A structural design method for an ultra-large horizontal vacuum device

Abstract

This invention provides a structural design method for an ultra-large horizontal vacuum device, belonging to the field of high vacuum equipment technology. It includes a vacuum chamber, a vacuum acquisition subsystem, a thermal model environment simulation subsystem, a cooling water circulation subsystem, a control and data acquisition subsystem, and an auxiliary support subsystem. The vacuum chamber includes an equipment room, intermediate testing chamber 1, intermediate testing chamber 2, intermediate testing chamber 3, a damage chamber, and a flight section. All chambers and the flight section of this ultra-large horizontal vacuum experimental device are coaxially connected. The ultra-large space environment simulation high vacuum experimental device constructed by this invention forms aerospace industrial testing capabilities such as space environment simulation, platform simulation, and high-precision real-time coordinate measurement. It possesses the conditions for conducting basic scientific space environment simulation experiments such as space debris capture, space electronic device overload, and high-speed collision experiments, enabling satellite-borne related technology testing and certification, and providing technical service support for aerospace manufacturing.

Description

Technical Field

[0001] This invention relates to the field of high vacuum equipment technology, and in particular to a structural design method for an ultra-large horizontal vacuum device. Background Technology

[0002] High vacuum devices are crucial testing equipment used to simulate the vacuum environment of space, providing a vacuum simulation test environment for satellites and their components or materials. They are an important part of vacuum technology. During vacuum testing, the high vacuum device, through the coordinated operation and adjustment of Roots pumps, backing dry pumps, molecular pumps, cryogenic pump sets, and heat sink systems, achieves the high vacuum and high / low temperature simulation test environment required for satellites and their components / materials. Inside the high vacuum chamber, it provides the corresponding test platform and integrated measurement system for relevant load tests.

[0003] Based on the technical specifications and configuration requirements of the equipment, the ultimate vacuum level of a high vacuum device needs to be achieved in stages through the coordinated operation of vacuum-generating equipment such as oil-free pump sets, reaching both the working vacuum level and the ultimate vacuum level. Previous high vacuum devices were mostly vertical structures with limited horizontal distance (≤24m), primarily meeting the static functional testing requirements of static satellite payloads and their components, as well as the low-speed (≤1m / s) motion testing requirements of conventional moving mechanisms. Therefore, existing high vacuum devices cannot meet the high-speed (≥500m / s), high-overload (≥20000g), and long-distance (≥50m) large-span high vacuum environment requirements for space debris and electronic devices. Furthermore, due to the high-speed collisions involved in the testing process, the tank must also meet the environmental and testing requirements for strong impact resistance. This presents new technical and application challenges for ultra-large-size high vacuum testing devices. Therefore, this application provides a structural design method for an ultra-large-size horizontal vacuum device to meet these requirements. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a structural design method for an ultra-large horizontal vacuum device to solve the problem that existing high vacuum devices cannot meet the high vacuum environment requirements of space debris and electronic devices.

[0005] To solve the above-mentioned technical problems, the present invention provides the following technical solution:

[0006] A structural design method for an ultra-large horizontal vacuum device includes a vacuum chamber, a vacuum acquisition subsystem, a thermal model environment simulation subsystem, a cooling water circulation subsystem, a control and data acquisition subsystem, and an auxiliary support subsystem.

[0007] The vacuum chamber includes an equipment room, intermediate testing room 1, intermediate testing room 2, intermediate testing room 3, damage chamber, and flight section;

[0008] The vacuum chambers and flight section of this ultra-large horizontal vacuum experimental device are coaxially connected, and the maximum test area and distance of the test piece are more than 65 meters.

[0009] The test specimens can be tested in the original equipment room or in the newly built damage chamber. The measuring equipment can be used to observe the test results in multiple areas of the intermediate testing room 1, intermediate testing room 2, intermediate testing room 3 or the damage chamber.

[0010] The flight segment includes Flight Segment A, Flight Segment B, Flight Segment C, Equipment Room, Flight Segment A, Intermediate Inspection Room 1, Flight Segment B, Intermediate Inspection Room 2, Flight Segment C, Intermediate Inspection Room 3, Flight Segment D, and Damage Room, which are distributed from right to left.

[0011] Optionally, the equipment room is 5.5m long, flight section A is 12.5m long, intermediate inspection room 1 is 3m long, flight section B is 12.5m long, intermediate inspection room 2 is 6.1m long, flight section C is 12.5m long, intermediate inspection room 3 is 3.5m long, flight section D is 12.5m long, and damage room is 5.5m long.

[0012] Optionally, the workflow of this ultra-large horizontal vacuum device structural design method is divided into four parts: test device integration, test environment preparation, dynamic high-precision measurement of high-speed overload and collision processes, and collision effect evaluation. Among them, the test environment preparation includes large-span anti-long-term settlement structural design, wide-range extreme high and low temperature thermal expansion and contraction compensation design, and high-speed collision anti-strong impact structural design.

[0013] Optionally, the design of a large-span structure resistant to long-term settlement includes: a wall thickness of 14mm for the equipment room, 14mm and 12mm for the two intermediate testing rooms, 12mm for the damage room, and 8mm for the flight section.

[0014] Optionally, before equipment installation, an AT401 laser tracker is used to check whether the horizontal plane of the foundation surface of each chamber is consistent. If the error is large, shims must be used for adjustment. At the same time, the center axis of the equipment installation is found. In addition, before design and installation, the load-bearing settlement of the tank foundation is simulated, and an overall adjustment measure using adjusting shims and adjusting bolts is proposed. The foundation settlement deviation should not exceed 5mm. The proposed adjustment measures ensure that the adjustment amount of the vacuum chamber is 10mm and the minimum adjustment amount of the flight section is 10mm. The equipment room, intermediate inspection chamber 1, intermediate inspection chamber 2, intermediate inspection chamber 3 and damage chamber are installed. Next, an AT401 laser tracker was used to check whether the center points of the DN1200 flange interfaces of each chamber were on a straight line. After passing the test, the flight section and bellows equipment were installed to ensure that the coaxiality of the entire set of equipment was within ±20mm after installation. After installation, the final coaxiality measurement was performed, and the measurement results were evaluated using the SA software that comes with the AT401 laser tracker. Based on the fitted data of the outer circle measurement of the DN1200 flange and each DN2900 flange of the vacuum tank, the axis of the vacuum tank was found to be approximately 8.1mm off from the ideal axis within a range of more than 65 meters, which meets the design requirements.

[0015] Optionally, a wide range of extreme high and low temperature thermal expansion and contraction compensation design:

[0016] The equipment rooms at both ends of the tank are located in cleanrooms with controlled temperature and humidity, while the intermediate flight section and intermediate testing chambers 1, 2, and 3 are located in the general environment of the experimental hall. The thermal expansion and contraction of the flight section are calculated. When the ambient temperature changes to 45℃, the thermal expansion and contraction of the equipment room, intermediate testing chamber 1, 2, and 3 is approximately 3.6mm, and the expansion of the flight section (12.5 meters in length) is 6.2mm. The equipment room, intermediate testing chamber 1, 2, and 3 are fixed, and compensation measures are set at both ends of the flight section. To absorb the deformation caused by the thermal expansion of each chamber, eight flexible expansion structures with a diameter of Φ1200mm and a deformability of ±10mm are designed along the axial direction of the vacuum tank to absorb the deformation. At the same time, the damage chamber, intermediate testing chamber 1, 2, and 3 are fixed with anchor bolts, and the flight section is fixed with slide rail support to solve the compensation requirements for the thermal expansion and contraction of the vacuum tank.

[0017] Optionally, a high-speed collision resistance structural design:

[0018] A design to prevent electromagnetic shock from damaging the thin walls of a vacuum tank is proposed, ensuring the equipment chamber is not subjected to impact forces. A test platform through-chamber fixing structure is employed, with the test platform base mounted on a load-bearing foundation. The test platform base and the vacuum tank are isolated and sealed by a flexible hydraulic bellows structure. Stable support is provided to the two guide rails at the bottom of the test platform by eight through-chamber columns fixed to the load-bearing foundation and two auxiliary support columns fixed to the saddle of the vacuum chamber. Each guide rail is supported by four through-chamber columns and two auxiliary support columns, and the guide rails and auxiliary support columns are bolted together. The test platform can be pushed from outside the equipment chamber into the equipment chamber via two rows of rollers and locked to the guide rails by eight M20 bolts. Finite element analysis and electromagnetic emission tests demonstrate that this structure can prevent electromagnetic shock from damaging the vacuum tank, ensuring a high vacuum state.

[0019] Compared with the prior art, the present invention has at least the following beneficial effects:

[0020] This ultra-large horizontal vacuum experimental device provides a stable and reliable simulation environment for fundamental scientific space environment simulation experiments, such as space debris capture, overload of space electronic devices, and high-speed collision experiments. It enables dynamic and high-precision measurement of the entire experimental process. By integrating multiphysics measurement probes and other components onto the corresponding payloads and placing them in the vacuum chamber, the device simulates the high vacuum and thermal alternation environment of space under the action of the vacuum system and heat sink system. During the experiment, the multiphysics transient measurement device can detect changes in electrical, magnetic, thermal, and force parameters. At the same time, the experimental platform can perform initial velocity measurement, orientation measurement, and three-dimensional reconstruction of the high-speed flying experimental payload. The collision effect evaluation device can detect and evaluate the collision attitude and target collision damage effect.

[0021] The ultra-large space environment simulation high vacuum experimental device constructed by this invention forms aerospace industrial testing capabilities such as space environment simulation, platform simulation, and high-precision real-time coordinate measurement. It has the conditions to carry out basic scientific space environment simulation experiments such as space debris capture, space electronic device overload and high-speed collision experiments, realize satellite-borne related technology testing and certification, and provide technical service support for aerospace manufacturing. Attached Figure Description

[0022] The accompanying drawings, which are incorporated herein and form part of the specification, illustrate embodiments of the invention and, together with the specification, further serve to explain the principles of the invention and enable those skilled in the art to practice and use the invention.

[0023] Figure 1 This is a block diagram of the overall system structure.

[0024] Figure 2This is a schematic diagram of the overall system layout;

[0025] Figure 3 Schematic diagram of the expansion joint layout for deformation compensation;

[0026] Figure 4 A flowchart of the system operation for an ultra-large horizontal vacuum experimental apparatus.

[0027] Figure 5 A schematic diagram showing the installation and fixing method of the test specimen platform inside the vacuum tank.

[0028] As shown in the figure, specific structures and devices are marked in the figure to clearly illustrate the structure of the embodiments of the present invention. However, this is only for illustrative purposes and is not intended to limit the present invention to this specific structure, device and environment. Those skilled in the art can adjust or modify these devices and environments according to specific needs. Detailed Implementation

[0029] The present invention provides a detailed description of a structural design method for an ultra-large horizontal vacuum device, with reference to the accompanying drawings and specific embodiments. It should be noted that, to make the embodiments more detailed, the following embodiments are the best and preferred embodiments; those skilled in the art can also use other alternative methods to implement some known technologies; and the accompanying drawings are only for more specific description of the embodiments and are not intended to specifically limit the present invention.

[0030] It should be noted that the use of terms such as "an embodiment," "an embodiment," "an exemplary embodiment," and "some embodiments" in the specification indicates that the described embodiment may include a specific feature, structure, or characteristic, but not every embodiment necessarily includes that specific feature, structure, or characteristic. Furthermore, when a specific feature, structure, or characteristic is described in connection with an embodiment, implementing such a feature, structure, or characteristic in conjunction with other embodiments (whether explicitly described or not) should be within the knowledge of those skilled in the art.

[0031] Generally, terms can be understood at least partly from their use in context. For example, depending at least partly on the context, the term "one or more" as used herein can be used to describe any feature, structure, or characteristic in a singular sense, or a combination of features, structures, or characteristics in a plural sense. Additionally, the term "based on" can be understood not necessarily to convey an exclusive set of factors, but rather, alternatively, depending at least partly on the context, to allow for the presence of other factors that are not necessarily explicitly described.

[0032] It is understood that the meanings of “on”, “above”, and “above” in this invention should be interpreted in the broadest manner, such that “on” means not only “directly on” something, but also includes the meaning of being “on” something with an intervening feature or layer, and that “above” or “above” means not only “on” something, but also includes the meaning of being “on” something without an intervening feature or layer.

[0033] Furthermore, spatially related terms such as “below,” “under,” “lower,” “above,” and “upper” are used herein for convenience to describe the relationship of one element or feature to one or more other elements or features, as illustrated in the accompanying drawings. Spatially related terms are intended to cover different orientations in the use or operation of the device other than those depicted in the accompanying drawings. The device may be oriented in other ways, and the spatially related descriptive terms used herein can be interpreted similarly.

[0034] like Figures 1 to 5 As shown, an embodiment of the present invention provides a structural design method for an ultra-large horizontal vacuum device, including a vacuum chamber, a vacuum acquisition subsystem, a thermal model environment simulation subsystem, a cooling water circulation subsystem, a control and data acquisition subsystem, and an auxiliary support subsystem;

[0035] The vacuum chamber includes an equipment room, intermediate testing room 1, intermediate testing room 2, intermediate testing room 3, damage chamber, and flight section;

[0036] The vacuum chambers and flight section of this ultra-large horizontal vacuum experimental device are coaxially connected, and the maximum test area and distance of the test piece are more than 65 meters.

[0037] The test specimens can be tested in the original equipment room or in the newly built damage chamber. The measuring equipment can be used to observe the test results in multiple areas such as intermediate testing room 1, intermediate testing room 2, intermediate testing room 3 or damage chamber.

[0038] The flight segment includes Flight Segment A, Flight Segment B, and Flight Segment C, which, from right to left, are the Equipment Room, Flight Segment A, Intermediate Inspection Room 1, Flight Segment B, Intermediate Inspection Room 2, Flight Segment C, Intermediate Inspection Room 3, Flight Segment D, and Damage Room;

[0039] The equipment room is 5.5m long, flight section A is 12.5m long, intermediate inspection room 1 is 3m long, flight section B is 12.5m long, intermediate inspection room 2 is 6.1m long, flight section C is 12.5m long, intermediate inspection room 3 is 3.5m long, flight section D is 12.5m long, and the damage room is 5.5m long.

[0040] This ultra-large horizontal vacuum experimental device provides a stable and reliable simulation environment for fundamental scientific space environment simulation experiments, such as space debris capture, overload of space electronic devices, and high-speed collision experiments. It enables dynamic and high-precision measurement of the entire experimental process. By integrating multiphysics measurement probes onto the corresponding payloads and placing them in the vacuum chamber, the device simulates the high vacuum and thermal alternation environment of space under the action of the vacuum system and heat sink system. During the experiment, the multiphysics transient measurement device can detect changes in electrical, magnetic, thermal, and force parameters. At the same time, the experimental platform can perform initial velocity measurement, orientation measurement, and three-dimensional reconstruction of the high-speed flying test payload. The collision effect evaluation device can detect and evaluate the collision attitude and target collision damage effect.

[0041] The workflow of this ultra-large horizontal vacuum experimental device system can be divided into four parts: integration of the test device, preparation of the test environment, dynamic high-precision measurement of high-speed overload and collision processes, and evaluation of collision effects.

[0042] The integrated thermal vacuum environment simulation system comprises a vacuum chamber, a vacuum acquisition subsystem, a thermal model environment simulation subsystem, a cooling water circulation subsystem, a control and data acquisition subsystem, and an auxiliary support subsystem. It provides a test platform and high-vacuum test environment for high-speed load collision and debris retrieval tests. It consists of two Φ2900mm×5500mm equipment chambers, one Φ2500×3000mm intermediate testing chamber, one Φ2900×4500mm intermediate testing chamber, and one Φ2500×3500mm... The damage chamber and a Φ2500×1600mm transition chamber are each composed of four Φ1200mm×12500mm flight sections connected in series, with a total length exceeding 65 meters. Due to the large basic size, weight, span, and numerous interfaces of the vacuum tank, as well as the impact forces present in the electromagnetic launch test, there are issues to be addressed in the design of structural strength, thermal expansion and contraction compensation, and the design to prevent electromagnetic impact forces from damaging the thin-walled structure of the vacuum tank. Solving these problems ensures the smooth conduct of electromagnetic launches in high vacuum and high and low temperature environments.

[0043] Design of long-span structures resistant to long-term settlement:

[0044] This ultra-large horizontal vacuum experimental device system has a total length exceeding 65 mm. The working pressure inside the vacuum chamber is high vacuum, with an ultimate pressure exceeding 3 × 10⁻⁶. -4The vacuum tank will be subjected to a pressure difference of one atmosphere during operation. Based on the design principles of large vacuum tanks, the structural wall thickness and opening reinforcement structure of the vacuum tank are designed using analytical design standards. The tank wall thickness and reinforcement structure are designed according to the instability conditions. The wall thickness of the equipment chamber is designed to be 14 mm, the wall thickness of intermediate detection chamber 1 and intermediate detection chamber 2 are designed to be 14 mm and 12 mm respectively, the wall thickness of the damage chamber is designed to be 12 mm, and the wall thickness of the flight section is designed to be 8 mm. Through finite element software analysis and actual vacuuming operation of each chamber, the strength and stiffness design results of each chamber meet the technical requirements.

[0045] Tank foundation measurement: Before installation, use an AT401 laser tracker to check whether the horizontal plane of the foundation surface of each chamber is consistent. If the error is large, shims must be used for adjustment. At the same time, find the center axis of the equipment installation.

[0046] Foundation settlement compensation measures: Before design and installation, the load settlement of the tank foundation was simulated. Overall adjustment measures such as adjusting shims and adjusting bolts were used to support the adjustment needs of the large tank. The foundation settlement deviation did not exceed 5mm. The proposed adjustment measures ensured that the adjustment amount of the vacuum chamber was 10mm and the minimum adjustment amount of the flight section was 10mm.

[0047] During tank installation, timely measurements were taken: Each chamber was installed under the guidance of an AT401 laser tracker. After the equipment room, intermediate inspection chamber 1, intermediate inspection chamber 2, intermediate inspection chamber 3, and damage chamber were installed, the AT401 laser tracker was used to check whether the center points of the DN1200 flange interfaces of each chamber were aligned. After passing the test, the flight section and bellows equipment were installed, ensuring that the coaxiality of the entire equipment was within ±20mm after installation.

[0048] Re-measurement and coaxiality evaluation after installation: After installation, the final coaxiality measurement was performed. The measurement results were evaluated using the SA software built into the laser tracker. Based on the measurement data of the outer circle of the DN1200 flange and each DN2900 flange of the vacuum tank, the axis of the vacuum tank was fitted. The deviation of the axis of the vacuum tank from the ideal axis within a range of more than 65 meters was about 8.1mm, which meets the design requirements.

[0049] Wide-range extreme high and low temperature thermal expansion and contraction compensation design:

[0050] The vacuum tank has a total length exceeding 65 meters. The equipment rooms at both ends of the tank are located in cleanrooms with controlled temperature and humidity, while the intermediate flight section and testing section are situated in the general environment of the experimental hall. Given the experimental climate, the ambient temperature fluctuates by more than 40°C in both summer and winter. The thermal expansion and contraction of the vacuum tank material causes deformation along the axial direction of the vacuum chamber. Without special design, this would result in significant localized temperature stress within the vacuum tank, leading to excessive deformation and potential damage or failure. Calculations were made regarding the thermal expansion and contraction of the flight section. When the ambient temperature changes to 45°C, the thermal expansion and contraction of the equipment rooms, intermediate testing chambers 1, 2, and 3 is approximately 3.6 mm, while the expansion of the flight section (12.5 meters in length) is 6.2 mm. The equipment rooms, intermediate testing chambers 1, 2, and 3 are fixed in place, and compensation measures are implemented at both ends of the flight section. To absorb the deformation caused by the thermal expansion of each chamber, eight flexible expansion structures with a diameter of Φ1200mm and a deformability of ±10mm were designed along the axial direction of the vacuum tank to absorb the deformation. At the same time, the damage chamber, intermediate detection chamber 1, intermediate detection chamber 2, and intermediate detection chamber 3 were fixed with anchor bolts, and the flight section was fixed with slide rail support, which effectively solved the compensation requirements for the thermal expansion and contraction of the vacuum tank.

[0051] The flexible expansion structure reduces the temperature stress caused by thermal expansion and contraction, which greatly improves the vacuum sealing reliability of the vacuum tank compared with the structure without compensation measures, and avoids problems such as instability and irreversible large deformation that may be caused by the inability of ultra-long diameter vacuum tanks to expand and contract freely.

[0052] High-speed collision and high-impact resistance structural design:

[0053] High-speed impact testing involves mounting the test specimen on a test specimen platform inside an equipment chamber with a diameter of Φ2900mm×5500mm. The approximately 1.5-ton test specimen generates an impact force of about 40,000N for approximately 1.3ms during the high-speed impact test. Typically, the test specimen platform inside a vacuum tank is fixed to a base welded to the tank wall. The impact force is then unloaded onto the tank wall, resulting in a concentrated impact load on the test specimen platform mounting base, which bears a pressure difference of one atmosphere. This can cause vibrations in the vacuum tank or, in severe cases, permanent deformation leading to tank failure. Therefore, a design is proposed to prevent electromagnetic impact from damaging the thin walls of the vacuum tank, ensuring the equipment chamber is not subjected to impact forces, avoiding impact vibrations to the vacuum tank, and completely eliminating the destructive effects of electromagnetic impact on the vacuum tank.

[0054] In designing the installation and fixing structure of the test specimen, a through-chamber fixing structure for the test specimen platform was adopted. The platform base was installed on a load-bearing foundation. The test specimen platform base and the vacuum tank were isolated and sealed from impact forces through a flexible hydraulic bellows structure. Stable support was provided for the two guide rails at the bottom of the test specimen platform by eight through-chamber columns fixed to the load-bearing foundation and two auxiliary support columns fixed to the saddle of the vacuum chamber. Each guide rail was supported by four through-chamber columns and two auxiliary support columns, and the guide rails and auxiliary support columns were bolted together. The test specimen platform could be pushed from outside the equipment room into the equipment room via two rows of rollers, and locked to the guide rails by eight M20 bolts. Finite element analysis and electromagnetic emission tests both proved that this structure could prevent electromagnetic impact forces from damaging the vacuum tank, and the high vacuum state could also be guaranteed.

[0055] The design incorporates a large footprint-shaped penetration base and robust support columns to enhance load-bearing capacity. The two test platform guide rails are equipped with eight penetration columns (Φ95mm diameter) and four auxiliary support columns (Φ78mm diameter). The footprints of the eight column bases are 600mm x 600mm, and the vibration-damping corrugated pipe has a diameter of Φ140mm. Finite element analysis shows that during electromagnetic launch testing, the test platform's penetration structure withstands its own weight and the weight of the test specimen, as well as an impact force with a peak value of 40,000N lasting 1.3ms. At this point, the maximum stress on the test platform and penetration structure is 19.1MPa, lower than the allowable stress of 137MPa, located at the platform's fixing bolts. The maximum deformation is 0.13mm.

[0056] Traditional vacuum testing equipment designs typically have small inner diameters (≤2m) and limited lengths (≤10m), failing to meet the requirements of long-distance (maximum distance 65m) and high-vacuum (load capacity better than 6.5×10⁻⁶) high-speed testing loads. -3 The environment and testing requirements of high-speed collision and strong impact (collision impact speed ≥2km / s). Compared with previous technologies, the design and processing method proposed in this invention introduces the flexible compensation vibration isolation design and high vacuum stability technology, high coaxiality design and high precision assembly technology of tank body strong impact test into the structural design of ultra-large horizontal vacuum experimental device, which has the following advantages: (1) It solves the problem of rapid vacuuming of ultra-large vacuum chamber (the longest distance is 65m, the maximum outer envelope is Φ3m, and it has nearly 200 sealing interfaces), and achieves a vacuum degree better than 6.5x10 within 6 hours. -3 Pa's technical level; (2) It effectively solved the stability of ultra-long diameter vacuum tanks under extreme environments such as transient strong impact, long distance foundation span, high temperature and cold heat alternation high vacuum, and achieved the technical indicator that the axial deviation of ultra-long diameter horizontal tanks is less than 10mm.

[0057] The ultra-large space environment simulation high vacuum experimental device constructed by this invention forms aerospace industrial testing capabilities such as space environment simulation, platform simulation, and high-precision real-time coordinate measurement. It has the conditions to carry out basic scientific space environment simulation experiments such as space debris capture, space electronic device overload and high-speed collision experiments, realize satellite-borne related technology testing and certification, and provide technical service support for aerospace manufacturing.

[0058] This invention encompasses any substitutions, modifications, equivalent methods, and solutions made within the spirit and scope of this invention. To provide the public with a thorough understanding of this invention, specific details are described in detail in the following preferred embodiments; however, those skilled in the art will fully understand the invention even without these details. Furthermore, to avoid unnecessary misunderstanding of the essence of this invention, well-known methods, processes, procedures, components, and circuits are not described in detail.

[0059] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A method for designing a structure of an ultra-large size horizontal vacuum device, characterized in that, It comprises: a vacuum chamber, a vacuum acquisition subsystem, a thermal mode environment simulation subsystem, a cooling water circulation subsystem, a control and data acquisition subsystem and an auxiliary support subsystem; the vacuum chamber comprises an equipment room, an intermediate detection room 1, an intermediate detection room 2, an intermediate detection room 3, a damage room and a flight section; the chambers and the flight section of the vacuum chamber of the super-large-size horizontal vacuum device are coaxially connected and meet the requirements that the maximum test area and distance of the test piece are more than 65 meters; the test piece can work in the original equipment room or the newly-built damage room, and the measuring equipment can observe the test effect in multiple areas of the intermediate detection room 1, the intermediate detection room 2, the intermediate detection room 3 or the damage room; the flight section comprises a flight section A, a flight section B, a flight section C, and the equipment room, the flight section A, the intermediate detection room 1, the flight section B, the intermediate detection room 2, the flight section C, the intermediate detection room 3, the flight section D and the damage room are sequentially distributed from right to left; the working process of the structural design method of the super-large-size horizontal vacuum device comprises four parts of a measured piece integration, a test environment preparation, a high-speed overload and collision process dynamic high-precision measurement and a collision effect evaluation, wherein the test environment preparation comprises a large-span long-term settlement-resistant structure design, a large-range limit high-low temperature thermal expansion and cold contraction compensation design and a high-speed collision strong impact-resistant structure design; before the equipment is installed, whether the horizontal plane height of the foundation surface of the installation foundation of each chamber in the vacuum chamber is consistent is detected by using an AT401 laser tracker, and if the error is large, the installation center axis of the equipment is found out by using shims for adjustment; in addition, before the design and installation, the load settlement of the vacuum tank body foundation is simulated, and an overall adjustment measure of adjusting shims and adjusting bolts is proposed, the foundation settlement deviation is not more than 5mm, the adjustment measure ensures that the adjustment amount of the vacuum chamber is 10mm, and the minimum adjustment amount of the flight section is 10mm; after the installation of the equipment room, the intermediate detection room 1, the intermediate detection room 2, the intermediate detection room 3 and the damage room is completed, whether the center point connecting line of the DN1200 flange interface of each chamber in the vacuum chamber is on a straight line is detected by using the AT401 laser tracker, and after the detection is qualified, the flight section and the bellows equipment are installed, so as to ensure that the coaxiality of the whole set of equipment after installation is within ±20mm; after the installation is completed, the final coaxiality measurement is carried out, the SA software of the AT401 laser tracker is used to evaluate the measurement result, the axis of the vacuum tank body is fitted based on the measurement data of the outer diameter of the DN1200 flange of the vacuum tank body and each DN2900 flange, the deviation of the vacuum tank body axis from the ideal axis is about 8.1mm within a range of more than 65 meters, and the design requirement is met.

2. The method of designing a structure of an ultra-large size horizontal vacuum device according to claim 1, wherein, The length of the equipment room is 5.5m, the length of the flight section A is 12.5m, the length of the intermediate detection room 1 is 3m, the length of the flight section B is 12.5m, the length of the intermediate detection room 2 is 6.1m, the length of the flight section C is 12.5m, the length of the intermediate detection room 3 is 3.5m, the length of the flight section D is 12.5m and the length of the damage room is 5.5m.

3. The method of designing a very large scale horizontal vacuum device structure according to claim 1, wherein Large-span long-term settlement-resistant structure design: the wall thickness of the equipment chamber is designed to be 14 mm, the wall thickness of the two middle detection chambers is designed to be 14 mm and 12 mm respectively, the wall thickness of the damage chamber is designed to be 12 mm, and the wall thickness of the flight section is designed to be 8 mm.

4. The method of designing a very large scale horizontal vacuum device structure according to claim 1, wherein Large-range limit high-low temperature thermal expansion and cold contraction compensation design: The equipment chambers at both ends of the vacuum tank are in a clean room with controllable temperature and humidity, and the middle flight section and the middle detection chambers 1, 2 and 3 are in a general environment in the experiment hall. The thermal expansion and cold contraction of the flight section is calculated. When the environmental temperature changes by 45℃, the thermal expansion and cold contraction of the equipment chambers, the middle detection chambers 1, 2 and 3 is about 3.6mm, and the expansion of the flight section is 6.2mm. The equipment chambers, the middle detection chambers 1, 2 and 3 are fixed, and compensation measures are set at both ends of the flight section to absorb the deformation caused by the thermal expansion of each chamber. Eight flexible expansion structures with a diameter of Φ1200mm and a deformation amount of ±10mm are designed in the axial direction of the vacuum tank to absorb the deformation amount, and the damage chamber, the middle detection chambers 1, 2 and 3 are fixed by using anchor bolts, and the flight section is fixed by using slide rails to solve the compensation requirement of the thermal expansion and cold contraction of the vacuum tank.

5. The method of designing a very large scale horizontal vacuum device structure according to claim 1, wherein, High-speed collision-resistant strong impact force structure design: A design is proposed to prevent electromagnetic impact force from damaging the thin wall of the vacuum tank, so that the equipment chamber does not bear the impact force. A test piece platform through-cabin fixing structure is used, the test piece platform base is installed on the load-bearing foundation, the test piece platform base and the vacuum tank are connected by a hydraulic bellows flexible structure to realize impact force isolation and sealing, and eight through-cabin columns fixed on the load-bearing foundation and two auxiliary support columns fixed on the vacuum chamber saddle are used to form stable support for the two guide rails at the bottom of the test piece platform. Each guide rail is supported by four through-cabin columns and two auxiliary support columns. The guide rail and the auxiliary support column are connected by bolts. The test piece platform can be pushed into the equipment chamber by two rows of rollers outside the equipment chamber, and is locked by eight M20 bolts between the guide rail and the auxiliary support column. Finite element analysis and electromagnetic emission tests prove that this structure can avoid the damage of electromagnetic impact force to the vacuum tank, and the high vacuum state is guaranteed.

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