Deep space exploration simulation test system and method

Abstract

The invention provides a deep space exploration simulation test system and method.The deep space exploration simulation test system comprises a thermal interface structure, a cryogenic subsystem and a heating structure, the cryogenic subsystem can refrigerate and cool the thermal interface structure, and the heating structure can heat the thermal interface structure; the deep cooling subsystem comprises a low-temperature refrigeration assembly and a gas cooling assembly, the low-temperature refrigeration assembly transmits cold energy to the thermal interface structure in a one-way mode, and the gas cooling assembly cools the thermal interface structure through cooling gas. The continuous temperature regulation in the range of 300K to 423K is realized through the combination of air cooling and electric heating, and the continuous temperature regulation in the range of 38K to 300K is realized through the combination of a G-M low-temperature refrigerator and electric heating; compared with the existing space environment simulation equipment, the temperature zone can be expanded to 38K to 423K, and the extreme temperature zone environment required by deep space exploration including the lunar surface polar zone and the Mars can be completed; meanwhile, the integrated heat exchange cryogenic subsystem based on heat conduction and convection is compact in structure, liquid nitrogen and liquid helium do not need to be used, and energy conservation and environmental protection are achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of deep space exploration simulation equipment, and in particular to a deep space exploration simulation test system and method. Background Art

[0002] Deep space exploration is an important field in my country's aerospace system engineering. The space environment that probes need to experience in subsequent lunar and Mars exploration missions will be expanded to 48K to 400K, and the probes' motion performance needs to be tested under continuous arbitrary temperature conditions within this extreme temperature range to improve their working reliability. Therefore, a space environment simulation test and detection system with continuous stepless temperature adjustment in extreme temperature zones under a vacuum environment and comprehensive multi-stress capabilities such as dual-sided driving / loading has become a key means to test the functions, performance and reliability of deep space probes.

[0003] At present, deep space exploration environmental test systems at home and abroad can only achieve vacuum high and low temperature environments, and the structure is relatively complex. The use of consumable working fluids such as liquid nitrogen results in high operating costs. The space environment temperature range that can be simulated is narrow, and the system operation reliability is insufficient. At the same time, there are no public reports on vacuum extreme temperature zone high and low temperature environment test systems with driving / loading capabilities.

[0004] The existing Chinese patent application document with publication number CN113371236B specifically relates to a dual heat sink structure of liquid nitrogen and a GM-type cryogenic refrigerator. The outer liquid nitrogen heat sink assists in cooling the inner GM cryogenic refrigerator heat sink, and the liquid nitrogen passage of the outer heat sink is connected and cut off by controlling the solenoid valve through heat sink temperature feedback, thereby achieving wide temperature range regulation of 20K to 400K. However, this system requires two sets of heat sink structures and a liquid nitrogen storage tank for liquid supply, which is relatively complicated. In addition, a heating plate is directly provided on the inner heat sink that is directly connected to the cold-end refrigeration component of the GM refrigerator, which puts the cold-end component in a high-temperature heating environment and is easily damaged, resulting in failure to work normally. Finally, the system has a single function and can only provide a vacuum temperature environment, and cannot realize the drive / load test function.

[0005] CN101576359A discloses a component for a low-temperature process system in space environment simulation test equipment, specifically a liquid nitrogen / alcohol dual-medium compatible heat sink system for space environment simulation test equipment. This heat sink system allows liquid nitrogen and alcohol to share the same flow path, enabling adjustable temperature ranges from 110K to 232K. However, the system requires a liquid nitrogen storage tank for liquid supply, resulting in a complex design and a narrow temperature range. Furthermore, the system is limited in functionality, providing only a vacuum temperature environment and failing to implement drive / load testing.

[0006] CN103318427B discloses a space environment simulation test system, similar to CN101576359A, specifically a liquid nitrogen / helium dual-medium compatible heat sink system that achieves wide temperature range regulation from 68K to 373K. This system requires a liquid nitrogen storage tank for liquid supply, which is relatively complex and has a narrow temperature range. Furthermore, the system is limited in functionality, providing only a vacuum temperature environment and unable to perform drive / load testing.

[0007] Given that the existing test and detection systems cannot meet the test requirements of deep space exploration products, it is necessary for us to develop a test and detection system with vacuum deep cooling, high temperature and driving / loading capabilities to provide ground simulation test conditions for deep space probes and verify product functions, performance and reliability. Summary of the Invention

[0008] In view of the defects in the prior art, the purpose of the present invention is to provide a deep space exploration simulation test system and method.

[0009] According to the present invention, a deep space exploration simulation test system includes a tank structure, a cryogenic subsystem, a heating structure, a thermal interface structure, a vacuum pumping subsystem and a drive loading system. The tank structure includes a closable cavity, the thermal interface structure is installed in the closable cavity of the tank structure, and a loading platform for carrying a device to be tested is provided in the thermal interface structure. The vacuum pumping subsystem can evacuate the closable cavity of the tank structure; the cryogenic subsystem can cool the thermal interface structure, the heating structure can heat the thermal interface structure, and the drive loading system can drive and / or load the device to be tested on the loading platform.

[0010] Preferably, the deep cooling subsystem includes a low-temperature refrigeration component and a gas cooling component; the low-temperature refrigeration component includes a low-temperature refrigerator and a one-way cold transmission structure, the cold head of the low-temperature refrigerator is connected to the thermal interface structure through the one-way cold transmission structure, and the low-temperature refrigerator transfers cold to the thermal interface structure in one direction through the one-way cold transmission structure; the gas cooling component includes a cooling gas pipeline structure, a cooling gas inlet distributor, and a cooling gas outlet distributor, and the cooling gas pipeline structure is wrapped around the outer wall of the thermal interface structure; the cooling gas enters the cooling gas pipeline structure through the cooling gas inlet distributor and then flows out through the cooling gas outlet distributor.

[0011] Preferably, the one-way cold transmission structure includes a stainless steel tube structure embedded with sapphire, and copper plates are provided at both ends of the stainless steel tube structure embedded with sapphire. The copper plate at one end of the stainless steel tube structure embedded with sapphire is connected to the cold head of the low-temperature refrigerator, and the copper plate at the other end of the stainless steel tube structure embedded with sapphire is connected to the thermal interface structure.

[0012] Preferably, the thermal interface structure includes at least two temperature regulating zones, each of which is provided with at least one set of low-temperature refrigeration components, and each of which is provided with at least one cooling gas pipeline structure.

[0013] Preferably, the thermal interface structure further comprises a hexagonal copper screen heat sink, a copper plate and a heat flow copper belt, the stage is fixedly arranged inside the hexagonal copper screen heat sink, and the heat flow copper belt connects the copper plate, the hexagonal copper screen heat sink and the stage to form a heat flow path.

[0014] Preferably, the heating structure includes a heating bar, which is arranged in the hexagonal copper screen heat sink, and the heating bar is in contact with and connected to the hexagonal copper screen heat sink and / or the heat flow copper belt and copper plate.

[0015] Preferably, the drive loading system includes a servo motor, a first electromagnetic clutch device, a gear transmission device, a brake, a second electromagnetic clutch device and a loading shaft system; the output shaft of the servo motor is engaged or disengaged with the gear transmission device and the second electromagnetic clutch device respectively through the first electromagnetic clutch device, the brake is in transmission connection with the gear transmission device, and the second electromagnetic clutch device is in transmission connection with the loading shaft system.

[0016] Preferably, the drive loading system also includes a loading platform, and the loading platform, servo motor, first electromagnetic clutch device, gear transmission device, brake and second electromagnetic clutch device are all located outside the tank structure, and the servo motor is arranged on the loading platform; the loading shaft system includes an elastic coupling, a rigid coupling and a loading head, and the loading head extends into the thermal interface structure, and the elastic coupling and the rigid coupling are both arranged between the loading head and the output shaft of the second electromagnetic clutch device.

[0017] Preferably, the driving and loading systems are provided with a group on either opposite sides of the tank structure.

[0018] According to a deep space exploration simulation test method provided by the present invention, the test method comprises: placing a device to be tested on a stage, and connecting a driving loading system to the device to be tested; Turn on the vacuum pumping subsystem to evacuate the sealable cavity of the tank structure to the required test pressure; Turning on the cryogenic subsystem and / or the heating structure to adjust the environment in the enclosed cavity of the tank structure to a target temperature between 38K and 423K through the thermal interface structure; Start the driver loading system to drive and / or load the device under test.

[0019] Compared with the prior art, the present invention has the following beneficial effects: 1. The present invention utilizes sapphire's high thermal conductivity at low temperatures and low thermal conductivity at high temperatures to innovatively design a one-way cold transmission structure. This structure is combined with a low-temperature refrigerator and used in conjunction with compressed cooling air to construct a new integrated heat exchange deep cooling subsystem based on heat conduction and convection. At the same time, two electromagnetic clutch devices and a gear transmission device are used to disconnect and connect the servo motor and brake to the shaft system respectively, completing the switching and combined working modes of the drive and loading functions.

[0020] 2. The present invention realizes the switching of driving or loading functions on one side through a dual-clutch structure, and realizes the function of driving on one side and loading on the other side at the same time, or loading on both sides at the same time, through a bilaterally symmetrical driving and loading system; through an elastic coupling structure, the axial changes caused by the large temperature difference between the inside and outside of the tank structure are elastically compensated, and at the same time, the assembly tolerance can be compensated, thereby solving the problem of axial torque transmission error.

[0021] 3. The present invention adopts a one-way cold transmission structure to transmit the cold of the low-temperature refrigerator from the cold head of the refrigerator to the thermal interface structure in one direction, while preventing the heat of the heating structure from being reversely transmitted to the cold head of the refrigerator through the thermal interface structure, thereby ensuring that the low-temperature refrigerator can operate continuously and stably for a long time. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings: Figure 1 This is a schematic diagram of the overall structure of the cryogenic subsystem mainly embodied in the present invention; Figure 2 This is a cross-sectional view of the overall structure of the test system of the present invention; Figure 3 This is an axial schematic diagram of the overall structure of the test system mainly embodied in the present invention; Figure 4 This is a schematic diagram of the cooling gas pipeline structure on the outer wall of the hexagonal copper screen heat sink; Figure 5 This is a schematic diagram of the copper plate structure on the hexagonal copper screen heat sink of the present invention; Figure 6 This is a schematic diagram of the thermal interface structure mainly embodied in the present invention; Figure 7 This is a schematic diagram of the overall structure of the driving loading system mainly embodied in the present invention; Figure 8 This is a schematic diagram of the side structure of the driving loading system mainly embodied in the present invention; Figure 9 This is a top view of the driving and loading system mainly embodied in the present invention; Figure 10This is an axial schematic diagram of the overall structure of the driving loading system mainly embodied in the present invention; Figure 11 This is a schematic diagram of the connection structure of the elastic coupling and the rigid coupling mainly embodied in the present invention.

[0023] As shown in the figure: DETAILED DESCRIPTION

[0024] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0025] It should be noted that the Z-axis of the technical solution of the present application represents the height direction, the X-axis represents the axial direction of the tank structure 1 , and the Y-axis represents the radial direction of the tank structure 1 .

[0026] Example 1 like Figures 1 to 11 As shown, a deep space exploration simulation test system provided by the present invention includes a tank structure 1, a cryogenic subsystem 2, a heating structure 3, a thermal interface structure 4, a vacuum pumping subsystem 5, and a drive loading system 6. The tank structure 1 includes a sealable cavity, and the thermal interface structure 4 is installed in the sealable cavity of the tank structure 1. The thermal interface structure 4 is provided with a stage 4.4 for carrying the device to be tested. The vacuum pumping subsystem 5 can evacuate the sealable cavity of the tank structure 1. The cryogenic subsystem 2 can cool the thermal interface structure 4, the heating structure 3 can heat the thermal interface structure 4, and the drive loading system 6 can drive and / or load the device to be tested on the stage 4.4.

[0027] The vacuum pumping subsystem 5 can be a conventional vacuum pumping device that can achieve vacuuming of the closable cavity in the tank structure 1 .

[0028] The cryogenic subsystem 2 includes a cryogenic refrigeration assembly and a gas cooling assembly. The cryogenic refrigeration assembly includes a cryogenic refrigerator 2.1 and a one-way cold transmission structure 2.2. The cold head of the cryogenic refrigerator 2.1 is connected to the thermal interface structure 4 via the one-way cold transmission structure 2.2. The cryogenic refrigerator 2.1 transmits cold energy to the thermal interface structure 4 in a one-way manner via the one-way cold transmission structure 2.2. The gas cooling assembly includes a cooling gas piping structure 2.5, a cooling gas inlet distributor 2.3, and a cooling gas outlet distributor 2.4. The cooling gas piping structure 2.5 is wound around the outer wall of the thermal interface structure 4. Cooling gas enters the cooling gas piping structure 2.5 through the cooling gas inlet distributor 2.3 and flows out through the cooling gas outlet distributor 2.4.

[0029] One-way cold transmission structure 2.2 comprises a stainless steel tube structure embedded with sapphire. Copper plates are installed at both ends of the tube structure. The copper plate at one end of the tube structure is connected to the cold head of cryogenic refrigerator 2.1, while the copper plate at the other end is connected to thermal interface structure 4. Leveraging sapphire's high thermal conductivity at low temperatures and low thermal conductivity at high temperatures, the cold generated by cryogenic refrigerator 2.1 is transferred one-way to thermal interface structure 4. This not only cools thermal interface structure 4 but also prevents heat from high temperatures from being transferred to cryogenic refrigerator 2.1, thus improving its protection.

[0030] The thermal interface structure 4 includes at least two temperature adjustment zones, each of which is provided with at least one set of low-temperature refrigeration components, and each of which is provided with at least one cooling gas pipeline structure 2.5. The thermal interface structure 4 also includes a hexagonal copper screen heat sink 4.3, a copper plate 4.1, and a heat flow copper belt 4.2. The loading platform 4.4 is fixedly arranged inside the hexagonal copper screen heat sink 4.3. The heat flow copper belt 4.2 connects the copper plate 4.1, the hexagonal copper screen heat sink 4.3, and the loading platform 4.4 to form a heat flow path. In a feasible embodiment, the thermal interface structure 4 is fixedly installed in the tank structure 1 via a thermal insulation bracket 4.5. Specifically, the thermal insulation bracket 4.5 is made of a thermal insulation material, such as an epoxy resin material. The thermal insulation bracket 4.5 is fixed to the bottom of the inner wall of the tank structure 1, and the hexagonal copper screen heat sink 4.3 is fixedly placed on the thermal insulation bracket 4.5. The hexagonal copper screen heat sink 4.3 can be fixedly connected to the thermal insulation bracket 4.5 by fasteners such as screws. On the one hand, it realizes the fixed installation of the thermal interface structure 4 in the tank structure 1, and on the other hand, it realizes the thermal isolation of the thermal interface structure 4 from the outer wall of the tank structure 1.

[0031] The heating structure 3 includes a heating strip 3.1, which is positioned within a hexagonal copper screen heat sink 4.3. The heating strip 3.1 is in contact with and connected to the hexagonal copper screen heat sink 4.3 and / or the heat flux copper strip 4.2 and copper plate 4.1. It should be noted that a temperature sensor is also provided on the hexagonal copper screen heat sink 4.3, capable of measuring the temperature of the outer wall of the hexagonal copper screen heat sink 4.3 in real time. This facilitates the heating structure 3 to coordinate with the cryogenic subsystem 2 to regulate the temperature of the thermal interface structure 4.

[0032] The drive loading system 6 includes a servo motor 6.2, a first electromagnetic clutch 6.3, a gear transmission 6.4, a brake 6.5, a second electromagnetic clutch 6.6, and a loading shaft system. The output shaft of the servo motor 6.2 engages or disengages with the gear transmission 6.4 and the second electromagnetic clutch 6.6, respectively, via the first electromagnetic clutch 6.3. The brake 6.5 is in driving connection with the gear transmission 6.4, and the second electromagnetic clutch 6.6 is in driving connection with the loading shaft system. The drive loading system 6 also includes a loading platform 6.1. The loading platform 6.1, the servo motor 6.2, the first electromagnetic clutch 6.3, the gear transmission 6.4, the brake 6.5, and the second electromagnetic clutch 6.6 are all located outside the tank structure 1, with the servo motor 6.2 disposed on the loading platform 6.1. The loading shaft system includes an elastic coupling 6.8, a rigid coupling 6.9 and a loading head 6.10. The loading head 6.10 extends into the thermal interface structure 4. The elastic coupling 6.8 and the rigid coupling 6.9 are arranged between the loading head 6.10 and the output shaft of the second electromagnetic clutch device 6.6.

[0033] A group of driving and loading systems 6 is respectively provided on any two opposite sides of the tank structure 1 .

[0034] According to a deep space exploration simulation test method provided by the present invention, the test method includes: placing a device to be tested on a stage 4.4 and connecting a driving loading system 6 to the device to be tested; starting a vacuum pumping subsystem 5 to evacuate the closable cavity of the tank structure 1 to the test pressure required; vacuuming: starting a test detection system and starting the vacuum pumping subsystem 5 to reduce the pressure in the tank from the test room ambient pressure to the test index required pressure 10 -3 Pa. Turn on the cryogenic subsystem 2 and / or the heating structure 3, and adjust the environment in the enclosed cavity of the tank structure 1 to a target temperature between 38K and 423K through the thermal interface structure 4; turn on the driving and loading system 6 to drive and / or load the device under test.

[0035] It should be noted that the control system 7 of the technical solution of the present application is located outside the tank structure 1 .

[0036] The technical solution of this application proposes a new vacuum extreme temperature zone continuous temperature control drive loading multifunctional environmental simulation test and detection system, which can meet the test scenarios of continuous temperature control in extreme temperature ranges and drive and / or loading functions required by various types of deep space exploration mechanisms. The system realizes the continuous and stable temperature control function in a wide temperature range of 38K to 423K under vacuum; at the same time, the double-sided drive loading system 6 solves the drive and / or loading multifunctional test and detection needs required for deep space exploration. This system has the advantages of a wide temperature range, multiple functions, compact structure, energy saving and environmental protection, and is suitable for simulating extreme temperature environments and operating conditions in space such as the lunar polar regions and Mars.

[0037] The technical solution of this application achieves a vacuum degree better than 1.3×10 -3 Under Pa, it has the ability of stepless temperature regulation in the temperature range of 38K ~ 423K. At the same time, it has the function of any combination of dual-side drive and / or loading working mode. It is a test and detection system with deep cooling, high temperature, vacuum, and dual-side drive and / or loading functions required for deep space exploration.

[0038] The technical solution of this application differs from the previous liquid-cooled heat sink structure based on convection heat transfer used in space environment simulations. By utilizing the high thermal conductivity of sapphire at low temperatures and the low thermal conductivity at high temperatures, an innovative one-way cold transmission structure 2.2 is designed. This structure is combined with the GM cryogenic refrigerator 2.1 and used in conjunction with compressed cooling air to construct a new cryogenic subsystem 2 based on integrated heat transfer by heat conduction and convection. At the same time, two electromagnetic clutch devices and a gear transmission device 6.4 are used to disconnect and connect the servo motor 6.2 and the brake 6.5 to the shaft system, respectively, to complete the switching and combined working modes of the drive and loading functions. The cryogenic subsystem 2 and the heating structure 3 are nested and connected to the inside of the tank structure 1 through a thermal interface structure 4. The vacuum pumping subsystem 5 is connected to the outside of the tank structure 1. The double-sided drive / loading subsystem runs through both the inside and outside of the tank, and the control system 7 is placed on the outside of the tank.

[0039] Example 2 Based on Example 1, Figures 1 to 11 As shown, a temperature control system for a simulation device according to the present invention includes a thermal interface structure 4, a cryogenic subsystem 2, and a heating structure 3. The cryogenic subsystem 2 can cool the thermal interface structure 4, while the heating structure 3 can heat the thermal interface structure 4. The cryogenic subsystem 2 includes a low-temperature refrigeration component and a gas cooling component. The low-temperature refrigeration component transfers cold energy to the thermal interface structure 4 in a one-way manner, while the gas cooling component uses cooling gas to cool the thermal interface structure 4.

[0040] Specifically, the cryogenic refrigeration assembly includes a cryogenic refrigerator 2.1 and a one-way cold transmission structure 2.2. The cold head of the cryogenic refrigerator 2.1 is connected to the thermal interface structure 4 via the one-way cold transmission structure 2.2. The one-way cold transmission structure 2.2 comprises a stainless steel tube structure embedded with sapphires. Copper plates are provided at both ends of the stainless steel tube structure embedded with sapphires. The copper plate at one end of the stainless steel tube structure embedded with sapphires is connected to the cold head of the cryogenic refrigerator 2.1. The copper plate and the cold head of the cryogenic refrigerator 2.1 can be screwed together. The copper plate at the other end of the stainless steel tube structure embedded with sapphires is connected to the thermal interface structure 4. Specifically, the copper plate is screwed to the copper plate 4.1 of the thermal interface structure 4. In a preferred embodiment, the cryogenic refrigerator 2.1 is a GM type cryogenic refrigerator 2.1, whose extreme low temperature can reach ≤30K.

[0041] More specifically, the gas cooling assembly includes a cooling gas piping structure 2.5, a cooling gas inlet distributor 2.3, and a cooling gas outlet distributor 2.4. The cooling gas piping structure 2.5 is wound around the outer wall of the thermal interface structure 4. Cooling gas enters the cooling gas piping structure 2.5 through the cooling gas inlet distributor 2.3 and then flows out through the cooling gas outlet distributor 2.4.

[0042] The gas cooling assembly also includes an inlet gas circuit solenoid valve 2.10, an outlet gas circuit solenoid valve 2.11, a spool 2.8, a first gas temperature sensor 2.7, and a second gas temperature sensor 2.6. The inlet gas circuit solenoid valve 2.10 is connected to the inlet of the cooling gas inlet distributor 2.3 via the spool 2.8. The first gas temperature sensor 2.7 is connected to the inlet of the cooling gas inlet distributor 2.3 via the spool 2.8. The outlet of the cooling gas inlet distributor 2.3 is connected to the inlet of the cooling gas piping structure 2.5. The outlet gas circuit solenoid valve 2.11 is connected to the outlet of the cooling gas outlet distributor 2.4 via the spool 2.8. The second gas temperature sensor 2.6 is connected to the outlet of the cooling gas outlet distributor 2.4 via the spool 2.8. The inlet of the cooling gas inlet distributor 2.3 is connected to the outlet of the cooling gas piping structure 2.5.

[0043] In one feasible embodiment, the cooling gas inlet distributor 2.3 is fixedly mounted to the tank structure 1 via a mounting flange for the cooling gas inlet distributor 2.3. The lower end of the pipe section of the mounting flange of the cooling gas inlet distributor 2.3 is welded to the tank structure 1. The cooling gas inlet distributor 2.3 is threadedly connected to the cross-connection 2.8. The outlet of the cooling gas inlet distributor 2.3 is located inside the tank structure 1 and welded to the cooling gas piping structure 2.5. The outer wall of the cooling gas piping structure 2.5 is bent and welded to the outer wall of the thermal interface structure 4. The cooling gas outlet distributor 2.4 is installed in the same manner as the cooling gas inlet distributor.

[0044] More specifically, the thermal interface structure 4 includes a stage 4.4, a hexagonal copper screen heat sink 4.3, a copper plate 4.1, and a heat flow copper belt 4.2. The stage 4.4 is fixedly mounted inside the hexagonal copper screen heat sink 4.3. The heat flow copper belt 4.2 connects the copper plate 4.1, the hexagonal copper screen heat sink 4.3, and the stage 4.4 to form a heat flow path. A copper plate 4.1 is fixedly mounted on the upper and lower sides of the hexagonal copper screen heat sink 4.3, and the stage 4.4 is fixedly mounted on the copper plate 4.1 located on the lower side. Several evenly distributed heat flow copper belts 4.2 are screwed around the copper plate 4.1. The heat flow copper belts 4.2 connect the copper plate 4.1 to the hexagonal copper screen heat sink and the stage 4.4 to form a heat flow path.

[0045] Furthermore, the thermal interface structure 4 includes at least two temperature adjustment zones, each of which is provided with at least one set of low-temperature refrigeration components, and each of which is provided with at least one cooling gas pipeline structure 2.5. In a feasible embodiment, the upper and lower halves of the hexagonal copper screen heat sink 4.3 respectively constitute two temperature adjustment zones, and the cooling gas inlet distributor 2.3 and the cooling gas outlet distributor 2.4 are both connected to two cooling gas pipeline structures 2.5. The outer wall of one cooling gas pipeline structure 2.5 is bent and welded to the outer side of the upper wall of the hexagonal copper screen heat sink 4.3, and the outer wall of the other cooling gas pipeline structure 2.5 is bent and welded to the outer side of the lower wall of the hexagonal copper screen heat sink 4.3. A low-temperature refrigeration component is fixedly installed on the upper and lower sides of the hexagonal copper screen heat sink 4.3, and the copper plates of the two low-temperature refrigeration components are screwed to the corresponding copper plates 4.1.

[0046] By placing the GM cryogenic refrigerators 2.1 and the zoned heating structure 3 on the upper and lower parts of the tank, the upper and lower parts of the thermal interface structure 4 can be independently and accurately temperature-controlled, ensuring a temperature uniformity of ≤3K and a temperature control accuracy of ±0.1K.

[0047] More specifically, the heating structure 3 includes a heating strip 3.1, which is disposed within a hexagonal copper screen heat sink 4.3 and is in contact with and connected to a heat flux copper strip 4.2, a copper plate 4.1, and / or the hexagonal copper screen heat sink 4.3. A temperature sensor is provided on the hexagonal copper screen heat sink 4.3 to collect temperature.

[0048] In a preferred embodiment, cooling in the temperature range of 300K to 423K is performed by a gas cooling component, cooling in the temperature range of 38K to 300K is performed by a low-temperature refrigeration component, and the heating structure 3 is used for heating in the adjustable temperature range.

[0049] This technical solution leverages sapphire's high thermal conductivity at low temperatures and low thermal conductivity at high temperatures to innovatively design a one-way cooling transmission structure 2.2. This structure, combined with a GM cryogenic refrigerator 2.1 and compressed cooling air, creates a new cryogenic subsystem 2 based on integrated heat exchange through conduction and convection. Cryogenic subsystem 2 and heating structure 3 are nested and connected to the inside of tank structure 1 via a thermal interface structure 4, enabling temperature regulation within tank structure 1.

[0050] According to the present invention, a temperature adjustment method for a simulation device is provided, the temperature adjustment method comprising: Cooling method within the temperature range of 300K to 423K: cooling gas enters the cooling gas pipeline structure 2.5 through the cooling gas inlet distributor 2.3 and then flows out through the cooling gas outlet distributor 2.4; Cooling method within the temperature range of 38K to 300K: The cold head of the cryogenic refrigerator 2.1 stably outputs cooling power, maintaining the temperature at the interface between it and the one-way cold transmission structure 2.2 at a stable 30K. The cold energy is transferred to the thermal interface structure 4 through the linearly increasing cooling capacity of the one-way cold transmission structure 2.2 below 300K. During the temperature stabilization process at any temperature between 38K and 423K, the heat provided by the heating structure 3 is balanced with the cooling capacity in different temperature zones.

[0051] Specifically, the continuous cooling process from 300K to 423K is accomplished by the cooling provided by the compressed air in cryogenic subsystem 2. Furthermore, room-temperature compressed air with a back pressure of 4 to 6 bar enters the cooling gas inlet distributor 2.3 through a cross-connect 2.8. This splits the air into two separate cooling gas pipeline structures 2.5, located on the upper and lower sides of the hexagonal copper screen heat sink 4.3. Finally, the two high-temperature compressed air streams, after heat exchange, converge at the cooling gas outlet distributor 2.4 and exit the system through the cross-connect 2.8. Both sets of cross-connect 2.8 are equipped with one active and one backup temperature sensor to collect the cooling gas inlet and outlet temperatures and feed them back to the control system 7. The control system 7 determines whether to open or close the gas solenoid valve based on the temperature difference between the inlet and outlet temperatures. As the cooling process progresses, the gas valve is closed when the temperature difference is less than 1°C. Continuous cooling from 38K to 300K is accomplished by the cooling provided by the GM cryogenic refrigerator 2.1 in the cryogenic subsystem 2. Furthermore, when the GM cryogenic refrigerator 2.1 maintains a stable cold head temperature of 30K, its cooling energy is transferred to the copper plate 4.1 via the linearly increasing cooling energy unidirectional transmission structure 2.2 below 300K. This cooling energy is then transferred to the hexagonal copper screen heat sink 4.3 and / or the stage 4.4 via the heat flux copper strip 4.2. The cooling energy is then transferred to the device under test via the hexagonal copper screen heat sink 4.3 and the stage 4.4 via radiation and conduction, respectively. Temperature stabilization between 38K and 423K is achieved by balancing the heat provided by the heating structure 3 with the cooling energy from different temperature zones. Furthermore, the control system 7 automatically performs PID control of the heater power output, achieving temperature stability with a control accuracy of ±0.1°C. The heating process from 38K to 423K is similar to the temperature stabilization process, achieved through the system's automatic PID control of the heater power output.

[0052] It should be noted that the control system 7 of the technical solution of the present application is located outside the tank structure 1 .

[0053] The technical solution of the present application realizes continuous temperature control in the range of 300K to 423K by combining air cooling with electric heating, and realizes continuous temperature control in the range of 38K to 300K by combining the GM cryogenic refrigerator 2.1 with electric heating. Compared with the existing space environment simulation equipment, the temperature range can be expanded to 38K to 423K, which can complete the extreme temperature environment required for deep space exploration including the lunar polar regions and Mars. At the same time, the deep cooling subsystem 2 based on integrated heat exchange of heat conduction and convection has a compact structure and does not require the use of liquid nitrogen or liquid helium, which is energy-saving and environmentally friendly.

[0054] Example 3 Based on Example 1 or Example 2, Figures 1 to 11 As shown, the technical solution of the present application also provides a drive loading system 6 for a simulation device, comprising a servo motor 6.2, a first electromagnetic clutch device 6.3, a gear transmission device 6.4, a brake 6.5, a second electromagnetic clutch device 6.6, an angular torque sensor 6.7, an elastic coupling 6.8, a rigid coupling 6.9, and a loading head 6.10. The output shaft of the servo motor 6.2 engages or disengages with the gear transmission device 6.4 and the second electromagnetic clutch device 6.6 respectively through the first electromagnetic clutch device 6.3. The brake 6.5 is in transmission connection with the gear transmission device 6.4. The loading head 6.10 extends into the tank structure 1 and is connected to the device under test. The elastic coupling 6.8 and the rigid coupling 6.9 are both disposed between the output shafts of the loading head 6.10 and the second electromagnetic clutch device 6.6. The angular torque sensor 6.7 is disposed on the elastic coupling 6.8.

[0055] The technical solution of the present application utilizes two electromagnetic clutch devices and a gear transmission device 6.4 to disconnect and connect the servo motor 6.2 and the brake 6.5 with the shaft system respectively to complete the switching and combined working modes of the driving and loading functions.

[0056] Specifically, it also includes a loading platform 6.1, which serves as the support base for driving the loading system 6. Below the loading platform 6.1 is a loading platform support mechanism 6.1.2. The upper surface of the loading platform 6.1 is maintained at the same level as the upper surface of the test platform 4.4 within the tank structure 1, where the device under test is placed. It should be noted that the loading platform support mechanism 6.1.2 is a mechanical support that specifically performs a leveling function.

[0057] The loading platform 6.1 also includes a fixture structure, wherein the upper surface of the loading platform 6.1 is provided with a positioning slot, the length direction of the positioning slot being in the same direction as the axial direction of the drive loading system 6, and the fixture structure being screwed into the positioning slot. In one feasible embodiment, the fixture structure includes a servo motor fixture 6.2.2, an electromagnetic clutch device fixture 6.6.3, a brake fixture 6.5.1, and an elastic coupling fixture 6.8.1. The servo motor 6.2 is fixedly connected to the servo motor fixture 6.2.2, the second electromagnetic clutch device 6.6 is fixedly mounted on the electromagnetic clutch device fixture 6.6.3, the brake 6.5 is fixedly mounted on the brake fixture 6.5.1, and the elastic coupling 6.8 is fixedly mounted on the elastic coupling fixture 6.8.1.

[0058] More specifically, the gear transmission device 6.4 includes a large gear and a small gear, the large gear is meshed with the small gear, the output shaft of the first electromagnetic clutch device 6.3 is coaxially connected to the large gear, and the output shaft of the brake 6.5 is coaxially connected to the small gear.

[0059] In a feasible embodiment, the upper surface of the loading platform body 6.1 and the upper surface of the loading platform 4.4 in the tank structure 1 are leveled and maintained at the same horizontal reference by the loading platform support mechanism 6.1.2, and the servo motor fixture 6.2.2 is screwed and installed in the positioning groove on the upper surface of the loading platform body 6.1 to ensure that the servo motor 6.2 axis is coaxial with the tank structure 1 in the y direction, and the output shaft of the servo motor 6.2 passes through the servo motor fixture 6.2.2 and is nested with the mounting hole of the input end driving wheel of the first electromagnetic clutch device 6.3; the output shaft of the first electromagnetic clutch device 6.3 is connected to the large gear hole of the gear transmission device 6.4 and the second electromagnetic clutch device fixture 6.6.3. The input end of clutch device 6.6 is nested with the driving wheel mounting hole. By controlling the on / off power of the coil in first electromagnetic clutch device 6.3, the output shaft of first electromagnetic clutch device 6.3 switches between engaged and disengaged states, thereby controlling the power output of servo motor 6.2 to brake 6.5 and second electromagnetic clutch device 6.6. The output shaft of second electromagnetic clutch device 6.6 passes through elastic coupling fixture 6.8.1 and connects to elastic coupling 6.8. The on / off power of the coil in second electromagnetic clutch device 6.6 controls the output shaft of second electromagnetic clutch device 6.6 between engaged and disengaged states, thereby controlling the connection or disengagement between the device under test and the drive loading system 6 within tank structure 1. Brake 6.5 is connected to the output shaft of first electromagnetic clutch device 6.3 via gear transmission 6.4, and the braking torque it applies is transmitted through the output shaft of first electromagnetic clutch device 6.3.

[0060] It should be further explained that the rigid coupling 6.9 includes a coupling mounting shell and a coupling shaft. The coupling shaft can rotate relative to the coupling mounting shell. A coupling mounting flange 6.9.1 is integrally formed on the coupling mounting shell. A mounting site is reserved on the tank structure 1. The mounting site on the tank structure 1 allows the coupling mounting flange 6.9.1 of the coupling mounting shell to be fixedly connected thereto by fasteners. At the same time, the mounting site on the tank structure 1 allows the coupling shaft to rotate and extend into the interior of the tank structure 1. It should be further explained that the coupling shaft can be directly and coaxially fixedly connected to the loading head 6.10. The coupling shaft can also be coaxially fixedly connected to the loading head 6.10 through a connecting piece in the prior art such as a coupling. The elastic coupling 6.8 and the rigid coupling 6.9 of the technical solution of the present application cooperate to elastically compensate for the axial changes caused by the large temperature difference between the inside and outside of the tank structure 1. At the same time, it can also compensate for the assembly tolerance, thereby solving the problem of axial torque transmission error.

[0061] After the driving and loading system 6 is aligned with the shaft system of the device under test, the shaft sleeve structure of the loading head 6.10 is used to cooperate with the mounting bolts for screw connection. The driving mode and loading mode are both transmitted to the device under test inside the tank structure 1 through the shaft system.

[0062] Furthermore, a thermal interface structure 4 is provided in the tank structure 1, and a loading platform 4.4 is provided in the thermal interface structure 4. The loading head 6.10 extends into the loading platform 4.4 in the thermal interface structure 4.

[0063] Furthermore, the driving mode is: the first electromagnetic clutch device 6.3 is turned on, the second electromagnetic clutch device 6.6 is turned on, and the servo motor 6.2 is connected to the loading head 6.10. The loading mode is: the first electromagnetic clutch device 6.3 is disconnected, the second electromagnetic clutch device 6.6 is turned on, and the brake 6.5 is connected to the loading head 6.10 through the gear transmission device 6.4.

[0064] In a preferred embodiment, a set of drive and loading systems 6 are provided on either opposite side of the tank structure 1. The drive and loading systems 6 can be configured to drive one side while loading the other, drive both sides, or load both sides. In a feasible embodiment, the loading platforms 6.1 of the two drive and loading systems 6 are installed on the left and right sides of the tank structure 1, i.e., on both sides in the Y direction.

[0065] The single-sided drive mode is achieved by connecting the servo motor 6.2 to the clutch and shafting. Furthermore, the first and second electromagnetic clutches 6.3 and 6.6 are engaged to ensure the connection between the servo motor 6.2 and the shafting. Angle data is collected and input into the control system 7, which then adjusts the output speed of the servo motor 6.2 to form a PID closed-loop control. The single-sided loading mode is achieved by connecting the brake 6.5 to the clutch and shafting via the gear transmission 6.4. Furthermore, the first electromagnetic clutch 6.3 is disconnected and the second electromagnetic clutch 6.6 is engaged to ensure the connection between the brake 6.5 and the shafting via the gear transmission 6.4. Torque data is collected and input into the control system 7, which then adjusts the output torque of the brake 6.5 to form a PID closed-loop control. Switching between the single-sided drive and loading functions is achieved by connecting and disconnecting the first and second electromagnetic clutches 6.3 and 6.6. By combining the single-sided drive and loading functions, single-sided drive and loading modes and dual-sided loading modes are also possible.

[0066] According to the present invention, a driving and loading method for a simulation device is provided, which includes: connecting a loading head 6.10 to a device under test, and controlling the disconnection or connection of a first electromagnetic clutch device 6.3 and a second electromagnetic clutch device 6.6 to drive or load.

[0067] The technical solution of this application uses a dual-clutch structure to achieve switching between driving and loading functions on one side. The technical solution of this application uses a bilaterally symmetrical drive and loading system 6 to achieve the function of driving on one side and loading on the other side at the same time, or loading on both sides at the same time. The technical solution of this application uses the elastic coupling 6.8 structure to elastically compensate for axial changes caused by large temperature differences between the inside and outside of the tank structure 1, solving the problem of axial torque transmission errors.

[0068] It should be noted that the control system 7 of the technical solution of the present application is located outside the tank structure 1 .

[0069] In the description of this application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.

[0070] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A deep space exploration simulation test system, characterized in that: The device comprises a tank structure, a cryogenic subsystem, a heating structure, a thermal interface structure, a vacuum pumping subsystem, and a drive loading system. The tank structure comprises a closable cavity, the thermal interface structure is installed in the closable cavity of the tank structure, a stage for carrying the device to be tested is provided in the thermal interface structure, and the vacuum pumping subsystem can evacuate the closable cavity of the tank structure; The cryogenic subsystem can cool down the thermal interface structure, the heating structure can heat up the thermal interface structure, and the driving and loading system can drive and / or load the device to be tested on the stage.

2. The deep space exploration simulation test system according to claim 1, characterized in that: The cryogenic subsystem includes a cryogenic refrigeration component and a gas cooling component; The low-temperature refrigeration assembly includes a low-temperature refrigerator and a one-way cold transmission structure, wherein the cold head of the low-temperature refrigerator is connected to the thermal interface structure through the one-way cold transmission structure, and the low-temperature refrigerator transfers cold energy to the thermal interface structure in a one-way manner through the one-way cold transmission structure; The gas cooling assembly includes a cooling gas pipeline structure, a cooling gas inlet distributor, and a cooling gas outlet distributor. The cooling gas pipeline structure is wound around the outer wall of the thermal interface structure; the cooling gas enters the cooling gas pipeline structure through the cooling gas inlet distributor and then flows out through the cooling gas outlet distributor.

3. The deep space exploration simulation test system according to claim 2, characterized in that: The one-way cold transmission structure includes a stainless steel tube structure embedded with sapphire, and copper plates are provided at both ends of the stainless steel tube structure embedded with sapphire. The copper plate at one end of the stainless steel tube structure embedded with sapphire is connected to the cold head of the low-temperature refrigerator, and the copper plate at the other end of the stainless steel tube structure embedded with sapphire is connected to the thermal interface structure.

4. The deep space exploration simulation test system according to claim 2, characterized in that: The thermal interface structure includes at least two temperature adjustment zones, each of which is provided with at least one set of low-temperature refrigeration components, and each of which is provided with at least one cooling gas pipeline structure.

5. The deep space exploration simulation test system according to claim 1, characterized in that: The thermal interface structure further includes a hexagonal copper screen heat sink, a copper plate and a heat flow copper belt. The stage is fixedly arranged inside the hexagonal copper screen heat sink. The heat flow copper belt connects the copper plate, the hexagonal copper screen heat sink and the stage to form a heat flow path.

6. The deep space exploration simulation test system according to claim 5, characterized in that: The heating structure includes a heating bar, which is arranged in the hexagonal copper screen heat sink and is in contact with and connected to the hexagonal copper screen heat sink and / or the heat flow copper belt and copper plate.

7. The deep space exploration simulation test system according to claim 1, characterized in that: The driving loading system includes a servo motor, a first electromagnetic clutch device, a gear transmission device, a brake, a second electromagnetic clutch device and a loading shaft system; The output shaft of the servo motor is engaged or disengaged with the gear transmission device and the second electromagnetic clutch device respectively through the first electromagnetic clutch device, the brake is in transmission connection with the gear transmission device, and the second electromagnetic clutch device is in transmission connection with the loading shaft system.

8. The deep space exploration simulation test system according to claim 7, characterized in that: The driving loading system further comprises a loading platform, wherein the loading platform, the servo motor, the first electromagnetic clutch device, the gear transmission device, the brake and the second electromagnetic clutch device are all located outside the tank structure, and the servo motor is arranged on the loading platform; The loading shaft system includes an elastic coupling, a rigid coupling and a loading head. The loading head extends into the thermal interface structure. The elastic coupling and the rigid coupling are arranged between the loading head and the output shaft of the second electromagnetic clutch device.

9. The deep space exploration simulation test system according to claim 1, characterized in that: The driving and loading systems are provided with a group on either opposite sides of the tank structure.

10. A deep space exploration simulation test method, characterized in that: The deep space exploration simulation test system according to any one of claims 1 to 9 is used, and the test method comprises: placing a device under test on a stage, and connecting a driving loading system to the device under test; Turn on the vacuum pumping subsystem to evacuate the sealable cavity of the tank structure to the required test pressure; Turning on the cryogenic subsystem and / or the heating structure to adjust the environment in the enclosed cavity of the tank structure to a target temperature between 38K and 423K through the thermal interface structure; Start the driver loading system to drive and / or load the device under test.

Images