In-situ test device and method for simulating space multi-temperature-domain environment irradiation

Abstract

The invention relates to an in-situ test device and method for simulating space multi-temperature-range environment irradiation, and belongs to the technical field of material tests.The device comprises an annular pipe, a sample table, a refrigerator, a heater and an irradiation source, the sample table is arranged in the annular pipe, the sample table can periodically move in the annular pipe, and the sample table can also rotate; according to the invention, a multi-temperature-zone design is adopted, and conversion of different temperature zones is realized by using a periodic rotation orbit, so that the temperature field effect of the spacecraft is simulated; and the irradiation uniformity of the ground point radiation source is realized by utilizing the autorotation of the irradiated sample, so that the authenticity and effectiveness of the ground test are further improved. Ground equipment is utilized, the method is simple, the cost is low, in-situ test simulation of various space environments such as vacuum, high and low temperature, irradiation and the like can be realized, and the method has important application value for improving selection and reliability tests of space materials.

Description

Technical Field

[0001] This invention belongs to the field of materials testing technology, specifically relating to an in-situ testing device and method for simulating multi-temperature-domain irradiation in space. Background Technology

[0002] Materials used in space face varying service environments depending on their orbit and application within the spacecraft. Typically, materials in space encounter environmental effects such as extreme temperature cycles and space particle radiation. Actual space service conditions involve a combination of factors including temperature, vacuum, and radiation, making it virtually impossible to simulate the exact same multidimensional space physics on Earth. These environmental differences lead to technical discrepancies in reliability analysis of simulated space environments, thus affecting material selection and the accuracy of reliability assessments. Therefore, developing ground-based systems that more closely resemble real-world space service environments is crucial for addressing this issue.

[0003] In the space environment, the temperature field changes periodically with the spacecraft's flight trajectory. The irradiation environment can be set as a uniform irradiation dose field within a certain period (excluding events such as solar flares). Currently, these two important space environment simulation experiments are mostly conducted separately, or using complex sealed cabins to construct a combined temperature and irradiation environment. However, due to the large scale of the combined irradiation environment and the high cost of equipment construction (for example, the combined irradiation equipment in the large-scale scientific project built by Harbin Institute of Technology cost tens of millions of yuan), the cost of reliability assessment tests is also very high.

[0004] Furthermore, during the irradiation of materials or products, due to the limitations of radiation energy and penetrability, it is difficult to achieve uniform radiation dose absorption across the three-dimensional dimensions of the sample. Especially for low-energy electron beams, the irradiation effect can only be achieved in the shallow, micrometer-scale region of the irradiated surface, and cannot simulate the irradiation effect from multiple directions in space.

[0005] Therefore, developing a new experimental method to simulate the irradiation environment in multiple temperature regions while ensuring the irradiation uniformity of the irradiated sample is of great significance for providing an accurate, efficient, and reliable experimental method for the selection of space materials. Summary of the Invention

[0006] The purpose of this invention is to provide an in-situ test device and method for simulating multi-temperature-domain irradiation in space. By combining the revolution and rotation of the sample, the uniformity of irradiation received by the sample is improved, avoiding the non-uniformity caused by only one surface of the sample receiving irradiation. This invention solves the problems of imperfection and high cost of existing simulated space environment test technology, and has great application value for characterizing the service reliability of materials in aerospace engineering.

[0007] The above-mentioned objectives of the present invention are mainly achieved through the following technical solutions:

[0008] An in-situ experimental device for simulating multi-temperature-domain irradiation in space includes a ring tube, a sample stage, a cooler, a heater, and an irradiation source. The sample stage is disposed inside the ring tube and can move periodically within the ring tube. The sample stage can also rotate. A section of the tubular structure in the ring tube is heated by the heater, and another section of the tubular structure is cooled by the cooler. The irradiation source irradiates the ring tube with Co60.

[0009] The annular tube is circular, elliptical, rectangular, or a combination of these shapes. The side length of the annular tube is 0.5m to 1m. The annular tube is a high-purity quartz tube with a quartz purity of not less than 99.99%.

[0010] The heater and cooler are protected from radiation damage to the circuit equipment by lead bricks.

[0011] The annular tube has a square or circular channel inside, with the square channel having a side length of 30mm to 50mm and the circular channel having a diameter of 30mm to 50mm.

[0012] An in-situ experimental method for simulating multi-temperature-domain irradiation in space, using the aforementioned apparatus, specifically includes the following steps:

[0013] (1) Clean and dry the inner wall of the annular tube with an organic solvent;

[0014] (2) Fix the sample on the sample stage and seal it in the annular tube, and evacuate the annular tube.

[0015] (3) Heat the heater or cool the cooler as needed;

[0016] (4) Irradiate the annular tube with Co60 through the irradiation source, and adjust the relative position of the annular tube and the irradiation source, the moving speed of the sample stage on the track inside the quartz tube and the rotation speed of the sample stage as needed.

[0017] (5) Monitor the total irradiation dose and end the test when the required total dose is reached; after the heater and cooler return to room temperature, stop the vacuum pump, and after returning to normal pressure, open the quartz tube to take out the sample.

[0018] In step (3), the heater parameters are as follows: heating temperature is 25℃~200℃, heating rate is 1~20℃ / min, and holding time is 1~30min; the cooler parameters are as follows: cooling temperature is -120℃~25℃, cooling rate is 1~20℃ / min, and holding time is 1min~30min.

[0019] In step (4), the angular velocity of the sample as it rotates with the sample stage is 30° to 360° / s, and the sample completes 1 to 5 revolutions per minute on the track.

[0020] In step (4), the annular tube can be adjusted in both the height and horizontal directions: in the height direction, the adjustable height is 0.2 to 0.5 m; in the horizontal direction, the adjustable distance is 0.2 to 0.5 m.

[0021] In step (4), the time the sample spends or operates within a single temperature range is greater than the time required for the sample temperature to reach equilibrium.

[0022] In step (4), the rotation period of the sample stage is less than the time spent running or staying within a single temperature range.

[0023] Compared with the prior art, the present invention has at least the following beneficial effects:

[0024] (1) The present invention provides a total dose irradiation device for simulating a multi-temperature environment in space, which enables the sample to be irradiated under a set constant temperature or a temperature cycle that can be periodically changed, which is closer to the real application scenario and more conducive to the performance evaluation of materials for space use.

[0025] (2) The present invention realizes the self-rotation of the sample and the periodic revolution around the irradiation source. Compared with the case where the sample is fixed and receives irradiation or only revolves for irradiation, it improves the uniformity of the sample receiving irradiation and avoids the unevenness caused by only one side of the sample receiving irradiation.

[0026] (3) By superimposing the temperature field effect, this invention increases the self-rotation and revolution of the sample, and more realistically simulates the irradiation scenario of materials under different temperatures and alternating temperatures under real space conditions, thereby improving the irradiation uniformity and having important significance for evaluating the radiation resistance performance of materials used in space environments. Attached Figure Description

[0027] Figure 1 This invention provides an in-situ experimental device for simulating multi-temperature-domain environmental irradiation in space. Detailed Implementation

[0028] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments:

[0029] This invention provides a scientific, rapid, and effective method for simulating total dose irradiation tests of materials under multi-temperature domain conditions in space. By employing a multi-temperature domain design and utilizing a periodic rotating orbit to achieve switching between different temperature ranges, this method solves the problems of uncontrollable sample temperature during material irradiation, the inability to simulate irradiation of materials at different temperatures in space, and uneven irradiation. This method can better simulate the irradiation effects of materials under temperature influence, and more scientifically and effectively evaluate the radiation resistance of materials.

[0030] The principle of this invention is to use high-purity quartz as a vacuum chamber, which can not only achieve the vacuum environment required for the sample, but also apply temperature and total dose irradiation stress. By conducting total dose irradiation tests on materials under different temperature ranges, the irradiation performance and degradation law of the materials are studied, thereby obtaining more realistic data on the total dose irradiation performance of materials for the performance evaluation of space materials.

[0031] like Figure 1 As shown, an in-situ experimental device for simulating multi-temperature-domain irradiation in space is characterized by comprising a ring tube, a sample stage, a cooler, a heater, and an irradiation source. The sample stage is disposed inside the ring tube and can move periodically within the ring tube, and can also rotate. A section of tubular structure in the ring tube is disposed inside the heater to provide a high-temperature environment, and another section of tubular structure is disposed inside the cooler to provide a low-temperature environment. The irradiation source irradiates the ring tube with Co60.

[0032] This invention provides an in-situ experimental method for simulating multi-temperature-domain irradiation in space, comprising the following steps:

[0033] (1) The material sample to be irradiated is processed and prepared according to the size of the sample stage and then mounted on the sample stage (the sample stage is a hollow frame to ensure that the sample can be irradiated on both sides during the rotation of the sample stage); or the sample is processed and prepared according to the size requirements of the performance to be tested after the total dose irradiation test, so as to ensure that the sample can be mounted on the sample stage.

[0034] (2) Seal the sample stage containing the material sample into a high-purity quartz tube with a quartz purity of not less than 99.99%. The quartz tube contains a transmission device to ensure that the sample stage can move periodically (revolve) along the track in the quartz tube, while the sample itself can rotate. After the sample is installed and sealed, a vacuum device (vacuum pump) is used to continuously evacuate the inner cavity of the quartz tube;

[0035] (3) The quartz tube is a square ring, divided into four parts: front, back, left, and right. The left part is in the heater, providing a high-temperature environment, and is heated by the tube furnace heating element; the right part is in the cooler, providing a low-temperature environment, and is cooled by liquid nitrogen. After reaching the specified vacuum level, the heater and cooler temperatures are set and heating or cooling begins to reach the specified temperature.

[0036] (4) The quartz tube was irradiated with Co60 by an irradiation source. During the test, lead bricks were used to block the Co60 rays from irradiating the circuit equipment in the heater and cooler.

[0037] (5) When conducting a total dose irradiation test at a constant temperature, the position of the quartz tube can be adjusted so that the sample in the heater or cooler is facing the irradiation source. When conducting a total dose irradiation test under high and low temperature cycling conditions, the position of the quartz tube can be adjusted to ensure that the irradiation source is in the center of the front of the quartz tube. At the same time, the moving speed of the sample stage on the track inside the quartz tube can be set according to the test conditions.

[0038] (5) Monitor the total irradiation dose and end the test when the required total dose is reached. After the test, wait for the high temperature chamber and low temperature chamber to return to room temperature, stop the vacuum pump and return to normal pressure, then open the quartz tube to take out the sample.

[0039] In one specific embodiment, the method for vacuum sealing a quartz tube using a high-vacuum device includes the following steps:

[0040] (1) The diameter or side length of the annular pure quartz tube should be between 30 mm and 50 mm to facilitate the loading of the sample while taking into account the revolution and rotation of the sample stage.

[0041] (2) Use organic solvents such as alcohol and acetone to clean the cavity inside the pure quartz tube;

[0042] (3) Then dry the cavity of the pure quartz tube;

[0043] (4) Fix the sample on the sample stage in the cavity, ensuring that a single sample does not bend or fold, and that multiple samples do not overlap or obstruct each other; adjust the quartz tube and the irradiation source to achieve the optimal relative position according to the test requirements.

[0044] Vacuum evacuation was performed using a low-vacuum mechanical pump, a high-vacuum diffusion pump, or a molecular pump, with a vacuum level better than 1×10⁻⁶. - 4At Pa, the heater is heated or the cooler is cooled. The heater parameters are as follows: temperature range 25℃~200℃, accuracy ±3℃, heating rate adjustable from 1℃ / min to 20℃ / min, and holding time adjustable from 1min to 30min. The cooler temperature parameters are as follows: temperature range -120℃~25℃, accuracy ±3℃, cooling rate adjustable from 1℃ / min to 20℃ / min, and holding time adjustable from 1min to 30min.

[0045] In one specific embodiment, the angular velocity of the sample as it rotates with the sample stage is adjustable between 30° / s and 360° / s, and the number of revolutions the sample completes per minute on the track is adjustable between 1 and 5 revolutions.

[0046] In one specific embodiment, the side length of the square annular quartz tube is 0.5m to 1m; the height of the annular quartz tube is adjustable in both the height and horizontal directions: in the height direction, the adjustable height is 0.2m to 0.5m to ensure that the sample stage and the irradiation source in the quartz tube are at the same height; in the horizontal direction, the adjustable distance is 0.2m to 0.5m to adjust the relative position of the irradiation source and the sample stage to the required position.

[0047] This invention provides an in-situ testing method for simulating multi-temperature-domain irradiation in space. It can simulate the total dose irradiation process of materials under complex space conditions, including high and low temperatures, and alternating high and low temperatures, to evaluate the radiation resistance of materials. This method can achieve in-situ irradiation tests in three temperature domains: vacuum + constant high temperature + total dose irradiation, vacuum + constant high temperature + total dose irradiation, or vacuum + temperature alternation + total dose, enabling ground-based simulation tests of material irradiation under multiple temperature domains. Compared with conventional single total dose irradiation, this method incorporates temperature effects and employs a combination of sample revolution and rotation for irradiation, resulting in better sample irradiation uniformity and a more realistic environmental effect, making it more suitable for evaluating the radiation resistance of materials in space environments.

[0048] Example

[0049] This embodiment includes the following steps:

[0050] (1) Determine the sample size and prepare it according to the characteristics of the material sample itself and the performance testing requirements after the irradiation test. Mount it on the sample stage to ensure that the sample does not fall off during the revolution and rotation process.

[0051] (2) Seal the sample stage containing the material sample into a high-purity quartz tube with a quartz purity of not less than 99.99%. The diameter of the pure quartz tube should be between 30 mm and 50 mm to facilitate sample loading while allowing for the rotation and revolution of the sample stage. Clean the cavity inside the pure quartz tube using organic solvents such as alcohol and acetone to prevent cross-contamination of samples during different testing processes. Place the sample in the cavity, ensuring that no single sample is bent or folded, and that multiple samples do not overlap or obstruct each other. Continuously evacuate using a low-vacuum mechanical pump, a high-vacuum diffusion pump, or a molecular pump, achieving a vacuum level better than 1×10⁻⁶. -4 At Pa, the heater is heated or the cooler is cooled.

[0052] (3) The quartz tube is irradiated with Co60 through an irradiation source. During the test, lead bricks are used in the heater and cooler to block the Co60 rays from causing irradiation damage to the circuit equipment. Preferably, when conducting a total dose irradiation test at a constant temperature, the position of the quartz tube can be adjusted so that the sample in the heater or cooler is directly facing the irradiation source; when conducting a total dose irradiation test under high and low temperature cycling conditions, the position of the quartz tube is adjusted to ensure that the irradiation source is in the center of the front of the quartz tube, and the moving speed of the sample stage on the track inside the quartz tube is set according to the test conditions.

[0053] (4) Simulate a high-temperature environment of 100℃, a low-temperature environment of -50℃, a heating-cooling alternation time of no more than 1 min (the sample is transferred from the heater to the cooler, or from the cooler to the heater), a residence time of 20 min in the heater, a residence time of 20 mm in the cooler, and a total dose of 5×10 7 Material irradiation test at rad(Si). The irradiation source is Co60 gamma rays, and the dose rate is not less than 10 rad(Si) / s. When the number of cycles is required, the dose rate can be adjusted, and the exposure time of the two environmental stresses should be basically the same.

[0054] (5) Monitor the total irradiation dose and end the experiment when the required total dose is reached. After the experiment, wait for the high-temperature chamber and low-temperature chamber to return to room temperature, then stop the vacuum pump and return to normal pressure before opening the quartz tube to remove the sample. This method fully considers the irradiation environment in space, simulates the in-situ synergistic effect of temperature and total dose irradiation, and is closer to the real scene, which is beneficial to the evaluation of the radiation resistance performance of materials.

[0055] The above description is only the best specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the protection scope of the present invention.

[0056] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. An in-situ experimental device for simulating multi-temperature-domain irradiation in space, characterized in that: The device comprises a ring-shaped tube, a sample stage, a refrigerator, a heater and an irradiation source, the sample stage is arranged in the ring-shaped tube and can move periodically in the ring-shaped tube and also can rotate by itself; a section of the tube-shaped structure in the ring-shaped tube is heated by the heater, a section of the tube-shaped structure is cooled by the refrigerator, and the ring-shaped tube is irradiated by the irradiation source.

2. The in-situ test device for simulating space multi-temperature zone environment irradiation according to claim 1, characterized in that: The ring-shaped tube has a circular, elliptical, rectangular or combined shape, and the side length of the ring-shaped tube is 0.5-1 m; the ring-shaped tube is a high-purity quartz tube, and the purity of the quartz is not less than 99.99%.

3. The in-situ test device for simulating space multi-temperature zone environment irradiation according to claim 1, characterized in that: The heater and the refrigerator are shielded from the irradiation damage of the circuit equipment by lead bricks.

4. The in-situ test device for simulating space multi-temperature zone environment irradiation according to claim 1, characterized in that: The inside of the ring-shaped tube is a square channel or a circular channel, the side length of the square channel is 30-50 mm, and the diameter of the circular channel is 30-50 mm.

5. An in-situ test method for simulating space multi-temperature zone environment irradiation, characterized in that: The device of any one of claims 1-4 comprises the following steps: (1) cleaning and drying the inner wall of the ring-shaped tube with an organic solvent; (2) fixing the sample on the sample stage and sealing in the ring-shaped tube, and vacuumizing the ring-shaped tube; (3) heating the heater or cooling the refrigerator as needed; (4) irradiating the ring-shaped tube by the irradiation source, and adjusting the relative position of the ring-shaped tube and the irradiation source, the moving speed of the sample stage on the track in the quartz tube and the rotation speed of the sample stage as needed; (5) monitoring the total irradiation dose, and ending the test when the required total dose is reached; after the heater and the refrigerator return to room temperature, stopping the vacuum pump, returning to normal pressure and opening the quartz tube to take out the sample.

6. The in-situ test method for simulating space multi-temperature zone environment irradiation according to claim 5, characterized in that: In step (3), the heater parameters are as follows: the heating temperature is 25-200℃, the heating rate is 1-20℃ / min, and the holding time is 1-30 min; the refrigerator parameters are as follows: the cooling temperature is -120-25℃, the cooling rate is 1-20℃ / min, and the holding time is 1-30 min.

7. The in-situ test method of simulating space multi-temperature zone environment irradiation according to claim 5, characterized in that: In step (4), the angular velocity of the sample rotating with the sample stage is 30-360° / s, and the number of laps of the sample on the track per minute is 1-5 laps.

8. The in-situ test method of simulating space multi-temperature zone environment irradiation according to claim 5, characterized in that: In step (4), the ring-shaped tube can be adjusted in the height direction and the horizontal direction: in the height direction, the adjustable height is 0.2-0.5 m; in the horizontal direction, the adjustable distance is 0.2-0.5 m.

9. The in-situ test method of simulating space multi-temperature zone environmental irradiation according to claim 5, characterized in that: In step (4), the running or staying time of the sample in a single temperature range is greater than the time required for the sample temperature to balance.

10. The in-situ test method of simulating space multi-temperature zone environment irradiation according to claim 5, characterized in that: In step (4), the rotation period of the sample stage is less than the running or staying time in a single temperature range.

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