Thermoelectric material performance testing device and method applied to cross-domain aircraft

Abstract

The invention relates to the technical field of thermoelectric material performance testing, and particularly discloses a thermoelectric material performance testing device applied to a cross-domain aircraft, the device is of a cylindrical structure, is horizontally arranged and can be separated into a left part and a right part through thermal insulation design, and the testing device has the function of adjusting the internal pressure intensity; the low-pressure state of the internal space can be realized; by inputting rare gas (for example, a high-pressure state can be realized), the pressure change of the aircraft in different environments can be simulated. In the testing process, the hot end of the test piece is heated through the heating device, the high-temperature environment of the surface of the aircraft is simulated, and the cold end is in a cooling state to simulate the temperature difference in the real working environment. The device can test the thermoelectric performance of the thermoelectric material in a variable-voltage environment. According to the invention, data support can be provided for design and optimization of thermoelectric materials in cross-domain aircrafts, and application research of the thermoelectric materials in waste heat power generation in aviation and deep sea environments is promoted.

Description

Technical Field

[0001] The present invention belongs to the technical field of thermoelectric material performance testing, and specifically relates to a thermoelectric material performance testing method applied to cross-domain vehicles. Background Art

[0002] In recent years, with the rapid development of high-performance cross-domain vehicles (aircraft that cross high altitude, atmosphere and deep sea), exploring energy utilization technology in extreme environments has gradually become a research hotspot. Cross-domain vehicles can perform tasks in complex environments such as high altitude and deep sea, which is of great significance to the country's strategic reconnaissance, military defense and scientific research. This type of aircraft not only has to face drastic temperature changes, but also needs to withstand drastic pressure changes from extremely low pressure to high pressure, so it puts forward extremely high performance requirements for various energy devices on board.

[0003] In this context, thermoelectric power generation technology, as an important means of energy recovery, has begun to attract widespread attention. Thermoelectric power generation technology uses thermoelectric materials to directly convert temperature differences into electrical energy. It does not rely on mechanical components and has the advantages of high efficiency, reliability, no noise, and small size. It is very suitable for the waste heat recovery system of cross-domain vehicles.

[0004] For example, in high-altitude environments, the outer surface of a spacecraft will generate a higher temperature due to friction from high-speed airflow and sunlight radiation, while its cold end can be in contact with the low-temperature atmosphere. In deep-sea environments, the internal equipment of a spacecraft is running at a higher temperature, while the cold end is in direct contact with the low-temperature seawater in the deep sea, forming a large temperature difference, which provides an exploitable temperature difference environment for thermoelectric materials, enabling them to effectively recycle surface waste heat for power generation.

[0005] However, the performance of thermoelectric materials is significantly affected by changes in pressure. In high-altitude environments, the external pressure is extremely low due to the thin air; in deep-sea environments, the pressure rises exponentially with increasing water depth. This drastic pressure change will directly affect the microstructure and carrier transport behavior of thermoelectric materials, thereby changing their thermoelectric properties. Especially under high pressure environments, the material's lattice may be distorted or have microstructural defects, which will affect the conduction efficiency of electrons and phonons, thereby weakening its thermoelectric conversion capability. Therefore, accurate testing and evaluation of the performance of thermoelectric materials under different pressure environments is of great theoretical and engineering significance for optimizing material performance and designing efficient temperature difference power generation systems.

[0006] At present, the common thermoelectric material performance test devices on the market are mostly used for measurements under normal pressure or single temperature environments, and there is a lack of equipment that can simulate high-altitude and deep-sea environments for testing. This makes the application of temperature difference power generation technology in cross-domain vehicles face great challenges: it is impossible to obtain the real performance data of thermoelectric materials in actual working environments. In order to solve this problem, the present invention proposes a new type of thermoelectric material performance test device and method, which can test the thermoelectric performance of thermoelectric materials under variable pressure environments. Summary of the invention

[0007] The purpose of the present invention is to provide a thermoelectric material performance test and method for cross-domain vehicles to solve the problems raised in the above background technology.

[0008] To achieve the above object, the present invention provides the following technical solutions:

[0009] A thermoelectric material performance testing device for cross-domain spacecraft, comprising:

[0010] A high and low pressure test chamber, the high and low pressure test chamber comprising a left insulation substrate, a right insulation substrate, a temperature monitoring system and a pressure monitoring system;

[0011] The high and low pressure test chamber is used to simulate the pressure changes of the aircraft in different environments. The low pressure state is achieved by extracting gas from the gas outlet, and the high pressure state is achieved by inputting rare gas, so as to adjust the pressure of the internal space and simulate the pressure change range of the aircraft from high altitude to deep sea.

[0012] The left thermal insulation substrate is in the shape of a hollow cylinder, with a cylindrical through hole in the middle and a thermal insulation outlet duct on the periphery for regulating the inlet and outlet of gas. A left transmission signal column passes through the inner side of the cylindrical through hole, and a cold pipe passes through the periphery of the left transmission signal column. A test piece is placed at one end of the cold pipe; a cold end electrode is provided at one end of the cold pipe;

[0013] The left end opening of the right thermal insulation substrate is a hollow cylindrical structure, with a through hole in the middle, and a right transmission signal column passes through the inside of the through hole; the left end of the right transmission signal column is sequentially installed with a thermal insulation layer, a heating wire, a heat storage block and a hot end electrode, and the hot end electrode is used to fix the right end of the test piece, and the surface of the right thermal insulation substrate is surrounded by a thermal insulation air inlet;

[0014] The temperature monitoring system includes a cold-end infrared temperature measuring device and a hot-end infrared temperature measuring device. The cold-end infrared temperature measuring device and the hot-end infrared temperature measuring device are installed on the lower side of the inner wall of the right insulation substrate, and are used to measure the cold-end and hot-end temperatures of the test piece in real time;

[0015] The pressure monitoring system includes a pressure monitoring device, and the pressure monitoring device is installed on the upper side of the inner wall of the right temperature-insulating substrate, which is used to measure the pressure environment of the test piece in real time.

[0016] A testing method for a thermoelectric material performance testing device applied to a cross-domain vehicle comprises the following steps:

[0017] Step 1: Install the test piece, put its left end close to the cold tube and its right end close to the hot end electrode, make sure the infrared temperature measuring device is aimed at the cold end and hot end of the test piece respectively, and record the temperature of both ends;

[0018] Step 2: Start the high and low pressure test chamber, set the simulated environment, and extract air through the air outlet to make the internal space reach a low pressure state; input rare gas, which includes but is not limited to helium and argon, and pressurize it to a high pressure state to simulate the different pressure environments of the spacecraft at high altitude and deep sea;

[0019] Step 3: Start the refrigeration system, control the temperature of the left end of the test piece by circulating the coolant through the control pipe; start the heating wire, adjust the temperature of the right end, obtain the temperature of the cold end and the hot end through the infrared temperature measuring device, and ensure that the temperature difference ΔT meets the test requirements;

[0020] Step 4: Record the voltage difference ΔV and current I of the test piece under different temperature differences ΔT, and calculate the thermoelectric performance parameters:

[0021] Seebeck coefficient: α = ΔV / ΔT

[0022] Conductivity: σ=I·L / (ΔV·S)

[0023] Step 5: Adjust the pressure in the high and low pressure test chambers, repeat step 2, collect test data under different pressure conditions, and analyze the performance changes of thermoelectric materials under variable pressure environments.

[0024] Compared with the prior art, the present invention has the following beneficial effects:

[0025] The thermoelectric material performance test device proposed in the present invention can simulate the full pressure range experienced by cross-domain vehicles from high altitude to deep sea, including low pressure state to high pressure state, and environment with drastic temperature difference changes. This makes the test conditions closer to the actual application scenario, and provides more accurate and comprehensive data support for the performance evaluation of thermoelectric materials. By testing the performance of thermoelectric materials under different pressure and temperature difference conditions, it can reveal the law of material performance changes with environmental parameters, and provide a scientific basis for the optimization design and improvement of materials. This helps to quickly screen out high-performance thermoelectric materials suitable for working in extreme environments and accelerate their application process in cross-domain vehicles. Through the present invention, data support can be provided for the design and optimization of thermoelectric materials in cross-domain vehicles, and the application research of thermoelectric materials in waste heat power generation in aviation and deep-sea environments can be promoted. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is the general assembly structure diagram of the present invention.

[0027] In the figure: 1. high and low pressure test chamber; 101. left insulation substrate; 102. left transmission signal column; 103. cold end electrode; 104. cold pipe; 105. insulation outlet duct; 210. right insulation substrate; 202. right transmission signal column; 203. insulation layer; 204. heating wire; 205. heat storage block; 206. hot end electrode; 208. cold end infrared temperature measuring device; 209. hot end infrared temperature measuring device; 210. insulation inlet duct; 3. test piece; 4. pressure monitoring device. DETAILED DESCRIPTION

[0028] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0029] Embodiment 1:

[0030] See also Figure 1 As shown, a thermoelectric material performance testing device applied to a cross-domain vehicle comprises a high- and low-pressure test chamber 1, wherein the high- and low-pressure test chamber 1 comprises a left insulation substrate 101, a right insulation substrate 201, a temperature monitoring system and a pressure monitoring system;

[0031] The high and low pressure test chamber 1 is used to simulate the pressure changes of the aircraft in different environments. The low pressure vacuum state is achieved by extracting gas through the gas outlet, and the high pressure state is achieved by inputting rare gas, so as to adjust the pressure of the internal space and simulate the pressure change range of the aircraft from high altitude to deep sea.

[0032] The left insulation substrate 101 is in the shape of a hollow cylinder, with a cylindrical through hole in the middle and an insulation outlet 105 on the periphery for regulating the inlet and outlet of gas. A left transmission signal column 102 passes through the inner side of the cylindrical through hole, and a cold pipe 104 passes through the periphery of the left transmission signal column 102. A test piece 3 is placed at one end of the cold pipe 104; a cold end electrode 103 is provided at one end of the cold pipe 104;

[0033] The left end opening of the right thermal insulation substrate 201 is a hollow cylindrical structure, with a through hole in the middle, and a right transmission signal column 202 passes through the inside of the through hole; the left end of the right transmission signal column 202 is sequentially installed with a thermal insulation layer 203, a heating wire 204, a heat storage block 205 and a hot end electrode 206, and the hot end electrode 206 is used to fix the right end of the test piece 3, and a thermal insulation air inlet 210 is arranged around the surface of the right thermal insulation substrate 201;

[0034] Temperature monitoring system, the temperature monitoring system includes a cold end infrared temperature measuring device 208 and a hot end infrared temperature measuring device 209, which are installed on the lower side of the inner wall of the right insulation substrate 201, and are used to measure the cold end and hot end temperatures of the test piece 3 in real time;

[0035] The pressure monitoring system includes a pressure monitoring device 4 . The pressure monitoring device 4 is installed on the upper side of the inner wall of the right thermal insulation substrate 201 , and is used to measure the pressure environment of the test piece 3 in real time.

[0036] A testing method for a thermoelectric material performance testing device applied to a cross-domain vehicle, characterized in that it comprises the following steps:

[0037] Step 1: Install the test piece 3, with its left end close to the cold tube 104 and its right end close to the hot end electrode 206, ensure that the infrared temperature measuring devices 208 and 209 are respectively aimed at the cold end and hot end of the test piece 3, and record the temperatures at both ends;

[0038] Step 2: Start the high and low pressure test chamber, set the simulated environment, and extract air through the air outlet to make the internal space reach a low pressure state; input rare gas, including but not limited to helium and argon, and pressurize it to a high pressure state to simulate the different pressure environments of the spacecraft at high altitude and deep sea;

[0039] Step 3: Start the refrigeration system, circulate the coolant through the control pipe 104, and control the temperature of the left end of the test piece 3; start the heating wire 204, adjust the temperature of the right end, obtain the cold end and hot end temperatures through the infrared temperature measuring device, and ensure that the temperature difference ΔT meets the test requirements;

[0040] Step 4: Record the voltage difference ΔV and current I of the test piece 3 under different temperature differences ΔT, and calculate the thermoelectric performance parameters:

[0041] Seebeck coefficient: α = ΔV / ΔT

[0042] Conductivity: σ=I·L / ΔV·S

[0043] Step 5: Adjust the pressure in the high and low pressure test chambers, repeat step 2, collect test data under different pressure conditions, and analyze the performance changes of thermoelectric materials under variable pressure environments.

[0044] It should be understood that in the development of any actual implementation, as in any engineering or design project, numerous implementation-specific decisions may be made. Such a development effort may be complex and time-consuming, but for those of ordinary skill having the benefit of this disclosure, the development effort will be a routine task of design, fabrication, and production without undue experimentation.

[0045] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solutions of the present invention may be modified or replaced by equivalents without departing from the spirit and scope of the technical solutions of the present invention, which should all be included in the scope of the claims of the present invention.

Claims

1. A thermoelectric material performance testing device for cross-domain vehicles, characterized in that: It comprises a high and low pressure test chamber (1), wherein the high and low pressure test chamber (1) comprises a left thermal insulation substrate (101), a right thermal insulation substrate (201), a temperature monitoring system and a pressure monitoring system; The high and low pressure test chamber (1) is used to simulate the pressure changes of the aircraft in different environments, to realize the low pressure (vacuum) state by extracting gas through the gas outlet, and to realize the high pressure state by inputting rare gas, to adjust the pressure of the internal space, and to simulate the pressure change range of the aircraft from high altitude to deep sea; The left thermal insulation substrate (101) is in the shape of a hollow cylinder, with a cylindrical through hole in the middle and a thermal insulation outlet passage (105) on the periphery for regulating the inlet and outlet of gas. A left transmission signal column (102) passes through the inner side of the cylindrical through hole, and a cold pipe (104) passes through the periphery of the left transmission signal column (102). A test piece (3) is placed at one end of the cold pipe (104); a cold end electrode (103) is provided at one end of the cold pipe (104); The left end opening of the right thermal insulation substrate (201) is a hollow cylindrical structure, with a through hole in the middle, and a right transmission signal column (202) passes through the inside of the through hole; a thermal insulation layer (203), a heating wire (204), a heat storage block (205) and a hot end electrode (206) are sequentially installed on the left end of the right transmission signal column (202), and the hot end electrode (206) is used to fix the right end of the test piece (3); and a thermal insulation air inlet duct (210) is arranged around the surface of the right thermal insulation substrate (201); The temperature monitoring system comprises a cold-end infrared temperature measuring device (208) and a hot-end infrared temperature measuring device (209), the cold-end infrared temperature measuring device (208) and the hot-end infrared temperature measuring device (209) being installed on the lower side of the inner wall of the right thermal insulation substrate (201) for real-time measurement of the cold-end and hot-end temperatures of the test piece (3); The pressure monitoring system comprises a pressure monitoring device (4), the pressure monitoring device (4) is installed on the upper side of the inner wall of the right thermal insulation substrate (201), and is used for real-time measurement of the pressure environment of the test piece (3).

2. The testing method of a thermoelectric material performance testing device applied to a cross-domain vehicle according to claim 1 is characterized in that: The following steps are involved: Step 1: Install the test piece (3), place its left end close to the cold tube (104), and its right end close to the hot end electrode (206), ensure that the infrared temperature measuring devices (208) and (209) are respectively aligned with the cold end and the hot end of the test piece (3), and record the temperatures of the two ends; Step 2: Start the high and low pressure test chamber, set the simulated environment, and extract air through the air outlet to make the internal space reach a low pressure state; input rare gas, which includes but is not limited to helium and argon, and pressurize it to a high pressure state to simulate the different pressure environments of the spacecraft at high altitude and deep sea; Step 3: Start the refrigeration system, circulate the coolant through the control pipe (104), and control the temperature of the left end of the test piece (3); start the heating wire (204), adjust the temperature of the right end, and obtain the cold end and hot end temperatures through the infrared temperature measuring device to ensure that the temperature difference ΔT meets the test requirements; Step 4: Record the voltage difference ΔV and current I of the test piece (3) under different temperature differences ΔT, and calculate the thermoelectric performance parameters: Seebeck coefficient: α = ΔV / ΔT Conductivity: σ=I·L / (ΔV·S) Step 5: Adjust the pressure in the high and low pressure test chambers, repeat step 2, collect test data under different pressure conditions, and analyze the performance changes of thermoelectric materials under variable pressure environments.

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