Research on structural design method of oversized horizontal vacuum device

Abstract

The invention provides research on a structural design method of an oversized horizontal vacuum device, and belongs to the technical field of high-vacuum equipment. Comprising a vacuum chamber, a vacuum acquisition subsystem, a hot mold environment simulation subsystem, a cooling water circulation subsystem, a control and data acquisition subsystem and an auxiliary guarantee subsystem, the vacuum chamber comprises an equipment chamber, a middle detection chamber 1, a middle detection chamber 2, a middle detection chamber 3, a damage chamber and a flight section; vacuum chambers and flight sections of the oversized horizontal vacuum experiment device are coaxially connected. The ultra-large space environment simulation high-vacuum experiment device constructed by the invention forms aerospace industrial experiment testing capabilities such as space environment simulation, platform simulation and high-precision real-time coordinate measurement, and has space environment simulation experiment conditions for carrying out basic science such as space debris grabbing, space electronic device overload and high-speed collision experiments; satellite carrying related technology test authentication is realized, and technical service support is provided for aerospace manufacturing.

Description

Technical Field

[0001] The invention relates to the technical field of high vacuum equipment, and in particular to a study on a structural design method of an ultra-large horizontal vacuum device. Background Art

[0002] The high vacuum device is an important test equipment used to simulate the vacuum environment of space and provide a vacuum simulation test environment for satellites and some of their components or materials. It is an important part of vacuum technology. During the vacuum test, the high vacuum device achieves the high vacuum and high and low temperature simulation test environment required by satellites and their components / materials through the mutual coordination and adjustment of the Roots pump, the front stage dry pump, the molecular pump, the cryogenic pump group and the heat sink system, and provides a corresponding test platform and comprehensive measurement system for the relevant tests of the load inside the high vacuum tank.

[0003] According to the requirements of equipment technical indicators and configuration, the ultimate vacuum index of the high vacuum device needs to be coordinated with vacuum obtaining equipment such as an oil-free pump group to achieve the working vacuum and ultimate vacuum in stages. In the past, most high vacuum devices were vertical structures, and their horizontal distance was limited (≤24m), mainly meeting the static functional test of static satellite payloads and their components, as well as the low-speed (≤1m / s) motion test requirements of conventional active mechanisms. Therefore, the existing high vacuum device cannot meet the high-speed (≥500m / s), high overload (≥20000g) and long-distance (≥50m) large-span high vacuum environment requirements of space debris and electronic devices. At the same time, due to the high-speed collision in its test process, the tank body also needs to meet the environment and test requirements of strong impact resistance, which poses new technical and application problems for the ultra-large-sized high vacuum test device. Therefore, this application provides a research on the structural design method of an ultra-large-sized horizontal vacuum device to meet the needs. Summary of the invention

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

[0005] In order to solve the above technical problems, the present invention provides the following technical solutions:

[0006] A study on the structural design method of an ultra-large horizontal vacuum device, including a vacuum chamber, a vacuum acquisition subsystem, a thermal mold 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, an intermediate detection room 1, an intermediate detection room 2, an intermediate detection room 3, a damage room, and a flight section;

[0008] The vacuum chambers and flight sections of this ultra-large horizontal vacuum experimental device are connected on a coaxial line and meet the following requirements: the maximum test area and distance of the test piece is more than 65 meters;

[0009] The test pieces can work in the original equipment room or in the newly built damage room, and the measuring equipment can observe the test results in multiple areas of each intermediate test room or damage room.

[0010] Optionally, the equipment room, flight section A, intermediate inspection room 1, flight section B, intermediate inspection room 2, flight section C, intermediate inspection room 3, flight section D and damage room are distributed from right to left.

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

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

[0013] Optionally, a large-span long-term settlement resistant structure is designed: the wall thickness of the equipment room is designed to be 14mm, the wall thickness of the two intermediate detection rooms are designed to be 14mm and 12mm respectively, the wall thickness of the damage room is designed to be 12mm, and the wall thickness of the flight section is designed to be 8mm.

[0014] Optionally, before the equipment is installed, use the AT401 laser tracker to detect whether the horizontal height of the foundation surface of each chamber is consistent. If the error is large, it must be adjusted with shims, and the central axis of the equipment installation must be found. In addition, before design and installation, the load settlement of the tank foundation is simulated and overall adjustment measures such as adjusting shims and adjusting bolts are proposed. The foundation settlement deviation does 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. After the equipment room, transition section, intermediate inspection room and damage room are installed , use a laser tracker to detect whether the connecting line of the center points of the DN1200 interfaces of each chamber is in a straight line. After the detection is qualified, install the flight section and bellows equipment to ensure that the coaxiality of the whole set of equipment after installation is within ±20mm; after the installation is completed, carry out the final coaxiality measurement, and use the SA software provided by the laser tracker to evaluate the measurement results. The axis of the vacuum tank is fitted based on the measurement data of the outer circle of the DN1200 flange of the vacuum tank and each DN2900 flange. The deviation of the axis of the vacuum tank from the ideal axis is about 8.1mm 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 in clean rooms with controllable temperature and humidity, the middle flight section and the inspection section are in the general environment of the laboratory hall, and the thermal expansion and contraction of the flight section are calculated. When the ambient temperature changes to 45°C, the thermal expansion and contraction of the equipment room and the middle inspection room are about 3.6mm, and the expansion of the flight section (12.5 meters in length) is 6.2mm; the equipment room and the middle inspection room are fixed, and compensation measures are set at both ends of the flight section. In order to absorb the deformation caused by the thermal expansion of each chamber, 8 flexible expansion structures with a diameter of Φ1200mm and a deformable amount of ±10mm are designed in the axial direction of the vacuum tank to absorb the deformation. At the same time, the damage room, the middle inspection room and the transition section are fixed with anchor bolts, and the flight section is fixed with slide rails to solve the compensation needs of thermal expansion and contraction of the vacuum tank.

[0017] Optionally, high-speed collision and strong impact resistance structure design:

[0018] A design is proposed to prevent electromagnetic impact force from damaging the thin wall of the vacuum tank, so that the equipment room does not bear the impact force. A test piece platform through-cabin fixed structure is used. The platform base is installed on the load-bearing foundation. The hydraulic bellows flexible structure is used to isolate and seal the platform base from the vacuum tank. Eight through-cabin columns fixed on the load-bearing foundation and four auxiliary support columns fixed on the saddle of the vacuum chamber form a stable support for the two guide rails at the bottom of the test platform. Each of the two guide rails is supported by four through-cabin columns and two auxiliary support columns. The guide rails and the support columns are connected by bolts. The test piece platform can be pushed into the equipment room from outside the equipment room through two rows of rollers, and is connected and locked with the guide rails by 8 M20 bolts. Finite element analysis and electromagnetic emission tests have proved that the structure can prevent electromagnetic impact force from damaging the vacuum tank, and the high vacuum state is guaranteed.

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

[0020] This ultra-large horizontal vacuum experimental device can provide a stable and reliable simulation test environment for basic scientific space environment simulation experiments such as space debris simulation grabbing, space electronic device overload and high-speed collision experiments, and realize dynamic high-precision measurement of the entire test process. By integrating multi-physical field measurement probes on the corresponding loads and placing them in the vacuum equipment room, the high vacuum and thermal alternating environment of space are simulated under the action of the vacuum system and the heat sink system. During the test, the multi-physical field transient measurement device can detect changes in electrical, magnetic, thermal, force and other parameters during the test. At the same time, the test platform can be used to carry out initial velocity measurement, azimuth measurement and three-dimensional reconstruction of high-speed flying test loads; and the collision effect evaluation device can be used to detect and evaluate the collision posture, target collision damage effect, etc.

[0021] The ultra-large space environment simulation high-vacuum experimental device constructed by the present invention has formed aerospace industry test and testing capabilities such as space environment simulation, platform simulation, and high-precision real-time coordinate measurement. It has the conditions for conducting basic scientific space environment simulation experiments such as space debris capture, space electronic device overload and high-speed collision experiments, and can achieve satellite-borne related technology testing and certification, providing technical service support for aerospace manufacturing. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0023] Figure 1 This is the overall structure diagram of the system;

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

[0025] Figure 3 This is a schematic diagram of the layout of the deformation compensation expansion joint;

[0026] Figure 4 This is the working flow chart of the super-large horizontal vacuum experimental device system;

[0027] Figure 5 Schematic diagram of the installation and fixing method of the test piece platform in the vacuum tank.

[0028] As shown in the figure, in order to clearly implement the structure of the embodiment of the present invention, specific structures and devices are marked in the figure, but this is only for illustrative purposes and is not intended to limit the present invention to the specific structure, device and environment. According to specific needs, ordinary technicians in this field can adjust or modify these devices and environments. DETAILED DESCRIPTION

[0029] The following is a detailed description of the research on the structural design method of a super-large horizontal vacuum device provided by the present invention in combination with the accompanying drawings and specific embodiments. At the same time, it is explained here that in order to make the embodiments more detailed, the following embodiments are the best and preferred embodiments, and those skilled in the art may also adopt other alternative methods to implement some known technologies; and the accompanying drawings are only for a more specific description of the embodiments, and are not intended to specifically limit the present invention.

[0030] It should be noted that the references to "one embodiment", "an embodiment", "an exemplary embodiment", "some embodiments" and the like in the specification indicate that the embodiments described may include specific features, structures or characteristics, but not every embodiment may include the specific features, structures or characteristics. In addition, when a specific feature, structure or characteristic is described in conjunction with an embodiment, it should be within the knowledge of a person skilled in the art to implement such feature, structure or characteristic in conjunction with other embodiments (whether or not explicitly described).

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

[0032] It will be understood that the meanings of “on,” “over,” and “above” in the present invention should be interpreted in the broadest manner, so that “on” not only means “directly on” something, but also includes the meaning of being “on” something with intervening features or layers therebetween, and “on” or “over” not only means “on” or “above” something, but also includes the meaning of being “on” or “above” something with no intervening features or layers therebetween.

[0033] Additionally, spatially relative terms such as "under," "beneath," "lower," "above," "upper," and the like may be used herein for descriptive convenience to describe the relationship of one element or feature to another element or features, as shown in the accompanying drawings. Spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the accompanying drawings. The device may be oriented in other ways, and the spatially relative descriptors used herein may be similarly interpreted accordingly.

[0034] like Figures 1 to 5 As shown, an embodiment of the present invention provides a method for structural design of an ultra-large horizontal vacuum device, including a vacuum chamber, a vacuum acquisition subsystem, a thermal mold 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, an intermediate detection room 1, an intermediate detection room 2, an intermediate detection room 3, a damage room, and a flight section;

[0036] The vacuum chambers and flight sections of this ultra-large horizontal vacuum experimental device are connected on a coaxial line and meet the following requirements: the maximum test area and distance of the test piece is more than 65 meters;

[0037] The test piece can work in the original equipment room or in the newly built damage room, and the measuring equipment can observe the test results in multiple areas such as the intermediate test room or the damage room;

[0038] From right to left, they are the equipment room, flight section A, intermediate inspection room 1, flight section B, intermediate inspection room 2, flight section C, intermediate inspection room 3, flight section D and damage room;

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

[0040] This super-large horizontal vacuum experimental device can provide a stable and reliable simulation test environment for basic scientific space environment simulation experiments such as space debris simulation grabbing, space electronic device overload and high-speed collision experiments, and realize dynamic high-precision measurement of the entire test process. By integrating multi-physical field measurement probes on the corresponding loads and placing them in the vacuum equipment room, the high vacuum and thermal alternating environment of space are simulated under the action of the vacuum system and the heat sink system. During the test, the multi-physical field transient measurement device can detect changes in electrical, magnetic, thermal, force and other parameters during the test. At the same time, the test platform can be used to measure the initial velocity, azimuth and three-dimensional reconstruction of the high-speed flying test load; and the collision effect evaluation device can be used to detect and evaluate the collision posture, target collision damage effect, etc.

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

[0042] The vacuum chamber, vacuum acquisition subsystem, thermal mold environment simulation subsystem, cooling water circulation subsystem, control and data acquisition subsystem and auxiliary support subsystem constitute the thermal vacuum environment simulation comprehensive system, which provides a test platform and high vacuum test environment for load high-speed collision and debris grabbing tests. It consists of 2 equipment rooms with a diameter of Φ2900mm×5500mm, 1 intermediate detection room with a diameter of Φ2500×3000mm, 1 intermediate detection room with a diameter of Φ2900×4500mm, and 1 Φ2500×3500mm. The damage chamber and a Φ2500×1600mm transition chamber are composed of 4 Φ1200mm×12500mm flight sections connected in series, with a total length of more than 65 meters. Due to the large basic size, weight, span, multiple interfaces of the vacuum tank and the impact force of the electromagnetic launch test, it brings about problems such as structural strength design, thermal expansion and contraction compensation design, and prevention of electromagnetic impact force from damaging the thin-walled structure of the vacuum tank. Solving the above problems is to ensure the smooth implementation of electromagnetic launch in a high vacuum and high temperature environment.

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

[0044] The ultra-large horizontal vacuum experimental device system has a total length of more than 65 meters. The working pressure in the vacuum tank is high vacuum, and the ultimate pressure is better than 3×10 -4Pa, the vacuum tank will withstand a pressure difference of atmospheric pressure in the working state. According to 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 room is designed to be 14mm, the wall thickness of the two intermediate detection rooms are designed to be 14mm and 12mm respectively, the wall thickness of the damage room is designed to be 12mm, and the wall thickness of the flight section is designed to be 8mm. Through finite element software analysis and actual vacuum pumping tests in each chamber, the strength and stiffness design results of each chamber meet the technical requirements.

[0045] Tank foundation measurement: Before installation, use AT401 laser tracker to check whether the horizontal height of the foundation surface of each chamber is consistent. If the error is large, it must be adjusted with shims, and the central axis of the equipment installation must be found.

[0046] Foundation settlement compensation measures: Before design and installation, the load settlement of the tank foundation is simulated and overall adjustment measures such as adjustment shims and adjustment bolts are proposed to support the adjustment needs of large tanks. The foundation settlement deviation does 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.

[0047] Timely measurement during tank installation: Install each chamber under the guidance of the laser tracker. After the equipment room, transition section, intermediate inspection room and damage room are installed, use the laser tracker to detect whether the center point connection line of the DN1200 interface of each chamber is in a straight line. After the test is qualified, install the flight section and bellows equipment to ensure that the coaxiality of the whole set of equipment after installation is within ±20mm.

[0048] Re-measurement and coaxiality evaluation after installation: After installation, the final coaxiality measurement is carried out, and the SA software that comes with the laser tracker is used to evaluate the measurement results. The axis of the vacuum tank is fitted based on the outer circle measurement data of the DN1200 flange of the vacuum tank and each DN2900 flange. The deviation of the axis of the vacuum tank from the ideal axis is about 8.1mm within a range of more than 65 meters, which meets the design requirements.

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

[0050] The total length of the vacuum tank is more than 65 meters. The equipment rooms at both ends of the tank are in clean rooms with controllable temperature and humidity, and the middle flight section and the inspection section are in the general environment of the laboratory hall. According to the experimental environment and climate, the ambient temperature fluctuations in summer and winter exceed 40°C. The thermal expansion and contraction of the vacuum tank material causes the vacuum cavity to deform in the axial direction. Without special design, it will cause great local temperature stress in the vacuum tank, resulting in excessive local deformation of the vacuum tank and damage and failure. The thermal expansion and contraction of the flight section is calculated. When the ambient temperature changes to 45°C, the thermal expansion and contraction of the equipment room and the middle inspection room are about 3.6mm, and the expansion of the flight section (length 12.5 meters) is 6.2mm; the equipment room and the middle inspection room are fixed, and compensation measures are set at both ends of the flight section. In order to absorb the deformation caused by the thermal expansion of each chamber, 8 flexible expansion structures with a diameter of Φ1200mm and a deformation range of ±10mm are designed in the axial direction of the vacuum tank to absorb the deformation. At the same time, the damage chamber, the intermediate inspection chamber and the transition section are fixed with anchor bolts, and the flight section is fixed with slide rails, which effectively solves the compensation needs for thermal expansion and contraction of the vacuum tank.

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

[0052] High-speed collision and strong impact resistance structure design:

[0053] The high-speed collision test is to install the test piece on the test piece platform in the equipment room with a diameter of Φ2900mm×5500mm. The test piece weighing about 1.5 tons will generate an impact force of about 40000N and a duration of about 1.3ms during the high-speed collision test. The general test piece platform in the vacuum tank usually fixes the test piece platform on the platform base welded to the vacuum tank wall. The impact force will be unloaded to the vacuum tank wall, and a concentrated impact load will be generated locally on the vacuum tank wall test piece platform installation base that is subjected to a pressure difference of 1 atmosphere. In mild cases, a vibration effect will be generated on the vacuum tank body, and in severe cases, local permanent deformation will be generated, resulting in failure of the vacuum tank. Therefore, a design to prevent electromagnetic impact force from damaging the thin wall of the vacuum tank body is proposed, so that the equipment room does not bear the impact force, the vacuum tank is avoided from being subjected to impact vibration, and the destructive effect of electromagnetic impact force on the vacuum tank body is completely eliminated.

[0054] When designing the installation and fixing structure of the test piece, a test piece platform through-cabin fixing structure is proposed. The platform base is installed on the load-bearing foundation. The impact force isolation and sealing are achieved between the platform base and the vacuum tank through the hydraulic bellows flexible structure. The two guide rails at the bottom of the test platform are stably supported by 8 through-cabin columns fixed on the load-bearing foundation and 4 auxiliary support columns fixed on the saddle of the vacuum chamber. Each of the two guide rails is supported by 4 through-cabin columns and 2 auxiliary support columns, and the guide rails and support columns are connected by bolts. The test piece platform can be pushed into the equipment room from outside the equipment room through two rows of rollers, and is connected and locked with the guide rails by 8 M20 bolts. Finite element analysis and electromagnetic emission tests have proved that this structure can prevent electromagnetic impact from damaging the vacuum tank, and the high vacuum state can also be guaranteed.

[0055] The design of a large-footprint cabin-penetrating base and sturdy supporting columns increases the bearing capacity. The two test platform guide rails are equipped with a total of 8 cabin-penetrating columns with a diameter of Φ95mm, 4 auxiliary supporting columns with a diameter of Φ78mm, and the footprint of the 8 sets of column bases is 600mm×600mm. The diameter of the vibration isolation bellows is Φ140mm. Through finite element analysis, the test platform cabin-penetrating structure bears its own and the test piece's gravity during the electromagnetic emission test and feels the impact force with a peak value of 40,000N and a duration of 1.3ms. At this time, the maximum stress of the test platform and the cabin-penetrating structure is 19.1MPa, which is lower than the allowable stress of 137MPa. The maximum deformation is 0.13mm at the platform fixing bolt.

[0056] In the past, vacuum test equipment was usually designed with a small inner diameter (≤2m) and a limited length (≤10m), which could not meet the requirements of long distance (maximum distance 65m) and high vacuum (load degree better than 6.5×10 -3 Pa), high-speed collision and strong impact (collision impact speed ≥ 2km / s) environment and test requirements. Compared with the previous technology, the design and processing research and development method proposed in the present invention introduces the flexible compensation vibration isolation design of the tank strong impact test and the high vacuum stability technology, high coaxiality design and high-precision assembly technology into the structural design of the ultra-large horizontal vacuum experimental device, which has the following advantages: (1) It solves the problem of fast vacuuming of ultra-large vacuum chambers (maximum distance 65m, maximum outer envelope Φ3m, with 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 and large diameter vacuum tanks under extreme environments such as transient strong impact, long-distance foundation span, high and low temperature alternating hot and cold, and high vacuum, and achieved the technical indicator that the axis deviation of the ultra-long and large diameter horizontal tank is less than 10mm.

[0057] The ultra-large space environment simulation high-vacuum experimental device constructed by the present invention has formed aerospace industry test and testing capabilities such as space environment simulation, platform simulation, and high-precision real-time coordinate measurement. It has the conditions for conducting basic scientific space environment simulation experiments such as space debris capture, space electronic device overload and high-speed collision experiments, and can achieve satellite-borne related technology testing and certification, providing technical service support for aerospace manufacturing.

[0058] The present invention covers any substitution, modification, equivalent method and scheme made on the essence and scope of the present invention. In order to make the public have a thorough understanding of the present invention, specific details are described in detail in the following preferred embodiments of the present invention, but those skilled in the art can fully understand the present invention without the description of these details. In addition, in order to avoid unnecessary confusion about the essence of the present invention, well-known methods, processes, procedures, components and circuits are not described in detail.

[0059] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principle of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A research on the structural design method of an ultra-large horizontal vacuum device, characterized in that: include: Vacuum chamber, vacuum acquisition subsystem, thermal mold environment simulation subsystem, cooling water circulation subsystem, control and data acquisition subsystem and auxiliary support subsystem; The vacuum chamber includes 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 vacuum chambers and flight sections of this ultra-large horizontal vacuum experimental device are connected on a coaxial line and meet the following requirements: the maximum test area and distance of the test piece is more than 65 meters; The test pieces can work in the original equipment room or in the newly built damage room, and the measuring equipment can observe the test results in multiple areas of each intermediate test room or damage room.

2. According to claim 1, the structural design method of the super-large horizontal vacuum device is characterized in that: The equipment room, flight section A, intermediate inspection room 1, flight section B, intermediate inspection room 2, flight section C, intermediate inspection room 3, flight section D and damage room are distributed from right to left.

3. The research on the structural design method of the super-large horizontal vacuum device according to claim 2 is characterized in that: The length of the equipment room is 5.5m, the length of flight section A is 12.5m, the length of intermediate inspection room 1 is 3m, the length of flight section B is 12.5m, the length of intermediate inspection room 2 is 6.1m, the length of flight section C is 12.5m, the length of intermediate inspection room 3 is 3.5m, the length of flight section D is 12.5m and the length of the damage room is 5.5m.

4. The research on the structural design method of the super-large horizontal vacuum device according to claim 1 is characterized in that: The workflow of the research on the structural design method of the ultra-large-scale horizontal vacuum device is divided into four parts: integration of the test piece, preparation of the test environment, dynamic high-precision measurement of high-speed overload and collision process, and evaluation of collision effect. Among them, the test environment preparation includes the design of large-span long-term settlement-resistant structures, large-range extreme high and low temperature thermal expansion and contraction compensation design, and high-speed collision and strong impact-resistant structural design.

5. The research on the structural design method of the super-large horizontal vacuum device according to claim 4 is characterized in that: Large-span anti-long-term settlement structure design: the wall thickness of the equipment room is designed to be 14mm, the wall thickness of the two intermediate detection rooms are designed to be 14mm and 12mm respectively, the wall thickness of the damage room is designed to be 12mm, and the wall thickness of the flight section is designed to be 8mm.

6. The research on the structural design method of the super-large horizontal vacuum device according to claim 4 is characterized in that: Before the equipment is installed, the AT401 laser tracker is used to detect whether the horizontal height of the foundation surface of each chamber is consistent. If the error is large, it must be adjusted with shims, and the central axis of the equipment installation must be found. In addition, before design and installation, the load settlement of the tank foundation is simulated and overall adjustment measures such as adjusting shims and adjusting bolts are proposed. The deviation of the foundation settlement does 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. After the equipment room, transition section, intermediate detection room and damage room are installed, the laser tracker is used to The optical tracker detects whether the line connecting the center points of the DN1200 interfaces of each chamber is in a straight line. After the test is qualified, the flight section and bellows equipment are installed to ensure that the coaxiality of the entire set of equipment is within ±20mm after installation; after the installation is completed, the final coaxiality measurement is carried out, and the SA software provided by the laser tracker is used to evaluate the measurement results. The axis of the vacuum tank is fitted based on the measurement data of the outer diameter of the DN1200 flange of the vacuum tank and each DN2900 flange. The deviation of the axis of the vacuum tank from the ideal axis is about 8.1mm within a range of more than 65 meters, which meets the design requirements.

7. The research on the structural design method of the super-large horizontal vacuum device according to claim 4 is characterized in that: Wide range of extreme high and low temperature thermal expansion and contraction compensation design: The equipment rooms at both ends of the tank are in clean rooms with controllable temperature and humidity, the middle flight section and the inspection section are in the general environment of the laboratory hall, and the thermal expansion and contraction of the flight section are calculated. When the ambient temperature changes to 45°C, the thermal expansion and contraction of the equipment room and the middle inspection room are about 3.6mm, and the expansion of the flight section (12.5 meters in length) is 6.2mm; the equipment room and the middle inspection room are fixed, and compensation measures are set at both ends of the flight section. In order to absorb the deformation caused by the thermal expansion of each chamber, 8 flexible expansion structures with a diameter of Φ1200mm and a deformable amount of ±10mm are designed in the axial direction of the vacuum tank to absorb the deformation. At the same time, the damage room, the middle inspection room and the transition section are fixed with anchor bolts, and the flight section is fixed with slide rails to solve the compensation needs of thermal expansion and contraction of the vacuum tank.

8. The research on the structural design method of the super-large horizontal vacuum device according to claim 1 is characterized in that: High-speed collision and strong impact resistance structure design: A design is proposed to prevent electromagnetic impact force from damaging the thin wall of the vacuum tank, so that the equipment room does not bear the impact force. A test piece platform through-cabin fixed structure is used. The platform base is installed on the load-bearing foundation. The hydraulic bellows flexible structure is used to isolate and seal the platform base from the vacuum tank. Eight through-cabin columns fixed on the load-bearing foundation and four auxiliary support columns fixed on the saddle of the vacuum chamber form a stable support for the two guide rails at the bottom of the test platform. Each of the two guide rails is supported by four through-cabin columns and two auxiliary support columns. The guide rails and the support columns are connected by bolts. The test piece platform can be pushed into the equipment room from outside the equipment room through two rows of rollers, and is connected and locked with the guide rails by 8 M20 bolts. Finite element analysis and electromagnetic emission tests have proved that the structure can prevent electromagnetic impact force from damaging the vacuum tank, and the high vacuum state is guaranteed.

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