Method and device for comprehensively simulating surface comprehensive environment of airless celestial body

Abstract

The present invention discloses a method and device for comprehensively simulating the surface comprehensive environment of an airless celestial body to be determined. In the present invention, in a vacuum environment, an H ion source and a He ion source are used alone or jointly to irradiate a sample; a speckle electron gun is used to provide medium and low energy electron irradiation; a wide ultraviolet band light source is used to irradiate the sample with ultraviolet light; a pulsed laser is used to simulate the energy part in micro-meteorite bombardment; and by adjusting a five-axis sample stage, it is ensured that the sample can receive irradiation from multiple angles; finally, the purpose of simulating the surface comprehensive environment of an airless celestial body close to the actual situation is achieved. To solve the problem that the prior art cannot comprehensively and effectively simulate the surface comprehensive environment of an actual airless celestial body. The present invention is easy to implement, has a simple structure, and good use effects.

Description

Technical Field

[0001] The present invention relates to the field of mechanical technology, and in particular to a method and device for simulating the comprehensive environment on the surface of an airless celestial body. Background Art

[0002] With the gradual development of China's deep space exploration activities, the impact of the space environment on astronauts, exploration satellites, and space stations is still relatively scarce, and relevant research needs to be carried out to make up for the existing deficiencies. The space environment simulator is a device for simulating the cosmic space environment, and is used to test the capabilities of spacecraft to withstand vacuum, cold black, solar radiation, high-energy particle radiation, meteorites, etc. High-energy particles seriously affect the normal operation of satellites. When they hit the microelectronic devices of the satellite control system, they can form incorrect instructions, resulting in anomalies at least and chaos at worst, threatening the safety of the satellite. For manned spaceflight, the radiation damage of high-energy particles has always been one of the main issues concerned in spaceflight safety guarantee. The bombardment of micrometeorites poses a major threat to space exploration. Their speed relative to the spacecraft in the Earth's orbit is about several kilometers per second, and resisting the impact of micrometeorites is an important problem faced in the design of spacecraft and spacesuits.

[0003] Space environment simulators are mainly divided into thermal vacuum environment simulators, space dynamics simulators, space combined environment simulators, etc. The existing space combined environment simulators can simulate environments including solar radiation, ultraviolet rays, electrons, protons, solar wind, extremely high vacuum, cold and heat alternation, plasma, etc., but they cannot simulate high-energy particle radiation and micrometeorite bombardment. The importance of high-energy particles and micrometeorite bombardment for the space environment has been recognized. Therefore, the need to develop a comprehensive space environment simulation device is even more urgent. Summary of the Invention

[0004] The purpose of the present invention is to provide a method and device for simulating the comprehensive environment on the surface of an airless celestial body, which can not only simulate the vacuum and temperature environment on the surface of the celestial body, but also simulate the comprehensive environment such as solar wind irradiation, cosmic ray irradiation, and micrometeorite bombardment received on the surface of the celestial body, obtain a more realistic surface environment of the airless celestial body, provide technical support for the research on the irradiation environment process on the surface of the celestial body, and provide a test environment for material property research and engineering protection research.

[0005] The present invention is implemented as follows: The method for simulating the comprehensive environment on the surface of an airless celestial body is characterized in that: the cavity is evacuated by a vacuum device to make its vacuum degree reach above 10 -8 Pa; the specimen is loaded into the lifting sample stage, and the sample temperature is adjusted in the range of 100 - 500K by electronic refrigeration and infrared heating; one or several of H ions, He ions, X-rays, extreme ultraviolet rays, visible light, or high-energy pulsed lasers are used for single irradiation or co-irradiation and bombardment, so as to achieve the purpose of simulating the surface environment of an airless planet.

[0006] An integrated environmental simulation device for the surface of an airless celestial body, comprising a main cavity. The top of the main cavity is a hemispherical structure, and a laser optical reflection component is provided at the hemispherical top of the main cavity; an H ion emission component, a He ion emission component, an ultraviolet light source, an X-ray source, a speckle electron gun, a sample optical observatory, a visible light source and a non-contact sample temperature detector are also provided in the upper part of the hemispherical main cavity; a sample preparation chamber, an ion / electron beam spot detector, an ultraviolet light detector, an X-ray detector, a vacuum gauge and a spare interface are respectively connected in the middle part of the main cavity; the lower part of the main cavity is a cylindrical structure, and a five-axis lifting sample stage is provided at the lower part; a sample inlet and a sample transfer rod are connected to the sample preparation chamber.

[0007] The laser optical reflection component comprises a high-energy pulsed laser light source and a laser beam spot regulator; the H ion emission component comprises an H ion source and an H ion acceleration and focusing device; the He ion emission component comprises a He ion source and a He ion acceleration and focusing device.

[0008] A sample groove is provided on the five-axis lifting sample stage, an electrically controlled openable and closable microporous cover is provided above the sample groove, and an electronic cryogenic cold stage is provided at the bottom of the sample groove. The electronic cryogenic cold stage can realize temperature regulation from 100K to 300K.

[0009] Due to the adoption of the above technical solution, compared with the prior art, the present invention irradiates a sample alone or jointly with an H ion source and a He ion source in a vacuum environment; uses a speckle electron gun to provide medium and low energy electron irradiation; uses a wide ultraviolet band light source to irradiate the sample with ultraviolet light; uses a pulsed laser to simulate the energy part in micro-meteorite bombardment; and adjusts the five-axis sample stage to ensure that the sample can be irradiated from multiple angles; finally achieving the purpose of simulating an integrated environment on the surface of an airless celestial body close to the actual situation. To solve the problem that the prior art cannot comprehensively and effectively simulate the integrated environment on the surface of an actual airless celestial body. The present invention is easy to implement, has a simple structure and good use effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Attached Figure 1 is a schematic structural diagram of the present invention;

[0011] Attached Figure 2 is a top view of Attached Figure 1 ;

[0012] Attached Figure 3 is a sectional view of Attached Figure 1 ;

[0013] Attached Figure 4 is an internal structural schematic diagram of Attached Figure 1 ;

[0014] AttachedFigure 5 is an attached Figure 1 Schematic diagram of the internal structure from another angle;

[0015] attached Figure 6 is an attached Figure 1 Schematic diagram of the internal structure from yet another angle. Specific implementation manner

[0016] Embodiment of the present invention: a comprehensive environmental simulation device for the surface of an airless celestial body, including a main cavity 4, the top of the main cavity 4 is a hemispherical structure, and a laser optical reflection component is provided at the hemispherical top of the main cavity 4; an H ion emission component, a He ion emission component, an ultraviolet light source 9, an X-ray source 12, a speckle electron gun 13, a sample optical observator 14, a visible light source 15, and a non-contact sample temperature detector 16 are also provided in the upper part of the hemisphere of the main cavity 4; a sample preparation chamber 2, an ion / electron beam spot detector 17, an ultraviolet light detector 18, an X-ray detector 19, a vacuum gauge 21, and a spare interface 20 are respectively connected in the middle of the main cavity 4; the lower part of the main cavity 4 is a cylindrical structure, and a five-axis lifting sample stage 22 is provided at the lower part; a sample inlet 1 and a sample transfer rod 3 are connected to the sample preparation chamber 2.

[0017] The laser optical reflection component includes a high-energy pulsed laser light source 10 and a laser beam spot regulator 11; the H ion emission component includes an H ion source 5 and an H ion acceleration and focusing device 6; the He ion emission component includes a He ion source 7 and a He ion acceleration and focusing device 8.

[0018] A sample slot 23 is provided on the five-axis lifting sample stage 22, an electrically controlled openable and closable micro-hole cover is provided above the sample slot 23, and an electronic cryogenic cold stage is provided at the bottom of the sample slot 23, and the electronic cryogenic cold stage can realize temperature adjustment from 100K to 300K.

[0019] The specific operation steps are as follows:

[0020] 1. Load the specimen

[0021] Load the specimen onto the sample transfer rod 3 in the sample preparation chamber 2. If there is a circuit connection, first connect to the external circuit through the spare interface 20 on the main cavity 4.

[0022] 2. Calibrate each irradiation source:

[0023] (1) Close the sample inlet 1 of the sample preparation chamber 2, turn on the external vacuum equipment, and evacuate to 10 -8 Pa.

[0024] (2) Insert the X-ray detector 19, turn on the X-ray source 12, detect and adjust the position of the X-ray to the center of the detection area, calibrate the X-ray output intensity and the beam spot area, turn off the X-ray source 12, and withdraw the X-ray detector 19;

[0025] (3) Insert the ion / electron beam detector 17, turn on the H ion source 5, detect and adjust its distribution, beam current intensity, and beam spot area at the preset detection area position, and then turn off the H ion source 5; Calibrate the He ion source 7 and the electron beam current in the same way, and finally withdraw the ion / electron beam detector 17.

[0026] (4) Insert the X-ray detector 18, turn on the ultraviolet light source 9, detect and adjust the ultraviolet irradiation position to the center of the detection area, calibrate the ultraviolet irradiation output intensity and the spot area, and turn off the ultraviolet light source 9;

[0027] (5) Turn on the visible light source 15, detect and adjust the visible light irradiation position to the center of the detection area, calibrate the visible light irradiation output intensity and the spot area, turn off the visible light source, and withdraw the X-ray detector 19;

[0028] (6) Push the laser sample target into the center position of the detection area through the two-dimensional horizontal displacement stage. Turn on the high-energy pulsed laser light source 10 and the sample optical observation instrument 14, adjust the laser beam spot regulator 11, adjust the beam position so that its center coincides with the center of the preset simulation environment, detect the spot area and the spot pulse energy intensity of the pulsed laser through the optical observer, turn off the high-energy pulsed laser light source 10, and pull out the laser sample target;

[0029] 3. Push in the specimen

[0030] Push the specimen to be tested from the sample transfer rod 3 in the sample preparation chamber 2 to the five-axis lifting sample stage 22 in the main cavity and raise it to the center position of the preset detection area.

[0031] 4. Sample temperature control

[0032] Turn on the infrared heating source (24) in the environmental simulation chamber, heat the sample in the form of infrared irradiation, rely on the non-contact sample temperature detector 16 to measure the specimen temperature in real time, and use the PID regulator to control the output signal and power of the infrared heating source to maintain the specimen temperature stable at the set value.

[0033] 5. Simulate the irradiation environment

[0034] According to the specific irradiation environmental factors of the airless planet to be simulated, turn on the required irradiation sources (H ion source 5, He ion source 7, ultraviolet light source 9, X-ray source 12, electron gun 13, visible light source 15), adjust their output power to the set value, adjust the acceleration voltage and focusing voltage in the ion acceleration and focusing device to adjust the output energy range and irradiation range of the ion source, adjust the grating inside the ultraviolet light source to control the ultraviolet irradiation intensity, adjust the emission energy and beam spot voltage of the electron gun to adjust the electron beam current intensity and area, and adjust the grating inside the visible light source to control the visible light intensity, so as to simulate the overall radiation environment of the test sample. Irradiate the specimen sequentially or synergistically according to the set time.

[0035] 6. Micro-meteorite bombardment simulation

[0036] Turn on the high-energy pulsed laser light source 10, and adjust the laser bombardment position by adjusting the lens and mirror group inside the laser beam spot regulator 11. Cooperate with the movement of the sample stage position to realize the automatic bombardment program to simulate micro-meteorite bombardment.

[0037] 7. Sample stage adjustment

[0038] Control the position of the sample in the simulation environment by moving the five-axis sample lifting stage 22 in the horizontal and vertical directions, rotating in the horizontal plane, and tilting the Z axis, so as to simulate irradiation and bombardment at different angles. In addition, the sample temperature can also be adjusted using the sample slot 23 on the five-axis sample lifting stage 22 to simulate the low-temperature environment when the sample is not irradiated by the sun.

Claims

1. A comprehensive environmental simulation device for the surface of an airless celestial body, characterized in that: It includes a main cavity (4), the top of the main cavity (4) is a hemispherical structure, and a laser optical reflection component is provided at the hemispherical top of the main cavity (4); an H ion emission component, a He ion emission component, an ultraviolet light source (9), an X-ray source (12), a speckle electron gun (13), a sample optical observator (14), a visible light source (15), an infrared heating source (24) and a non-contact sample temperature detector (16) are also provided on the upper part of the hemisphere of the main cavity (4); a sample preparation chamber (2), an ion / electron beam spot detector (17), an ultraviolet light detector (18), an X-ray detector (19), a vacuum gauge (21) and a spare interface (20) are respectively connected to the middle part of the main cavity (4); the lower part of the main cavity (4) is a cylindrical structure, and a five-axis lifting sample stage (22) is provided at the lower part; a sample inlet (1) and a sample transfer rod (3) are connected to the sample preparation chamber (2); a sample slot (23) is provided on the five-axis lifting sample stage (22), an electrically controlled openable and closable microporous cover is provided above the sample slot (23), and an electronic cryogenic cold stage is provided at the bottom of the sample slot (23), and the electronic cryogenic cold stage can realize temperature regulation from 100K to 300K.

2. The comprehensive environmental simulation device for the surface of airless celestial bodies according to claim 1, wherein: The laser optical reflection component includes a high-energy pulsed laser light source (10) and a laser beam spot regulator (11); the H ion emission component includes an H ion source (5) and an H ion acceleration and focusing device (6); the He ion emission component includes a He ion source (7) and a He ion acceleration and focusing device (8).

3. A method of using a comprehensive environmental simulation device for the surface of an airless celestial body as described in claim 1, characterized in that: The cavity is evacuated by a vacuum device to a vacuum degree of above 10 -8 Pa; the sample is loaded into the lifting sample stage, and the sample temperature is adjusted in the range of 100 - 500K by electronic refrigeration and infrared heating; one or several of H ions, He ions, X-rays, extreme ultraviolet, visible light or high-energy pulsed lasers are used for individual irradiation or combined irradiation and bombardment, so as to achieve the purpose of simulating the surface environment of an airless planet.

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