Deep space exploration simulation test system and method

Abstract

The application provides a deep space exploration simulation test system and method, which comprises a thermal interface structure, a deep cooling subsystem and a heating structure. The deep cooling subsystem can 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 unidirectionally transmits cold energy to the thermal interface structure, and the gas cooling assembly cools the thermal interface structure by using cooling gas. Through the combination of gas cooling and electric heating, continuous temperature adjustment in the range of 300K to 423K is realized. Through the combination of a G-M low-temperature refrigerator and electric heating, continuous temperature adjustment in the range of 38K to 300K is realized. Compared with the existing space environment simulation equipment, the temperature range is extended to 38K to 423K, and the extreme temperature environment required for deep space exploration including the lunar polar region and Mars can be realized. At the same time, based on the integrated heat exchange deep cooling subsystem of heat conduction and convection, the structure is compact, and liquid nitrogen and liquid helium are not needed, which is energy-saving and environmentally friendly.

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, which is similar to CN101576359A, and particularly relates to a liquid nitrogen / gas helium dual medium compatible heat sink system, which realizes 68K to 373K wide temperature range adjustment. The system needs to be provided with a liquid nitrogen storage tank for liquid supply, has a relatively complex form, and has a relatively narrow temperature range. In addition, the system has a single function, and can only provide a vacuum temperature environment, and cannot realize driving / loading test function.

[0007] Since the existing test detection system cannot meet the test requirements of deep space exploration products, it is necessary to develop a test detection system with vacuum deep cooling high temperature and driving / loading capacity, so as to provide ground simulation test conditions for deep space probes, and verify the functions, performance and reliability of the products. SUMMARY

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

[0009] According to the deep space exploration simulation test system provided by the present application, the tank body structure includes a closable cavity, the thermal interface structure is installed in the closable cavity of the tank body structure, the thermal interface structure is provided with a load table for carrying the to-be-tested equipment, and the vacuum air extraction subsystem can extract the closable cavity of the tank body structure to vacuum.

[0010] Preferably, the deep cooling subsystem includes a low-temperature refrigeration assembly and a gas cooling assembly; the low-temperature refrigeration assembly includes a low-temperature refrigerator and a cold quantity one-way transmission structure, the cold head of the low-temperature refrigerator is connected with the thermal interface structure through the cold quantity one-way transmission structure, and the low-temperature refrigerator unidirectionally transmits cold quantity to the thermal interface structure through the cold quantity one-way transmission structure; the gas cooling assembly includes a cooling gas pipeline structure, a cooling gas inlet distributor and a cooling gas outlet distributor, and the cooling gas pipeline structure is wound on the outer wall of the thermal interface structure; 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 cold quantity one-way transmission structure includes a stainless steel pipe structure with embedded sapphire, both ends of the stainless steel pipe structure with embedded sapphire are provided with purple copper plates, the purple copper plate at one end of the stainless steel pipe structure with embedded sapphire is connected with the cold head of the low-temperature refrigerator, and the purple copper plate at the other end of the stainless steel pipe structure with embedded sapphire is connected with the thermal interface structure.

[0012] Preferably, the thermal interface structure comprises at least two temperature adjustment zones, each of the temperature adjustment zones is provided with at least one set of low-temperature refrigeration components, and each of the temperature adjustment zones 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 object table 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 object table to form a heat flow passage.

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

[0015] Preferably, the driving and loading system comprises 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 with or separated from the gear transmission device and the second electromagnetic clutch device through the first electromagnetic clutch device, the brake is in driving connection with the gear transmission device, and the second electromagnetic clutch device is in driving connection with the loading shaft system.

[0016] Preferably, the driving and loading system further comprises a loading table body, and the loading table body, 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; the servo motor is arranged on the loading table body; the loading shaft system comprises an elastic coupling, a rigid coupling, and a loading head; 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 system is provided with a set of driving and loading systems on each of the opposite sides of the tank structure.

[0018] According to the deep space exploration simulation test method provided by the present application, the test method comprises the following steps: placing a device to be tested on an object table and connecting a driving and loading system with the device to be tested;

[0019] A vacuum pumping subsystem is started to pump the closable cavity of the tank structure to a test required pressure;

[0020] A deep cooling subsystem and / or a heating structure is started to adjust the environment in the closable cavity of the tank structure to a target temperature through a thermal interface structure, and the target temperature is between 38K and 423K;

[0021] The driving and loading system is started to drive and / or load the device to be tested.

[0022] Compared with the prior art, the application has the following beneficial effects:

[0023] 1、The application utilizes the high-thermal-conductivity characteristics of sapphire at low temperature and the low-thermal-conductivity characteristics of sapphire at high temperature, innovatively designs a cold quantity one-way transmission structure, utilizes the structure to combine with a low-temperature refrigerator, simultaneously combines with compressed cooling air to construct a brand-new integrated heat exchange cryogenic subsystem based on thermal conduction and convection, simultaneously utilizes two electromagnetic clutch devices and gear transmission devices to disconnect and connect the servo motor and the brake from and with the shaft system to complete the switching and combination working mode of the driving and loading functions.

[0024] 2、The application realizes the switching of the single-side driving or loading function through the double-clutch structure, realizes the single-side driving and the function of simultaneously loading on the other side or the function of simultaneously loading on both sides through the bilateral symmetrical driving and loading system, realizes the elastic compensation of the axial change caused by the large temperature difference inside and outside the tank structure through the elastic coupling structure, simultaneously can compensate the assembly tolerance, and solves the problem of the axial torque transmission error.

[0025] 3、The application can one-way transmit the cold quantity of the low-temperature refrigerator from the cold head of the refrigerator to the thermal interface structure through the cold quantity one-way transmission structure, simultaneously avoids the heat of the heating structure from being reversely transmitted to the cold head of the refrigerator through the thermal interface structure, and thus guarantees the long-time continuous and stable work of the low-temperature refrigerator. BRIEF DESCRIPTION OF DRAWINGS

[0026] Other characteristics, objects and advantages of the application will become more apparent through reading the following detailed description of the non-restrictive embodiments with reference to the accompanying drawings:

[0027] Figure 1 It is a schematic diagram of the overall structure of the cryogenic subsystem mainly embodied by the application;

[0028] Figure 2 It is a sectional view of the overall structure of the test system mainly embodied by the application;

[0029] Figure 3 It is an axial schematic diagram of the overall structure of the test system mainly embodied by the application;

[0030] Figure 4 It is a schematic diagram of the cooling gas pipeline structure outside the wall of the hexagonal copper screen heat sink mainly embodied by the application;

[0031] Figure 5 It is a schematic diagram of the copper plate structure on the hexagonal copper screen heat sink mainly embodied by the application;

[0032] Figure 6 It is a schematic diagram of the thermal interface structure mainly embodied by the application;

[0033] Figure 7This is a schematic diagram of the overall structure of the driving loading system mainly embodied in the present invention;

[0034] Figure 8 This is a schematic diagram of the side structure of the driving loading system mainly embodied in the present invention;

[0035] Figure 9 This is a top view of the driving and loading system mainly embodied in the present invention;

[0036] Figure 10 This is an axial schematic diagram of the overall structure of the driving loading system mainly embodied in the present invention;

[0037] 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.

[0038] As shown in the figure:

[0039] DETAILED DESCRIPTION

[0040] The present invention is described in detail below with reference to specific embodiments. The following embodiments 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, without departing from the scope of the present invention, a number of variations and improvements may be made by those skilled in the art. These all fall within the scope of protection of the present invention.

[0041] 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 .

[0042] Example 1

[0043] 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.

[0044] 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 .

[0045] The cryogenic subsystem 2 comprises a low-temperature refrigeration assembly and a gas cooling assembly. The low-temperature refrigeration assembly comprises a low-temperature refrigerator 2.1 and a cold-quantity one-way transmission structure 2.2, and a cold head of the low-temperature refrigerator 2.1 is connected with the thermal interface structure 4 through the cold-quantity one-way transmission structure 2.2. The low-temperature refrigerator 2.1 transmits cold quantity to the thermal interface structure 4 through the cold-quantity one-way transmission structure 2.2. The gas cooling assembly comprises a cooling gas pipeline structure 2.5, a cooling gas inlet distributor 2.3 and a cooling gas outlet distributor 2.4, and the cooling gas pipeline structure 2.5 is wound on an outer wall of the thermal interface structure 4. Cooling gas enters the cooling gas pipeline structure 2.5 through the cooling gas inlet distributor 2.3 and flows out through the cooling gas outlet distributor 2.4.

[0046] The cold-quantity one-way transmission structure 2.2 comprises a sapphire-embedded stainless steel pipe structure, and both ends of the sapphire-embedded stainless steel pipe structure are provided with a red copper plate. The red copper plate at one end of the sapphire-embedded stainless steel pipe structure is connected with the cold head of the low-temperature refrigerator 2.1, and the red copper plate at the other end of the sapphire-embedded stainless steel pipe structure is connected with the thermal interface structure 4. By virtue of the high-thermal-conductivity characteristics of the sapphire at low temperature and the low-thermal-conductivity characteristics of the sapphire at high temperature, the cold quantity generated by the low-temperature refrigerator 2.1 is transmitted to the thermal interface structure 4 in one direction, thereby achieving refrigeration of the thermal interface structure 4 and preventing high-temperature heat of the thermal interface structure 4 from being transmitted to the low-temperature refrigerator 2.1, and improving the protection of the low-temperature refrigerator 2.1.

[0047] The thermal interface structure 4 comprises at least two temperature adjustment zones, each of which is provided with at least one set of low-temperature refrigeration assembly, and each of which is provided with at least one cooling gas pipeline structure 2.5. The thermal interface structure 4 further comprises a hexagonal copper screen heat sink 4.3, a copper plate 4.1 and a heat flow copper belt 4.2. A sample table 4.4 is fixedly arranged inside the hexagonal copper screen heat sink 4.3, and the heat flow copper belt 4.2 connects the copper plate 4.1, the hexagonal copper screen heat sink 4.3 and the sample table 4.4 to form a heat flow passage. In an available embodiment, the thermal interface structure 4 is fixedly installed in the tank structure 1 through a heat insulation support 4.5. Specifically, the heat insulation support 4.5 is made of a heat insulation material, such as an epoxy resin material. The heat insulation support 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 arranged on the heat insulation support 4.5. The hexagonal copper screen heat sink 4.3 can be fixedly connected with the heat insulation support 4.5 through screws or other fasteners, thereby achieving fixed installation of the thermal interface structure 4 in the tank structure 1 and thermal isolation of the thermal interface structure 4 from the outer wall of the tank structure 1.

[0048] The heating structure 3 comprises a heating strip 3.1, the heating strip 3.1 is arranged in the hexagonal copper screen heat sink 4.3, and the heating strip 3.1 is in contact with and connected with the hexagonal copper screen heat sink 4.3 and / or the heat flow copper strip 4.2 and the copper plate 4.1. It should be noted that the hexagonal copper screen heat sink 4.3 is also provided with a temperature sensor, which can measure the temperature of the outer wall of the hexagonal copper screen heat sink 4.3 in real time, so as to facilitate the heating structure 3 to adjust the temperature of the thermal interface structure 4 in cooperation with the cryogenic subsystem 2.

[0049] The driving and loading system 6 comprises 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 and a loading shaft system. The output shaft of the servo motor 6.2 is connected with the gear transmission device 6.4 and the second electromagnetic clutch device 6.6 through the first electromagnetic clutch device 6.3, the brake 6.5 is in transmission connection with the gear transmission device 6.4, and the second electromagnetic clutch device 6.6 is in transmission connection with the loading shaft system. The driving and loading system 6 further comprises a loading table body 6.1, and the loading table body 6.1, the servo motor 6.2, the first electromagnetic clutch device 6.3, the gear transmission device 6.4, the brake 6.5 and the second electromagnetic clutch device 6.6 are located outside the tank body structure 1, and the servo motor 6.2 is arranged on the loading table body 6.1. The loading shaft system comprises 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, and 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.

[0050] The driving and loading system 6 is arranged on one side of the tank body structure 1.

[0051] According to the deep space exploration simulation test method provided by the application, the test method comprises the following steps: placing the to-be-tested equipment on the object table 4.4 and connecting the driving and loading system 6 with the to-be-tested equipment; opening the vacuum pumping subsystem 5 to pump the closed cavity of the tank body structure 1 to a test required pressure; pumping: starting the test detection system, opening the vacuum pumping subsystem 5, and reducing the pressure in the tank from the laboratory environment pressure to the test index required pressure 10 -3 Pa. Opening the cryogenic subsystem 2 and / or the heating structure 3, adjusting the environment in the closed cavity of the tank body structure 1 to a target temperature through the thermal interface structure 4, and the target temperature is between 38K and 423K; opening the driving and loading system 6 to drive and / or load the to-be-tested equipment.

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

[0053] The technical scheme of the present application provides a new vacuum extreme temperature zone continuous temperature regulating driving loading multifunctional environment simulation test detection system, which can meet the test scene of extreme temperature zone continuous temperature regulation with driving and / or loading functions required by various types of deep space exploration mechanism products. The system realizes the functions of continuous stable temperature regulation in a wide temperature range of 38K to 423K in vacuum; at the same time, the double-sided driving and loading system 6 solves the driving and / or loading multifunctional test detection requirements required by deep space exploration. The system has the advantages of wide temperature range, multiple functions, compact structure, energy saving and environmental protection, and is suitable for lunar polar region and Mars space extreme temperature environment and use condition simulation.

[0054] The technical scheme of the present application realizes stepless temperature regulation in a temperature range of 38K to 423K under a vacuum degree better than 1.3x10 -3 Pa, and has the function of double-sided driving and / or loading in any combination mode, which is a test detection system with deep cooling, high temperature, vacuum, double-sided driving and / or loading functions required by deep space exploration.

[0055] The technical scheme of the present application is different from the liquid cooling heat sink structure based on convection heat transfer in the past space environment simulation. The low-temperature high-thermal-conductivity and high-temperature low-thermal-conductivity characteristics of sapphire are utilized to innovatively design a cold quantity one-way transmission structure 2.2. The structure is combined with a G-M low-temperature refrigerator 2.1, and is used together with compressed cooling air to construct a new deep cooling subsystem 2 based on heat conduction and convection integrated heat exchange. At the same time, two electromagnetic clutches and gear transmission devices 6.4 are used to disconnect and connect the servo motor 6.2 and the brake 6.5 with the shaft system respectively to complete the switching and combination of the driving and loading functions. The deep cooling subsystem 2 and the heating structure 3 are nested and connected inside the tank structure 1 through the thermal interface structure 4, the vacuum pumping subsystem 5 is connected to the outside of the tank structure 1, the double-sided driving / loading subsystem penetrates the inside and outside of the tank, and the control system 7 is placed outside the tank.

[0056] Embodiment two

[0057] Based on embodiment one, as shown in Figures 1 to 11 Fig. 2, the temperature regulating system for simulating equipment provided by the present application comprises a thermal interface structure 4, a deep cooling subsystem 2 and a heating structure 3. The deep cooling subsystem 2 can cool the thermal interface structure 4, and the heating structure 3 can heat the thermal interface structure 4. The deep cooling subsystem 2 comprises a low-temperature refrigeration assembly and a gas cooling assembly. The low-temperature refrigeration assembly unidirectionally transmits cold quantity to the thermal interface structure 4, and the gas cooling assembly cools the thermal interface structure 4 by using cooling gas.

[0058] Specifically, the low-temperature refrigeration assembly comprises a low-temperature refrigerator 2.1 and a coldness one-way transmission structure 2.2, and the cold head of the low-temperature refrigerator 2.1 is connected with the thermal interface structure 4 through the coldness one-way transmission structure 2.2. The coldness one-way transmission structure 2.2 comprises a stainless steel pipe structure with embedded sapphire, and both ends of the stainless steel pipe structure with embedded sapphire are provided with red copper plates. The red copper plate at one end of the stainless steel pipe structure with embedded sapphire is connected with the cold head of the low-temperature refrigerator 2.1, and the red copper plate and the cold head of the low-temperature refrigerator 2.1 can be screwed. The red copper plate at the other end of the stainless steel pipe structure with embedded sapphire is connected with the thermal interface structure 4, and specifically, the red copper plate and the copper plate 4.1 of the thermal interface structure 4 are screwed.

[0059] More specifically, the gas cooling assembly comprises a cooling gas pipeline structure 2.5, a cooling gas inlet distributor 2.3 and a cooling gas outlet distributor 2.4, and the cooling gas pipeline structure 2.5 is wound on the outer wall of the thermal interface structure 4. Cooling gas enters the cooling gas pipeline structure 2.5 through the cooling gas inlet distributor 2.3 and flows out through the cooling gas outlet distributor 2.4.

[0060] The gas cooling assembly further comprises an inlet gas path electromagnetic valve 2.10, an outlet gas path electromagnetic valve 2.11, a four-way valve 2.8, a first gas temperature sensor 2.7 and a second gas temperature sensor 2.6. The inlet gas path electromagnetic valve 2.10 is communicated with the inlet of the cooling gas inlet distributor 2.3 through the four-way valve 2.8, the first gas temperature sensor 2.7 is communicated with the inlet of the cooling gas inlet distributor 2.3 through the four-way valve 2.8, and the outlet of the cooling gas inlet distributor 2.3 is communicated with the inlet of the cooling gas pipeline structure 2.5. The outlet gas path electromagnetic valve 2.11 is communicated with the outlet of the cooling gas outlet distributor 2.4 through the four-way valve 2.8, the second gas temperature sensor 2.6 is communicated with the outlet of the cooling gas outlet distributor 2.4 through the four-way valve 2.8, and the inlet of the cooling gas inlet distributor 2.3 is communicated with the outlet of the cooling gas pipeline structure 2.5.

[0061] In a feasible embodiment, the cooling gas inlet distributor 2.3 is fixedly installed on the tank structure 1 through a cooling gas inlet distributor 2.3 mounting flange. The lower end pipe section of the cooling gas inlet distributor 2.3 mounting flange is welded to the tank structure 1, the cooling gas inlet distributor 2.3 is screwed with the four-way valve 2.8, the outlet of the cooling gas inlet distributor 2.3 is located inside the tank structure 1, and the outlet of the cooling gas inlet distributor 2.3 is welded with the cooling gas pipeline structure 2.5. The outer wall of the cooling gas pipeline structure 2.5 is bent and welded to the outer side of the wall of the thermal interface structure 4. The cooling gas outlet distributor 2.4 is installed in the same way as the cooling gas inlet distributor 2.3.

[0062] 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.

[0063] 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.

[0064] 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.

[0065] 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.

[0066] 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.

[0067] The technical scheme of the application utilizes the high thermal conductivity characteristics of sapphire at low temperature and the low thermal conductivity characteristics of sapphire at high temperature, innovatively designs the cold quantity one-way transmission structure 2.2, utilizes the structure in combination with the G-M low-temperature refrigerator 2.1, simultaneously uses compressed cooling air to construct a brand-new deep cooling subsystem 2 based on the integrated heat exchange of conduction and convection. The deep cooling subsystem 2 and the heating structure 3 are connected to the inside of the tank structure 1 through the thermal interface structure 4, so as to realize the temperature regulation of the tank structure 1.

[0068] According to the application, a temperature regulation method for a simulation device is provided, and the temperature regulation method comprises the following steps:

[0069] The cooling method in 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;

[0070] The cooling method in the temperature range of 38K to 300K: the cold head of the low-temperature refrigerator 2.1 stably outputs refrigeration power, keeps the temperature at the interface between the low-temperature refrigerator 2.1 and the cold quantity one-way transmission structure 2.2 at 30K, and transmits the cold quantity to the thermal interface structure 4 through the linearly increasing characteristics of the cold quantity one-way transmission structure 2.2 in the cold conduction capacity below 300K;

[0071] The heat provided by the heating structure 3 and the cold quantity in different temperature zones are balanced in any temperature stabilization process in the range of 38K to 423K.

[0072] Specifically, the continuous cooling process in the range of 300K to 423K is completed by the cold energy provided by the compressed air in the cryogenic subsystem 2, further, the normal temperature compressed air with back pressure of 4bar to 6bar enters the cooling gas inlet distributor 2.3 through the four-way 2.8, and then is split into two paths through the cooling gas inlet distributor 2.3, and enters the cooling gas pipeline structure 2.5 placed on the upper part and the lower part of the hexagonal copper screen heat sink 4.3, respectively, finally, the two paths of high temperature compressed air after heat exchange are converged at the cooling gas outlet distributor 2.4, and are discharged from the system through the four-way 2.8. Each of the two sets of four-ways 2.8 is provided with a primary and a backup temperature sensor, which is used to collect the inlet temperature and outlet temperature of the cooling gas and feed back to the control system 7, and the control system 7 judges whether to turn on and turn off the gas path electromagnetic valve according to the temperature difference between the inlet temperature and the outlet temperature, and turns off the gas path valve when the temperature difference is less than 1℃. The continuous cooling in the range of 38K to 300K is completed by the cold energy provided by the G-M cryogenic refrigerator 2.1 in the cryogenic subsystem 2, further, the cold head temperature of the G-M cryogenic refrigerator 2.1 is stabilized at 30K when the output is stable, and the cold energy is transmitted to the copper plate 4.1 through the cold energy one-way transmission structure 2.2, which has the characteristic of linearly increasing below 300K, and then is transmitted to the hexagonal copper screen heat sink 4.3 and / or the object table 4.4 through the heat flow copper belt 4.2, and the cold energy is transmitted to the equipment to be tested through the hexagonal copper screen heat sink 4.3 and the object table 4.4 by radiation and heat conduction, respectively. In the temperature stabilization process at any temperature in the range of 38K to 423K, the heat provided by the heating structure 3 is balanced with the cold energy in different temperature zones, further, the control system 7 automatically adjusts the power output of the heater by PID, that is, the temperature is stabilized, and the temperature control accuracy can reach ±0.1℃. In the temperature rising process in the range of 38K to 423K, the same as in the temperature stabilization process, the power output of the heater is adjusted by PID to achieve the temperature rising process.

[0073] It should be noted that the control system 7 of the technical scheme of the present application is located outside the tank structure 1.

[0074] The technical scheme of the present application realizes continuous temperature adjustment in the range of 300K to 423K by combining air cooling and electric heating, and realizes continuous temperature adjustment in the range of 38K to 300K by combining the G-M cryogenic refrigerator 2.1 and electric heating; compared with the existing space environment simulation equipment, the temperature range is expanded to 38K to 423K, and the extreme temperature environment required for deep space exploration including the lunar polar region and Mars can be completed; at the same time, the compact structure of the cryogenic subsystem 2 based on heat conduction and convection integrated heat exchange does not need to use liquid nitrogen and liquid helium, which is energy-saving and environmentally friendly.

[0075] Example Three

[0076] Based on example one or example two, as Figures 1 to 11As shown, the technical scheme of the present application also provides a driving and loading system 6 for a simulation device, which comprises 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 angle 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 is connected with the gear transmission device 6.4 and the second electromagnetic clutch device 6.6 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 with the device to be tested. 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, and the angle torque sensor 6.7 is arranged on the elastic coupling 6.8.

[0077] The technical scheme of the present application utilizes two electromagnetic clutch devices and the gear transmission device 6.4 to disconnect and connect the servo motor 6.2 and the brake 6.5 with the shafting respectively, so as to complete the switching and combination of the driving and loading functions.

[0078] Specifically, it also comprises a loading table body 6.1, which is the support base of the driving and loading system 6. The loading table body 6.1 is provided below with a loading table foot mechanism 6.1.2, and the upper surface of the loading table body 6.1 is kept at the same horizontal reference as the upper surface of the object table 4.4 on which the device to be tested is placed in the tank structure 1. It should be noted that the loading table foot mechanism 6.1.2 is a mechanical support for specific leveling function.

[0079] It also comprises a tool structure, which is screw-connected and installed in a positioning clamping groove arranged on the upper surface of the loading table body 6.1. The length direction of the positioning clamping groove is the same as the axial direction of the driving and loading system 6. In a feasible implementation manner, the tool structure comprises a servo motor tool 6.2.2, an electromagnetic clutch device tool 6.6.3, a brake tool 6.5.1, and an elastic coupling tool 6.8.1. The servo motor 6.2 is fixedly connected with the servo motor tool 6.2.2, the second electromagnetic clutch device 6.6 is fixedly installed on the electromagnetic clutch device tool 6.6.3, the brake 6.5 is fixedly installed on the brake tool 6.5.1, and the elastic coupling 6.8 is fixedly installed on the elastic coupling tool 6.8.1.

[0080] More specifically, the gear transmission device 6.4 comprises a large gear and a small gear, the large gear is engaged with the small gear, the output shaft of the first electromagnetic clutch device 6.3 is coaxially connected with the large gear, and the output shaft of the brake 6.5 is coaxially connected with the small gear.

[0081] In a feasible implementation, the upper surface of the loading table body 6.1 and the upper surface of the loading table 4.4 in the tank structure 1 are leveled and kept at the same horizontal reference by the loading table foot mechanism 6.1.2. The servo motor tool 6.2.2 is screwed into the positioning clamping groove on the upper surface of the loading table body 6.1, which ensures that the shaft of the servo motor 6.2 is coaxial with the y direction of the tank structure 1. The output shaft of the servo motor 6.2 is nested and connected with the mounting hole of the input end driving wheel of the first electromagnetic clutch 6.3 through the servo motor tool 6.2.2. The output shaft of the first electromagnetic clutch 6.3 is nested and connected with the large gear hole of the gear transmission device 6.4 and the input end driving wheel mounting hole of the second electromagnetic clutch 6.6 connected to the electromagnetic clutch tool 6.6.3. By controlling the on-off electricity of the coil in the first electromagnetic clutch 6.3, the output shaft of the first electromagnetic clutch 6.3 is switched between engagement and disengagement, thereby controlling the power output of the servo motor 6.2 to the brake 6.5 and the second electromagnetic clutch 6.6. The output shaft of the second electromagnetic clutch 6.6 is connected with the elastic coupling 6.8 through the elastic coupling tool 6.8.1. The on-off electricity of the coil in the second electromagnetic clutch 6.6 controls the output shaft of the second electromagnetic clutch 6.6 to switch between engagement and disengagement, thereby controlling the connection or disconnection between the device to be tested in the tank structure 1 and the driving loading system 6. The brake 6.5 is connected with the output shaft of the first electromagnetic clutch 6.3 through the gear transmission device 6.4, and the braking torque applied by the brake 6.5 is transmitted through the output shaft of the first electromagnetic clutch 6.3.

[0082] It should be further explained that the rigid coupling 6.9 includes a coupling mounting shell and a coupling rotating shaft, the coupling rotating shaft can rotate relative to the coupling mounting shell, and the coupling mounting flange 6.9.1 is integrally formed on the coupling mounting shell. The tank structure 1 has a reserved mounting site, and the coupling mounting flange 6.9.1 of the coupling mounting shell is fixedly connected to the mounting site of the tank structure 1 through fasteners, and at the same time, the coupling rotating shaft can rotate and extend into the interior of the tank structure 1. It should be further explained that the coupling rotating shaft can be directly coaxially fixedly connected with the loading head 6.10, or the coupling rotating shaft can be coaxially fixedly connected with the loading head 6.10 through a connecting member such as a coupling in the prior art. The elastic coupling 6.8 and the rigid coupling 6.9 of the technical scheme of the present application cooperate to not only elastically compensate the axial change caused by the large temperature difference between the interior and the exterior of the tank structure 1, but also compensate the assembly tolerance, thereby solving the problem of axial torque transmission error.

[0083] After the driving loading system 6 and the shafting of the device to be tested are aligned, the shaft sleeve structure of the loading head 6.10 is used to screw and install the bolts, and the driving mode and the loading mode are transmitted to the device to be tested in the interior of the tank structure 1 through the shafting.

[0084] Further, the tank structure 1 is provided with a thermal interface structure 4, and the loading platform 4.4 is arranged in the thermal interface structure 4. The loading head 6.10 extends into the loading platform 4.4 in the thermal interface structure 4.

[0085] Further, the driving mode is: the first electromagnetic clutch 6.3 is turned on, the second electromagnetic clutch 6.6 is turned on, and the servo motor 6.2 is in transmission connection with the loading head 6.10. The loading mode is: the first electromagnetic clutch 6.3 is turned off, the second electromagnetic clutch 6.6 is turned on, and the brake 6.5 is in transmission connection with the loading head 6.10 through the gear transmission device 6.4.

[0086] In a preferred embodiment, the driving and loading system 6 is arranged on any opposite side of the tank structure 1. The driving and loading system 6 includes unilateral driving and loading, bilateral driving, or bilateral loading. In a feasible embodiment, the loading platforms 6.1 of the two driving and loading systems 6 are respectively arranged on the left and right sides of the tank structure 1, that is, on the Y-direction sides.

[0087] The unilateral driving mode is completed by connecting the clutch and the shaft system through the servo motor 6.2. Further, the first electromagnetic clutch 6.3 is turned on, the second electromagnetic clutch 6.6 is turned on, the servo motor 6.2 is ensured to be connected with the shaft system, the angle data is collected and input into the control system 7, and then the output rotating speed of the servo motor 6.2 is adjusted to form the PID closed-loop control. The unilateral loading mode is completed by connecting the clutch and the shaft system through the brake 6.5 through the gear transmission device 6.4. Further, the first electromagnetic clutch 6.3 is turned off, the second electromagnetic clutch 6.6 is turned on, the brake 6.5 is ensured to be connected with the shaft system through the gear transmission device 6.4, the torque data is collected and input into the control system 7, and then the output torque of the brake 6.5 is adjusted to form the PID closed-loop control. The unilateral driving and loading function switching is realized by turning on and off the first electromagnetic clutch 6.3 and the second electromagnetic clutch 6.6. Through the cooperation of the unilateral driving and loading functions, the unilateral driving and bilateral loading mode and the bilateral loading mode can also be realized.

[0088] According to the driving and loading method for the simulation device, the loading head 6.10 is connected with the device to be tested, and the turning off or turning on of the first electromagnetic clutch 6.3 and the second electromagnetic clutch 6.6 is controlled to drive or load.

[0089] The technical scheme of the present application realizes the unilateral driving or loading function switching through the double clutch structure. The technical scheme of the present application realizes the unilateral driving and the function of simultaneously loading on the other side, or the function of simultaneously loading on both sides through the bilateral symmetrical driving and loading system 6. The technical scheme of the present application realizes the elastic compensation of the axial change caused by the large temperature difference between the inside and outside of the tank structure 1 through the elastic coupling structure 6.8, and solves the problem of the axial torque transmission error.

[0090] It should be noted that the control system 7 of the technical solution of the present application is located outside the tank structure 1 .

[0091] 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.

[0092] 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 driving and 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 a device under test is arranged in the thermal interface structure, and the vacuum pumping subsystem can pump the closable cavity of the tank structure to vacuum; The cryogenic subsystem can cool the thermal interface structure, the heating structure can heat the thermal interface structure, and the driving and loading system can drive and / or load the device under test on the stage; The cryogenic subsystem comprises a low-temperature refrigeration assembly and a gas cooling assembly; The low-temperature refrigeration assembly comprises a low-temperature refrigerator and a cold energy one-way transmission structure, the cold head of the low-temperature refrigerator is connected with the thermal interface structure through the cold energy one-way transmission structure, and the low-temperature refrigerator unidirectionally transmits cold energy to the thermal interface structure through the cold energy one-way transmission structure; The gas cooling assembly comprises a cooling gas pipeline structure, a cooling gas inlet distributor and a cooling gas outlet distributor, the cooling gas pipeline structure is wound on the outer wall of the thermal interface structure, cooling gas enters the cooling gas pipeline structure through the cooling gas inlet distributor and then flows out through the cooling gas outlet distributor; The cold energy one-way transmission structure comprises a stainless steel pipe structure with embedded sapphire, both ends of the stainless steel pipe structure with embedded sapphire are provided with purple copper plates, the purple copper plate at one end of the stainless steel pipe structure with embedded sapphire is connected with the cold head of the low-temperature refrigerator, and the purple copper plate at the other end of the stainless steel pipe structure with embedded sapphire is connected with the thermal interface structure.

2. The deep space exploration analog test system of claim 1, wherein, The thermal interface structure comprises at least two temperature adjustment zones, each of the temperature adjustment zones is provided with at least one set of low-temperature refrigeration assemblies, and each of the temperature adjustment zones is provided with at least one cooling gas pipeline structure.

3. The deep space exploration analog test system of claim 1, wherein, 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 in 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 passage.

4. The deep space exploration analog test system of claim 3, wherein, The heating structure comprises a heating strip, the heating strip is arranged in the hexagonal copper screen heat sink, and the heating strip is in contact with and connected with the hexagonal copper screen heat sink and / or the heat flow copper belt and the copper plate.

5. The deep space exploration analog test system of claim 1, wherein, The driving and loading system comprises 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 with or separated from the gear transmission device and the second electromagnetic clutch device through the first electromagnetic clutch device, the brake is in driving connection with the gear transmission device, and the second electromagnetic clutch device is in driving connection with the loading shaft system.

6. The deep space exploration analog test system of claim 5, wherein, The driving and loading system further comprises a loading table body, the loading table body, the servo motor, the first electromagnetic clutch device, the gear transmission device, the brake and the second electromagnetic clutch device are located outside the tank structure, and the servo motor is arranged on the loading table body. The loading shaft system comprises an elastic coupling, a rigid coupling and a loading head, the loading head extends into the thermal interface structure, and the elastic coupling and the rigid coupling are arranged between the loading head and an output shaft of the second electromagnetic clutch device.

7. The deep space exploration analog test system of claim 1, wherein, The driving and loading system is arranged on any two opposite sides of the tank structure.

8. A method of deep space exploration simulation test, characterized in that, The test method comprises: placing the to-be-tested equipment on the object table, and connecting the driving and loading system with the to-be-tested equipment; The vacuum pumping subsystem is started to pump the closable cavity of the tank structure to a test-required pressure; The cryogenic subsystem and / or the heating structure are started to adjust the environment in the closable cavity of the tank structure to a target temperature through the thermal interface structure, and the target temperature is between 38K and 423K; The driving and loading system is started to drive and / or load the to-be-tested equipment.

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