Simulated space environment test platform for thermophotovoltaic isotope power source prototype

Abstract

The present invention relates to the field of engineering thermophysics, and in particular to a simulated space environment test platform for a thermophotovoltaic isotope power source prototype, which comprises a vacuum system, a water cooling system, an electric power input system, a wafer output system, and a temperature monitoring system; the vacuum system has a cavity, and the cavity is used to install a system to be tested; the vacuum system can evacuate the cavity so that a 0.03m 3 The vacuum environment; the water cooling system is connected to the vacuum system and can ensure a constant low temperature in the cavity; the power input system is set on the side of the system to be tested; the temperature monitoring system is connected to the system to be tested and is used to detect the temperature of the system to be tested. This application can maintain 0.03m 3 Cavity stable 3x10 ‑3 Pa to 10 ‑5 Pa high vacuum environment, which can meet the various performance tests of existing and future isotope thermal photovoltaic isotope power systems and measure various performance changes in real time.

Description

Technical Field

[0001] The invention relates to the field of engineering thermophysics, and in particular to a simulated space environment test platform for a thermophotovoltaic isotope power source prototype. Background Art

[0002] The isotope thermo-photovoltaic power (RTPV) system is a system that converts the heat energy of isotope decay into electrical energy in the form of light energy. The isotope thermo-photovoltaic power (RTPV) system has the advantages of long life, high conversion efficiency, high specific power, stability and reliability, and is suitable for special application scenarios such as deep space, deep sea, and remote land, and plays an irreplaceable role.

[0003] From the perspective of planning, isotope power sources are one of the core elements of future deep space exploration development. According to my country's development plan for deep space exploration, interplanetary spacecraft will reach Uranus or beyond, when solar power generation will not be able to meet the power demand, so the development of radioisotope power generation technology will become an inevitable trend in the development of deep space exploration. In addition, due to the limited access to plutonium 238 raw materials in my country, radioisotope thermoelectric generators (RTG), isotope Stirling generators (ASRG) and isotope thermophotovoltaic converters (RTPV) are the main research and development objects.

[0004] The existing isotope power supply design, thermoelectric conversion technology, and safety protection technology are bound to be unable to meet the needs of planetary crossing missions. Therefore, breakthroughs in high-efficiency, long-life, safe and reliable isotope power generation technology have become an urgent need for the development of deep space exploration. Summary of the invention

[0005] The purpose of this application is to provide a simulated space environment test platform for a thermophotovoltaic isotope power source prototype, which can solve the existing technical problems to a certain extent.

[0006] The present application also provides a simulated space environment test platform for a thermophotovoltaic isotope power source prototype, including a vacuum system, a water cooling system, an electric power input system, a wafer output system, and a temperature monitoring system;

[0007] The vacuum system has a cavity, and the cavity is used to install the system to be tested;

[0008] The vacuum system can evacuate the cavity so that a vacuum of at least 0.03 m 3 Vacuum environment;

[0009] The water cooling system is connected to the vacuum system and can ensure a constant low temperature in the cavity;

[0010] The electric power input system is arranged on the side of the system to be tested;

[0011] The wafer output system and the internal temperature measurement point are connected to the outside of the vacuum environment through a vacuum aviation connector;

[0012] The temperature monitoring system is attached to the system to be tested and is used to detect the temperature of the system to be tested.

[0013] In the above technical solution, further, the vacuum system includes a molecular pump, a mechanical pump and a tank;

[0014] The tank body has the cavity;

[0015] The mechanical pump, the molecular pump and the tank are connected in sequence;

[0016] The mechanical pump and the molecular pump can evacuate the tank.

[0017] In the above technical solution, further, the vacuum system also includes a filtering mechanism, and the filtering mechanism is arranged at the connection between the molecular pump and the tank body.

[0018] In the above technical solution, further, the diameter of the tank body is set between 350-450 mm, the height of the tank body is set between 350-450 mm; and the thickness of the tank body is set between 1-10 mm.

[0019] In the above technical solution, further, the water cooling and heat dissipation system is provided with at least two sets, at least one set of the water cooling and heat dissipation system and the system to be tested constitute a wafer cooling circuit, and at least another set of the water cooling and heat dissipation system and the system to be tested constitute a non-crystalline cooling circuit.

[0020] In the above technical solution, further, the wafer output circuit in the wafer output system detects the wafer output short-circuit current I sc With open circuit voltage V oc , and then connect the load R L ;

[0021] When the load R L The size of can enable the chip to obtain a preset output power point.

[0022] In the above technical solution, further, the temperature monitoring system includes a B-type thermocouple and a T-type thermocouple;

[0023] The B-type thermocouple is used to measure the temperature range of 0 to 1800°C; the T-type thermocouple is used to measure the temperature range of -200 to 350°C.

[0024] Compared with the prior art, the beneficial effects of this application are:

[0025] The application provides a simulated space environment test platform for a thermophotovoltaic isotope power source prototype, including a vacuum system, a water cooling system, an electric power input system, a wafer output system, and a temperature monitoring system;

[0026] The vacuum system has a cavity, and the cavity is used to install the system to be tested;

[0027] The vacuum system can evacuate the cavity so that a vacuum of at least 0.03 m 3 Vacuum environment;

[0028] The water cooling system is connected to the vacuum system and can ensure a constant low temperature in the cavity;

[0029] The electric power input system is arranged on the side of the system to be tested;

[0030] The wafer output system and the internal temperature measurement point are connected to the outside of the vacuum environment through a vacuum aviation connector;

[0031] The temperature monitoring system is attached to the system to be tested and is used to detect the temperature of the system to be tested.

[0032] Specifically, this application can maintain 0.03m 3 The cavity has a stable high vacuum environment of 3x10-3Pa to 10-5Pa, and can maintain a low temperature environment of -30℃ for 250W-500W constant power heating, and ensure that the input voltage is displayed at 0~250V and the input current is displayed at 0~10A. It can meet the various performance tests of existing and future isotope thermophotovoltaic isotope power supply systems and measure various performance changes in real time. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] In order to more clearly illustrate the specific implementation methods of the present application or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0034] Figure 1 A front view of a simulated space environment test platform for a thermophotovoltaic isotope power source prototype provided in this application;

[0035] Figure 2 A side view of a simulated space environment test platform for a thermophotovoltaic isotope power source prototype provided in this application;

[0036] Figure 3A top view of the cavity of the simulated space environment test platform of the thermophotovoltaic isotope power source prototype provided in this application.

[0037] Figure numerals: 1-cavity; 2-molecular pump; 3-mechanical pump; 4-water cooling system; 5-electric power input system; 6-wafer output system; 7-temperature monitoring system. DETAILED DESCRIPTION

[0038] The technical solution of the present application will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all of the embodiments.

[0039] The components of the embodiments of the present application generally described and shown in the drawings herein can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the application claimed, but merely represents the selected embodiments of the present application.

[0040] Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making any creative work shall fall within the scope of protection of this application.

[0041] In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying 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 limiting the present application. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0042] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0043] Combination Figure 1-Figure 3 As shown, the present application provides a simulated space environment test platform for a thermophotovoltaic isotope power source prototype, including a vacuum system, a water cooling system 4, an electric power input system 5, a wafer output system 6 and a temperature monitoring system 7.

[0044] Specifically, the vacuum system has a cavity 1, and the cavity 1 is used to install the system to be tested; the vacuum system can evacuate the cavity 1 so that a 0.03m 3 Vacuum environment;

[0045] Specifically, the water cooling system 4 is connected to the vacuum system through a short-circuited water cooling pipe, and can ensure a constant low temperature in the cavity 1;

[0046] Specifically, the electric power input system 5 is arranged on the side of the system to be tested;

[0047] Specifically, the wafer output system 6 and the internal temperature measurement point are connected to the outside of the vacuum environment through a vacuum aviation joint; the wafer output circuit in the wafer output system 6 detects the wafer output short-circuit current I sc With open circuit voltage V oc , and then connect the load R L ; When adjusting the load R L The size of can enable the chip to obtain a preset output power point.

[0048] Specifically, the temperature monitoring system 7 is in communication with the system to be tested and is used to detect the temperature of the system to be tested; the temperature monitoring system 7 uses a PID temperature control system to adjust feedback to fix two sets of metal columns to ensure heating temperature and power.

[0049] Furthermore, in order to accurately measure the working temperature, the temperature monitoring system 7 includes a B-type thermocouple and a T-type thermocouple; the B-type thermocouple is used to measure the temperature range of 0 to 1800° C.; the T-type thermocouple is used to measure the temperature range of -200 to 350° C.

[0050] It is worth noting that: this application strictly follows the actual working environment. Except for the heating element and the real isotope heat source raw materials, the rest of the systems remain consistent, overcoming the technical problem that the existing electric heating simulation heat source and the real isotope heat source have poor equivalence in internal structure, heat distribution and temperature distribution with the real isotope heat source.

[0051] In this embodiment, in order to ensure that the simulated space environment test platform of the thermophotovoltaic isotope power source prototype provides a sufficiently simulated environment and reduce costs; the system vacuum system provides 0.03m 3 The circular cavity 1 is a vacuum environment.

[0052] Specifically, in order to improve the working efficiency of the vacuum system, the vacuum system in this embodiment adopts a combination of a molecular pump 2 and a mechanical pump 3; more specifically, the vacuum system includes a molecular pump 2, a mechanical pump 3 and a tank body; the tank body has the cavity 1; the mechanical pump 3, the molecular pump 2 and the tank body are connected in sequence; the mechanical pump 3 and the molecular pump 2 can evacuate the tank body.

[0053] Furthermore, the diameter of the tank body is set between 300-400 mm, the height of the tank body is set between 300-380 mm; and the thickness of the tank body is set between 1-10 mm.

[0054] In this embodiment, in order to prevent debris from falling into the molecular pump 2 and then entering the tank body, the vacuum system further includes a filtering mechanism, which is arranged at the connection between the molecular pump 2 and the tank body.

[0055] Specifically, the filtering mechanism comprises a filter screen, which is arranged at the connection between the molecular pump 2 and the tank body to filter out debris.

[0056] Preferably, a cylindrical stainless steel cavity 1 with a diameter of 390 mm, a height of 350 mm and a thickness of 5 mm is quickly evacuated by a combined vacuum pump to form a 0.03 m 3 Vacuum environment.

[0057] In this embodiment, in order to reduce the vacuum environment interface and maintain high vacuum, the lower part of the vacuum chamber is mainly a vacuum wall-penetrating socket for water cooling and access to electrical signals. At the same time, there is a Φ150 CF flange interface at the bottom connected to the molecular pump 2, a Φ50 round hole for connecting the input electrode and the high-temperature thermocouple interface, and two Φ22.7 round holes for connecting vacuum wall-penetrating parts, one of which is used for wiring the temperature control thermocouple output, and the other is used for wiring the wafer output. At the same time, eight water-cooling joints with an inner diameter of Φ6.75 are set for connecting water-cooling pipes.

[0058] In this embodiment, in order to ensure that important wafer positions have a lower temperature and reduce excess heat dissipation losses at the wafer positions, two sets of water-cooling heat dissipation systems 4 are provided in the present application, wherein one set of the water-cooling heat dissipation systems 4 and the system to be tested constitute a wafer cooling circuit, and the other set of the water-cooling heat dissipation systems 4 and the system to be tested constitute a non-crystalline cooling circuit.

[0059] In addition, molecular pump 2 is used for water cooling to improve the overall working stability of the system.

[0060] In this embodiment, in order to set a high-efficiency cooling effect at a fixed low temperature, the cooling system uses a ratio of coolant and pure water to ensure that the coolant does not turn into an ice-water mixture, causing the flow rate to slow down and block the water cooler. At the same time, it can ensure the heat dissipation efficiency and reduce temperature deviation.

[0061] In this embodiment, an electrically input simulated heat source is used to replace the radioisotope input power, and the power is adjusted through PID system feedback to make the measured temperature close to the target temperature, while ensuring that the input power, input voltage, and input current are within the specified range.

[0062] It is worth noting that: under the condition of constant light intensity, the wafer is equivalent to a constant current source, and the wafer output circuit detects the wafer output short-circuit current I sc With open circuit voltage

[0063] V oc , connect the chip to the load R L The voltage drop on the load will generate a positive bias on the wafer, weakening the built-in electric field of the wafer, thereby generating a dark current and causing the output current to decrease. Adjust the load R L The size of can make the chip get an optimal output power point, this optimal output power P max It represents the output characteristics of the chip.

[0064] P max =I sc ·V oc FF.

[0065] In summary, the specific usage process of this application is as follows: before use, the vacuum tank must be opened for inspection and the thermal photovoltaic system must be assembled and cleaned. At the same time, each subsystem must be inspected and the vacuum tank must be closed for reinforcement.

[0066] System working process: Step 100: Turn on the mechanical pump 3 and the vacuum detection device of the vacuum system to perform low vacuum extraction, and repeatedly extract through inert gas.

[0067] Step 200: After the low vacuum is stable, the high vacuum molecular pump 2 and the supporting water cooling are turned on to perform long-term vacuuming. When the vacuum system is working, the experimental work progress and temperature rise plan are set through the electronic control system.

[0068] Step 300: After the high vacuum is stable for a long time, start the experiment, turn on the supporting working water cooling including wafer circuit water cooling and amorphous circuit water cooling, and start working.

[0069] Step 400: During the experiment start-up process, the temperature monitoring system 7 implements and displays the working conditions of the thermocouple test at each point, and adjusts the cooling temperature in real time according to the temperature rise. When the constant peak value is reached, the wafer output display system is turned on to detect the wafer output short-circuit current Isc With open circuit voltage V oc , and then connect the load R L , adjust the load R L The size of gets the best output power point.

[0070] Step 500: After completing the peak measurement stabilization task, cool down according to the set plan, cool down to room temperature and then cool naturally.

[0071] System disassembly process: After ensuring that the experiment is completed, the pressure of cavity 1 is restored by flushing inert gas, and the coolant in the system is refluxed through the air pump.

[0072] The beneficial effect of this application is that it can maintain 0.03m 3 Cavity 1 can maintain a stable 3x10-3 high vacuum environment to a 10-5 extreme environment, and can also maintain a -30℃ low temperature environment with a constant power of 250W-500W for heating, and ensure that the input voltage is displayed at 0~250V and the input current is displayed at 0~10A at the same time.

[0073] The present invention can meet various performance tests of existing and future isotope thermophotovoltaic isotope power supply systems and measure various performance changes in real time.

[0074] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit it. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present application.

Claims

1. A simulated space environment test platform for a thermophotovoltaic isotope power source prototype, characterized in that: Including vacuum system, water cooling system, electric power input system, wafer output system and temperature monitoring system; The vacuum system has a cavity, and the cavity is used to install the system to be tested; The vacuum system can evacuate the cavity so that a vacuum of at least 0.03 m 3 Vacuum environment; The water cooling system is connected to the vacuum system and can ensure a constant low temperature in the cavity; The electric power input system is arranged on the side of the system to be tested; The wafer output system and the internal temperature measurement point are connected to the outside of the vacuum environment through a vacuum aviation connector; The temperature monitoring system is attached to the system to be tested and is used to detect the temperature of the system to be tested; The water cooling and heat dissipation system is provided with at least two sets, wherein at least one set of the water cooling and heat dissipation system and the system to be tested form a wafer cooling loop, and at least another set of the water cooling and heat dissipation system and the system to be tested form an amorphous cooling loop; The wafer output circuit in the wafer output system detects the wafer output short-circuit current With open circuit voltage , and then connect the load ; When adjusting the load When the size is large, the chip can obtain the preset output power point.

2. The simulated space environment test platform of a thermophotovoltaic isotope power source prototype according to claim 1, characterized in that: The vacuum system includes a molecular pump, a mechanical pump and a tank; The tank body has the cavity; The mechanical pump, the molecular pump and the tank are connected in sequence; The mechanical pump and the molecular pump can evacuate the tank.

3. The simulated space environment test platform of a thermophotovoltaic isotope power source prototype according to claim 2, characterized in that: The vacuum system further comprises a filtering mechanism, which is arranged at the connection point between the molecular pump and the tank body.

4. The simulated space environment test platform for a thermophotovoltaic isotope power source prototype according to claim 2, characterized in that: The diameter of the tank body is set between 350-450 mm, the height of the tank body is set between 350-450 mm, and the thickness of the tank body is set between 1-10 mm.

5. The simulated space environment test platform for a thermophotovoltaic isotope power source prototype according to claim 1, characterized in that: The temperature monitoring system includes a B-type thermocouple and a T-type thermocouple; The B-type thermocouple is used to measure the temperature range of 0 to 1800°C; the T-type thermocouple is used to measure the temperature range of -200 to 350°C.

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