 are also designed.

[0037] A second capture layer 320 is laid on the inner wall of the target chamber 100, so that the second capture layer 320 covers the other parts of the inner wall of the target chamber 100 except for the test window;

[0038] A first capture layer 310 is laid on the second capture layer 320, and the first capture layer 310 covers the second capture layer 320 except for the test window.

[0039] Install the spacecraft model, debug the testing equipment, and start the experiment;

[0040] After the experiment, the first capture layer 310 and the second capture layer 320 were recovered respectively; the fragments on the first capture layer 310 could be directly observed and extracted, while the fragments on the second capture layer 320 could be located by X-ray scanning and then extracted using the profiling method.

[0041] The mass of each extracted fragment is measured to obtain the total mass of the recovered fragments. The mass percentage of recovered fragments, N%, is calculated, where N% = M. d / (M) p +M s M d To recover the total mass of the debris, M p For the mass of the projectile, M s To simulate the mass of target 200;

[0042] The effectiveness of recycling is assessed based on the mass ratio of the recycled fragments.

[0043] Adjust the density and number of layers of the flexible membrane 311, as well as the diameter and thickness of the bubble 312 and the density and thickness of the second capture layer 320, according to the recycling effect.

[0044] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.

[0045] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0046] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between components; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0047] In this application, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0048] Although embodiments of this application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting this application. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of this application.

Claims

1. A shatter-recovery device for a ballistic disintegration test, characterized in that, The application relates to a target chamber, comprising: a target chamber formed inside for placing a simulation target; a capture structure arranged on the inner wall of the target chamber, the capture structure comprising a first capture layer and a second capture layer, the second capture layer being arranged on the inner wall of the target chamber, the first capture layer being arranged on the side of the second capture layer away from the inner wall of the target chamber, the density of the first capture layer being smaller than that of the second capture layer, and the first capture layer being a transparent structure; the first capture layer is a multilayer film structure comprising at least two flexible films, and bubbles are uniformly formed between adjacent two flexible films through interval bonding.

2. The impact disintegration test fragment recovery apparatus of claim 1, wherein: The bubbles are circular.

3. The impact disintegration test fragment recovery apparatus of claim 2, wherein: The interval between adjacent two bubbles is smaller than the diameter of the bubbles.

4. The impact disintegration test fragment recovery apparatus of claim 3, wherein: The diameter of the bubbles is 6-25 mm; and / or the thickness of the bubbles is 2-12 mm.

5. The impact disintegration test fragment recovery apparatus of any one of claims 1-4, wherein: The density of the flexible film is 0.015 g / cm 3 -0.045 g / cm 3 .

6. The impact disintegration test fragment recovery apparatus of any one of claims 1-4, wherein: The density of the second capture layer is 2-4 times that of the flexible film.

7. The impact disintegration test fragment recovery apparatus of any one of claims 1-4, wherein: The second capture layer is a foam board structure.

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