A method and device for measuring dynamic dust emission from lunar plume during soft landing of spacecraft

Abstract

The present application relates to a method and device for measuring the dynamic dust emission of the lunar plume during the soft landing of a spacecraft. The short-circuit current of the solar cell, the lunar surface ambient temperature and the overall brightness value of the lunar surface measured by the dynamic dust emission of the lunar plume are collected; the extinction factor of the solar cell measured by the dynamic dust emission of the lunar plume is calculated based on the short-circuit current of the solar cell; the mass of the lunar surface dust erosion measured by the dynamic dust emission of the lunar plume is calculated based on the short-circuit current of the solar cell, the lunar surface ambient temperature, the overall brightness value of the lunar surface and the extinction factor of the solar cell. The present application can measure the mass of the lunar surface dust erosion during the soft landing process of the lunar surface in situ on orbit. The mass of the lunar surface dust erosion reflects the characteristics of the dynamic dust emission process of the plume, thereby providing a technical basis for the subsequent spacecraft landing site selection and dust obstacle avoidance.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and more specifically, to a method and device for measuring dynamic dust emission from lunar plumes during a spacecraft soft landing process. Background Art

[0002] When a spacecraft soft-lands on the moon, the engine plume on the landing mechanism will hit the lunar weathering layer and raise a large amount of lunar dust. The raised lunar dust will reduce visibility and form erosion pits on the lunar surface, greatly reducing landing safety.

[0003] In order to solve the dust problem caused by the soft landing on the moon, the existing technology uses a single solar cell to measure the accumulated mass deposited on it to measure the moon dust. The sensor of this measurement method can only reflect the moon dust situation when the spacecraft lands through the accumulated mass of moon dust on the horizontally placed solar cell. The measured moon dust is the moon dust of charged dust suspended and deposited by photoelectrons in the solar wind, as well as the moon dust caused by human activities. There is also a method for determining the distribution of moon dust during the landing process on the moon in the existing technology. This method obtains the position information of the spacecraft at the current moment and the flow field data of the calculation domain, and describes how to find the moon dust information of the spacecraft at different positions through computational simulation methods.

[0004] The present application provides a method and device for measuring dynamic dust raised by lunar plumes during the soft landing of a spacecraft, which is completely different from the prior art. The present application can directly measure the dynamic dust raised during the soft landing of a spacecraft. Summary of the invention

[0005] The embodiments of the present application provide a method and device for measuring the dynamic dust emission of the lunar plume during the soft landing of a spacecraft. In order to have a basic understanding of some aspects of the disclosed embodiments, a simple summary is given below. This summary is not a general review, nor is it intended to identify key / important components or describe the scope of protection of these embodiments. Its only purpose is to present some concepts in a simple form as a preface to the detailed description that follows.

[0006] In a first aspect, the present application provides a method for measuring the dynamic dust emission of lunar plumes during a spacecraft soft landing process, the method comprising:

[0007] Collect the short-circuit current of solar cells, the ambient temperature of the lunar surface, and the overall brightness of the lunar surface measured by the dynamic dust emission of the lunar plume;

[0008] Calculating the solar cell extinction factor of the lunar plume dynamic dust measurement according to the solar cell short-circuit current;

[0009] The lunar surface dust erosion mass of the lunar surface plume dynamic dust measurement is calculated according to the short-circuit current of the solar cell, the lunar surface ambient temperature, the overall brightness value of the lunar surface and the extinction factor of the solar cell.

[0010] According to a preferred embodiment, the collection of the short-circuit current of the solar cell, the lunar surface ambient temperature and the overall brightness value of the lunar surface measured by the dynamic dust emission of the lunar plume includes:

[0011] Using a dynamic dust measurement sensor to collect the short-circuit current of the solar cell and the lunar surface ambient temperature measured by the dynamic dust of the lunar plume;

[0012] The overall brightness value of the lunar surface measured by the dynamic dust emission of the lunar plume is collected by a camera.

[0013] According to a preferred embodiment, the four dynamic dust measurement sensors are located at the same horizontal height and are respectively installed in the middle of the four quadrants of the landing mechanism; the four cameras are located at the same horizontal height and are respectively installed on the four landing legs of the landing mechanism; the central axes of the four cameras and the four dynamic dust measurement sensors are on the same straight line.

[0014] In a second aspect, the present application provides a device for measuring the dynamic dust emission of lunar plumes during a spacecraft soft landing process, the device comprising:

[0015] The acquisition module is used to collect the short-circuit current of solar cells, the ambient temperature of the lunar surface, and the overall brightness of the lunar surface for the dynamic dust measurement of the lunar plume;

[0016] An extinction factor calculation module, used to calculate the extinction factor of the solar cell for the lunar plume dynamic dust measurement according to the short-circuit current of the solar cell;

[0017] The erosion mass calculation module is used to calculate the lunar surface dust erosion mass of the lunar surface plume dynamic dust measurement according to the short-circuit current of the solar cell, the lunar surface ambient temperature, the overall brightness value of the lunar surface and the extinction factor of the solar cell.

[0018] According to a preferred embodiment, the acquisition module is specifically used for:

[0019] Using a dynamic dust measurement sensor to collect the short-circuit current of the solar cell and the lunar surface ambient temperature measured by the dynamic dust of the lunar plume;

[0020] The overall brightness value of the lunar surface measured by the dynamic dust emission of the lunar plume is collected by a camera.

[0021] According to a preferred embodiment, the four dynamic dust measurement sensors are located at the same horizontal height and are respectively installed in the middle of the four quadrants of the landing mechanism; the four cameras are located at the same horizontal height and are respectively installed on the four landing legs of the landing mechanism; the central axes of the four cameras and the four dynamic dust measurement sensors are on the same straight line.

[0022] In a third aspect, the present application provides a computer storage medium, which stores a plurality of instructions, and the instructions are suitable for being loaded by a processor and executing the above-mentioned method steps.

[0023] In a fourth aspect, the present application provides a terminal, which may include: a processor and a memory; wherein the memory stores a computer program, and the computer program is suitable for being loaded by the processor and executing the above-mentioned method steps.

[0024] The technical solution provided by this application may have the following beneficial effects:

[0025] In the present application, the method for measuring the dynamic dust emission of the lunar plume during the soft landing of the spacecraft collects the short-circuit current of the solar cell, the lunar surface ambient temperature and the overall brightness value of the lunar surface measured by the dynamic dust emission of the lunar plume; the extinction factor of the solar cell measured by the dynamic dust emission of the lunar plume is calculated according to the short-circuit current of the solar cell; the dust erosion mass of the lunar surface measured by the dynamic dust emission of the lunar plume is calculated according to the short-circuit current of the solar cell; the dynamic dust emission principle and sensor design of the measurement method described in the present application are completely different from those of the prior art. The present application describes a measurement scheme that uses an in-situ measurement sensor based on the extinction principle and a landing image coupling, which can realize the measurement of the characteristics of the lunar surface dust erosion mass and the like in the three-dimensional space of the lunar surface; the present application can measure the lunar surface dust erosion mass in the process of the soft landing of the lunar surface in-situ on orbit, and the lunar surface dust erosion mass reflects the characteristics of the dynamic dust emission process of the plume, thereby providing a technical basis for the subsequent spacecraft landing site selection and dust obstacle avoidance.

[0026] It is to be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the invention and, together with the description, serve to explain the principles of the invention.

[0028] Figure 1 It is a flow chart of a method for measuring dynamic dust emission from lunar plumes during a spacecraft soft landing process provided in an embodiment of the present application;

[0029] Figure 2This is a schematic diagram of the distribution of a dynamic dust measurement system for a method for measuring dynamic dust on the lunar surface plume during a spacecraft soft landing process provided in an embodiment of the present application;

[0030] Figure 3 It is a schematic diagram of the structure of a dynamic dust measurement sensor for a method for measuring dynamic dust on the lunar surface plume during a spacecraft soft landing process provided in an embodiment of the present application;

[0031] Figure 4 This is a schematic diagram of a device for measuring the dynamic dust emission of lunar plumes during a spacecraft soft landing process provided by an embodiment of the present application;

[0032] Figure 5 This is a terminal schematic diagram provided in an embodiment of the present application.

[0033] Reference numerals:

[0034] 1. first camera, 2. second camera, 3. third camera, 4. fourth camera, 5. first dynamic dust measurement sensor, 6. second dynamic dust measurement sensor, 7. third dynamic dust measurement sensor, 8. fourth dynamic dust measurement sensor; 51. first solar cell, 52. second solar cell, 53. third solar cell, 54. fourth solar cell;

[0035] 10000, acquisition module, 20000, extinction factor calculation module, 30000, erosion quality calculation module;

[0036] 1001. Processor, 1002. Communication bus, 1003. User interface, 1004. Network interface, 1005. Memory. DETAILED DESCRIPTION

[0037] The following description and the drawings sufficiently illustrate specific embodiments of the invention to enable those skilled in the art to practice them.

[0038] It should be clear that the described embodiments are only some embodiments of the present invention, not all 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.

[0039] When the following description refers to the drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Instead, they are only examples of systems and methods consistent with some aspects of the present invention as detailed in the attached claims.

[0040] In the description of the present invention, it should be understood that the terms "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances. In addition, in the description of the present invention, unless otherwise specified, "plurality" refers to two or more. "And / or" describes the association relationship of associated objects, indicating that three relationships may exist. For example, A and / or B can represent: A exists alone, A and B exist at the same time, and B exists alone. The character " / " generally indicates that the previously associated objects are in an "or" relationship.

[0041] The following will be combined with the attached Figure 1 -Attached Figure 3 , a method for measuring the dynamic dust emission of the lunar surface plume during the soft landing process of a spacecraft provided in an embodiment of the present application is introduced in detail.

[0042] See also Figure 1-3 The method of the embodiment of the present application may include the following steps:

[0043] The embodiment of the present application provides a method for measuring the dynamic dust emission of the lunar surface plume during the soft landing of a spacecraft on the lunar surface, which can be used to measure the dynamic dust emission of the lunar surface induced by the plume during the soft landing of a spacecraft on the lunar surface in situ, and corresponds to a dynamic dust emission measurement system. The entire dynamic dust emission measurement system is adapted to the high vacuum environment of the lunar surface and the temperature range of -100°C to 100°C, such as Figure 2 As shown, it includes: four dynamic dust measurement sensors and four cameras. The four dynamic dust measurement sensors are respectively a first dynamic dust measurement sensor 5, a second dynamic dust measurement sensor 6, a third dynamic dust measurement sensor 7, and a fourth dynamic dust measurement sensor 8; the four cameras are respectively a first camera 1, a second camera 2, a third camera 3, and a fourth camera 4.

[0044] Specifically, the four dynamic dust measurement sensors have the same structure. Each dynamic dust measurement sensor consists of four solar cells, four temperature sensors, a sensor bracket, a signal acquisition circuit and a control circuit. The solar cell sensor assembly consists of four solar cells; solar cells are also called solar cell sensors; a temperature sensor is required on the back of each solar cell sensor to measure the lunar surface ambient temperature in real time.

[0045] like Figure 3 As shown, each dynamic dust measurement sensor is equipped with a first solar cell 51, a second solar cell 52, a third solar cell 53, and a fourth solar cell 54. Figure 3The left and right sides of the figure show the dynamic dust measurement sensor in different directions. The structures and functions of these four solar cells are exactly the same. The solar cells are attached to the sensor bracket perpendicular to each other. The solar cells on each pasting plane should be attached to the center of the structural surface, and each edge of the solar cell should be parallel to each edge of the structural surface. Each solar cell is coated with a transparent lunar dust protection film with a thickness of about 120μm to 135μm to prevent the raised lunar dust from adhering to the surface of the solar cell and affecting the measurement results. The size of a single solar cell is 5cm×5cm, and the corresponding output short-circuit current range at no load should be 190mA to 220mA, and the data acquisition rate is 20 times / s.

[0046] The test indicators of the four cameras are the same. The four cameras are required to be able to observe lunar dust particles of 1mm in size at a height of 0.5m from the lunar surface, and the camera working frame rate is 20 frames / s. The field of view of the four cameras should cover the entire bottom of the landing mechanism.

[0047] In the embodiment of the present application, the four dynamic dust measurement sensors are located at the same horizontal height, and are respectively installed in the middle of the four quadrants of the landing mechanism, two by two are perpendicular, and the installation position is about 1.0m to 1.2m above the lunar surface; the four cameras are located at the same horizontal height, and are respectively installed on the four landing legs of the landing mechanism, and the vertical distance from the landing leg pads of the spacecraft is 5cm to 10cm; the four cameras and the central axes of the four dynamic dust measurement sensors are on the same straight line. The four cameras can work independently, and the four cameras can be used in combination with each other; the four dynamic dust measurement sensors can work independently, and the four dynamic dust measurement sensors can also be used in combination with each other; any dynamic dust measurement sensor and any camera can be used in combination to complete all measurement work during the descent process.

[0048] The four cameras in the embodiment of the present application need to be powered on once in the Earth-Moon transfer orbit and also need to be powered on once in the lunar orbit to ensure that all four cameras are working properly; the four dynamic dust measurement sensors need to be powered on once in the lunar orbit to ensure that each dynamic dust measurement sensor is working properly.

[0049] S100, collecting the short-circuit current of solar cells, the ambient temperature of the lunar surface and the overall brightness value of the lunar surface measured by the dynamic dust emission of the lunar plume, including: using a dynamic dust emission measurement sensor to collect the short-circuit current of solar cells and the ambient temperature of the lunar surface measured by the dynamic dust emission of the lunar plume; collecting the overall brightness value of the lunar surface measured by the dynamic dust emission of the lunar plume through a camera. The details are as follows:

[0050] Step S101, when the landing mechanism descends to a height of 1 km from the lunar surface, the dynamic dust measurement sensor and the camera are turned on at the same time;

[0051] Step S102: after powering on, it is necessary to detect whether each dynamic dust measurement sensor and camera is working properly. If all dynamic dust measurement sensors and cameras are working properly, directly jump to step S103. If there is a dynamic dust measurement sensor or camera that is not working properly, find the dynamic dust measurement sensor or camera with the problem, re-power it and test it until it works normally.

[0052] Step S103, calibrate the normal working dynamic dust measurement sensor under no-load, record the short-circuit current of the solar cell and the lunar surface ambient temperature of different solar cells; use I s0i (i=1-16) represents the solar cell short-circuit current of the i-th solar cell calibrated on-track under no-load, which is the initial output short-circuit current value; in this application, i represents the i-th solar cell;

[0053] Step S104, calibrating the normally working camera, and recording the overall brightness value of the lunar surface when there is no dust through the initial image taken by the camera;

[0054] Step S105: After ensuring that all dynamic dust measurement sensors and cameras are working properly, continuously record the short-circuit current of the solar cells of all dynamic dust measurement sensors, the lunar surface ambient temperature, and the overall brightness of the lunar surface reflected in the landing images taken by the camera when dust is present. The acquisition frequency of the short-circuit current of the solar cells, the lunar surface ambient temperature, and the overall brightness of the lunar surface is required to be 20 times / s. Record the short-circuit current of the solar cells, the lunar surface ambient temperature, and the overall brightness of the lunar surface output at different times until all cameras are turned off 10 to 15 minutes after the landing mechanism lands on the moon, and all dynamic dust measurement sensors are turned off 1 hour after landing on the moon. Use I si (i=1-16) represents the short-circuit current of the solar cell of the ith solar cell measured when the machine is turned on during the moon landing process; T i (i=1-16) represents the lunar surface ambient temperature of the i-th solar cell measured when the moon landing process of the above step S103 and the present step S105 is started, and X i (i=1-16) represents the overall brightness value of the moon surface of the i-th solar cell obtained when the moon landing process in the above step S104 and the present step S105 is started.

[0055] In the above process, the data collection times of the four dynamic dust measurement sensors and the four cameras correspond one to one, and they are time-calibrated respectively, so that the short-circuit current of the solar cell, the lunar surface ambient temperature and the overall brightness of the lunar surface measured at the same time are consistent.

[0056] S200: Calculate the solar cell extinction factor of the lunar plume dynamic dust measurement according to the short-circuit current of the solar cell.

[0057] The embodiment of the present application calculates the solar cell extinction factor of each solar cell on each dynamic dust measurement sensor within the time range from the start-up time to the shutdown time. The specific calculation method is: α i =I si / I s0i , α i represents the solar cell extinction factor of the i-th solar cell.

[0058] S300, calculating the lunar surface dust erosion mass of the lunar surface plume dynamic dust measurement according to the short-circuit current of the solar cell, the lunar surface ambient temperature, the overall brightness value of the lunar surface and the extinction factor of the solar cell.

[0059] The embodiment of the present application calculates the dust erosion mass of the lunar surface at different times according to the overall brightness value of the lunar surface at different times. The dust erosion mass of the lunar surface can be expressed as m i (i=1~16) indicates.

[0060] The overall brightness value of the lunar surface of the ith solar cell obtained when the moon landing process is started at different times, as well as the corresponding solar cell short-circuit current of the ith solar cell calibrated on-orbit under no-load, the solar cell short-circuit current of the ith solar cell measured when the moon landing process is started, the lunar surface ambient temperature of the ith solar cell measured when the moon landing process is started, and the solar cell extinction factor of the ith solar cell are obtained to obtain the function of the dust erosion mass on the lunar surface. The functional relationship is:

[0061] So far, we have completed the measurement of the plume dust characteristics at different landing altitudes during the spacecraft soft landing process, and quantitatively determined the plume dust mass, etc., to provide a design input basis for future spacecraft safe landing and dust pollution. The plume dust mass is the above-mentioned lunar surface dust erosion mass.

[0062] In the embodiment of the present application, the method for measuring the dynamic dust of the lunar plume during the soft landing of the spacecraft collects the short-circuit current of the solar cell, the lunar surface ambient temperature and the overall brightness value of the lunar surface measured by the dynamic dust of the lunar plume; the extinction factor of the solar cell measured by the dynamic dust of the lunar plume is calculated according to the short-circuit current of the solar cell; the lunar surface dust erosion mass measured by the dynamic dust of the lunar plume is calculated according to the short-circuit current of the solar cell, the lunar surface ambient temperature, the overall brightness value of the lunar surface and the extinction factor of the solar cell. The dynamic dust principle and sensor design of the measurement method described in the present application are completely different from the prior art. The present application describes a measurement scheme that uses an in-situ measurement sensor based on the extinction principle and a landing image coupling, which can realize the measurement of the characteristics of the lunar surface dust erosion mass in the three-dimensional space of the lunar surface; the present application can measure the lunar surface dust erosion mass in the process of the soft landing of the lunar surface in-situ on orbit, and the lunar surface dust erosion mass reflects the characteristics of the dynamic dust process of the plume, thereby providing a technical basis for the subsequent spacecraft landing site selection and dust obstacle avoidance.

[0063] The following are embodiments of the device of the present invention, which can be used to implement the method embodiments of the present invention. For details not disclosed in the device embodiments of the present invention, please refer to the method embodiments of the present invention.

[0064] See also Figure 4 , which shows a schematic diagram of the structure of a device for measuring the dynamic dust emission of lunar plumes during the soft landing of a spacecraft provided by an exemplary embodiment of the present invention. The device includes: a collection module 10000, an extinction factor calculation module 20000 and an erosion mass calculation module 30000.

[0065] The acquisition module 10000 is used to collect the short-circuit current of the solar cell, the lunar surface ambient temperature and the overall brightness value of the lunar surface for the dynamic dust measurement of the lunar plume;

[0066] An extinction factor calculation module 20000, for calculating the extinction factor of the solar cell for the lunar plume dynamic dust measurement according to the short-circuit current of the solar cell;

[0067] The erosion mass calculation module 30000 is used to calculate the lunar surface dust erosion mass of the lunar surface plume dynamic dust measurement according to the short-circuit current of the solar cell, the lunar surface ambient temperature, the overall brightness value of the lunar surface and the extinction factor of the solar cell.

[0068] According to a preferred embodiment, the acquisition module 10000 is specifically used for:

[0069] Using a dynamic dust measurement sensor to collect the short-circuit current of the solar cell and the lunar surface ambient temperature measured by the dynamic dust of the lunar plume;

[0070] The overall brightness value of the lunar surface measured by the dynamic dust emission of the lunar plume is collected by a camera.

[0071] According to a preferred embodiment, the four dynamic dust measurement sensors are located at the same horizontal height and are respectively installed in the middle of the four quadrants of the landing mechanism; the four cameras are located at the same horizontal height and are respectively installed on the four landing legs of the landing mechanism; the central axes of the four cameras and the four dynamic dust measurement sensors are on the same straight line.

[0072] It should be noted that the device for measuring the dynamic dust emission of the lunar surface plume during the soft landing of a spacecraft provided in the above embodiment only uses the division of the above functional modules as an example when executing the method for measuring the dynamic dust emission of the lunar surface plume during the soft landing of a spacecraft. In actual applications, the above functional distribution can be completed by different functional modules as needed, that is, the internal structure of the device can be divided into different functional modules to complete all or part of the functions described above. In addition, the device for measuring the dynamic dust emission of the lunar surface plume during the soft landing of a spacecraft provided in the above embodiment and the method for measuring the dynamic dust emission of the lunar surface plume during the soft landing of a spacecraft belong to the same concept. The implementation process thereof is detailed in the method embodiment and will not be repeated here.

[0073] In the embodiment of the present application, the dynamic dust measurement device of the lunar plume during the soft landing of the spacecraft collects the short-circuit current of the solar cell, the lunar surface ambient temperature and the overall brightness value of the lunar surface measured by the dynamic dust measurement of the lunar plume; according to the short-circuit current of the solar cell, the extinction factor of the solar cell measured by the dynamic dust measurement of the lunar plume is calculated; according to the short-circuit current of the solar cell, the lunar surface ambient temperature, the overall brightness value of the lunar surface and the extinction factor of the solar cell, the lunar surface dust erosion mass measured by the dynamic dust measurement of the lunar plume is calculated. The dynamic dust principle and sensor design of the measuring device described in the present application are completely different from the prior art. The present application describes a measurement scheme that uses an in-situ measurement sensor based on the extinction principle and a landing image coupling, which can realize the measurement of the characteristics of the lunar surface dust erosion mass in the three-dimensional space of the lunar surface; the present application can measure the lunar surface dust erosion mass in the process of the soft landing of the lunar surface in-situ on orbit, and the lunar surface dust erosion mass reflects the characteristics of the dynamic dust process of the plume, thereby providing a technical basis for the subsequent spacecraft landing site selection and dust obstacle avoidance.

[0074] The present invention also provides a computer-readable medium having program instructions stored thereon, which, when executed by a processor, implements the method for measuring the dynamic dust emission of lunar plumes during the soft landing process of a spacecraft provided in the above-mentioned method embodiments.

[0075] The present invention also provides a computer program product comprising instructions, which, when executed on a computer, enables the computer to execute the method for measuring the dynamic dust emission of lunar plumes during the soft landing of a spacecraft in each of the above-mentioned method embodiments.

[0076] See also Figure 5 , which is a schematic diagram of the structure of a terminal according to an embodiment of the present application. The terminal may include: at least one processor 1001, at least one network interface 1004, a user interface 1003, a memory 1005, and at least one communication bus 1002.

[0077] The communication bus 1002 is used to realize the connection and communication between these components.

[0078] The user interface 1003 may include a display screen (Display) and a camera (Camera), and the optional user interface 1003 may also include a standard wired interface and a wireless interface.

[0079] The network interface 1004 may optionally include a standard wired interface or a wireless interface (such as a WI-FI interface).

[0080] Among them, the processor 1001 may include one or more processing cores. The processor 1001 uses various interfaces and lines to connect various parts in the entire terminal, and executes various functions of the terminal and processes data by running or executing instructions, programs, code sets or instruction sets stored in the memory 1005, and calling data stored in the memory 1005. Optionally, the processor 1001 can be implemented in at least one hardware form of digital signal processing (Digital Signal Processing, DSP), field programmable gate array (Field-Programmable Gate Array, FPGA), and programmable logic array (Programmable Logic Array, PLA). The processor 1001 can integrate one or a combination of a central processing unit (Central Processing Unit, CPU), a graphics processing unit (Graphics Processing Unit, GPU) and a modem. Among them, the CPU mainly processes the operating system, user interface and application programs; the GPU is responsible for rendering and drawing the content to be displayed on the display screen; the modem is used to process wireless communications. It can be understood that the above-mentioned modem may not be integrated into the processor 1001, and it can be implemented separately through a chip.

[0081] Among them, the memory 1005 may include a random access memory (Random Access Memory, RAM) and may also include a read-only memory (Read-Only Memory). Optionally, the memory 1005 includes a non-transitory computer-readable storage medium. The memory 1005 can be used to store instructions, programs, codes, code sets or instruction sets. The memory 1005 may include a program storage area and a data storage area, wherein the program storage area may store instructions for implementing an operating system, instructions for at least one function (such as a touch function, a sound playback function, an image playback function, etc.), instructions for implementing the above-mentioned various method embodiments, etc.; the data storage area may store data involved in the above-mentioned various method embodiments, etc. The memory 1005 may optionally be at least one storage device located away from the aforementioned processor 1001. As Figure 5 As shown, the memory 1005 as a computer storage medium may include an operating system, a network communication module, a user interface module, and an application program for measuring the dynamic dust emission of the lunar plume during the soft landing of a spacecraft.

[0082] exist Figure 5 In the terminal shown, the user interface 1003 is mainly used to provide an input interface for the user and obtain the data input by the user; and the processor 1001 can be used to call the lunar surface plume dynamic dust measurement application program during the spacecraft soft landing process stored in the memory 1005, and specifically perform the following operations:

[0083] Collect the short-circuit current of solar cells, the ambient temperature of the lunar surface, and the overall brightness of the lunar surface measured by the dynamic dust emission of the lunar plume;

[0084] Calculating the solar cell extinction factor of the lunar plume dynamic dust measurement according to the solar cell short-circuit current;

[0085] The lunar surface dust erosion mass of the lunar surface plume dynamic dust measurement is calculated according to the short-circuit current of the solar cell, the lunar surface ambient temperature, the overall brightness value of the lunar surface and the extinction factor of the solar cell.

[0086] In one embodiment, when the processor 1001 executes the method of collecting the short-circuit current of the solar cell, the lunar surface ambient temperature and the overall brightness value of the lunar surface measured by the lunar plume dynamic dust emission, the processor 1001 specifically performs the following operations:

[0087] Using a dynamic dust measurement sensor to collect the short-circuit current of the solar cell and the lunar surface ambient temperature measured by the dynamic dust of the lunar plume; using a camera to collect the overall brightness value of the lunar surface measured by the dynamic dust of the lunar plume;

[0088] Among them, the four dynamic dust measurement sensors are located at the same horizontal height and are respectively installed in the middle of the four quadrants of the landing mechanism; the four cameras are located at the same horizontal height and are respectively installed on the four landing legs of the landing mechanism; the four cameras and the central axes of the four dynamic dust measurement sensors are on the same straight line.

[0089] In the embodiment of the present application, the method and device for measuring the dynamic dust of the lunar plume during the soft landing of the spacecraft collect the short-circuit current of the solar cell, the lunar surface ambient temperature and the overall brightness value of the lunar surface measured by the dynamic dust of the lunar plume; according to the short-circuit current of the solar cell, the extinction factor of the solar cell measured by the dynamic dust of the lunar plume is calculated; according to the short-circuit current of the solar cell, the lunar surface ambient temperature, the overall brightness value of the lunar surface and the extinction factor of the solar cell, the lunar surface dust erosion mass measured by the dynamic dust of the lunar plume is calculated. The dynamic dust principle and sensor design of the measurement method described in the present application are completely different from the prior art. The present application describes a measurement scheme that uses an in-situ measurement sensor based on the extinction principle and a landing image coupling, which can realize the measurement of the characteristics of the lunar surface dust erosion mass in the three-dimensional space of the lunar surface; the present application can measure the lunar surface dust erosion mass in the process of the soft landing of the lunar surface in-situ on orbit, and the lunar surface dust erosion mass reflects the characteristics of the dynamic dust process of the plume, thereby providing a technical basis for the subsequent spacecraft landing site selection and dust obstacle avoidance.

[0090] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiments can be implemented by instructing related hardware through a computer program, and the program can be stored in a computer-readable storage medium, and when the program is executed, it can include the processes of the embodiments of the above-mentioned methods. The storage medium can be a disk, an optical disk, a read-only storage memory, or a random access memory, etc.

[0091] The above disclosure is only the preferred embodiment of the present application, which certainly cannot be used to limit the scope of rights of the present application. Therefore, equivalent changes made according to the claims of the present application are still within the scope covered by the present application.

Claims

1. A method for measuring the dynamic dust emission of lunar plumes during a spacecraft soft landing, characterized in that: The following steps are involved: Collect the short-circuit current of solar cells, lunar surface ambient temperature and overall lunar surface brightness of the dynamic dust raised by the lunar plume during the soft landing of the spacecraft; Calculating the solar cell extinction factor of the lunar plume dynamic dust during the soft landing of the spacecraft according to the short-circuit current of the solar cell; The lunar surface dust erosion mass of the dynamic dust raised by the lunar surface plume during the soft landing of the spacecraft is calculated according to the short-circuit current of the solar cell, the lunar surface ambient temperature, the overall brightness value of the lunar surface and the extinction factor of the solar cell.

2. The method for measuring the dynamic dust emission of lunar plumes during the soft landing of a spacecraft according to claim 1, characterized in that: The short-circuit current of the solar cell, the lunar surface ambient temperature and the overall brightness value of the lunar surface collected during the soft landing of the spacecraft include: Using a dynamic dust measurement sensor to collect the short-circuit current of the solar cell and the lunar surface environment temperature of the dynamic dust of the lunar surface plume during the soft landing of the spacecraft; The camera is used to collect the overall brightness value of the lunar surface caused by the dynamic dust raised by the lunar plume during the soft landing process of the spacecraft.

3. The method for measuring the dynamic dust emission of lunar plumes during the soft landing of a spacecraft according to claim 2, characterized in that: The four dynamic dust measurement sensors are located at the same horizontal height and are respectively installed in the middle of the four quadrants of the landing mechanism; the four cameras are located at the same horizontal height and are respectively installed on the four landing legs of the landing mechanism; the central axes of the four cameras and the four dynamic dust measurement sensors are on the same straight line.

4. A device for measuring the dynamic dust emission of lunar plumes during the soft landing of a spacecraft, characterized in that: include: The acquisition module is used to collect the short-circuit current of the solar cell, the lunar surface ambient temperature and the overall brightness of the lunar surface during the soft landing of the spacecraft; An extinction factor calculation module, used to calculate the extinction factor of the solar cell caused by the dynamic dust raised by the lunar plume during the soft landing of the spacecraft according to the short-circuit current of the solar cell; The erosion mass calculation module is used to calculate the lunar surface dust erosion mass of the lunar surface plume dynamic dust during the soft landing process of the spacecraft according to the short-circuit current of the solar cell, the lunar surface ambient temperature, the overall brightness value of the lunar surface and the extinction factor of the solar cell.

5. The device for measuring the dynamic dust emission of lunar plume during the soft landing of a spacecraft according to claim 4, characterized in that: The acquisition module is specifically used for: Using a dynamic dust measurement sensor to collect the short-circuit current of the solar cell and the lunar surface environment temperature of the dynamic dust of the lunar surface plume during the soft landing of the spacecraft; The camera is used to collect the overall brightness value of the lunar surface caused by the dynamic dust raised by the lunar plume during the soft landing process of the spacecraft.

6. The device for measuring the dynamic dust emission of lunar plumes during the soft landing of a spacecraft according to claim 5, characterized in that: The four dynamic dust measurement sensors are located at the same horizontal height and are respectively installed in the middle of the four quadrants of the landing mechanism; the four cameras are located at the same horizontal height and are respectively installed on the four landing legs of the landing mechanism; the central axes of the four cameras and the four dynamic dust measurement sensors are on the same straight line.

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