Air pressure control system for space environment simulation of aviation or aerospace equipment

Abstract

The utility model relates to the field of space environment simulation equipment, in particular to an air pressure control system for space environment simulation of aviation or aerospace equipment. The air pressure control system further comprises a molecular pump, a dry pump, a resistance gauge, an ionization gauge and a piezoresistance gauge. The piezoresistance gauge is arranged on the vacuum chamber. One end of the molecular pump is connected with a butterfly valve, and the other end of the molecular pump is connected with a preceding-stage valve; the other end of the butterfly valve is communicated with the vacuum chamber; the dry pump is respectively connected with the other end of the forestage valve, the resistance gauge, the emptying valve and the roughing valve; the other end of the rough pumping valve is connected with the vacuum chamber, a first stop valve and a second stop valve, the other end of the first stop valve is connected with a mass flow meter, and the other end of the second stop valve is connected with an adjusting valve. The problem that existing equipment is high in use cost is solved. And meanwhile, the application range is expanded, and the device has remarkable advantages in the aspect of simulating a high-vacuum environment and also has better performance in simulating a low-air-pressure environment.

Description

Technical Field

[0001] The utility model relates to the field of space environment simulation equipment, in particular to an air pressure control system used for space environment simulation of aviation or aerospace equipment. Background Art

[0002] The KM1 Space Environment Simulator (KM1), a critical testing tool in the development of spacecraft components, simulates the vacuum, high- and low-temperature environments of outer space. By creating a controlled simulated environment, this device helps researchers evaluate the performance and reliability of spacecraft components under extreme conditions.

[0003] Cryopumps are currently the most widely used technology for maintaining a high vacuum within a one-cubic-meter vacuum vessel. With their efficient pumping capabilities, cryopumps can ensure a vacuum level of ≤103 Pascals (Pa). However, their application is not without its challenges. The imported cryopumps used in the laboratory's KM1 space environment simulation equipment are subject to high maintenance costs, long warm-up times, and significant energy consumption, all of which are significant factors limiting their widespread adoption. These challenges not only increase the overall cost of equipment operation but also potentially impact test continuity and efficiency.

[0004] Furthermore, the existing KM1 space environment simulation equipment has a fixed structure and operating parameters, making it suitable only for simulating high vacuum environments. It is ineffective at simulating and maintaining low-pressure environments, and users cannot modify it. Furthermore, the existing KM1 space environment simulation equipment has limitations in its structural design. In low-pressure environments, the resistance gauge is prone to increased errors when collecting data. Furthermore, the impact of pressure changes on gas flow rate becomes more complex, significantly increasing the difficulty of controlling gas flow rate. These issues limit the application scope of existing space ring simulation equipment, making it only suitable for simulation experiments of spacecraft components and not for simulation experiments of high-altitude aircraft components. Utility Model Content

[0005] The utility model provides an air pressure control system for simulating the space environment of aviation or aerospace equipment, which aims to improve the existing KM1 space environment simulation equipment in the laboratory and solve the problems of high energy consumption and high subsequent maintenance costs of the existing space environment simulation equipment.

[0006] In addition, the utility model provides an air pressure control system for simulating the space environment of aviation or aerospace equipment. Its purpose is also to improve the existing KM1 space environment simulation equipment in the laboratory and solve the problem that the existing space ring model equipment has poor effect in simulating low-pressure environments, resulting in its narrow scope of application.

[0007] In order to achieve the above purpose, the technical solution of the utility model is:

[0008] The utility model provides an air pressure control system for simulating a space environment of aviation or aerospace equipment, comprising a space environment simulation device body, the space environment simulation device body comprising a vacuum chamber, a vacuum gauge disposed on the vacuum chamber, a gate valve communicating with the vacuum chamber, and a vacuum pump group connected to the gate valve; the utility model is characterized in that: the air pressure control system further comprises a molecular pump, a dry pump, a resistance gauge, an ionization gauge, and a piezoresistive gauge, the piezoresistive gauge being disposed on the vacuum chamber;

[0009] One end of the molecular pump is connected to a butterfly valve, and the other end is connected to a front-stage valve; the other end of the butterfly valve is connected to the vacuum chamber, and the ionization gauge is arranged on the pipeline between the butterfly valve and the vacuum chamber;

[0010] The dry pump is respectively connected to the other end of the front valve, the resistance gauge, the vent valve and the roughing valve, and the other end of the vent valve is connected to the atmosphere;

[0011] The other end of the roughing valve is connected to the vacuum chamber, stop valve 1 and stop valve 2 respectively, the other end of the stop valve 1 is connected to a mass flow meter, the other end of the mass flow meter is connected to the atmosphere, the other end of the stop valve 2 is connected to a regulating valve, the other end of the regulating valve is connected to the atmosphere.

[0012] Furthermore, the butterfly valve is connected to the vacuum chamber through a wall flange.

[0013] Furthermore, the dry pump is connected to the other end of the front-stage valve, the resistance gauge, the vent valve and the roughing valve respectively through a six-way flange.

[0014] Furthermore, the other end of the roughing valve is connected to the vacuum chamber, the first stop valve and the second stop valve respectively through a four-way flange.

[0015] Furthermore, the roughing valve is connected to the vacuum chamber through a wall flange.

[0016] The beneficial effects achieved by the utility model are:

[0017] The present invention has a high degree of compatibility and flexibility, and is compatible with most KM1 type space ring mold equipment. It can not only solve the problems that may occur when using existing cryogenic pumps, such as long preheating time (specifically, the time from turning on the cryogenic pump of the existing KM1 type space ring mold equipment to being able to work is about 100 minutes, while this application uses a molecular pump when evacuating the vacuum, and the preheating time is less than 10 minutes), short maintenance cycle, and high cost of use, but also achieve the effect of reducing costs and improving test efficiency and safety. At the same time, the flexibility, accuracy and stability of the system can provide users with a reliable pressure control solution, ensuring the accuracy of the pressure change rate during the pressure relief and re-pressurization process, expanding the scope of application, and not only having significant advantages in simulating high vacuum environments, but also having good performance in simulating low pressure environments. It has broad application prospects in the fields of space science, aerospace testing, etc. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying any creative work.

[0019] Figure 1 It is a schematic diagram of the overall structure of the utility model (most of the structure of the space environment simulation device body is omitted).

[0020] Figure 2 3 is a high vacuum curve diagram of the present invention; wherein the horizontal axis represents time and the vertical axis represents pressure.

[0021] Figure 3 This is a pressure relief and re-pressure curve diagram of the present invention; wherein the horizontal axis represents time and the vertical axis represents pressure.

[0022] In the figure, D1, regulating valve; FT, mass flow meter; G, vacuum gauge; G1, resistance gauge; G2, ionization gauge; G3, piezoresistive gauge; P1, dry pump; P2, molecular pump; P3, vacuum pump group; V1, butterfly valve;

[0023] V2, front stage valve; V3, vent valve; V4, roughing valve; V5, stop valve 1; V6, stop valve 2;

[0024] V7, gate valve. DETAILED DESCRIPTION

[0025] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0026] It should be noted that if the embodiments of the present invention involve directional indications (such as up, down, left, right, front, back, etc.), the directional indications are only used to explain the relative position relationship, movement status, etc. between the various components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indications will also change accordingly.

[0027] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present invention, the descriptions of "first", "second", etc. are only for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of such features. In addition, if the meaning of "and / or" appearing in the full text is to include three parallel schemes, taking "A and / or B" as an example, it includes scheme A, or scheme B, or a scheme in which A and B are satisfied at the same time. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in this field to implement. When the combination of technical solutions is mutually contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0028] The utility model provides an air pressure control system for simulating space environment of aviation or aerospace equipment, specifically a low pressure (10 5 ~10 2 Pa) control and high vacuum (10 -1 ~10 -5 Pa), which is particularly suitable for thermal vacuum tests and pressure relief and re-pressure tests; the utility model is an external improvement device proposed for the existing KM1 type space environment simulation equipment, which is compatible with and can be connected to most KM1 type space ring model equipment, and solves the problems of high later maintenance and use costs and poor low-pressure environment simulation effects of the existing KM1 type space environment simulation equipment, and ultimately achieves the purpose of reducing laboratory operating costs and increasing the scope of application and usage frequency of the existing KM1 type space environment simulation equipment.

[0029] like Figure 1As shown, the air pressure control system includes a space environment simulation device body, which includes a vacuum chamber, a vacuum gauge G mounted on the chamber, a gate valve V7 communicating with the chamber, and a vacuum pump assembly P3 connected to the gate valve V7. The vacuum chamber is a pressure vessel with a volume of one cubic meter or less.

[0030] Since the space environment simulation equipment body is the existing KM1 type space environment simulation equipment, which is the existing technology, its specific structure, the connection method between the vacuum pump group P3 and other technical details and principles will not be repeated; wherein, the vacuum pump group P3 includes a dry pump and a cryogenic pump, etc., these pumps are basically imported equipment from abroad, for example, the dry pump model of the vacuum pump group P3 is generally the German Leybold VARODRYVD 160-50Hz type, and the cryogenic pump model is generally the German Leybold COOLVAC5000iCL; since these two pumps are imported equipment, regular maintenance and subsequent replacement of accessories require contacting foreign manufacturers, which has problems such as high subsequent maintenance costs and inconvenient maintenance; especially the cryogenic pump, the maintenance cost is particularly high.

[0031] The air pressure control system further includes a molecular pump P2, a dry pump P1, a resistance gauge G1, an ionization gauge G2 and a piezoresistive gauge G3, and the piezoresistive gauge G3 is arranged on the vacuum chamber;

[0032] One end of the molecular pump P2 is connected to a butterfly valve V1, and the other end is connected to a front-stage valve V2; the other end of the butterfly valve V1 is connected to the vacuum chamber, and the ionization gauge G2 is arranged on the pipeline between the butterfly valve V1 and the vacuum chamber;

[0033] The dry pump P1 is connected to the other end of the front valve V2, the resistance gauge G1, the vent valve V3 and the roughing valve V4 respectively, and the other end of the vent valve V3 is connected to the atmosphere;

[0034] The other end of the roughing valve V4 is connected to the vacuum chamber, stop valve 1 V5 and stop valve 2 V6 respectively. The other end of the stop valve 1 V5 is connected to a mass flowmeter FT, and the other end of the mass flowmeter FT is connected to the atmosphere. The other end of the stop valve 2 V6 is connected to a regulating valve D1, and the other end of the regulating valve D1 is connected to the atmosphere.

[0035] Among them, the model of the molecular pump P2 can be JFB-250 / 2201 of Zhongke Jiuwei or FF-250 / 2000 of Zhongke Keyi; the model of the dry pump P1 can be ECODRYplus of Germany Leybold or WXG-8B of Shenyang Keyi; naturally, the above two pumps can also be pumps of other models; the reason why the molecular pump P2 uses a domestic pump is to reduce the cost of use and maintenance, so as to extend the service life of the imported original pump.

[0036] The resistance gauge G1 is an instrument that measures vacuum levels based on the principle of thermal conductivity; the ionization gauge G2 is a common vacuum measuring instrument primarily used to measure high and ultra-high vacuum pressure; and the piezoresistive gauge G3 is an instrument capable of measuring pressure and vacuum levels with high precision, a feature that makes it widely applicable in industrial production and scientific research. All three of these measuring instruments are prior art, and their details will not be elaborated upon.

[0037] Furthermore, the butterfly valve V1 is connected to the vacuum chamber through a wall flange, and the butterfly valve V1 is used to isolate the molecular pump P2 from the vacuum chamber.

[0038] Furthermore, the dry pump P1 is connected to the other end of the front valve V2, the resistance gauge G1, the vent valve V3 and the roughing valve V4 through a six-way flange; the last interface of the six-way flange is sealed.

[0039] Furthermore, the other end of the roughing valve V4 is connected to the vacuum chamber, the first stop valve V5 and the second stop valve V6 respectively through a four-way flange.

[0040] Furthermore, the roughing valve V4 is connected to the vacuum chamber via a wall flange.

[0041] Furthermore, the air pressure control system also includes a control module, which is connected to the host computer, and the control module is connected to the above-mentioned pump groups, valves and measuring instruments. The control module is the control center of the present invention; the control module includes a PLC controller and several relays; for those skilled in the art, writing software running on the control module based on the functions of the present invention described in this article is not creative work and is easy to implement, so its technical details are not repeated.

[0042] The KM1 space environment simulation device improved by the utility model will have two major functions: one is to simulate a high vacuum environment, and the other is to simulate a low pressure environment.

[0043] When simulating a high vacuum environment, the control flow is as follows:

[0044] Under the initial state of normal pressure (all valves and pump groups are in the closed state), the space environment simulation equipment body is controlled to open its own plug valve V7 and vacuum pump group P3 to evacuate the vacuum chamber to below 10Pa.

[0045] Open the front valve V2, and then start the dry pump P1; when the measured value of the resistance gauge G1 is less than 10Pa, start the molecular pump P2; when the frequency of the molecular pump P2 displays 400Hz, it indicates that the molecular pump P2 has been started and is in working state.

[0046] When the measured value of the vacuum gauge G on the vacuum chamber is less than 10Pa, close the plug valve V7 and vacuum pump group P3 configured on the space environment simulation device itself; open the butterfly valve V1, and pump the vacuum chamber to 10Pa through the molecular pump P2. -3 Pa or less, and perform a thermal vacuum test.

[0047] After the test is completed, the ionization gauge G2 is closed, the butterfly valve V1 is closed, the molecular pump P2 is turned off, and when the molecular pump P2 completely stops running, the fore valve V2 and the dry pump P1 are closed.

[0048] Finally, open the vent valve V3, and when the resistance gauge G1 shows 1*10 5 When Pa, the vent valve V3 is closed.

[0049] When executing the above process, the pressure curve in the vacuum chamber is as follows: Figure 2 shown.

[0050] It is worth noting that when simulating a high vacuum environment, it is also possible not to open the plug valve V7 and vacuum pump group P3 of the space environment simulation device body itself, and rely entirely on the dry pump P1 and molecular pump P2 added by the utility model to evacuate the vacuum, but the speed will be slower; if you want to obtain a faster vacuuming speed, you can also use a higher-power dry pump P1 and molecular pump P2; or you can use the vacuum pump group P3 of the space environment simulation device body itself and the dry pump P1 and molecular pump P2 to evacuate the vacuum, which can also achieve a faster speed. This is all allowed, and various arrangements are no longer listed one by one. But in any case, the utility model greatly reduces the use time of the vacuum pump group P3 that comes with the space environment simulation device body, especially for those experiments that require the use of the space environment simulation device for a long time to simulate a high vacuum environment. This undoubtedly extends the service life of the vacuum pump group P3 of the space environment simulation device itself, thereby reducing the subsequent maintenance cost and the cost of use.

[0051] When simulating a low-pressure environment, the pressure in the vacuum chamber needs to be stable within the tolerance range of the set pressure value. The control process is as follows:

[0052] Select automatic mode for control mode.

[0053] ①Pressure relief process:

[0054] Under the initial state of normal pressure (all valves and pump groups are in the closed state), according to the test conditions, the pressure change rate and pressure value are set in the automatic mode to operate the utility model.

[0055] Open the plug valve V7 and vacuum pump group P3 of the space environment simulation equipment body, open the second stop valve V6, and at the same time, the control module automatically controls the opening degree of the regulating valve D1 using the PID algorithm to vacuum according to the set pressure change rate.

[0056] If the pressure setting value is required to be less than 2000 Pa, the stop valve V5 is automatically opened, and the mass flow meter FT is turned on, and the pressure control is completed in conjunction with the control of the regulating valve D1.

[0057] After reaching the set pressure, the control module prompts to close the plug valve V7 and vacuum pump group P3 of the space environment simulation equipment itself, and enter the pressure holding stage.

[0058] The dry pump P1 and the second stop valve V6 are turned on. At the same time, the control module opens or closes the roughing valve V4 and the regulating valve D1 according to the feedback of the piezoresistive gauge G3. The dry pump P1 exhausts air and the regulating valve D1 releases air, so that the pressure is stabilized within the tolerance range of the set pressure value.

[0059] As a matter of course, the above-mentioned pressure relief process can also not use the vacuum pump group P3 of the space environment simulation equipment itself, but only use the dry pump P1 and / or molecular pump P2 to cooperate with each other for pressure relief, and through the mutual restraint of the dry pump P1 vacuuming and the regulating valve D1 deflation, so that the pressure is stabilized within the tolerance range of the set pressure value; but the pressure relief speed will be slower.

[0060] ②Recompression process:

[0061] In the initial state, according to the test conditions, the pressure change rate and pressure value are set in the automatic mode to operate the utility model.

[0062] When the pressure relief process is completed, the control module controls the regulating valve D1 to open appropriately according to the vacuum chamber pressure measured by the piezoresistive gauge G3, and releases air slowly to meet the pressure rising rate.

[0063] After reaching the set pressure, the regulating valve D1 closes and enters the pressure holding stage.

[0064] For further explanation, the operating process of the present invention when simulating a low pressure environment is described below using the test conditions in Table 1 as an example:

[0065] Table 1 Relief and re-pressure test data

[0066] Serial number Pressure range Pressure relief rate Repressurization rate Rate tolerance 1 101.3kPa~50kPa 0.3kPa / s —— ±50％ 2 50kPa Constant pressure maintained for 30m —— —— 3 50kPa~25kPa 0.2kPa / s —— ±50％ 4 25kPa Constant pressure maintained for 30m —— —— 5 25kPa~50kPa —— 0.2kPa / s ±50％ 6 50kPa Constant pressure maintained for 30m —— —— 7 50kPa~101.3kPa —— 0.3kPa / s ±50％

[0067] The operator sets the parameters through the host computer control software and starts the control system of the utility model:

[0068] 1) Change the target setting value to 50 kPa, set the rate to 0.3 kPa / s, and conduct a pressure relief test;

[0069] 2) Manually open the gate valve V7 and vacuum pump group P3 of the space environment simulation equipment to extract air;

[0070] 3) The utility model automatically operates, comparing the actual pressure value measured by the piezoresistive gauge G3 on the vacuum chamber with the set value that changes at a set rate, controlling the regulating valve D1 to open appropriately for deflation, reducing the pumping rate of the space environment simulation device itself, and achieving a uniform decrease in the pressure value of the piezoresistive gauge G3 at the pressure change rate;

[0071] 4) When the pressure value of the piezoresistive gauge G3 reaches the set value of 50 kPa, the gate valve V7 and the vacuum pump group P3 of the space environment simulation device are manually closed, and the control module starts the dry pump P1;

[0072] 5) Compare the actual pressure value measured by the piezoresistive gauge G3 with the set value of 50 kPa. If the pressure value is higher than 50 kPa, open the roughing valve V4 and pump air with the dry pump P1 to reduce the pressure. If the pressure value is lower than 50 kPa, close the roughing valve V4 and moderately open the regulating valve D1 to release air so that the pressure value of the piezoresistive gauge G3 is always maintained at 50 kPa.

[0073] 6) After maintaining 50 kPa for 30 minutes, change the target setting value to 25 kPa, set the rate to 0.2 kPa / s, and conduct a pressure relief test;

[0074] 7) Repeat steps 2-5, and the system controls the pressure to maintain at 25 kPa;

[0075] 8) After maintaining 25 kPa for 30 minutes, change the target setting value to 50 kPa, set the rate to 0.2 kPa / s, and conduct a re-pressure test;

[0076] 9) The system calculates and compares the pressure value of the piezoresistive gauge G3 with the set value of 50kPa, and opens the regulating valve D1 appropriately to release air, so that the pressure value of the piezoresistive gauge G3 in the vacuum chamber can slowly rise according to the test requirements and remain at 50kPa;

[0077] 10) After maintaining 50 kPa for 30 minutes, change the target setting value to 101.3 kPa, set the rate to 0.3 kPa / s, and continue the pressure relief test;

[0078] 11) Repeat step 9, and the system controls the pressure value to 101.3 kPa.

[0079] Among them, the pressure curve of the above experimental test is as follows Figure 3 shown.

[0080] The above description is merely an optional embodiment of the present invention and does not limit the patent scope of the present invention. All equivalent structural transformations made by utilizing the contents of the present invention specification and drawings under the inventive concept of the present invention, or direct / indirect application in other related technical fields are included in the patent protection scope of the present invention.

Claims

1. An air pressure control system for simulating a space environment for aviation or aerospace equipment, comprising a space environment simulation device body, the space environment simulation device body comprising a vacuum chamber, a vacuum gauge (G) disposed on the vacuum chamber, a gate valve (V7) communicating with the vacuum chamber, and a vacuum pump group (P3) connected to the gate valve (V7); characterized in that: The air pressure control system further comprises a molecular pump (P2), a dry pump (P1), a resistance gauge (G1), an ionization gauge (G2) and a piezoresistive gauge (G3), wherein the piezoresistive gauge (G3) is arranged on the vacuum chamber; One end of the molecular pump (P2) is connected to a butterfly valve (V1), and the other end is connected to a front-stage valve (V2); the other end of the butterfly valve (V1) is in communication with the vacuum chamber, and the ionization gauge (G2) is arranged on a pipeline between the butterfly valve (V1) and the vacuum chamber; The dry pump (P1) is respectively connected to the other end of the front valve (V2), the resistance gauge (G1), the vent valve (V3) and the roughing valve (V4), and the other end of the vent valve (V3) is connected to the atmosphere; The other end of the roughing valve (V4) is respectively connected to the vacuum chamber, the first shut-off valve (V5) and the second shut-off valve (V6); the other end of the first shut-off valve (V5) is connected to a mass flow meter (FT); the other end of the mass flow meter (FT) is communicated with the atmosphere; the other end of the second shut-off valve (V6) is connected to a regulating valve (D1); the other end of the regulating valve (D1) is communicated with the atmosphere.

2. The air pressure control system for simulating space environment of aviation or aerospace equipment according to claim 1, characterized in that: The butterfly valve (V1) is connected to the vacuum chamber via a wall-penetrating flange.

3. The air pressure control system for simulating space environment of aviation or aerospace equipment according to claim 1, characterized in that: The dry pump (P1) is respectively connected to the other end of the front valve (V2), the resistance gauge (G1), the vent valve (V3) and the roughing valve (V4) through a six-way flange.

4. The air pressure control system for simulating space environment of aviation or aerospace equipment according to claim 1, characterized in that: The other end of the roughing valve (V4) is connected to the vacuum chamber, the first stop valve (V5) and the second stop valve (V6) respectively through a four-way flange.

5. The air pressure control system for simulating space environment of aviation or aerospace equipment according to claim 1, characterized in that: The roughing valve (V4) is connected to the vacuum chamber via a through-wall flange.

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