Thermal vacuum simulation system for space environment simulation and test

Abstract

The invention relates to the technical field of vacuum tanks, in particular to a thermal vacuum simulation system for space environment simulation and test, which comprises a thermal vacuum simulation container, a vacuum guarantee system, a temperature guarantee system, an illumination simulation system and a control system, the vacuum obtaining subsystem comprises a low-vacuum obtaining unit and a high-vacuum obtaining unit, a mechanical pump of the low-vacuum obtaining unit is used as a pre-pumping pump, a mechanical pump of the high-vacuum obtaining unit is used as a pre-pumping pump, and a mechanical pump of the high-vacuum obtaining unit is used as a pre-pumping pump. A molecular pump and a low-temperature pump of the high vacuum obtaining unit serve as main pumps, the vacuum degree required by an experiment can be rapidly obtained, the vacuum degree is more convenient to control, and the problem that the vacuum degree and the temperature of an existing thermal vacuum test tank are not easy to control is solved.

Description

Technical Field

[0001] The invention relates to the technical field of vacuum tanks, in particular to a thermal vacuum simulation system for space environment simulation and testing. Background Art

[0002] In the field of aerospace technology, some components on satellites and spacecraft need to undergo thermal vacuum testing. Thermal vacuum testing refers to testing that verifies the various performance and functions of a spacecraft and its components under vacuum and certain temperature conditions. The entire test process consists of cold soaking, hot soaking, and temperature change processes. Cold soaking is to place the spacecraft components at the specified minimum test temperature and keep them for a specified time; hot soaking is to place the spacecraft components at the specified maximum test temperature and keep them for a specified time. Starting from room temperature, drop to the specified minimum test temperature, perform the cold soak process, then rise to the specified maximum test temperature, perform the hot soak process, and finally return to room temperature to complete a temperature cycle test.

[0003] The existing thermal vacuum test is carried out in a thermal vacuum test tank. The thermal vacuum test tank includes a tank body and a tank cover. A fixing frame for fixing the test component is provided in the tank body. During the test, the tank cover is first opened, the test component is fixed to the fixing frame, and corresponding sensors (such as temperature sensors, etc.) are installed on the test component to obtain various test data during the test; the tank cover is closed, and then the tank body is evacuated to a vacuum, and the tank body is heated to the highest test temperature through the heating system in the tank body, or the tank body is cooled to the lowest test temperature through the low temperature system in the tank body. In this process, various data are collected through sensors installed on the test component, and then the test results are analyzed. However, the vacuum degree and temperature of the existing thermal vacuum test tank are not easy to control. Summary of the invention

[0004] The present invention is intended to provide a thermal vacuum simulation system for space environment simulation and testing, so as to solve the problem that the vacuum degree and temperature of the existing thermal vacuum test tank are difficult to control.

[0005] In order to achieve the above-mentioned purpose, the basic scheme of the present invention is as follows: a thermal vacuum simulation system for space environment simulation and testing, comprising a thermal vacuum simulation container, a vacuum guarantee system, a temperature guarantee system, a light simulation system and a control system, wherein the vacuum guarantee system and the temperature guarantee system are both connected to the inside of the thermal vacuum simulation container, the light simulation system is installed in the thermal vacuum simulation container, and the control system controls the vacuum guarantee system, the temperature guarantee system and the light simulation system;

[0006] The thermal vacuum simulation container comprises a pressure-bearing layer, an intermediate layer and a heating cage, wherein the pressure-bearing layer comprises a cylinder, a door, a plurality of flanges and a plurality of vacuum pipes, wherein the door is installed at the end of the cylinder, and the plurality of vacuum pipes are respectively connected to the inside of the cylinder through a plurality of flanges, wherein the intermediate layer is a heat sink system, the heating cage is located in the intermediate layer, and the bottom of the heating cage passes through the intermediate layer and is fixed to the cylinder;

[0007] The vacuum guarantee system includes a vacuum obtaining subsystem, a vacuum measuring subsystem and a pressure stabilizing subsystem. The vacuum obtaining subsystem includes a low vacuum obtaining unit and a high vacuum obtaining unit. The vacuum measuring subsystem includes a low vacuum measuring unit and a high vacuum measuring unit. The low vacuum obtaining unit includes several mechanical pumps, the high vacuum obtaining unit includes a cryogenic pump and a molecular pump, and the pressure stabilizing subsystem includes several valves.

[0008] The temperature assurance system comprises a refrigeration unit, a heat transfer oil unit and a cold plate unit. The refrigeration unit adopts a mechanical refrigerator. The heat transfer oil unit comprises a heater, an oil tank, an oil pump and a heat transfer oil pipeline. The cold plate unit is installed in a heating cage. The heat transfer oil pipeline is connected to the oil tank. The oil pump is installed on the heat transfer oil pipeline. The heater is connected to the heat transfer oil pipeline to heat the heat transfer oil. The heat transfer oil pipeline is laid on the heating cage.

[0009] The illumination simulation system adopts an illumination simulator.

[0010] Furthermore, the low vacuum obtaining unit meets the following requirements: from normal pressure to 10 kPa, the time is no more than 1.5 min, from normal pressure to 3000 Pa, the average rate is no less than 10 kPa / min, from 3000 Pa to 10 Pa, the average rate is no less than 200 Pa / min; the high vacuum obtaining unit meets the following requirements: the pressure reduction rate is from normal pressure to 5×10 -3 Pa, time is no more than 40min, from normal pressure to 5×10 -4 Pa, time is no more than 120min, from normal pressure to 5×10 -5 Pa, time not more than 4h.

[0011] Furthermore, the low vacuum measurement unit has a measurement range of 1×10 5 Pa to 1×10 -1 The high vacuum measurement unit has a measurement range of 100 kPa to 1 × 10 -6 Pa vacuum regulator.

[0012] Furthermore, it also includes an auxiliary system, which uses an air-cooled circulating water machine and cools down the high vacuum obtaining unit.

[0013] Furthermore, the heat sink system adopts double-layer stainless steel, and the inner surface of the heat sink system is sprayed with imported radiation paint with strong adhesion, hemispherical emissivity ≥0.95, and solar absorption coefficient ≥0.93. The heat sink system acts as a radiation screen to absorb and emit radiation energy. The outer surface of the heat sink system is polished to increase the reflectivity. The heat sink system processing technology uses water for pressurization to make the double-layer stainless steel bulge produce a flow channel, and water is used to maintain the pressure. Dehydration treatment is performed before installing the heat sink system. The dehydration method is as follows: the heat sink system is placed in a cylinder, the interface is connected to nitrogen, the outlet is placed outside the cylinder, the temperature inside the cylinder is raised to 110°C, and nitrogen is blown out every 2 hours to blow out the water until all the water is blown out.

[0014] The beneficial effects of this scheme are as follows: (1) This scheme can realistically simulate the cold, hot and lighting environment of a vacuum space, and can effectively control, monitor and record the vacuum degree and temperature of the space.

[0015] (2) The vacuum acquisition subsystem in this scheme includes a low vacuum acquisition unit and a high vacuum acquisition unit. The mechanical pump of the low vacuum unit serves as a pre-pump, and the molecular pump and cryogenic pump of the high vacuum acquisition unit serve as main pumps. They can quickly obtain the vacuum degree required by the experiment and are more convenient to control the vacuum degree.

[0016] (3) The temperature assurance system in this scheme uses a combination of a refrigeration unit, a thermal oil unit and a cold plate unit, which can quickly and evenly complete heating and cooling. Combined with the vacuum assurance system, it truly simulates the vacuum and hot and cold environment in space. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the overall structure of an embodiment of the present invention;

[0018] Figure 2 is a schematic diagram of the specific structure of the heating cage in an embodiment of the present invention;

[0019] Figure 3 Schematic diagram of the connection of the thermal oil unit in the embodiment of the present invention;

[0020] Figure 4 Schematic diagram of the structure of the flow channel in the heat sink system in an embodiment of the present invention. DETAILED DESCRIPTION

[0021] 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 described embodiments 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 creative work are within the scope of protection of the present invention.

[0022] The figure marks in the drawings of the specification include: cylinder 1, door 2, flange 3, heat sink system 4, cold plate unit 5, refrigeration unit 6, arc-shaped body 7, end cover 8, support frame 9, guide rail 10, support plate 11, locking assembly 12, slide rail frame 13, heater 14, oil tank 15, oil pump 16, thermal oil pipeline 17.

[0023] Example

[0024] Basically as attached Figure 1 As shown: a thermal vacuum simulation system for space environment simulation and testing, including a thermal vacuum simulation container, a vacuum guarantee system, a temperature guarantee system, a lighting simulation system, an auxiliary system and a control system. The vacuum guarantee system and the temperature guarantee system are both connected to the inside of the thermal vacuum simulation container, the lighting simulation system is installed in the thermal vacuum simulation container, and the control system controls the vacuum guarantee system, the temperature guarantee system and the lighting simulation system;

[0025] The thermal vacuum simulation container includes a pressure-bearing layer, an intermediate layer and a heating cage. The pressure-bearing layer includes a cylinder 1, a door 2, a plurality of flanges 3 and a plurality of vacuum pipes. The cylinder 1 is a 304 stainless steel cylinder. The gas outlet rate of the cylinder 1 after polishing is 2.93×10-7Pa·L·s-1·cm-2. The wall thickness of the cylinder 1 is S, S=S0+C, where S0 is the designed wall thickness of the cylinder 1, C is the additional wall thickness, C=C1+C2+C3, C1=0.5mm, C2=0, C3=4.7×0.1=0.47mm, C=0.97mm, Where D B is the inner diameter of the cylinder, in this embodiment, D B =1200mm, p is the atmospheric pressure, in this embodiment p = 0.1MPa, L is the length of the cylinder, in this embodiment L = 1200mm, E t is the elastic modulus of the cylinder material at temperature t. In this embodiment, E t =195000MPa, after calculation, S0=4.7mm, S=4.7+0.96=5.65mm, the integer is 6mm after rounding, the gate 2 is installed at the end of the cylinder 1, and a plurality of vacuum pipes are connected with the inside of the cylinder 1 through a plurality of flanges 3 respectively, the flange 3 is a large flange 3 with a thickness of 50mm, the middle layer is a heat sink system 4, the heating cage is located in the middle layer, and the bottom of the heating cage passes through the middle layer and is fixed to the cylinder 1;

[0026] The vacuum assurance system includes a vacuum acquisition subsystem, a vacuum measurement subsystem and a pressure stabilization subsystem. The vacuum acquisition subsystem includes a low vacuum acquisition unit and a high vacuum acquisition unit. The vacuum measurement subsystem includes a low vacuum measurement unit and a high vacuum measurement unit. The low vacuum acquisition unit includes a screw pump (German Leybold LV80) and a single-stage rotary vane pump (German Leybold SV200B). The pumping speed of the screw pump is 22L / s, and the pumping speed of the single-stage rotary vane pump is 49L / s. The low vacuum acquisition unit meets the following requirements: from normal pressure to 10kPa, the time is not more than 1.5min, from normal pressure to 3000Pa, the average rate is not less than 10kPa / min, from 3000Pa to 10Pa, the average rate is not less than 200Pa / min; since the limit pressure of the single-stage rotary vane pump is 10Pa, the single-stage rotary vane pump will be closed at about 100Pa, and 100Pa~10Pa can only be evacuated by a screw pump. The high vacuum acquisition unit includes a cryopump (MAG2201lip) and a molecular pump (VAC3000ICL). The pumping speed of the cryopump is 5000L / s, and the pumping speed of the molecular pump is 2000L / s. The auxiliary system uses a 10KW air-cooled circulating water machine to cool the high vacuum acquisition unit. The high vacuum acquisition unit meets the following requirements: the pressure reduction rate is from normal pressure to 5×10 -3 Pa, time is no more than 40min, from normal pressure to 5×10 -4 Pa, time is no more than 120min, from normal pressure to 5×10 -5 Pa, the time is not more than 4h; the low vacuum measurement unit adopts a measurement range of 1×10 5 Pa to 1×10 -1 The high vacuum measurement unit has a measurement range of 100 kPa to 1 × 10 -6 Vacuum regulation of Pa. The pressure stabilization subsystem includes several valves;

[0027] The temperature guarantee system includes a refrigeration unit 6, a heat transfer oil unit and a cold plate unit 5. The refrigeration unit 6 adopts a mechanical refrigerator. The heat transfer oil unit includes a heater 14, an oil tank 15, an oil pump 16 and a heat transfer oil pipeline 17. The cold plate unit 5 is installed in a heating cage. The heat transfer oil pipeline 17 is connected to the oil tank 15. The oil pump 16 is installed on the heat transfer oil pipeline 17. The heater 14 is connected to the heat transfer oil pipeline 17 to heat the heat transfer oil. The heat transfer oil pipeline 17 is laid on the heating cage. The heat transfer oil adopts CS100 heat transfer oil.

[0028] Combination Figure 2As shown, the heating cage includes a cage body and a sample platform. The cage body includes an arc-shaped main body 7 and two end covers 8. The arc-shaped main body 7 is fixed in the cylinder 1, one end cover 8 is fixed at one end of the arc-shaped main body 7, and the other end cover 8 is fixed on the inner side of the gate 2. The sample platform includes a support frame 9, a guide rail 10, a support plate 11 and a locking assembly 12. The bottom of the support frame 9 is fixed on the inner side of the cylinder 1, and the top of the support frame 9 passes through the heat sink system 4 and is located in the cage body. The guide rail 10 is fixed on the top of the support frame 9, and the support plate 11 is slidably connected to the guide rail 10. The locking assembly 12 includes a latch, a pin hole seat, a latch seat and an elastic member. The latch seat is fixed to the bottom of the support plate 11. The latch is vertically slidably connected to the latch seat. The elastic member is connected between the latch and the latch seat. The pin hole seat is fixed to the guide rail 10 directly below the latch. The cold plate unit 5 is fixed to the support plate 11. The heat transfer oil pipeline 17 is laid at the bottom of the cold plate unit 5 and the inner side of the cage. The outside of the cylinder 1 is provided with a slide rail frame 13 docking with the guide rail 10. The bottom of the slide rail frame 13 is provided with a walking wheel. Figure 4 As shown, the heat sink system 4 adopts double-layer stainless steel, and the inner surface is sprayed with imported radiation paint with strong adhesion, hemispherical emissivity ≥ 0.95, and solar absorption coefficient ≥ 0.93. The heat sink system 4 acts as a radiation screen to absorb and emit radiation energy. The outer surface of the heat sink system 4 is polished to increase the reflectivity and prevent outward radiation. The heat sink system 4 is processed by water for pressurization to make the double-layer stainless steel bulge produce a flow channel, and water is used to maintain the pressure. Before installing the heat sink system 4, water is removed. The water removal method is as follows: the heat sink system 4 is placed in the cylinder 1, the interface is connected to nitrogen, and the outlet is placed outside the box. The temperature in the cylinder 1 is raised to 110°C, and nitrogen is blown out every 2 hours until all the water is blown out. The cold plate unit 5 is completed by punching and welding a whole piece of stainless steel, and the thickness of the cold plate unit 5 is 15mm.

[0029] The lighting simulation system uses a lighting simulator.

[0030] The control system adopts Siemens S71200PLC+touch screen, the electronic control components adopt ABB components, the communication module adopts Weiluntong SVR communication module, the sensor adopts 16 patch sensors, and the sensor is directly connected to PLC.

[0031] The specific implementation process is as follows: the support plate 11 and the cold plate unit 5 slide out of the cylinder 1 along the guide rail 10 to the slide rail frame 13, and the test sample is placed on the cold plate unit 5. After the test sample is fixed, the support plate 11 and the cold plate are pushed into the cylinder 1. After they are in place, the support plate 11 and the cold plate are locked by the locking assembly 12. After closing the door 2, the thermal vacuum test can be started. It can truly simulate the cold and hot environment and lighting environment of the vacuum space, and can effectively control, monitor and record the vacuum degree and temperature of the space.

[0032] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0033] The above is only an embodiment of the present invention. The common sense such as the known specific structure and characteristics in the scheme is not described in detail here. The ordinary technicians in the relevant field know all the common technical knowledge in the technical field of the invention before the application date or priority date, can obtain all the existing technologies in the field, and have the ability to apply the conventional experimental means before that date. The ordinary technicians in the relevant field can improve and implement this scheme in combination with their own abilities under the enlightenment given by this application. Some typical known structures or known methods should not become obstacles for ordinary technicians in the relevant field to implement this application. It should be pointed out that for those skilled in the art, without departing from the structure of the present invention, several deformations and improvements can be made, which should also be regarded as the protection scope of the present invention, which will not affect the effect of the implementation of the present invention and the practicality of the patent. The protection scope required by this application shall be based on the content of its claims, and the specific implementation methods and other records in the specification can be used to interpret the content of the claims.

Claims

1. Thermal vacuum simulation system for space environment simulation and testing, characterized by: It includes a thermal vacuum simulation container, a vacuum guarantee system, a temperature guarantee system, a light simulation system and a control system. The vacuum guarantee system and the temperature guarantee system are both connected to the inside of the thermal vacuum simulation container. The light simulation system is installed in the thermal vacuum simulation container. The control system controls the vacuum guarantee system, the temperature guarantee system and the light simulation system. The thermal vacuum simulation container comprises a pressure-bearing layer, an intermediate layer and a heating cage, wherein the pressure-bearing layer comprises a cylinder, a door, a plurality of flanges and a plurality of vacuum pipes, wherein the door is installed at the end of the cylinder, and the plurality of vacuum pipes are respectively connected to the inside of the cylinder through a plurality of flanges, wherein the intermediate layer is a heat sink system, the heating cage is located in the intermediate layer, and the bottom of the heating cage passes through the intermediate layer and is fixed to the cylinder; The vacuum guarantee system includes a vacuum obtaining subsystem, a vacuum measuring subsystem and a pressure stabilizing subsystem. The vacuum obtaining subsystem includes a low vacuum obtaining unit and a high vacuum obtaining unit. The vacuum measuring subsystem includes a low vacuum measuring unit and a high vacuum measuring unit. The low vacuum obtaining unit includes several mechanical pumps, the high vacuum obtaining unit includes a cryogenic pump and a molecular pump, and the pressure stabilizing subsystem includes several valves. The temperature assurance system comprises a refrigeration unit, a heat transfer oil unit and a cold plate unit. The refrigeration unit adopts a mechanical refrigerator. The heat transfer oil unit comprises a heater, an oil tank, an oil pump and a heat transfer oil pipeline. The cold plate unit is installed in a heating cage. The heat transfer oil pipeline is connected to the oil tank. The oil pump is installed on the heat transfer oil pipeline. The heater is connected to the heat transfer oil pipeline to heat the heat transfer oil. The heat transfer oil pipeline is laid on the heating cage. The illumination simulation system adopts an illumination simulator.

2. The thermal vacuum simulation system for space environment simulation and testing according to claim 1, characterized in that: The low vacuum obtaining unit meets the following requirements: from normal pressure to 10 kPa, the time is no more than 1.5 min, from normal pressure to 3000 Pa, the average rate is no less than 10 kPa / min, from 3000 Pa to 10 Pa, the average rate is no less than 200 Pa / min; the high vacuum obtaining unit meets the following requirements: the pressure reduction rate is from normal pressure to 5×10 -3 Pa, time is no more than 40min, from normal pressure to 5×10 -4 Pa, time is no more than 120min, from normal pressure to 5×10 -5 Pa, time not more than 4h.

3. The thermal vacuum simulation system for space environment simulation and testing according to claim 2, characterized in that: The low vacuum measurement unit has a measurement range of 1×10 5 Pa to 1×10 -1 The high vacuum measurement unit has a measurement range of 100 kPa to 1 × 10 -6 Pa vacuum gauge.

4. The thermal vacuum simulation system for space environment simulation and testing according to claim 3, characterized in that: It also includes an auxiliary system, which uses an air-cooled circulating water machine to cool the high vacuum acquisition unit.

5. The thermal vacuum simulation system for space environment simulation and testing according to claim 1, characterized in that: The heat sink system adopts double-layer stainless steel, and the inner surface of the heat sink system is sprayed with imported radiation paint with strong adhesion, hemispherical emissivity ≥0.95, and solar absorption coefficient ≥0.

93. The heat sink system acts as a radiation screen to absorb and emit radiation energy. The outer surface of the heat sink system is polished to increase the reflectivity. The heat sink system processing technology uses water for pressurization to make the double-layer stainless steel bulge produce a flow channel, and water is used to maintain the pressure. Before installing the heat sink system, dewatering is performed. The dewatering method is as follows: the heat sink system is placed in a cylinder, the interface is connected to nitrogen, the outlet is placed outside the cylinder, the temperature inside the cylinder is raised to 110°C, and nitrogen is blown out every 2 hours to blow out the water until all the water is blown out.

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