Device and method for dynamically monitoring weak components during rocket simulation launch

Abstract

A device and method for dynamically monitoring weak components during a simulated rocket launch, belonging to the field of detection technology, addresses the technical problem that the combination of traditional speckle marking methods and DIC technology cannot meet the requirements for remote, real-time dynamic monitoring of the deformation of weak components on the rocket shell in the first few seconds of rocket launch. The solution is to affix a matrix of quantum dot stickers to the surface of the weak components on the rocket shell. When the quantum dot stickers are stimulated by light and emit light within a certain period of time, the position changes of the luminescent quantum dot stickers are tracked and observed by a visual signal acquisition system arranged at an appropriately remote location. The present invention combines quantum dot technology with DIC technology to achieve timely monitoring and analysis of the surface deformation degree and structural reliability of weak components on the rocket shell during the first few seconds of rocket launch, under conditions of high thrust and high acceleration, thereby accelerating the rocket development cycle and improving the safety and reliability of the rocket.

Description

Technical Field

[0001] The present invention belongs to the field of detection technology, and in particular relates to a device and method for dynamically monitoring weak components during a rocket simulation launch process. Background Art

[0002] The outer shell of a rocket assembly has a number of weak components. For example, the interstage separation ring (known as the V-shaped weak groove structure) must be resistant to radial damage during both static and dynamic launches to ensure smooth separation between stages, while also ensuring reliable axial load-bearing capacity. Therefore, these weak components in the outer shell of a rocket become a key and challenging area in rocket design and development, crucial to the success or failure of the rocket's launch mission after final assembly.

[0003] During the first few seconds of a rocket launch, the high accelerations can easily damage vulnerable components such as weakening grooves in the rocket shell. Therefore, during the R&D phase, remote, real-time dynamic monitoring of these vulnerable components is essential, simulating an actual launch. Electrical measurement requires extensive wiring connections to collect, analyze, and analyze strain gauge data, which is impossible during the dynamic process of a rocket launch. Over the past few decades, DIC (Digital Image Correlation) technology has made significant progress. DIC is a measurement method that uses correlation to obtain deformation information from a specimen. Its basic principle is to correlate two digital images of the specimen before and after deformation to obtain deformation information in the region of interest. This method has flexible experimental requirements and offers advantages such as full-field measurement, strong interference immunity, and high measurement accuracy. It is widely used in fields such as materials science, biomedicine, and aerospace. However, the speckle pattern generation required for monitoring relies heavily on operator experience, making precise placement difficult, especially on complex structures. Due to the limitations of monitoring distance, high-brightness environment, smoke and other complex conditions during rocket launch, the DIC speckle marking method used to monitor and track the deformation process of the target sample is difficult to accurately and effectively track the stress and deformation of weak components on the rocket shell (especially in the first few seconds of the rocket launch).

[0004] On the other hand, driven by the large demand for aerospace engineering research and development, many theoretical models related to material deformation have been proposed. When further experimentally verified, if the finite element analysis method is used, the verification steps are complicated and may differ greatly from the actual launch situation. If the number of experimental verifications is to be increased, actual launch experiments will be subject to the high cost of components with special structures, and it is impossible to conduct frequent and large-scale launch experiments to fully verify these theoretical models, resulting in a delay in the development of the entire aerospace vehicle. Summary of the Invention

[0005] The main purpose of the present invention is to overcome the shortcomings of the existing technology and solve the technical problem that the combination of traditional speckle marking method and DIC technology cannot meet the requirements of long-distance real-time dynamic monitoring of the deformation of weak components on the rocket shell in the first few seconds of rocket launch. The present invention provides a device and method for dynamic monitoring of weak components during a simulated rocket launch.

[0006] The design concept of the present invention is to combine quantum dot technology with DIC technology to replace the DIC-speckle deformation monitoring technology commonly used for static monitoring of rockets. The present invention sticks a matrix of quantum dot stickers on the surface of weak components on the rocket shell. When the quantum dot stickers are stimulated by light and emit light within a certain period of time, the position changes of the luminous quantum dot stickers are tracked and observed by multiple groups of high-precision monocular cameras and high-magnification binoculars (visual signal acquisition systems) arranged at appropriately long distances. In the first few seconds of the rocket launch, when the rocket is subjected to high thrust and high acceleration conditions, timely monitoring and analysis of the surface deformation degree and structural reliability of weak components on the rocket shell can be achieved, thereby accelerating the rocket research and development cycle and improving the safety and reliability of the rocket.

[0007] In order to achieve the above-mentioned object of the invention, the present invention provides the following technical solutions:

[0008] A device for dynamically monitoring weak components during a simulated rocket launch, comprising a quantum dot matrix and a visual signal acquisition system, wherein: a plurality of the quantum dot matrixes are attached to the surface of weak components on a rocket casing, and the visual signal acquisition system is disposed at a predetermined distance from the weak components;

[0009] The quantum dot sticker matrix includes a number of quantum dot stickers, each of which includes a quantum dot layer, a water and oxygen barrier material layer, a release paper, a visible light filter membrane, and an adhesive layer. The water and oxygen barrier material layers are respectively provided on the inner and outer surfaces of the quantum dot layer. The visible light filter membrane is adhered to the outer surface of the release paper (i.e., anti-sticking paper). The visible light filter membrane is detachably adhered to the water and oxygen barrier material layer near the outer side through the release paper, and an adhesive layer is provided on the water and oxygen barrier material layer near the inner side. Before dynamic monitoring of weak components, the visible light filter membrane can effectively block visible light, so that the quantum dot layer will not be excited by visible light and emit light. When the weak component needs to be dynamically monitored, the visible light filter membrane is manually torn off along with the release paper. The quantum dot layer is excited by the visible light in the experimental environment and emits light, which is then captured and collected by the visual signal acquisition system.

[0010] The visual signal acquisition system includes a base, a transparent cover, and a vibration-damping mechanism, a high-precision monocular camera, and a high-magnification telescope arranged in the transparent cover. The vibration-damping mechanism includes a column, a glass fiber rope, a viscous damper, a spring, a circular pendulum, and a rectangular pendulum. The circular pendulum includes a primary circular pendulum and a secondary circular pendulum, and the rectangular pendulum includes a primary rectangular pendulum, a secondary rectangular pendulum, and a tertiary rectangular pendulum. The columns are vertically fixed upward at the four corners of the base. The four corners of the primary circular pendulum are flexibly suspended between the tops of the four columns by glass fiber ropes. The secondary circular pendulum is arranged below the primary circular pendulum. A plurality of viscous dampers are evenly distributed at the edge position between the primary circular pendulum and the secondary circular pendulum, and a plurality of springs are evenly distributed at the center position between the primary circular pendulum and the secondary circular pendulum; a primary rectangular pendulum, a secondary rectangular pendulum and a tertiary rectangular pendulum are arranged in order from top to bottom below the secondary circular pendulum, and the four corners of the secondary circular pendulum and the primary rectangular pendulum, as well as the four corners of adjacent rectangular pendulums, are flexibly connected by glass fiber ropes; a bracket is fixedly provided on the upper surface of the tertiary rectangular pendulum, and a plurality of high-precision monocular cameras and a plurality of high-magnification telescopes are fixedly installed on the bracket, and the high-precision monocular cameras and the high-magnification telescopes are aligned with the quantum dot patch matrix.

[0011] Furthermore, the thickness of the quantum dot sticker is 3 μm-4 μm.

[0012] Furthermore, the weak component on the rocket casing is the rocket stage separation ring.

[0013] Furthermore, the base is made of stone, and the transparent cover is a double-layer impact-proof vacuum glass cover.

[0014] A method for dynamically monitoring weak components in rocket launches using the above-mentioned device comprises the following steps:

[0015] S1. Preparing a quantum dot sticker: Selecting the type of quantum dots according to the experimental environment and then preparing a quantum dot layer, then preparing a water- and oxygen-blocking material layer on the inner and outer surfaces of the quantum dot layer, respectively. Finally, a visible light filter membrane is adhered to the water- and oxygen-blocking material layer near the outer side through release paper, and an adhesive layer is provided on the water- and oxygen-blocking material layer near the inner side to prepare the quantum dot sticker;

[0016] S2. Pasting a quantum dot patch matrix: Cut the quantum dot patch prepared in step S1 into various shapes and sizes according to the location and area of ​​the weak parts on the rocket shell, and then paste the quantum dot patch on the parts where deformation or strain may occur, forming a pasted quantum dot patch matrix;

[0017] S3. Arrange visual signal acquisition system: With the rocket launch position as the center, arrange at least one visual signal acquisition system within a radius of 300-3000m, so that each quantum dot matrix corresponds to at least one visual signal acquisition system;

[0018] S4. Dynamic monitoring of deformation / strain of weak components: Before dynamic monitoring, a dedicated person will tear off the release paper and visible light filter membrane from all quantum dot matrixes. The quantum dot matrix will be excited by the light from the experimental environment and emit light. The high-precision monocular camera and high-magnification telescope will be adjusted to align with the corresponding and luminous quantum dot matrix to dynamically monitor the deformation / strain of weak components in real time at a long distance. The high-precision monocular camera and high-magnification telescope will transmit the visual signals of the collected quantum dot position changes to the DIC technology software, and the two digital images before and after the deformation / strain of the weak component will be calculated to obtain deformation information, determine the degree of surface deformation of the weak component, and perform real-time analysis of the structural reliability of the weak component.

[0019] Furthermore, the light source in the experimental environment is sunlight or visible light lighting equipment.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] The present invention combines quantum dot technology with DIC technology by flexibly arranging multiple groups of visual signal acquisition systems within an appropriate range, in conjunction with a quantum dot sticker matrix pasted at the locations of weak components on the outside of the rocket shell. This replaces the traditional DIC-speckle deformation monitoring technology for static analysis of rockets, and solves the technical problem that the combination of traditional speckle marking methods and DIC technology cannot meet the requirements of long-distance real-time dynamic monitoring of the deformation of weak components on the rocket shell in the first few seconds of rocket launch. This shortens the rocket research and development cycle and improves the safety and reliability of the rocket. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 This is a schematic diagram of the arrangement of the rocket and the visual signal acquisition system in the present invention;

[0023] Figure 2 This is a schematic diagram of the assembly structure of the quantum dot matrix and weak components in the present invention;

[0024] Figure 3 This is a schematic diagram of the overall cross-sectional structure of the quantum dot sticker in the present invention;

[0025] Figure 4 This is a schematic diagram of the three-dimensional structure of the visual signal acquisition system;

[0026] Figure 5 This is a schematic diagram of the main structure of the visual signal acquisition system (transparent cover omitted);

[0027] Figure 6 This is an exploded view of the visual signal acquisition system parts (transparent cover omitted).

[0028] In the figure, 1 is a rocket, 2 is a visual signal acquisition system, 3 is a quantum dot sticker, 4 is a weak component, 5 is a visible light filter membrane, 6 is a release paper, 7 is a water and oxygen barrier material layer, 8 is a quantum dot layer, 9 is a transparent cover, 10 is a base, 11 is a fiberglass rope, 12 is a circular pendulum, 13 is a spring, 14 is a viscous damper, 15 is a rectangular pendulum, 16 is a high-precision monocular camera, 17 is a bracket, 18 is a column, 19 is a high-magnification telescope, and 20 is an adhesive layer. DETAILED DESCRIPTION

[0029] The present invention will be described in further detail below with reference to the accompanying drawings and examples.

[0030] like Figures 1 to 6 The device shown is a device for dynamically monitoring weak components during a simulated rocket launch, comprising a quantum dot matrix and a visual signal acquisition system 2. Several of the quantum dot matrixes are attached to the surface of a weak component 4 (in this embodiment, the weak component 4 is a separation ring between rocket stages) on the outer shell of a rocket 1, and the visual signal acquisition system 2 is positioned at a predetermined distance from the weak component 4.

[0031] The quantum dot patch matrix includes a plurality of quantum dot patches 3, each having a thickness of 3 μm to 4 μm. The quantum dot patch 3 includes a quantum dot layer 8, a water and oxygen barrier material layer 7, a release paper 6, a visible light filter membrane 5, and an adhesive layer 20. The water and oxygen barrier material layers 7 are respectively provided on the inner and outer surfaces of the quantum dot layer 8. The visible light filter membrane 5 is adhered to the outer surface of the release paper 6. The visible light filter membrane 5 is detachably adhered to the water and oxygen barrier material layer 7 near the outer side through the release paper 6. The adhesive layer 20 is provided on the water and oxygen barrier material layer 7 near the inner side.

[0032] The visual signal acquisition system 2 includes a base 10, a transparent cover 9, and a vibration elimination mechanism, a high-precision monocular camera 16 and a high-magnification telescope 19 arranged in the transparent cover 9. The base 10 is made of stone, and the transparent cover 9 is a double-layer impact-proof vacuum glass cover. The vibration elimination mechanism includes a column 18, a glass fiber rope 11, a viscous damper 14, a spring 13, a circular pendulum 12 and a rectangular pendulum 15. The circular pendulum 12 includes a first-level circular pendulum and a second-level circular pendulum, and the rectangular pendulum 15 includes a first-level rectangular pendulum, a second-level rectangular pendulum and a third-level rectangular pendulum; the column 18 is fixedly installed vertically upward at the four corners of the base 10, and the four corners of the first-level circular pendulum are flexibly suspended on the top of the four columns 18 through the glass fiber rope 11. Between the parts, the secondary circular pendulum is arranged below the primary circular pendulum, a number of viscous dampers 14 are evenly distributed at the edge position between the primary circular pendulum and the secondary circular pendulum, and a number of springs 13 are evenly distributed at the center position between the primary circular pendulum and the secondary circular pendulum; below the secondary circular pendulum, a primary rectangular pendulum, a secondary rectangular pendulum and a tertiary rectangular pendulum are arranged from top to bottom, and the four corners of the secondary circular pendulum and the first rectangular pendulum and the four corners of the adjacent rectangular pendulum 15 are flexibly connected by glass fiber ropes 11; a bracket 17 is fixed on the upper surface of the three-stage rectangular pendulum, and a number of high-precision monocular cameras 16 and a number of high-magnification telescopes 19 are fixedly mounted on the bracket 17, and the high-precision monocular cameras 16 and the high-magnification telescopes 19 are aligned with the quantum dot matrix.

[0033] A method for dynamically monitoring weak components in rocket launches using the above-mentioned device comprises the following steps:

[0034] S1. Preparing a quantum dot patch 3: Selecting the type of quantum dots according to the experimental environment to prepare a quantum dot layer 8, then preparing a water- and oxygen-blocking material layer 7 on the inner and outer surfaces of the quantum dot layer 8, respectively. Finally, attaching a visible light filter membrane 5 to the water- and oxygen-blocking material layer 7 near the outer side via a release paper 6, and providing an adhesive layer 20 on the water- and oxygen-blocking material layer 7 near the inner side, thereby preparing a quantum dot patch 3;

[0035] S2. Pasting a quantum dot patch matrix: According to the position and area of ​​the weak parts 4 on the shell of the rocket 1, the quantum dot patches 3 prepared in step S1 are cut into shapes and sizes of various specifications, and then the quantum dot patches 3 are pasted on the parts of the weak parts 4 where deformation or strain may occur, forming a pasted quantum dot patch matrix;

[0036] S3. Arrange visual signal acquisition system 2: With the launch position of rocket 1 as the center, arrange at least one visual signal acquisition system 2 within a radius of 300-3000m, so that each quantum dot matrix corresponds to at least one visual signal acquisition system 2;

[0037] S4. Dynamic Monitoring of Deformation / Strain Locations of Weak Component 4: Prior to dynamic monitoring, a dedicated personnel will remove the release paper 6 and visible light filter 5 from all quantum dot matrix patches. The quantum dot matrix patches are then stimulated by the ambient light in the experimental environment to emit light. If observed during the day, sunlight (i.e., daylight) will activate the quantum dots in quantum dot layer 8 to emit corresponding light. If observed at night, visible light illumination equipment installed on the rocket launch tower will illuminate the rocket 1 and activate the quantum dots in quantum dot layer 8 to emit light. A high-precision monocular camera 16 and a high-magnification telescope 19 are aligned with the corresponding, luminous quantum dot matrix patches to dynamically monitor the deformation / strain of weak component 4 from a distance in real time. The high-precision monocular camera 16 and the high-magnification telescope 19 transmit the captured visual signals of quantum dot position changes to the DIC technology software. The two digital images, before and after the deformation / strain location of weak component 4, are calculated to obtain deformation information, determine the degree of surface deformation of weak component 4, and conduct real-time analysis of the structural reliability of weak component 4.

[0038] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present invention should be included in the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be based on the scope of protection of the claims.

Claims

1. A device for dynamically monitoring weak components during a simulated rocket launch, comprising a quantum dot matrix and a visual signal acquisition system (2), characterized in that: A plurality of the quantum dot matrix stickers are attached to the surface of a weak component (4) on the outer shell of the rocket (1), and a visual signal acquisition system (2) is arranged at a predetermined distance from the weak component (4); The quantum dot patch matrix includes a plurality of quantum dot patches (3), the quantum dot patch (3) includes a quantum dot layer (8), a water- and oxygen-blocking material layer (7), a release paper (6), a visible light filter membrane (5), and an adhesive layer (20), the water- and oxygen-blocking material layer (7) being provided on the inner and outer surfaces of the quantum dot layer (8), the visible light filter membrane (5) being adhered to the outer surface of the release paper (6), the visible light filter membrane (5) being detachably adhered to the water- and oxygen-blocking material layer (7) near the outer side through the release paper (6), and the adhesive layer (20) being provided on the water- and oxygen-blocking material layer (7) near the inner side; The visual signal acquisition system (2) includes a base (10), a transparent cover (9), and a vibration elimination mechanism, a high-precision monocular camera (16), and a high-magnification telescope (19) arranged in the transparent cover (9). The vibration elimination mechanism includes a column (18), a glass fiber rope (11), a viscous damper (14), a spring (13), a circular pendulum (12), and a rectangular pendulum (15). The circular pendulum (12) includes a first-stage circular pendulum and a second-stage circular pendulum. The rectangular pendulum (15) includes a first-stage rectangular pendulum, a second-stage rectangular pendulum, and a third-stage rectangular pendulum. The column (18) is fixedly mounted vertically upward at the four corners of the base (10). The four corners of the first-stage circular pendulum are flexibly suspended between the tops of the four columns (18) through the glass fiber rope (11). The second-stage circular pendulum is The pendulum is arranged below the first-stage circular pendulum, a plurality of viscous dampers (14) are evenly distributed at the edge position between the first-stage circular pendulum and the second-stage circular pendulum, and a plurality of springs (13) are evenly distributed at the center position between the first-stage circular pendulum and the second-stage circular pendulum; a first-stage rectangular pendulum, a second-stage rectangular pendulum and a third-stage rectangular pendulum are arranged in order from top to bottom below the second-stage circular pendulum, and the four corner positions of the second-stage circular pendulum and the first-stage rectangular pendulum and the four corner positions of the adjacent rectangular pendulum (15) are flexibly connected by glass fiber ropes (11); a bracket (17) is fixedly arranged on the upper surface of the third-stage rectangular pendulum, and a plurality of high-precision monocular cameras (16) and a plurality of high-magnification telescopes (19) are fixedly installed on the bracket (17), and the high-precision monocular cameras (16) and the high-magnification telescopes (19) are aligned with the quantum dot matrix.

2. The device for dynamically monitoring weak components during a rocket simulated launch according to claim 1, characterized in that: The thickness of the quantum dot sticker (3) is 3 μm-4 μm.

3. The device for dynamically monitoring weak components during a rocket simulated launch according to claim 1, characterized in that: The weak component (4) on the outer shell of the rocket (1) is a rocket stage separation ring.

4. The device for dynamically monitoring weak components during a rocket simulated launch according to claim 1, characterized in that: The base (10) is made of stone, and the transparent cover (9) is a double-layer impact-proof vacuum glass cover.

5. A method for dynamically monitoring weak components during a simulated rocket launch using the device according to claim 1, characterized in that: The following steps are involved: S1. Preparation of quantum dot sticker (3): Select the type of quantum dots according to the experimental environment and then prepare a quantum dot layer (8); then prepare water-blocking and oxygen-blocking material layers (7) on the inner and outer surfaces of the quantum dot layer (8); finally, adhere the visible light filter membrane (5) to the water-blocking and oxygen-blocking material layer (7) near the outer side through release paper (6); and set an adhesive layer (20) on the water-blocking and oxygen-blocking material layer (7) near the inner side to prepare the quantum dot sticker (3); S2. Pasting a quantum dot patch matrix: cutting the quantum dot patch (3) prepared in step S1 into shapes and sizes of various specifications according to the position and area of ​​the weak parts (4) on the shell of the rocket (1), and then pasting the quantum dot patch (3) on the parts of the weak parts (4) where deformation or strain may occur, to form a pasted quantum dot patch matrix; S3. Arrange the visual signal acquisition system (2): with the launch position of the rocket (1) as the center, arrange at least one visual signal acquisition system (2) within a radius of 300 to 3000 m, so that each quantum dot matrix corresponds to at least one visual signal acquisition system (2); S4. Dynamic monitoring of deformation / strain of weak components (4): Before dynamic monitoring, a dedicated person will tear off the release paper (6) and visible light filter (5) in all quantum dot matrixes. The quantum dot matrix will be excited by the experimental environment light and emit light. The high-precision monocular camera (16) and the high-magnification telescope (19) will be adjusted to align with the corresponding and luminous quantum dot matrix. The deformation / strain of the weak component (4) will be dynamically monitored in real time at a long distance. The high-precision monocular camera (16) and the high-magnification telescope (19) will transmit the visual signals of the collected quantum dot position changes to the DIC technology software. The two digital images before and after the deformation / strain of the weak component (4) will be calculated to obtain deformation information, determine the degree of surface deformation of the weak component (4), and conduct real-time analysis of the structural reliability of the weak component (4).

6. The method according to claim 5, characterized in that The light source in the experimental environment is sunlight or visible light lighting equipment.

Images