Spacecraft image recording dial plate, management method and management system

Abstract

The invention relates to the technical field of spacecraft image arrangement, in particular to a spacecraft image recording dial plate, a management method and a management system.The spacecraft image recording dial plate comprises a first recognition part, a second recognition part and a covering body, and the first recognition part is provided with a marker; at least one information group is arranged on the second identification part, and each information group comprises a plurality of sub-information carriers; the covering body is connected with the first recognition part and used for covering the second recognition part, the covering body is provided with a recognition window, and the covering body and the second recognition part can make any sub-information carrier located at the recognition window by generating relative movement; the information of the spacecraft image to be shot can be clearly displayed in the dial plate by rotating the second recognition part, so that the arrangement work of the spacecraft image is preposed to a shooting link, the requirements of image arrangement personnel on memory and file arrangement capability are reduced, and the subsequent arrangement difficulty of the spacecraft image is reduced.

Description

Technical Field

[0001] The present application relates to the technical field of spacecraft image organization, and in particular to a spacecraft image recording dial, management method and management system. Background Art

[0002] The images taken during the development of spacecraft models need to be classified and stored for retrieval. After the shooting is completed, the photographer imports the image records into the computer, manually classifies and organizes them, and completes the archiving work. Since most spacecraft assembly work does not form a fixed working mode, aerospace products such as satellites belong to the development-based production and discrete assembly mode, and there are a lot of reverse processes. Spacecraft assembly image recording requires personnel to have strong memory and file organization ability, which restricts the quality and efficiency of image recording work. Summary of the invention

[0003] The present application provides a spacecraft image recording dial, management method and management system to solve the problem in the prior art that spacecraft assembly image recording requires personnel to have strong memory and file organization capabilities, which restricts the quality and efficiency of image recording work.

[0004] In a first aspect, the present application provides a spacecraft image recording dial, comprising:

[0005] A first identification part, wherein the first identification part has a marker;

[0006] A second identification portion, wherein at least one information group is arranged on the second identification portion, and each information group includes a plurality of sub-information carriers;

[0007] The covering body is connected to the first identification part and is used to cover the second identification part. The covering body has an identification window. The covering body and the second identification part can make any sub-information carrier be located at the identification window by generating relative motion.

[0008] In a possible design, the second identification part is rotatably connected to the first identification part, and the second identification part can be rotated around a preset axis so that any sub-information carrier is located at the identification window.

[0009] In a possible design, the second identification part includes at least one rotating ring, and the rotating ring corresponds to the information group one by one. Each rotating ring can rotate around a preset axis to position any sub-information carrier in the corresponding information group at the identification window.

[0010] In a possible design, a central shaft is provided on the first identification part, and each rotating ring is rotatably connected to the central shaft along the axial direction of the central shaft, and the outer diameter of the rotating ring gradually increases.

[0011] In one possible design, the marker includes at least one of color, pattern, text, letter and number.

[0012] In a possible design, the sub-information carrier includes at least one of color, pattern, text, letter and number.

[0013] In a second aspect, the present application further provides a spacecraft image management method, which uses the above-mentioned spacecraft image recording dial to acquire and organize spacecraft images, and the method includes:

[0014] Adjust and take images of the dial;

[0015] Take spacecraft images that correspond to the information in the dial image;

[0016] Based on the marker on the first identification part, obtain the dial image and the corresponding spacecraft name;

[0017] Based on the sub-information carrier on the second identification part, acquiring attribute information of the spacecraft image;

[0018] Based on the spacecraft name and the attribute information, acquiring an attribute label of the spacecraft image;

[0019] Based on the attribute labels, all the spacecraft images are classified and stored in a database.

[0020] In a possible design, after all spacecraft images are classified and stored in a database based on attribute labels, the following is also included:

[0021] Store spacecraft images, attribute labels, and storage locations in the index table.

[0022] In a third aspect, the present application further provides a spacecraft image management system, which uses the spacecraft image management method as described above to organize spacecraft images, and the system includes:

[0023] A marker recognition module, used to obtain a dial image and a corresponding spacecraft name based on the marker on the first recognition part;

[0024] A sub-information carrier identification module, used to obtain attribute information of the spacecraft image based on the sub-information carrier on the second identification part;

[0025] The data annotation module is used to obtain the attribute labels of spacecraft images based on the spacecraft name and attribute information;

[0026] The structured storage module is used to classify all spacecraft images based on attribute labels and store them in the database.

[0027] In one possible design, the system also includes an index module, which is used to retrieve spacecraft images using attribute tags and storage locations.

[0028] In a fourth aspect, the present application also provides an electronic device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the spacecraft image management method as described above when executing the program.

[0029] In a fifth aspect, the present application also provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the spacecraft image management method as described above.

[0030] In a sixth aspect, the present application also provides a computer program product, including a computer program, which implements the spacecraft image management method as described above when executed by a processor.

[0031] The beneficial effects of this application are as follows:

[0032] The spacecraft image recording dial provided in the present application includes a first identification part, a second identification part and a covering body. The relative movement between the covering body and the second identification part can enable any sub-information carrier to be located at the identification window, so that the information of the spacecraft image to be taken (such as the stage, cabin, and subsystem of the equipment / part of the spacecraft to be photographed) can be clearly displayed on the dial through the sub-information carrier by rotating the second identification part, thereby moving the work of organizing the spacecraft image forward to the shooting stage, greatly reducing the requirements on the memory and file organization ability of the image organizer, and reducing the difficulty of subsequent organization of the spacecraft image.

[0033] The spacecraft image management method and management system provided in the present application can adjust the dial before shooting so that the information on the dial is consistent with the attribute information of the spacecraft to be photographed, so that the sorting work of spacecraft image records can be put in advance to the shooting stage, effectively reducing the requirements of image sorting on personnel's memory and file sorting ability; by identifying the markers on the first identification part, it is possible to quickly and accurately screen out images containing the dial from the many imported images, and obtain the spacecraft name corresponding to each spacecraft image taken after each dial image; by identifying the sub-information carrier on the second identification part, it is possible to obtain the attribute information corresponding to each spacecraft image taken after each dial image, and each spacecraft image can be quickly and accurately labeled according to the spacecraft name and attribute information, so as to obtain the attribute label of each spacecraft image, so as to classify all spacecraft images based on the attribute labels and store them in the database, so as to realize automatic screening, classification and sorting of images, effectively reduce the difficulty of the sorting personnel's work, and improve the quality and efficiency of image sorting. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] In order to more clearly illustrate the specific implementation methods of the present application or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0035] Figure 1 A front view of a spacecraft image recording dial provided in an embodiment of the present application;

[0036] Figure 2 for Figure 1 Cross-sectional view along CC;

[0037] Figure 3 A schematic diagram of the structure of the cover of the spacecraft image recording dial provided in an embodiment of the present application;

[0038] Figure 4 A schematic diagram of a process flow of a spacecraft image management method provided in an embodiment of the present application;

[0039] Figure 5 A schematic diagram of the structure of a spacecraft image management system provided in an embodiment of the present application;

[0040] Figure 6 A schematic diagram of the structure of an electronic device provided in an embodiment of the present application.

[0041] Reference numerals:

[0042] 810, first identification part; 820, second identification part; 821, rotating ring; 830, covering body; 831, identification window; 840, central axis. DETAILED DESCRIPTION

[0043] The technical solution of the present application will be described clearly and completely below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present application.

[0044] Combine the following Figure 1-Figure 3 , describing the spacecraft image recording dial provided in an embodiment of the present application.

[0045] Reference Figure 1 , Figure 2As shown, in the embodiment provided in the present application, the spacecraft image recording dial includes a first identification part 810, a second identification part 820 and a covering body 830, the first identification part 810 has a marker; the second identification part 820 is provided with at least one information group, each information group includes a plurality of sub-information carriers; the covering body 830 is connected to the first identification part 810, and is used to cover the second identification part 820, the covering body 830 has an identification window 831, and the covering body 830 and the second identification part 820 can make any sub-information carrier located at the identification window 831 by generating relative movement. Specifically, the dial is a non-powered tooling, the material of the dial is anti-static, the marker includes at least one of color, pattern, text, letters and numbers; the information carrier includes at least one of color, pattern, text, letters and numbers; in some specific embodiments, the marker is a combination of color, pattern, text, letters and numbers, so that the marker can have significant image features, so as to facilitate the subsequent selection of the dial image containing the marker based on the image features, and the name of the spacecraft in the subsequent images can also be identified through the marker; the sub-information carrier is text, so that it is convenient to add various information and make the various information clearly displayed on the dial. In some specific embodiments, the information group includes three groups, namely, the stage information group, the compartment information group and the subsystem information group; wherein, the sub-information carriers in the stage information group include thermal test, mechanical test, compartment docking, etc.; the sub-information carriers in the compartment information group include the service module south plate, the service module north plate, the propulsion module middle plate, etc.; the sub-information carriers in the subsystem information group include data management, control system, energy system, etc.; in other embodiments, the information group may also include other information groups besides the above three information groups. In some specific embodiments, the covering body 830 and the second identification part 820 are slidably matched, and by making the second identification part 820 move linearly or circularly relative to the covering body 830, any sub-information carrier can be moved to the identification window 831 of the covering body 830 so as to be exposed to the identification window 831.

[0046] By utilizing the technical solution provided in the present application, by causing relative movement between the covering body 830 and the second identification part 820, any sub-information carrier can be positioned at the identification window 831, so that the information of the spacecraft image to be captured (information on the stage, compartment, subsystem, etc. of the equipment / part of the spacecraft to be captured) can be clearly displayed on the dial through the sub-information carrier by rotating the second identification part 820, thereby moving the work of organizing the spacecraft image forward to the shooting stage, greatly reducing the requirements on the memory and file organization ability of the image organizer, and reducing the difficulty of subsequent organization of the spacecraft image.

[0047] Reference Figure 1As shown, in some embodiments provided in the present application, the second identification part 820 is rotatably connected to the first identification part 810, and the second identification part 820 can make any sub-information carrier located at the identification window 831 by rotating around a preset axis. By rotating the second identification part 820 around a preset axis, different sub-information carriers can be rotated to the position of the identification window 831 in sequence, and other sub-information carriers are rotated to the back of the cover body 830 so as to be covered by the cover body 830, thereby realizing a rapid conversion between different sub-information carriers, which is beneficial for the photographer to quickly adjust the corresponding sub-information carrier so that it is clearly displayed on the dial.

[0048] Reference Figure 2As shown, in some embodiments provided by the present application, the second identification part 820 includes at least one rotating ring 821, and the rotating ring 821 corresponds to the information group one by one. Each rotating ring 821 can make any sub-information carrier in the corresponding information group be located at the identification window 831 by rotating around a preset axis. Specifically, the preset axis is the central axis 840 line of the circumference of the rotating ring 821. The rotating ring 821 is evenly divided into a plurality of areas, each area corresponds to a sub-information carrier, and the area of ​​each area is equal and smaller than the area of ​​the identification window 831. In this way, by rotating each rotating ring 821 around the preset axis, the sub-information carrier corresponding to each area can be exposed from the identification window 831. In some specific embodiments, a central axis 840 is fixed on the first identification part 810, and each rotating ring 821 is rotatably connected to the central axis 840. Along the axial direction of the central axis 840, the outer diameter of the rotating ring 821 gradually increases. By gradually increasing the outer diameter of the rotating ring 821, the sub-information carrier is arranged at the edge of the rotating ring 821 away from the central axis 840, so that the upper layer of the rotating ring 821 can avoid covering the sub-information carrier on the next rotating layer, and ensure that the sub-information carrier on each rotating ring 821 can be exposed. Therefore, by rotating the corresponding rotating ring 821, the sub-information carrier on the corresponding rotating ring 821 can be exposed from the identification window 831 in sequence, so as to ensure that the identification window 831 can simultaneously expose the sub-information carriers in different information groups, so as to meet the spacecraft image shooting in different scenes. Before the photographer shoots the spacecraft, by rotating each rotating ring 821 on the dial, the information corresponding to the spacecraft image to be shot on each rotating ring 821 can be presented respectively. In some specific embodiments, the central axis 840 is provided with an annular groove along its axial direction, and the inner wall of the annular groove is respectively matched with the corresponding rotating ring 821, so that each rotating ring 821 can rotate around the central axis 840 in the corresponding annular groove. In some of the embodiments, circular limiting grooves are respectively provided on the oppositely arranged end faces of two adjacent layers of rotating rings 821, and balls are commonly provided in the two circular limiting grooves. When one of the rotating rings 821 is rotated, the balls roll in the two circular limiting grooves, thereby maintaining a distance between the two adjacent layers of rotating rings 821 and maintaining appropriate friction between the two layers of rotating rings 821, thereby preventing the rotation of one of the rotating rings 821 from causing the other rotating ring 821 to shift.

[0049] Based on the same inventive concept, an embodiment of the present application also provides a spacecraft image management method, which uses the spacecraft image recording dial in the above embodiment to acquire and organize spacecraft images.

[0050] Reference Figure 4 As shown, the spacecraft image management method includes the following steps:

[0051] Step S110, adjusting and photographing the dial image;

[0052] Step S120, photographing a spacecraft image corresponding to the information in the dial image;

[0053] Step S200, based on the marker on the first identification part, obtaining the dial image and the corresponding spacecraft name;

[0054] Step S300, acquiring attribute information of the spacecraft image based on the sub-information carrier on the second identification part;

[0055] Step S400: acquiring attribute labels of spacecraft images based on the spacecraft name and attribute information;

[0056] Step S500: Classify all spacecraft images based on attribute labels and store them in a database.

[0057] In some specific embodiments, step S110 specifically includes:

[0058] The dial is adjusted according to the stage information, cabin information and subsystem information of the spacecraft image to be photographed; specifically: according to the stage information of the spacecraft image to be photographed, the second identification part 820 of the uppermost layer is rotated so that the stage information on the second identification part 820 exposed from the identification window 831 is consistent with the stage information of the spacecraft image to be photographed; similarly, according to the cabin information of the spacecraft image to be photographed, the second identification part 820 of the middle layer is rotated so that the cabin information on the second identification part 820 exposed from the identification window 831 is consistent with the cabin information of the spacecraft image to be photographed; similarly, according to the subsystem information of the spacecraft image to be photographed, the second identification part 820 of the lowermost layer is rotated so that the subsystem information on the second identification part 820 exposed from the identification window 831 is consistent with the subsystem information of the spacecraft image to be photographed; in this way, the stage information, cabin information and subsystem information of the spacecraft image to be photographed can be clearly displayed on the dial;

[0059] Then the adjusted dial is placed at a suitable position and photographed to obtain a dial image;

[0060] After step S110, step S120 is performed, that is, taking a spacecraft image corresponding to the information in the dial image.

[0061] After step S110 and step S120, the dial image and the spacecraft image captured by the camera are respectively imported into the spacecraft image management system, and step S200 is performed.

[0062] In some specific embodiments, step S200 specifically includes:

[0063] All dial images with landmarks are selected through image feature recognition technology. Image feature recognition technology requires taking photos of the dial in the early stage, including taking photos of the dial in different scenes, different lighting conditions and different angles, marking feature points of different photos and storing them in the feature database; after importing the image, the computer calculates the similarity between the imported image and the dial image based on the feature points, thereby selecting the dial image imported into the spacecraft image management system;

[0064] Then, based on the marker on the first identification part in the dial image, the spacecraft name is obtained, which is the spacecraft name in the spacecraft image taken after the dial image is taken; after step S200, the spacecraft name of each spacecraft photo subsequent to the dial image can be obtained. Then, step S300 is performed.

[0065] In some specific embodiments, step S300 specifically includes:

[0066] The sub-information carrier (text information) on the second identification part 820 of the dial is identified by the text feature recognition technology. The text feature recognition technology includes five steps: image preprocessing, text segmentation, text refinement, text extraction, and text recognition. After image preprocessing, text segmentation, text refinement, text extraction, and text recognition, the sub-information carrier (text information) on the second identification part 820 of the dial in the spacecraft image can be identified, and the attribute information corresponding to the subsequent spacecraft image of each dial image is obtained, and then step S400 is entered.

[0067] In step S400, attribute labels are set for the spacecraft images according to the spacecraft name in the spacecraft images following each dial photo and the attribute information of the spacecraft images following each dial image; in step S500, all spacecraft images are labeled, classified and stored in the database according to the attribute labels.

[0068] By utilizing the technical solution provided in the above-mentioned embodiment, by adjusting the dial before shooting so that the information on the dial is consistent with the information of the spacecraft image to be shot, the work of organizing the spacecraft image records can be advanced to the shooting stage, effectively reducing the requirements of image organization on the personnel's memory and file organization ability; by identifying the marker on the first identification part 810, the dial image can be quickly and accurately screened out from the numerous imported images, and the spacecraft name corresponding to the spacecraft image following each dial image can be obtained; by identifying the sub-information carrier on the second identification part 820, the attribute information of the spacecraft image taken after each dial image is taken can be obtained respectively, and each spacecraft image can be quickly and accurately labeled according to the spacecraft name and attribute information, so as to obtain the attribute label of each spacecraft image, and then all the spacecraft images can be classified and stored in the database based on the attribute label, so as to realize automatic screening, classification and organization of images, and effectively reduce the difficulty of the work of the organizer, so as to improve the efficiency of image recording work and realize rapid retrieval of image records.

[0069] In some embodiments provided by the present application, after all spacecraft images are classified and stored in a database based on attribute tags, the process further includes: storing the spacecraft images, attribute tags, and storage locations in an index table. By storing the spacecraft images, attribute tags, and storage locations in the index table, during image retrieval, the searcher can quickly retrieve the required spacecraft images and their storage locations through the attribute tags stored in the index table.

[0070] The spacecraft image management method of the present application is specifically applied to the image recording link of spacecraft assembly in development-type production and discrete assembly modes. In the work of confirming the quality of spacecraft assembly, the image recorder needs to know the stage, compartment, subsystem and other information to which A (equipment / part of the spacecraft to be photographed) belongs, and set the dial according to the above information to display the above information on the dial, then photograph the dial to obtain the dial image, and then photograph A (A image) according to the process requirements until the photography of A is completed; when the image recorder needs to photograph B (other spacecraft equipment / parts to be photographed), the dial should also be set first, and after photographing the dial to obtain the dial image, B should be photographed (B image). When the photographer finishes a period of photography tasks, the photography data needs to be imported into the computer and spacecraft image data management system.

[0071] When the shooting data is imported into the spacecraft image data management system, the system will first mark the image through the shooting time and camera model in the camera EXIT information to prevent the image order from being disordered; secondly, the image feature recognition technology is used to first identify all the dial images and obtain the spacecraft name corresponding to the spacecraft image following the dial image; then the text feature recognition technology is used to identify the text in the corresponding area of ​​the above-selected dial photo to obtain the attribute information corresponding to the spacecraft image following the dial image; then, attribute labels are set for each spacecraft image following the dial image according to the spacecraft name and attribute information; finally, the above attribute labels and file storage locations are stored in the index table of the database; when searching for images, the searcher can quickly retrieve the required spacecraft image through the attribute labels stored in the index table.

[0072] Based on the same inventive concept, an embodiment of the present application also provides a spacecraft image management system, which uses the spacecraft image management method in the above embodiment to organize spacecraft images.

[0073] Reference Figure 5 As shown, the spacecraft image management system includes:

[0074] The landmark recognition module 610 is used to obtain the dial image and the corresponding spacecraft name based on the landmark on the first recognition unit 810;

[0075] The sub-information carrier identification module 620 is used to obtain attribute information of the spacecraft image based on the sub-information carrier on the second identification part 820;

[0076] The data labeling module 630 is used to obtain attribute labels of spacecraft images based on the spacecraft name and attribute information;

[0077] The structured storage module 640 is used to classify all spacecraft images based on attribute labels and store them in the database.

[0078] Furthermore, this embodiment also includes an index module, which is used to retrieve spacecraft images using attribute tags and storage locations.

[0079] Based on the same inventive concept, an embodiment of the present application also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the program, the spacecraft image management method as described above is implemented.

[0080] like Figure 6As shown, the electronic device may include: a processor 710, a communication interface 720, a memory 730 and a communication bus 740, wherein the processor 710, the communication interface 720 and the memory 730 communicate with each other through the communication bus 740. The processor 710 may call the logic instructions in the memory 730 to execute the spacecraft image management method, which includes: obtaining the spacecraft image based on the marker on the first identification part 810; obtaining the image information of the spacecraft image based on the sub-information carrier on the second identification part 820; obtaining the attribute label of the spacecraft image based on the image information; and classifying all the spacecraft images based on the attribute label and storing them in the database.

[0081] In addition, the logic instructions in the above-mentioned memory 730 can be implemented in the form of a software functional unit and can be stored in a computer-readable storage medium when it is sold or used as an independent product. Based on such an understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art or the part of the technical solution, can be embodied in the form of a software product, and the computer software product is stored in a storage medium, including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present invention. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk and other media that can store program codes.

[0082] On the other hand, the present application also provides a non-transitory computer-readable storage medium having a computer program stored thereon, which implements the above-mentioned spacecraft image management method when executed by a processor. The method includes: acquiring a spacecraft image based on a marker on the first identification unit 810; acquiring image information of the spacecraft image based on the sub-information carrier on the second identification unit 820; acquiring an attribute label of the spacecraft image based on the image information; and classifying all spacecraft images based on the attribute label and storing them in a database.

[0083] In another aspect, the present application also provides a computer program product, including a computer program, which implements the above-mentioned spacecraft image management method when executed by a processor. The method includes: acquiring a spacecraft image based on a marker on the first identification unit 810; acquiring image information of the spacecraft image based on the sub-information carrier on the second identification unit 820; acquiring an attribute label of the spacecraft image based on the image information; and classifying all spacecraft images based on the attribute label and storing them in a database.

[0084] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0085] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of this application, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0086] In this application, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0087] The device embodiments described above are merely illustrative, wherein the units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment. Ordinary technicians in this field can understand and implement it without paying creative labor.

[0088] Through the description of the above implementation methods, those skilled in the art can clearly understand that each implementation method can be implemented by means of software plus a necessary general hardware platform, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solution is essentially or the part that contributes to the prior art can be embodied in the form of a software product, and the computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a disk, an optical disk, etc., including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0089] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A spacecraft image recording dial, characterized in that: include: a first identification portion, wherein the first identification portion has a marker thereon; A second identification portion, wherein at least one information group is arranged on the second identification portion, and each of the information groups includes a plurality of sub-information carriers; The covering body is connected to the first identification part and is used to cover the second identification part. The covering body has an identification window. The covering body and the second identification part can make any of the sub-information carriers be located at the identification window by generating relative movement.

2. The spacecraft image recording dial according to claim 1, characterized in that: The second identification part is rotatably connected to the first identification part, and the second identification part can make any of the sub-information carriers be located at the identification window by rotating around a preset axis.

3. The spacecraft image recording dial according to claim 2, characterized in that: The second identification part includes at least one rotating ring, and the rotating ring corresponds to the information group one by one. Each of the rotating rings can be rotated around a preset axis to position any sub-information carrier in the corresponding information group at the identification window.

4. The spacecraft image recording dial according to claim 3, characterized in that: The first identification part is provided with a central axis, and each of the rotating rings is rotatably connected to the central axis along the axial direction of the central axis, and the outer diameter of the rotating ring increases gradually.

5. The spacecraft image recording dial according to any one of claims 1 to 4, characterized in that: The marker includes at least one of color, pattern, text, letter and number.

6. The spacecraft image recording dial according to any one of claims 1 to 4, characterized in that: The sub-information carrier includes at least one of color, pattern, text, letter and number.

7. A spacecraft image management method, characterized in that: Using the spacecraft image recording dial according to any one of claims 1 to 6 to acquire and organize spacecraft images, the method comprising: Adjust and take images of the dial; capturing a spacecraft image corresponding to the information in the dial image; Based on the marker on the first identification part, obtaining the dial image and the corresponding spacecraft name; Based on the sub-information carrier on the second identification part, acquiring attribute information of the spacecraft image; Based on the spacecraft name and the attribute information, acquiring an attribute label of the spacecraft image; Based on the attribute labels, all the spacecraft images are classified and stored in a database.

8. The spacecraft image management method according to claim 7, characterized in that: After classifying all the spacecraft images based on the attribute labels and storing them in the database, the method further includes: The spacecraft image, the attribute label, and the storage location are stored in an index table.

9. A spacecraft image management system, characterized in that: The spacecraft image management method according to claim 7 or 8 is used to organize spacecraft images, and the system comprises: A marker recognition module, used to obtain a dial image and a corresponding spacecraft name based on the marker on the first recognition part; A sub-information carrier identification module, used to obtain attribute information of the spacecraft image based on the sub-information carrier on the second identification part; A data labeling module, used for obtaining an attribute label of the spacecraft image based on the spacecraft name and the attribute information; The structured storage module is used to classify all the spacecraft images based on the attribute labels and store them in a database.

10. The spacecraft image management system according to claim 9, characterized in that: It also includes an index module, which is used to retrieve the spacecraft image using the attribute label and storage location.

Images