Device and method for dynamically monitoring weak parts in simulated rocket launching process

Abstract

The invention discloses a device and a method for dynamically monitoring a weak part in a rocket simulation launching process, belongs to the technical field of detection, and solves the technical problem that the deformation condition of the weak part on a rocket shell cannot be remotely and dynamically monitored in real time in the scene of the first few seconds of rocket launching by combining a traditional speckle marking method and a DIC technology. According to the solution, a quantum dot paste matrix is pasted on the surface of a weak component on a rocket shell, and after quantum dot pastes are excited by light to emit light within a certain time, position changes of the light-emitting quantum dot pastes are tracked and observed through a visual signal acquisition system arranged at a proper long-distance position. The quantum dot technology and the DIC technology are combined, the surface deformation degree and structural reliability of weak parts on a rocket shell can be monitored and analyzed in time under the conditions that the rocket bears large thrust and has large acceleration in the first few seconds of rocket launching, the rocket research and development period is shortened, and the safety and reliability of the rocket are improved.

Description

Technical Field

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

[0002] There are a certain number of weak parts on the outer shell of the rocket assembly. For example, the rocket stage separation ring (i.e., the V-shaped weak groove structure) needs to ensure that it is easy to be damaged radially during static and dynamic launches, so that the rocket stages can be separated smoothly, and at the same time, it needs to ensure reliable axial bearing capacity. Therefore, such weak parts on the rocket shell have become the focus and difficulty of rocket design and development, and are related to the success or failure of the rocket launch mission after assembly.

[0003] In the first few seconds of rocket launch, the high acceleration environment can easily damage weak parts such as weakening grooves on the rocket shell. Therefore, in the research and development stage, it is necessary to conduct long-distance real-time dynamic monitoring of such weak parts when simulating actual launch. If the electrical measurement method is used for real-time dynamic monitoring, more line connection components need to be arranged to realize the acquisition, collection and analysis of strain gauge sensing data, which cannot be achieved in the dynamic process of rocket launch. After decades of development, DIC technology (Digital Image Correlation) has made great progress. DIC technology is a measurement method that obtains specimen deformation information through correlation calculation. Its basic principle is to perform correlation calculation on two digital images before and after the specimen deformation to obtain deformation information of the area of ​​interest. This method has loose requirements on the experimental environment and has the advantages of full-field measurement, strong anti-interference ability and high measurement accuracy. It is widely used in materials science, biomedicine, aerospace and other fields, but the speckle production required for its monitoring depends on the operator's experience, especially on complex structures. It is difficult to achieve accurate arrangement of speckles. 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 restricted by the high cost of components with special structures, and it is impossible to conduct a large number of launch experiments frequently 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 deficiencies in the prior art and solve the technical problem that the combination of the traditional speckle marking method and the DIC technology cannot satisfy the long-distance real-time dynamic monitoring of the deformation of weak components on the rocket shell in the first few seconds of the 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: combining quantum dot technology with DIC technology, replacing the DIC-speckle deformation monitoring technology commonly used in rocket static monitoring. The present invention sticks a quantum dot sticker matrix on the surface of weak components on the rocket shell. When the quantum dot sticker is stimulated by light and emits light within a certain period of time, multiple groups of high-precision monocular cameras and high-magnification binoculars (visual signal acquisition system) arranged at appropriate long-distance positions are used to track and observe the position changes of the luminous quantum dot stickers. In the first few seconds of rocket launch, when the rocket is subjected to high thrust and has 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: A device for dynamically monitoring weak parts during rocket simulated launch, comprising a quantum dot sticker matrix and a visual signal acquisition system, wherein: a plurality of the quantum dot sticker matrices are attached to the surface of the weak parts on the rocket shell, and the visual signal acquisition system is arranged at a predetermined distance from the weak parts; The quantum dot sticker matrix includes a number of quantum dot stickers, and the quantum dot stickers include a quantum dot layer, a water- and oxygen-blocking material layer, a release paper, a visible light filter membrane, and an adhesive layer. The water- and oxygen-blocking material layers are respectively arranged on the inner and outer surfaces of the quantum dot layer, and 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-blocking material layer near the outer side through the release paper, and an adhesive layer is arranged on the water- and oxygen-blocking material layer near the inner side. Before the 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 to emit light; when the weak components need to be dynamically monitored, the visible light filter membrane is manually torn off together with the release paper, and the quantum dot layer is excited by the visible light in the experimental environment to emit light, and then captured and collected by the visual signal acquisition system; The visual signal acquisition system comprises a base, a transparent cover, and a vibration-absorbing mechanism, a high-precision monocular camera and a high-magnification telescope arranged in the transparent cover. The vibration-absorbing mechanism comprises a column, a fiberglass rope, a viscous damper, a spring, a circular pendulum and a rectangular pendulum. The circular pendulum comprises a primary circular pendulum and a secondary circular pendulum, and the rectangular pendulum comprises 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 fiberglass ropes, the secondary circular pendulum is arranged below the primary circular pendulum, and a 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 sequence 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 the adjacent rectangular pendulums are flexibly connected by glass fiber ropes; a bracket is fixedly arranged 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 sticker matrix.

[0008] Furthermore, the thickness of the quantum dot paste is 3 μm-4 μm.

[0009] Furthermore, the weak component on the rocket shell is a rocket stage separation ring.

[0010] Furthermore, the base is made of stone, and the transparent cover is a double-layer impact-proof vacuum glass cover.

[0011] A method for dynamically monitoring weak components of rocket launches using the above device comprises the following steps: S1. Preparing a quantum dot sticker: selecting the type of quantum dots according to the experimental environment and then preparing a quantum dot layer, and then preparing water-blocking and oxygen-blocking material layers on the inner and outer surfaces of the quantum dot layer, respectively, and finally pasting a visible light filter membrane on the water-blocking and oxygen-blocking material layer near the outer side through release paper, and setting an adhesive layer on the water-blocking and oxygen-blocking material layer near the inner side to prepare a quantum dot sticker; S2, pasting the quantum dot sticker matrix: according to the position and area of ​​the weak parts on the rocket shell, the quantum dot stickers prepared in step S1 are cut into shapes and sizes of several specifications, and then the quantum dot stickers are pasted on the parts of the weak parts where deformation or strain may occur, so as to form a pasted quantum dot sticker matrix; S3. Arrange visual signal collection system: with the rocket launch position as the center, arrange at least one visual signal collection system within a radius of 300-3000m, so that each quantum dot matrix corresponds to at least one visual signal collection system; 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 film in all quantum dot matrixes. The quantum dot matrix will be stimulated by the light of the experimental environment to 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 conduct real-time analysis of the structural reliability of the weak component.

[0012] Furthermore, the light source in the experimental environment is sunlight or visible light lighting equipment.

[0013] Compared with the prior art, the present invention has the following beneficial effects: 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 positions of weak components on the outside of the rocket shell, thereby replacing the traditional DIC-speckle deformation monitoring technology for static analysis of rockets. This 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, shortens the rocket research and development cycle, and improves the safety and reliability of the rocket. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a schematic diagram of the arrangement of the rocket and the visual signal acquisition system in the present invention; Figure 2 This is a schematic diagram of the assembly structure of the quantum dot matrix and weak parts in the present invention; Figure 3 This is a schematic diagram of the overall cross-sectional structure of the quantum dot sticker in the present invention; Figure 4 It is a schematic diagram of the three-dimensional structure of the visual signal acquisition system; Figure 5 This is a schematic diagram of the main structure of the visual signal acquisition system (transparent cover omitted); Figure 6 This is an exploded view of the visual signal acquisition system parts (transparent cover omitted).

[0015] 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-blocking 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-power telescope, and 20 is an adhesive layer. DETAILED DESCRIPTION

[0016] The present invention is further described in detail below in conjunction with the accompanying drawings and embodiments.

[0017] like Figures 1 to 6 A device for dynamically monitoring weak parts during a rocket simulated launch is shown, which includes a quantum dot sticker matrix and a visual signal acquisition system 2, wherein: a plurality of the quantum dot sticker matrices are attached to the surface of a weak part 4 (in this specific embodiment, the weak part 4 is a rocket stage separation ring) on ​​the outer shell of a rocket 1, and a visual signal acquisition system 2 is arranged at a predetermined distance from the weak part 4; The quantum dot sticker matrix includes a plurality of quantum dot stickers 3, and the thickness of the quantum dot stickers 3 is 3 μm-4 μm; the quantum dot stickers 3 include a quantum dot layer 8, a water-blocking and oxygen-blocking material layer 7, a release paper 6, a visible light filter membrane 5, and an adhesive layer 20, the water-blocking and oxygen-blocking material layers 7 are respectively arranged 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-blocking and oxygen-blocking material layer 7 near the outer side through the release paper 6, and the adhesive layer 20 is arranged on the water-blocking and oxygen-blocking material layer 7 near the inner side; The visual signal acquisition system 2 includes a base 10, a transparent cover 10, and a vibration-absorbing mechanism, a high-precision monocular camera 16, and a high-power telescope 19 arranged in the transparent cover 10. The base 10 is made of stone, and the transparent cover 10 is a double-layer impact-proof vacuum glass cover. The vibration-absorbing mechanism includes a column 18, a fiberglass rope 11, a viscous damper 14, a spring 13, a circular pendulum 12, and a rectangular pendulum 15. The circular pendulum 12 includes a primary circular pendulum and a secondary circular pendulum, and the rectangular pendulum 15 includes a primary rectangular pendulum, a secondary rectangular pendulum, and a tertiary rectangular pendulum; the column 18 is vertically fixed upward at the four corners of the base 10, and the four corners of the primary circular pendulum are flexibly suspended on the four columns 18 through the fiberglass rope 11. 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; a primary rectangular pendulum, a secondary rectangular pendulum and a tertiary rectangular pendulum are arranged in sequence from top to bottom below the secondary circular pendulum, and the four corners of the secondary circular pendulum and the four corners 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 tertiary rectangular pendulum, and a number of high-precision monocular cameras 16 and a number 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.

[0018] A method for dynamically monitoring weak components of rocket launches using the above device comprises the following steps: S1, preparing quantum dot sticker 3: selecting the type of quantum dots according to the experimental environment and then preparing quantum dot layer 8, then preparing water-blocking and oxygen-blocking material layers 7 on the inner and outer surfaces of quantum dot layer 8 respectively, finally pasting visible light filter membrane 5 on water-blocking and oxygen-blocking material layer 7 near the outer side through release paper 6, and setting adhesive layer 20 on water-blocking and oxygen-blocking material layer 7 near the inner side, so as to prepare quantum dot sticker 3; S2, pasting the quantum dot sticker matrix: according to the position and area of ​​the weak component 4 on the shell of the rocket 1, the quantum dot sticker 3 prepared in step S1 is cut into shapes and sizes of several specifications, and then the quantum dot sticker 3 is pasted on the parts of the weak component 4 where deformation or strain may occur, so as to form a pasted quantum dot sticker matrix; S3. Arrange visual signal collection system 2: With the launch position of rocket 1 as the center, arrange at least one visual signal collection system 2 within a radius of 300-3000m, so that each quantum dot matrix corresponds to at least one visual signal collection system 2; S4. Dynamic monitoring of deformation / strain of weak component 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 is ​​stimulated by the light of the experimental environment to emit light. If observed during the day, the daylight (i.e., sunlight) can activate the quantum dots in the quantum dot layer 8 to emit light, and emit corresponding light; if observed at night, the visible light lighting equipment installed on the rocket launch tower can activate the quantum dots in the quantum dot layer 8 to emit light while illuminating the rocket 1. Adjust the high-precision monocular camera 16 and the high-magnification telescope 19 to align with the corresponding and luminous quantum dot matrix, and dynamically monitor the deformation / strain of the weak component 4 in real time at a long distance. The high-precision monocular camera 16 and the high-magnification telescope 19 transmit the visual signals of the collected quantum dot position changes to the DIC technology software, calculate the two digital images before and after the deformation / strain of the weak component 4, obtain deformation information, determine the degree of surface deformation of the weak component 4, and analyze the structural reliability of the weak component 4 in real time.

[0019] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed by the present invention should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention shall be based on the protection scope of the claims.

Claims

1. A device for dynamically monitoring weak parts during rocket simulation 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 pasted on the surface of a weak component (4) on the outer shell of the rocket (1), and a visual signal collection system (2) is arranged at a predetermined distance from the weak component (4); The quantum dot sticker matrix comprises a plurality of quantum dot stickers (3), wherein the quantum dot sticker (3) comprises 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 layers (7) are respectively arranged 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-blocking material layer (7) near the outer side through the release paper (6); and the adhesive layer (20) is arranged on the water- and oxygen-blocking material layer (7) near the inner side; The visual signal acquisition system (2) comprises a base (10), a transparent cover (10), and a vibration elimination mechanism, a high-precision monocular camera (16), and a high-power telescope (19) arranged in the transparent cover (10); the vibration elimination mechanism comprises 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) comprises a primary circular pendulum and a secondary circular pendulum; the rectangular pendulum (15) comprises a primary rectangular pendulum, a secondary rectangular pendulum, and a tertiary rectangular pendulum; the column (18) is fixedly mounted vertically upward at the four corners of the base (10); the four corners of the primary circular pendulum are flexibly suspended between the tops of the four columns (18) by means of the glass fiber rope (11); the secondary circular pendulum is A rectangular 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 fourth corner positions of the second-stage circular pendulum and the first-stage rectangular pendulum as well as the fourth 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 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.

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

5. A method for dynamically monitoring weak components during rocket simulation launch using the device as claimed in claim 1, characterized in that: The following steps are involved: S1, preparing a quantum dot sticker (3): selecting the type of quantum dots according to the experimental environment and then preparing a quantum dot layer (8), then preparing water-blocking and oxygen-blocking material layers (7) on the inner and outer surfaces of the quantum dot layer (8), respectively, and finally pasting a visible light filter membrane (5) on the water-blocking and oxygen-blocking material layer (7) close to the outer side through a release paper (6), and providing an adhesive layer (20) on the water-blocking and oxygen-blocking material layer (7) close to the inner side, thereby preparing a quantum dot sticker (3); S2, pasting a quantum dot sticker matrix: according to the position and area of ​​the weak component (4) on the shell of the rocket (1), the quantum dot sticker (3) prepared in step S1 is cut into shapes and sizes of several specifications, and then the quantum dot sticker (3) is pasted on the weak component (4) where deformation or strain may occur, so as to form a pasted quantum dot sticker matrix; S3, arranging a visual signal collection system (2): taking the launch position of the rocket (1) as the center of the circle, arranging at least one visual signal collection system (2) within a radius of 300 to 3000 m, so that each quantum dot matrix corresponds to at least one visual signal collection system (2); S4. Dynamic monitoring of deformation / strain locations of weak components (4): Prior to dynamic monitoring, a dedicated person will tear off the release paper (6) and visible light filter membrane (5) in all quantum dot matrixes. The quantum dot matrix will be stimulated by the light from the experimental environment to 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 to dynamically monitor the deformation / strain of the weak components (4) in real time at a long distance. The high-precision monocular camera (16) and the high-magnification telescope (19) will transmit the collected visual signals of the quantum dot position changes to the DIC technology software, and the two digital images before and after the deformation / strain location of the weak components (4) will be calculated to obtain deformation information, determine the degree of surface deformation of the weak components (4), and conduct real-time analysis of the structural reliability of the weak components (4).

6. The method for dynamic monitoring of weak components during rocket simulation launch according to claim 5, characterized in that: The light source in the experimental environment is sunlight or visible light lighting equipment.

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