Lunar dust interference effect test platform suitable for vacuum environment and use method thereof

Abstract

The invention discloses a lunar dust interference effect test platform suitable for a vacuum environment and a use method of the lunar dust interference effect test platform, and relates to the technical field of aerospace engineering ground simulation tests.The platform comprises a vacuum container system, a measuring system and a dustproof system; maintaining the normal-pressure and normal-temperature working state of the camera; the measurement system integrates a P IV camera, three high-speed cameras and a heat flow sensor, and realizes the multi-dimensional measurement of the moony dust excitation height / speed / impact range, the erosion pit three-dimensional reconstruction and the engine aerodynamic heat effect. The dustproof system adopts a high-transmittance acrylic dustproof cover and a vacuum gauge for differential pressure monitoring, so that lunar dust is prevented from polluting the heat sink, and the safety of the cover body is protected. The problems of pollution and single measurement of a vacuum system in the prior art are solved, multi-physical-quantity collaborative testing is achieved, key test data are provided for design of the lunar lander, and the method has engineering application value.

Description

Technical Field

[0001] The present invention relates to the technical field of ground simulation tests for aerospace engineering, and in particular to a lunar dust interference effect test platform suitable for a vacuum environment and a method for using the platform. Background Art

[0002] During the lunar landing process, the high-temperature and high-pressure combustion gas generated by the lander's engine expands and diffuses to form a plume and further interacts with the lunar surface, which will have a strong comprehensive effect on the lander itself. The reflection of the plume and the lunar surface will produce a large aerodynamic interference force and aerodynamic heat on the lander itself. At the same time, the plume scours and stirs up lunar dust, and the plume impacts and erodes the lunar surface. These phenomena affect each other.

[0003] The existing technology faces the following problems: During lunar landing, the reflection of the plume and the lunar surface will cause significant aerodynamic thermal interference on the lander body. At the same time, the plume will scour and stir up lunar dust, and the plume will impact and erode the lunar surface. Therefore, it is necessary to conduct ground simulation tests of the combined effects of real engine gas and lunar dust. However, the design and application of existing test and measurement systems have two shortcomings:

[0004] (1) Stirred lunar dust will contaminate the vacuum system. The vacuum system uses a multi-stage vacuum pump set and liquid nitrogen / liquid helium cryogenic heat sinks to maintain a high dynamic vacuum level in the cabin under multi-engine operation. The heat sink is made of porous metal. The stirred lunar dust generated during the ground simulation test of the engine's real gas and lunar dust combined effect will contaminate the heat sink surface, seriously affecting the vacuum level in the cabin.

[0005] (2) Single measurement data. During a lunar landing, the reflection of the plume and the lunar surface will produce a large aerodynamic thermal disturbance on the lander itself. At the same time, the plume will scour the lunar dust and the plume will impact and erode the lunar surface.

[0006] In view of this, this application is hereby filed. Summary of the Invention

[0007] The purpose of the present invention is to provide a lunar dust interference effect test platform suitable for a vacuum environment and a method of using the same, so as to solve the problems raised in the above-mentioned background technology.

[0008] In order to solve the above technical problems, this patent aims at the problem of testing the comprehensive effects of lunar dust on single and multiple engines with real gas. It invents a lunar dust interference effect test platform in a vacuum environment. The platform can measure the evolution of simulated lunar dust surface erosion pits, the size of the engine aerodynamic heat, and the height, speed and impact range of lunar dust under the action of real gas from multiple engines.

[0009] The present invention provides a lunar dust interference effect test platform suitable for a vacuum environment, comprising:

[0010] Vacuum container system: used to create experimental vacuum conditions and support equipment connection, including pressure vessel, PIV camera connection cable through-cabin flange, high-speed camera connection cable through-cabin flange, PLC&PXI cable through-cabin flange, camera vacuum protection cover and nitrogen cylinder;

[0011] Measurement system: used to obtain the parameters of the lunar dust interference effect, including a PIV camera, a high-speed camera, a heat flow sensor, a shadowless lamp, a PIV camera image acquisition and processing system, a heat flow acquisition system, a high-speed camera image acquisition and processing system, and a stabilized power supply;

[0012] Dust protection system: used to prevent lunar dust from contaminating the vacuum system, including lunar dust cover and vacuum gauge.

[0013] Through multi-system integrated design, comprehensive simulation of lunar dust interference effects and multi-dimensional data measurement in a vacuum environment are achieved, solving the problem of single function and susceptibility to lunar dust contamination in existing technologies.

[0014] Furthermore, in the vacuum container system, the pressure vessel has a size of Φ5.2m×12.5m, and the effective experimental space of the liquid nitrogen cryogenic pump is 138m 3 (Φ4.2m×12m), liquid nitrogen cold plate area 305m 2 The PIV camera cable and high-speed camera cable penetration flanges utilize standard LF250 flanges, secured to the pressure vessel with calipers and connected to the camera vacuum housing via a Φ40 bellows. The PIV camera cable penetration flange features two through-holes for connecting two PIV camera cables, while the high-speed camera cable penetration flange features three through-holes for connecting three high-speed camera cables. All five through-holes connect to nitrogen cylinders to maintain a constant operating temperature for the cameras. The PLC & PXI cable penetration flange features Y27A-37 and Y27-55 push / pull circular electrical connector sockets, respectively used for PLC & PXI cables for the heat flow sensor and vacuum gauge, and for the PLC & PXI cable for the voltage-regulated power supply, which powers the shadowless lamp. The standardized flange interface and nitrogen temperature control design ensure stable camera operation under normal pressure and temperature, preventing equipment failures caused by vacuum environments or overheating and improving test reliability.

[0015] Furthermore, the measurement system features a PIV camera with a maximum resolution of 2756×2208 pixels. The PIV camera image acquisition and processing system measures the height, velocity, and impact range of lunar dust. Three high-speed cameras, each with a maximum resolution of 1024×1024 pixels, are used. Two binocular high-speed cameras on top capture the three-dimensional coordinates of feature points, while a single high-speed camera on the bottom captures particle velocity. The high-speed camera image acquisition and processing system reconstructs the crater profile and depth in three dimensions and plots the particle trajectory. A GD series heat flux sensor is attached to the test engine, and the heat flux acquisition system measures the thermal effects of the interaction between the combustion gas and lunar dust. Shadowless lamps are arranged circumferentially around the lunar dust container. Light source limiters restrict the passage of monochromatic light with the same wavelength as the laser from the velocity measurement subsystem, and the system is powered by a regulated power supply. The integration of PIV, high-speed photography, and heat flux sensors enables non-contact and contact-based measurements of lunar dust trajectory, crater evolution, and aerodynamic thermal effects. This comprehensive data dimension enhances the accuracy and reliability of the test results.

[0016] Furthermore, the dust-proof system features a lunar dust cover constructed from a highly transparent acrylic sheet. Throughholes are reserved for the camera vacuum cover and the shadowless lamp, and the gap between the camera vacuum cover and the lunar dust cover is filled with multiple layers of sponge. A vacuum gauge is installed inside the lunar dust cover to monitor the pressure inside the cover in real time, adjusting the vacuum pump speed to prevent damage to the cover and contamination of the heat sink. The highly transparent dust cover, combined with a sponge seal and differential pressure monitoring design, prevents lunar dust from contaminating the vacuum system's heat sink and protects the cover from damage due to internal and external pressure differentials, ensuring test safety and maintaining a stable vacuum level within the chamber.

[0017] A method for using a lunar dust interference effect test platform suitable for a vacuum environment comprises the following steps:

[0018] Start the regulated power supply and signal acquisition system to ensure the normal operation of the shadowless lamp and collect signals from the heat flow sensor and vacuum gauge;

[0019] Start the PIV camera and high-speed camera and calibrate them to ensure that the test object is in the center of the field of view;

[0020] Start the vacuum pump group and pass nitrogen gas through the nitrogen bottle to the camera vacuum protection cover to cool it down, and monitor the pressure difference between the inside and outside of the lunar dust cover;

[0021] Real-time collection of lunar dust agitation process data and engine thermal effect data;

[0022] After data collection is completed, shut down the system and wait for the cabin pressure to balance with the atmospheric environment.

[0023] Standardized operating procedures ensure that all systems work together. Through pre-start calibration, real-time monitoring and pressure differential control, test efficiency and data acquisition stability are improved, avoiding test failures due to operational errors.

[0024] Furthermore, starting the regulated power supply and signal acquisition system specifically involves starting the regulated power supply to enable the shadowless lamp to operate normally, while simultaneously starting the PXI system to collect signals from the heat flow sensor and vacuum gauge. Initializing the light source and sensor signal acquisition in advance ensures data synchronization during the test and avoids data loss due to equipment startup delays.

[0025] Furthermore, the process of activating and calibrating the PIV camera and high-speed camera specifically involves activating the PIV camera and high-speed camera, activating the PIV camera image acquisition and processing system and the high-speed camera image acquisition and processing system after the equipment stabilizes, and calibrating the cameras to ensure that the test object is centered in the field of view and that images are captured normally. This warm-up and field of view calibration eliminates initial camera state deviations, ensuring the accuracy and effectiveness of image acquisition and providing a reliable data foundation for subsequent 3D reconstruction and trajectory analysis.

[0026] Furthermore, the real-time collection of lunar dust agitation data and engine thermal effects involves: PIV cameras measure the height, velocity, and impact radius of the lunar dust agitation; two high-speed cameras on the upper side capture the 3D coordinates of the crater's contour and depth and perform 3D reconstruction of the geometry, while a single high-speed camera on the lower side measures the particle's trajectory and velocity; and a heat flux sensor measures the aerodynamic thermal effects of the interaction between the plume and lunar dust at the engine base in real time. This simultaneous, real-time data collection from multiple devices enables dynamic tracking of multiple physical quantities related to the lunar dust interference effect. Combined with 3D reconstruction and trajectory analysis, this allows for a comprehensive assessment of the plume's mechanical and thermal effects, erosion and dusting, and transport effects, providing critical data support for lunar lander design.

[0027] Compared with the prior art, the present invention has the following beneficial effects:

[0028] 1. The test platform can protect the vacuum experiment container to prevent the contamination of the heat sink inside the container by the stirred-up lunar dust. At the same time, a vacuum gauge is installed inside the dust cover to monitor the internal pressure in real time to avoid damage to the dust cover due to excessive pressure difference between the inside and the outside.

[0029] 2. The system integrates a variety of contact and non-contact measurement equipment, and can obtain various types of data in ground simulation tests of the comprehensive effects of real engine gas and lunar dust, including the evolution of simulated lunar dust surface erosion pits, the size of the engine's aerodynamic heat, and the height, speed and impact range of lunar dust agitation. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 This is a two-dimensional overall schematic diagram of a lunar dust interference effect test platform suitable for a vacuum environment;

[0031] Figure 2 This is a schematic diagram of the overall cabin system in a lunar dust interference effect test platform suitable for a vacuum environment;

[0032] Figure 3 This is a front view of the installation of a high-speed camera in a lunar dust interference effect test platform suitable for a vacuum environment;

[0033] Figure 4 This is a top view of the high-speed camera installed in a lunar dust interference effect test platform suitable for a vacuum environment.

[0034] In the picture:

[0035] 101. Pressure vessel; 102. PIV camera connection line flange; 103. High-speed camera connection line flange; 104. PLC & PXI cable flange; 105. Camera vacuum protection cover; 106. Nitrogen cylinder;

[0036] 201. PIV camera; 202. High-speed camera; 203. Heat flow sensor; 204. Shadowless lamp; 205. PIV camera image acquisition and processing system; 206. Heat flow acquisition system; 207. High-speed camera image acquisition and processing system; 208. Regulated power supply;

[0037] 301. Lunar dust cover; 302. Vacuum gauge. DETAILED DESCRIPTION

[0038] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. 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 making creative efforts are within the scope of protection of the present invention.

[0039] See also Figure 1-4 The present invention provides a technical solution: a lunar dust interference effect test platform suitable for a vacuum environment and a method for using the same, comprising:

[0040] 1. Composition of the test platform

[0041] This embodiment provides a lunar dust interference effect test platform suitable for a vacuum environment, specifically including the following systems and components:

[0042] (1) Vacuum container system

[0043] 1. Pressure vessel 101: used to create experimental vacuum conditions, with dimensions of Φ5.2m×12.5m, equipped with a liquid nitrogen cryogenic pump inside, and an effective experimental space of 138m3 (Φ4.2m×12m), liquid nitrogen cold plate area 305m 2 .

[0044] 2. Penetration flange assembly:

[0045] PIV camera cable penetration flange 102: This flange utilizes a standard LF250 design and is secured to pressure vessel 101 via clamps. It features two through-holes for threading the cables from two PIV cameras 201, ensuring normal pressure operation. The flange is connected to the camera vacuum housing 105 via a Φ40 bellows.

[0046] High-speed camera cable penetration flange 103: Also using a standard LF250 flange, it is fixed to the pressure vessel 101 and has three through-holes for threading the cables of the three high-speed cameras 202, allowing the cameras 202 to operate at atmospheric pressure. It is connected to the camera vacuum protection cover 105 via a Φ40 corrugated tube. All five through-holes (2+3) are connected to nitrogen cylinders 106, which supply nitrogen to maintain a normal camera temperature and prevent overheating and shutdown.

[0047] PLC & PXI cable entry flange 104: Equipped with Y27A-37 and Y27-55 push / pull circular electrical connector sockets. The Y27A-37 socket is used for routing the PLC & PXI cables for the thermal flow sensor 203 and vacuum gauge 302, while the Y27-55 socket is used for routing the PLC & PXI cables for the voltage regulator 208, which supplies power to the shadowless lamp 204.

[0048] 3. Camera vacuum protection cover 105: connected to the PIV camera connection line through the cabin flange 102 and the high-speed camera connection line through the cabin flange-103 through a bellows to form a normal pressure working space for the camera.

[0049] 4. Nitrogen bottle 106: Nitrogen is introduced into the camera protective cover 105 through the through-hole of the cabin flange to maintain the camera working environment at normal temperature.

[0050] (2) Measurement system

[0051] 1. PIV cameras 201: Two cameras, with a maximum resolution of 2756 × 2208 pixels, measure the height, velocity, and impact range of lunar dust through the PIV camera image acquisition and processing system 205.

[0052] 2. High-speed cameras 202: Three in total, with a maximum resolution of 1024×1024 pixels. The top two are binocular high-speed cameras, used to obtain the 3D coordinates of characteristic points such as pit contours and depth; the bottom one is a monocular high-speed camera, used to obtain particle velocity. The accompanying high-speed camera image acquisition and processing system 207 enables 3D reconstruction of pit geometry, particle trajectory mapping, and velocity calculation.

[0053] 3. Heat flux sensor 203: Use the GD series, attached to the test engine, and measure the thermal effect on the engine when the gas interacts with lunar dust through the heat flux acquisition system 206.

[0054] 4. Shadowless lamp 204: It is arranged circumferentially around the lunar dust container. A limiting glass is installed on the light source to limit the passage of monochromatic light with the same wavelength as the laser of the speed measurement subsystem to avoid interference with the PIV camera 201. It is powered by a stabilized power supply 208.

[0055] 5. Supporting processing system and power supply: including PIV camera image acquisition and processing system 205, heat flow acquisition system 206, high-speed camera image acquisition and processing system 207 and stabilized power supply 208.

[0056] (3) Dust prevention system

[0057] 1. Moon dust cover 301: It is constructed with high-transmittance acrylic board. Through holes are reserved according to the diameters of the camera vacuum protective cover 105 and the shadowless lamp 204. The gap between the protective cover and the dust cover is filled with multiple layers of sponge to prevent moon dust from overflowing.

[0058] 2. Vacuum gauge 302: Installed inside the lunar dust cover 301, it monitors the pressure inside the cover in real time and adjusts the vacuum pump speed according to the pressure difference between the inside and outside to prevent the dust cover from being damaged by the pressure difference and causing heat sink contamination.

[0059] 2. How to use the test platform

[0060] Start the device and signal acquisition

[0061] 1. Turn on the stabilized power supply 208 to ensure that the shadowless lamp 204 emits light normally and eliminates the shadows of devices such as the nozzle fixing platform.

[0062] 2. Start the PXI system, collect the initial signals of the heat flow sensor 203 and the vacuum gauge 302, and confirm that the sensors are working properly.

[0063] Two-camera startup and calibration

[0064] 1. Start the two PIV cameras 201 and the three high-speed cameras 202 in sequence, and wait for the equipment to complete self-test and enter a stable working state (about 5 minutes).

[0065] 2. Start the PIV camera image acquisition and processing system 205 and the high-speed camera image acquisition and processing system 207, calibrate the camera's field of view using the calibration plate, and adjust the camera angle and position to ensure that the simulated lunar dust surface and the engine of the test object are in the center of the field of view, and the image is clear and without distortion.

[0066] 3. Vacuum environment establishment and equipment protection

[0067] 1. Start the vacuum pump group to evacuate the pressure vessel 101. At the same time, open the valve of the nitrogen bottle 106 and introduce nitrogen into the camera vacuum protective cover 105 to maintain the camera operating temperature at 25±5℃ to avoid malfunction due to low temperature in the vacuum environment or heating of the equipment.

[0068] 2. Real-time monitoring of the vacuum gauge 302 reading. When the pressure difference between the inside and outside of the dust cover 301 exceeds 10Pa, the vacuum pump speed is automatically adjusted to ensure the pressure balance inside and outside the dust cover to prevent the acrylic plate from breaking due to excessive pressure difference.

[0069] (4) Data Collection

[0070] 1. Dynamic measurement of lunar dust agitation: PIV camera 201 captures images at a frequency of 1000 frames per second, and calculates the motion trajectory of lunar dust particles through particle image velocimetry (PIV) technology to obtain the agitation height, velocity and impact range (error ±5%).

[0071] 2. Erosion pit evolution and particle velocity measurement: The two upper high-speed cameras 202 simultaneously shoot at a frequency of 5000 frames / second, and the three-dimensional contour and depth of the erosion pit are reconstructed using a binocular vision algorithm (accuracy ±0.5mm); the lower high-speed camera 202 shoots particle motion at a frequency of 10,000 frames / second, and the particle excitation velocity is calculated based on the time series (accuracy ±2%).

[0072] 3. Aerodynamic thermal effect measurement: The heat flux sensor 203 measures the heat flux density at the bottom of the engine in real time at a sampling frequency of 200 Hz, and the data is recorded by the heat flux acquisition system 206 with a resolution of 0.1 kW / m 2 .

[0073] 5. End of the test and system shutdown

[0074] 1. After data collection is completed, turn off the test engine and stop gas injection.

[0075] 2. Turn off the PIV camera 201, high-speed camera 202 and their supporting processing systems in sequence, and disconnect the regulated power supply 208.

[0076] 3. Turn off the vacuum pump group, stop vacuuming, and close the valve 106 of the nitrogen bottle at the same time.

[0077] 4. Monitor the reading of the vacuum gauge 302 in real time. When the pressure in the pressure vessel 101 is consistent with the atmospheric pressure (pressure difference ≤ 1 Pa), shut down the PXI system, remove the equipment connection line, and complete the test.

[0078] In summary, the lunar dust interference effect test platform suitable for a vacuum environment and its use method provided by the present invention effectively solve the problem of single lunar dust contamination vacuum system and measurement function in the prior art through the innovative integration of vacuum container system, measurement system and dust protection system. The platform can not only simulate the interaction process between lunar lander engine plume and lunar dust in a high vacuum environment, but also synchronously obtain key parameters such as lunar dust agitation trajectory, crater evolution characteristics and aerodynamic thermal effect through multiple types of measuring equipment, providing comprehensive experimental data support for in-depth research on plume thermodynamic effect, erosion dusting effect and transport effect. The pressure difference monitoring and sealing design of the dust protection system ensure the long-term stable operation of the vacuum system and improve the safety and reliability of the test. This invention provides an important technical means for the engineering design and optimization of lunar landers, and has significant engineering application value and innovation.

Claims

1. A lunar dust interference effect test platform suitable for vacuum environment, characterized by: include: Vacuum container system: used to create experimental vacuum conditions and support equipment connection, including pressure container (101), PIV camera connection line through-cabin flange (102), high-speed camera connection line through-cabin flange (103), PLC & PXI cable through-cabin flange (104), camera vacuum protection cover (105) and nitrogen bottle (106); A measurement system for obtaining lunar dust interference effect parameters, comprising a PIV camera (201), a high-speed camera (202), a heat flow sensor (203), a shadowless lamp (204), a PIV camera image acquisition and processing system (205), a heat flow acquisition system (206), a high-speed camera image acquisition and processing system (207), and a stabilized power supply (208); Dust prevention system: used to prevent lunar dust from contaminating the vacuum system, including a lunar dust cover (301) and a vacuum gauge (302).

2. The lunar dust interference effect test platform suitable for a vacuum environment according to claim 1, characterized in that: In the vacuum container system, the pressure container (101) has a size of Φ5.2m×12.5m; the PIV camera connection line through-cabin flange (102) and the high-speed camera connection line through-cabin flange (103) adopt standard LF250 flanges, which are fixed to the pressure container (101) by calipers and connected to the camera vacuum protection cover (105) by a Φ40 bellows; the PIV camera connection line through-cabin flange (102) is provided with two through holes for connecting two PIV camera connection lines, and the high-speed camera connection line is passed through The cabin flange (103) is provided with three through holes for connecting the cables of three high-speed cameras, and all five through holes are connected to nitrogen bottles (106) to maintain the normal temperature working environment of the cameras; the PLC&PXI cable cabin flange (104) is provided with Y27A-37 core and Y27-55 core push / pull type circular electrical connector sockets, which are respectively used for the PLC&PXI cables of the heat flow sensor (203), the vacuum gauge (302) and the PLC&PXI cables of the voltage-stabilized power supply (208) to pass through the cabin to power the shadowless lamp (204).

3. The lunar dust interference effect test platform suitable for a vacuum environment according to claim 1, characterized in that: In the measurement system, the height, speed and impact range of the lunar dust are measured by a PIV camera image acquisition and processing system (205); there are three high-speed cameras (202), two binocular high-speed cameras (202) on the upper side obtain the three-dimensional spatial coordinates of feature points, and a single high-speed camera (202) on the lower side obtains the particle movement speed; the high-speed camera image acquisition and processing system (207) performs three-dimensional reconstruction of the erosion pit contour and depth and draws the particle movement trajectory; the heat flow sensor (203) is attached to the test engine, and the heat flow acquisition system (206) measures the thermal effect of the interaction between the gas and the lunar dust; the shadowless lamp (204) is arranged circumferentially around the lunar dust container, and the light source is set with a limit glass to limit the passage of monochromatic light with the same wavelength as the laser of the speed measurement subsystem, and is powered by a stabilized power supply (208).

4. The lunar dust interference effect test platform suitable for a vacuum environment according to claim 1, characterized in that: In the dustproof system, the moon dust cover (301) is constructed of a high-transmittance acrylic plate, corresponding through holes are reserved according to the calibers of the camera vacuum protection cover (105) and the shadowless lamp (204), and the gap between the camera vacuum protection cover (105) and the moon dust cover (301) is filled with multiple layers of sponge; a vacuum gauge (302) is installed on the inner side of the moon dust cover (301) to monitor the pressure inside the cover in real time to adjust the vacuum pump pumping speed, thereby preventing damage to the dust cover and heat sink contamination.

5. A method for using a lunar dust interference effect test platform suitable for a vacuum environment, characterized by: The following steps are involved: Starting the voltage-stabilized power supply (208) and the signal acquisition system to ensure that the shadowless lamp (204) operates normally and to collect signals from the heat flow sensor (203) and the vacuum gauge (302); Start the PIV camera (201) and the high-speed camera (202) and calibrate them to ensure that the test object is in the center of the field of view; Start the vacuum pump group and introduce nitrogen gas into the camera vacuum protection cover (105) through the nitrogen bottle (106) to cool it down, and monitor the pressure difference between the inside and outside of the lunar dust cover (301); Real-time collection of lunar dust agitation process data and engine thermal effect data; After data collection is completed, shut down the system and wait for the cabin pressure to balance with the atmospheric environment.

6. The method for using the lunar dust interference effect test platform suitable for a vacuum environment as claimed in claim 5, characterized in that: The starting of the voltage-stabilized power supply (208) and the signal acquisition system specifically includes: starting the voltage-stabilized power supply (208) to enable the shadowless lamp (204) to work normally, and simultaneously starting the PXI system to acquire signals from the heat flow sensor (203) and the vacuum gauge (302).

7. The method for using the lunar dust interference effect test platform suitable for a vacuum environment as claimed in claim 5, characterized in that: The method of starting the PIV camera (201) and the high-speed camera (202) and performing calibration is specifically as follows: starting the PIV camera (201) and the high-speed camera (202), starting the PIV camera image acquisition and processing system (205) and the high-speed camera image acquisition and processing system (207) after the equipment is stable, and calibrating the cameras to ensure that the test object is in the center of the field of view and the image is captured normally.

8. The method for using the lunar dust interference effect test platform suitable for a vacuum environment as claimed in claim 5, characterized in that: The real-time collection of lunar dust agitation process data and engine thermal effect data is specifically as follows: a PIV camera (201) measures the height, speed and impact range of lunar dust agitation; two upper high-speed cameras (202) obtain the three-dimensional spatial coordinates of the erosion pit contour and depth and perform three-dimensional reconstruction of geometric information, and a lower single high-speed camera measures the particle motion trajectory and speed; a heat flow sensor (203) measures in real time the aerodynamic thermal effect of the mutual interference of the plume lunar dust at the bottom of the engine.

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