A multi-modal test device that simulates a space environment

Abstract

The utility model discloses a kind of multi-modal testing devices of simulated space environment, including vacuum chamber with vacuum module;Wherein, cooling module, heating module are respectively equipped in vacuum chamber, vacuum module, cooling module and heating module are respectively connected with the communication control module located outside;Vacuum chamber is also equipped with tray module, for placing sample to be measured;Cooling module can be relatively installed in vacuum chamber and displaced up and down, for adjusting the distance between it and sample to be measured;The utility model can greatly reduce the experimental time of cold and hot impact;While realizing the multi-modal testing effect of simulated space environment, reduce space solar cell array research and development test time and manufacturing cost of product control, help low-cost space technology development and application.

Description

Technical Field

[0001] This utility model relates to the field of testing equipment, specifically to a multimodal testing device for simulating a space environment. Background Technology

[0002] In current technology, solar arrays serve as the sole energy source for spacecraft, and their performance directly determines the spacecraft's on-orbit operational capability and lifespan. Because traditional high-orbit satellites emphasize high efficiency, high reliability, and long lifespan, they are less sensitive to cost, and their solar arrays generally utilize high-efficiency gallium arsenide (GaAs) solar cells. The entire process of creating a GaAs solar array, from cell fabrication and interconnection to assembly and satellite integration, undergoes rigorous evaluation and screening. Specifically, ground-based thermal vacuum and thermal cycling are essential baseline tests, with thermal shock temperatures required to be ±120°C, and deep space exploration projects even requiring ±150°C and over 3000 cycles.

[0003] Existing vacuum thermal shock devices generally use liquid nitrogen cooling and resistance wire heating. The equipment is bulky, has high operating costs, takes a long time (more than 1 hour) for a single cycle, consumes a lot of energy, and costs more than 500,000 yuan for a single test, with a long time cycle.

[0004] Therefore, the applicant wishes to seek technical solutions to address the above-mentioned technical problems. Summary of the Invention

[0005] In view of this, the purpose of this utility model is to provide a multimodal testing device for simulating a space environment, which can significantly reduce the experimental time of thermal shock; while achieving multimodal testing effects on the simulated space environment, it can reduce the R&D testing time and manufacturing quality control costs of space solar cell arrays, and help the development and application of low-cost space technologies.

[0006] The technical solution adopted in this utility model is as follows: A multimodal testing device for simulating a space environment includes a vacuum chamber equipped with a vacuum pumping module; wherein, a cooling module and a heating module are respectively provided in the vacuum chamber, and the vacuum pumping module, cooling module and heating module are respectively connected to an external communication control module; the vacuum chamber is also equipped with a tray module for placing the sample to be tested; the cooling module is installed in the vacuum chamber with relative vertical displacement to adjust the distance between it and the sample to be tested.

[0007] Preferably, the cooling module and the heating module are distributed vertically at intervals relative to the tray module; wherein the cooling module is located above the tray module and the heating module is located below the tray module.

[0008] Preferably, the cooling module includes a coolant container sealed and installed in a vacuum chamber; wherein, the open surface of the coolant container is fixedly covered with an insulation layer, and the coolant container is equipped with a coolant injection pipe and a pressure relief pipe penetrating the insulation layer; the coolant injection pipe and the pressure relief pipe are respectively connected to a communication control module; the coolant is preferably liquid nitrogen.

[0009] Preferably, the coolant container is installed in the vacuum chamber with relative vertical displacement. The coolant container is equipped with a corrugated pipe that penetrates the insulation layer. The corrugated pipe is connected to a position adjustment motor connected to the communication control module to drive the coolant container vertically, thereby adjusting the distance between the coolant container and the sample to be tested.

[0010] Preferably, the heating module includes a lamp support; wherein one or more heating lamps are mounted on the lamp support, and the heating lamps are preferably infrared lamps.

[0011] Preferably, the lamp holder is equipped with a holder rotation driver connected to the communication control module; wherein, the holder rotation driver drives the lamp holder to rotate relative to its drive shaft, and selectively connects or disconnects the power supply to the heating lamp according to the opening and closing state of the lamp holder.

[0012] Considering that, even with the current technology, existing vacuum thermal shock devices have a fatal flaw: they cannot achieve simultaneous coupled simulation testing of space illumination and thermal shock, resulting in an incomplete evaluation process; in addition, emerging commercial satellites place greater emphasis on cost-effectiveness, large-scale production capabilities, lightweight design, and modularity, current vacuum thermal shock devices are increasingly unable to meet the simulation testing needs of solar cell arrays used in space environments.

[0013] Preferably, the vacuum chamber is further provided with a light source module connected to the communication control module. The light source module is distributed vertically relative to the tray module. The light source module is preferably located below the tray module, and more preferably below the heating module.

[0014] Preferably, the light source module includes a light source bracket; wherein one or more light sources are mounted on the light source bracket, and the light sources are preferably LED beads.

[0015] Preferably, the light source bracket is equipped with a light source bracket rotation driver connected to the communication control module; wherein, the light source bracket rotation driver drives the light source bracket to rotate relative to its drive shaft, and selectively connects or disconnects the power supply to the light source lamp according to the open or closed state of the light source bracket.

[0016] Preferably, the vacuum module includes an exhaust pipe connected to the vacuum chamber, and the exhaust pipe is connected to a mechanical pump and a molecular pump respectively.

[0017] It should be noted that the specific operating parameters of the cooling module, heating module, vacuum module and light source module involved in this application can be set according to the needs of the simulated space environment, so as to realize the multimodal testing requirements of the simulated space environment. This can be done in combination with the common knowledge of the test of the simulated space environment. This application does not make any special limitations in this regard, nor does it propose any special innovative content.

[0018] This application proposes a cooling module that can be installed vertically within a vacuum chamber. The distance between the cooling module and the sample under test can be adjusted according to the requirements of thermal shock. The cooling source of the cooling module can be infinitely close to the sample under test, thereby achieving a rapid cooling effect and significantly reducing the experimental time of thermal shock. While achieving multimodal testing effects on simulated space environment, it reduces the R&D testing time and manufacturing quality control costs of space solar cell arrays, and helps the development and application of low-cost space technology. This application further proposes a vacuum chamber that integrates a cooling module, a heating module, and a light source module. Each module is connected to the control module of the communication control module, which can simultaneously simulate and couple more modal elements in the space environment such as light, heat, and cold, and more closely simulate the real space environment. Compared with traditional thermal shock simulation experiments, this application can realize more modal tests in practical applications, such as thermal vacuum, atmospheric pressure thermal cycling shock, vacuum thermal cycling shock, light irradiation attenuation, and photothermal / cold cycling shock. Moreover, the modules proposed in this application have simple structures and low operating costs, which can further reduce operating expenses, making it very suitable as a multimodal testing device for simulating space environments. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the principle structure of a multimodal testing device for simulating a space environment according to a specific embodiment of this application; Figure 2 This is a schematic diagram of the structure of the cooling module 2 according to a specific embodiment of this application; Figure 3 This is a schematic diagram of the structure of the heating module 6 according to a specific embodiment of this application; Figure 4 This is a schematic diagram of the structure of the light source module 7 in a specific embodiment of this application. Detailed Implementation

[0020] This embodiment proposes a multimodal testing device for simulating a space environment, including a vacuum chamber equipped with a vacuum pumping module; wherein, a cooling module and a heating module are respectively provided in the vacuum chamber, and the vacuum pumping module, cooling module and heating module are respectively connected to an external communication control module; a tray module is also provided in the vacuum chamber for placing the sample to be tested; the cooling module is installed in the vacuum chamber with relative vertical displacement to adjust the distance between it and the sample to be tested.

[0021] To enable those skilled in the art to better understand the technical solutions of this utility model, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, and not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort should fall within the protection scope of this utility model.

[0022] Please see Figure 1 As shown, a multimodal testing device simulating a space environment includes a vacuum chamber 1 equipped with a vacuum pumping module 8; wherein, a cooling module 2 and a heating module 6 are respectively provided in the vacuum chamber 1, and the vacuum pumping module 8, the cooling module 2 and the heating module 6 are respectively connected to an external communication control module 9; a tray module 3 is also provided in the vacuum chamber 1 for placing the sample 4 to be tested; the cooling module 2 is installed in the vacuum chamber 1 with relative vertical displacement to adjust the distance between it and the sample 4 to be tested.

[0023] Please refer to the above for further details. Figure 2 As shown, preferably, in this embodiment, the cooling module 2 and the heating module 6 are distributed vertically at intervals relative to the tray module 3; wherein, the cooling module 2 is located above the tray module 3, and the heating module 6 is located below the tray module 3; More preferably, in this embodiment, the cooling module 2 includes a coolant container 206 sealed and installed inside the vacuum chamber 1; wherein, the open surface of the coolant container 206 is fixedly covered with a heat insulation layer 203, and the lower surface of the coolant container 206 is left exposed to realize the management, transfer and effective utilization of cold energy loss; the coolant container 206 is equipped with a coolant injection pipe 204 and a pressure relief pipe 205 penetrating the heat insulation layer 203; the coolant injection pipe 204 and the pressure relief pipe 205 are respectively connected to the communication control module 9; specifically preferably, in this embodiment, the coolant is liquid nitrogen; preferably, in this embodiment, the vacuum chamber 1 can be made of aluminum alloy or 316 stainless steel to a predetermined size, and the coolant container 206 can be made of copper, aluminum or alloy material with good thermal conductivity; More preferably, in this embodiment, the vacuum chamber 1 is provided with a sample window 5 (which can be specifically set at the center of its side). The sample window 5 can adopt a known sealing method (for example, a combination of a switch flange and a sealing ring) to realize the opening / closing and vacuum sealing installation functions. Preferably, in this embodiment, the tray module 3 located in the vacuum chamber 1 is at the same level as the sample window 5, and thermocouples are respectively provided on the upper surface and / or lower surface of the tray module 3. Preferably, the distance between the detection point of the thermocouple and the corresponding surface of the tray module 3 is controlled within 2-10 mm. More preferably, in this embodiment, the coolant container 206 is installed in the vacuum chamber 1 with relative vertical displacement. The coolant container 206 is equipped with a bellows 202 that penetrates the insulation layer 203. The bellows 202 is connected to the position adjustment motor 201 connected to the communication control module 9 to realize the vertical drive connection of the coolant container 206, which is used to adjust the distance between the coolant container 206 and the sample 4 to be tested.

[0024] Please refer to the above for further details. Figure 3 As shown, preferably, in this embodiment, the heating module 6 includes a lamp support 602; wherein, one or more heating lamps 601 are mounted on the lamp support 602, and the heating lamps 601 are preferably infrared lamps. Further preferably, in this embodiment, the lamp holder 602 is equipped with a holder rotation driver 603 connected to the communication control module 9; wherein, the holder rotation driver 603 drives the lamp holder 602 to rotate relative to its drive shaft 603a, and selectively connects or disconnects the power supply to the heating lamp 601 according to the opening and closing state of the lamp holder 602; specifically preferably, in this embodiment, the lamp holder 602 can achieve relative opening and closing rotation within a 90-degree range through the holder rotation driver 603, wherein an interlocking contact mechanism is set according to the rotation opening and closing state of the lamp holder 602, specifically including: when the lamp holder 602 is in a horizontal state, the power supply to the heating lamp 601 is allowed to be turned on to the heating lamp 601; when the lamp holder 602 rotates to a vertical state of 90 degrees from the horizontal state, the power supply to the heating lamp 601 is cut off; preferably, in this embodiment, the holder rotation driver 603 is located outside the vacuum chamber 1, and can be a motor or a cylinder.

[0025] Considering that, even with the current technology, existing vacuum thermal shock devices have a fatal flaw: they cannot achieve simultaneous coupled simulation testing of space illumination and thermal shock, resulting in an incomplete evaluation process; in addition, emerging commercial satellites place greater emphasis on cost-effectiveness, large-scale production capabilities, lightweight design, and modularity, current vacuum thermal shock devices are increasingly unable to meet the simulation testing needs of solar cell arrays used in space environments.

[0026] Please refer to the above for further details. Figure 4 As shown, preferably, in this embodiment, the vacuum chamber 1 is further provided with a light source module 7 (a light source for simulating the space environment AM0) connected to the communication control module 9. The light source module 7 is distributed vertically relative to the tray module 3. The light source module 7 is preferably located below the tray module 3, and more preferably below the heating module 6. Preferably, in this embodiment, the light source module 7 includes a light source bracket 702; wherein, one or more light source lamps 701 are mounted on the light source bracket 702; specifically, preferably, in this embodiment, the light source lamps 701 are LED lamp beads; Further preferably, in this embodiment, the light source bracket 702 is equipped with a light source bracket rotation driver 703 connected to the communication control module 9; wherein, the light source bracket rotation driver 703 drives the light source bracket 702 to rotate relative to its drive shaft 703a, and selectively connects or disconnects the power supply to the light source lamp 701 according to the opening and closing state of the light source bracket 702; specifically preferably, in this embodiment, the light source bracket 702 can achieve relative opening and closing rotation within a 90-degree range through the light source bracket rotation driver 703, wherein an interlocking contact mechanism is set according to the rotation opening and closing state of the light source bracket 702, specifically including: when the light source bracket 702 is in a horizontal state, the power supply to the light source lamp 701 is allowed to be turned on; when the light source bracket 702 rotates to a vertical state of 90 degrees from the horizontal state, the power supply to the light source lamp 701 is cut off; preferably, in this embodiment, the light source bracket rotation driver 703 is located outside the vacuum chamber 1, and can be a motor or a cylinder.

[0027] Preferably, in this embodiment, the vacuum module 8 includes an exhaust pipe 801 connected to the vacuum chamber 1, and the exhaust pipe 801 is connected to a mechanical pump 802 and a molecular pump 803 respectively; this embodiment achieves a more efficient vacuuming effect by setting up a two-stage exhaust pump.

[0028] This embodiment proposes a cooling module 2 that can be installed vertically within a vacuum chamber 1. The distance between the cooling module and the sample under test can be adjusted according to the requirements of thermal shock. The cooling source of the cooling module 2 can be infinitely close to the sample under test, thereby achieving a rapid cooling effect and significantly reducing the experimental time of thermal shock. While achieving multimodal testing effects in simulated space environments, it reduces the R&D testing time and manufacturing quality control costs of space solar cell arrays, contributing to the development and application of low-cost space technologies. This embodiment also proposes a vacuum chamber 1 that integrates a cooling module 2, a heating module 6, and a light source module 7. Each module is connected to the control of a communication control module 8, which can simultaneously simulate and couple more modal elements in the space environment, such as light, heat, and cold, to more closely simulate the real space environment. Compared with traditional thermal shock simulation experiments, this application can achieve more modal tests in practical applications, such as thermal vacuum, atmospheric pressure thermal cycling shock, vacuum thermal cycling shock, light irradiation attenuation, and photothermal / cold cycling shock. Moreover, the modules proposed in this application have simple structures and low operating costs, which can further significantly reduce operating expenses, making them very suitable as a multimodal testing device for simulating space environments.

[0029] It will be apparent to those skilled in the art that this invention is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other specific forms without departing from the spirit or essential characteristics of this invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of this invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within this invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0030] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A multimodal testing device for simulating a space environment, characterized in that, The system includes a vacuum chamber (1) equipped with a vacuum pumping module (8); wherein, the vacuum chamber (1) is equipped with a cooling module (2) and a heating module (6), and the vacuum pumping module (8), the cooling module (2) and the heating module (6) are respectively connected to an external communication control module (9); the vacuum chamber (1) is also equipped with a tray module (3) for placing the sample to be tested (4); the cooling module (2) can be installed in the vacuum chamber (1) with relative vertical displacement to adjust the distance between it and the sample to be tested (4).

2. The multimodal testing device for simulating a space environment according to claim 1, characterized in that, The cooling module (2) and the heating module (6) are arranged vertically and horizontally relative to the tray module (3); wherein the cooling module (2) is located above the tray module (3) and the heating module (6) is located below the tray module (3).

3. The multimodal testing device for simulating a space environment according to claim 1 or 2, characterized in that, The cooling module (2) includes a coolant container (206) sealed and installed in a vacuum chamber (1); wherein, the opening surface of the coolant container (206) is fixedly covered with a heat insulation layer (203), and the coolant container (206) is provided with a coolant injection pipe (204) and a pressure relief pipe (205) penetrating the heat insulation layer (203); the coolant injection pipe (204) and the pressure relief pipe (205) are respectively connected to the communication control module (9); the coolant is preferably liquid nitrogen.

4. The multimodal testing device for simulating a space environment according to claim 3, characterized in that, The coolant container (206) is installed in the vacuum chamber (1) with relative vertical displacement. The coolant container (206) is equipped with a bellows (202) that penetrates the insulation layer (203). The bellows (202) is connected to the coolant container (206) by a position adjustment motor (201) connected to the communication control module (9) to drive the coolant container (206) up and down, and is used to adjust the distance between the coolant container (206) and the sample (4) to be tested.

5. The multimodal testing device for simulating a space environment according to claim 1 or 2, characterized in that, The heating module (6) includes a lamp support (602); wherein one or more heating lamps (601) are installed on the lamp support (602), and the heating lamps (601) are preferably infrared lamps.

6. The multimodal testing device for simulating a space environment according to claim 5, characterized in that, The lamp tube bracket (602) is equipped with a bracket rotation driver (603) connected to the communication control module (9); wherein, the bracket rotation driver (603) drives the lamp tube bracket (602) to rotate relative to its drive shaft, and selectively connects or disconnects the power supply to the heating lamp tube (601) according to the opening and closing state of the lamp tube bracket (602).

7. The multimodal testing device for simulating a space environment according to claim 1 or 2, characterized in that, The vacuum chamber (1) is also provided with a light source module (7) connected to the communication control module (9). The light source module (7) is distributed vertically relative to the tray module (3). The light source module (7) is preferably located below the tray module (3), and more preferably below the heating module (6).

8. The multimodal testing device for simulating a space environment according to claim 7, characterized in that, The light source module (7) includes a light source bracket (702); wherein one or more light source lamps (701) are installed on the light source bracket (702), and the light source lamps (701) are preferably LED lamp beads.

9. The multimodal testing device for simulating a space environment according to claim 8, characterized in that, The light source bracket (702) is equipped with a light source bracket rotation driver (703) connected to the communication control module (9); wherein, the light source bracket rotation driver (703) drives the light source bracket (702) to rotate relative to its drive shaft, and selectively connects or disconnects the power supply to the light source lamp (701) according to the opening and closing state of the light source bracket (702).

10. The multimodal testing device for simulating a space environment according to claim 1 or 2, characterized in that, The vacuum module (8) includes an exhaust pipe (801) connected to the vacuum chamber (1), and the exhaust pipe (801) is connected to a mechanical pump (802) and a molecular pump (803).

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