Combined spaceflight software test system

Abstract

The invention relates to the technical field related to spaceflight, in particular to a combined spaceflight software testing system which comprises a combined testing machine body, and a protection mechanism is arranged on the combined testing machine body. According to the combined spaceflight software testing system, by arranging the protection mechanism, when the combined testing machine tests spaceflight software, an exposed display screen can be protected, so that the display screen cannot be influenced by dust and moisture, and meanwhile, the use temperature of the combined testing machine is controlled in cooperation with the heat dissipation mechanism.

Description

Technical Field

[0001] This invention relates to the field of aerospace-related technologies, and in particular to a combined aerospace software testing system. Background Technology

[0002] Spaceflight, also known as space travel, cosmic flight, or space exploration, refers to all activities involving the entry, exploration, development, and utilization of outer space (the space beyond Earth's atmosphere, also known as outer space) and celestial bodies beyond Earth. Space activities encompass three main parts: space technology, space applications, and space science. Space technology refers to the comprehensive engineering technologies that provide the technical means and support conditions for space activities. Space applications refer to the various application technologies utilizing space technology and the space resources it develops in fields such as scientific research, national economy, national defense, and culture and education. Space resources refer to various environmental, energy, and material resources beyond Earth's atmosphere that can be developed and utilized by humankind, such as high-altitude locations, high vacuum, ultra-low temperatures, strong radiation, microgravity environments, solar energy, and material resources from celestial bodies beyond Earth. Therefore, a combined space software testing system is particularly needed.

[0003] Existing aerospace software testing systems expose the display screen to the outside environment during testing, which may be affected by external environmental interference such as dust and moisture, thus affecting the accuracy of test results. The exposed display screen may also be subject to accidental impacts or scratches, reducing its service life and reliability. Therefore, staff need to clean and maintain it regularly to ensure the clarity and sensitivity of the display screen, but this increases the workload and maintenance costs for staff. Summary of the Invention

[0004] The purpose of this invention is to provide a combined aerospace software testing system to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a combined aerospace software testing system, comprising a combined testing machine body, wherein a protective mechanism is provided on the combined testing machine body;

[0006] The protective mechanism includes a mounting shell, a slide rail, a slide base, a first connecting plate, a connecting shaft, a second connecting plate, a connecting rod, and a protective shell. The outer wall of the main body of the combined testing machine is provided with a mounting shell. A slide rail is fixed inside the mounting shell. A slide base is provided on the slide rail. A first connecting plate is installed on the slide base. A connecting shaft is fixed inside the mounting shell. One end of the connecting shaft is connected to the second connecting plate. A connecting rod is provided on the outer wall of the second connecting plate. A protective shell is installed on the first connecting plate.

[0007] Preferably, the main body of the combined testing machine includes a cabinet, a placement plate, and testing equipment. The placement plate is installed on the outer wall of the cabinet, and the testing equipment is installed on the placement plate.

[0008] Preferably, the main body of the combined testing machine is provided with a heat dissipation mechanism, which includes a fixing groove, a shell, a fan, a dust cover, and heat dissipation holes. The outer wall of the cabinet is provided with a fixing groove, the shell is installed inside the fixing groove, the fan is provided inside the shell, the outer wall of the shell is provided with a dust cover, and the dust cover is provided with heat dissipation holes.

[0009] Preferably, the protective mechanism is provided with a fixing component, which includes a cover plate and a sliding groove. The cover plate is installed on the mounting shell, and the sliding groove is formed on the cover plate.

[0010] Preferably, a protective cover is installed on the outer wall of the fixing groove.

[0011] Preferably, the outer wall of the cabinet is fitted with a support plate.

[0012] Preferably, a telescopic plate is installed on the bottom wall of the placement plate.

[0013] Preferably, an input device is installed on the telescopic plate.

[0014] Preferably, a combined aerospace software testing system includes the following steps in its operation:

[0015] S1. Project setup and test environment configuration: This involves establishing the test project within the test equipment and setting up the corresponding server within the cabinet.

[0016] S2. Test case selection and adjustment, and parameter configuration: Select test cases that match the current test objectives from the server test case library, or create test cases temporarily based on requirements, and set input data, execution conditions, and expected output for the test cases;

[0017] S3. Real-time data acquisition and monitoring: The system automatically records software output data and simulation environment feedback during the test process, displays key indicators in real time through the dashboard, and stores the test data on the server.

[0018] S4. Test report generation and export: Generate standardized templates based on test types and export them in various document formats.

[0019] Compared with the prior art, the beneficial effects of the present invention are: a combined aerospace software testing system, by setting up a protective mechanism, can protect the exposed display screen when the combined testing machine is testing aerospace software, so that it is not affected by dust, moisture, etc., and at the same time, the heat dissipation mechanism controls the operating temperature of the combined testing machine. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall appearance and structure of the present invention;

[0021] Figure 2 This is a schematic diagram of the protective mechanism structure of the present invention;

[0022] Figure 3 This is a schematic diagram of the structure of the fixing groove and the outer shell used in conjunction with the present invention;

[0023] Figure 4 For the present invention Figure 3 Enlarged structural diagram at point A in the middle;

[0024] Figure 5 For the present invention Figure 2 Enlarged structural diagram at point B

[0025] Figure 6 This is a schematic diagram of the overall practical process structure of the present invention.

[0026] In the diagram: 1. Main body of the combined testing machine; 11. Cabinet; 12. Placement plate; 13. Testing equipment; 2. Protective mechanism; 21. Mounting shell; 22. Slide rail; 23. Slide base; 24. First connecting plate; 25. Connecting shaft; 26. Second connecting plate; 27. Connecting rod; 28. Protective shell; 3. Heat dissipation mechanism; 31. Fixing groove; 32. Outer shell; 33. Fan; 34. Dust cover; 35. Heat dissipation hole; 4. Fixing component; 41. Cover plate; 42. Slide groove; 5. Protective cover; 6. Support plate; 7. Telescopic plate; 8. Input device. Detailed Implementation

[0027] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0028] Please see Figure 1-5 The present invention provides a technical solution: a combined aerospace software testing system, including a combined testing machine body 1, and a protective mechanism 2 is provided on the combined testing machine body 1;

[0029] The protective mechanism 2 includes a mounting shell 21, a slide rail 22, a slide block 23, a first connecting plate 24, a connecting shaft 25, a second connecting plate 26, a connecting rod 27, and a protective shell 28. The outer wall of the main body 1 of the combined testing machine is provided with the mounting shell 21. The slide rail 22 is fixed inside the mounting shell 21. A slide block 23 is provided on the slide rail 22. The first connecting plate 24 is mounted on the slide block 23. The connecting shaft 25 is fixed inside the mounting shell 21. One end of the connecting shaft 25 is connected to the second connecting plate 26. The outer wall of the second connecting plate 26 is provided with the connecting rod 27. The protective shell 28 is mounted on the first connecting plate 24. The mounting shell 21, slide rail 22, slide block 23, first connecting plate 24, connecting shaft 25, second connecting plate 26, connecting rod 27, and protective shell 28... In this configuration, during use, the mounting shell 21 is installed on the outer wall of the cabinet 11, the slide rail 22 is installed inside the mounting shell 21, the first connecting plate 24 is then installed onto the slide rail 22 via the slide block 23, the protective shell 28 is then installed on the first connecting plate 24, the connecting shaft 25 is installed at the center of the mounting shell 21, the second connecting plate 26 is installed on the connecting shaft 25, and the first connecting plate 24 and the second connecting plate 26 on both sides of the mounting shell 21 are connected by the connecting rod 27. When using the combined testing machine body 1 to test aerospace software, pulling one side of the protective shell 28 causes the other side of the protective shell 28 to move outward synchronously under the action of the connecting rod 27 and the second connecting plate 26, thereby exposing the testing equipment 13 for use.

[0030] Furthermore, the main body 1 of the combined test machine includes a cabinet 11, a placement plate 12, and a test device 13. The placement plate 12 is installed on the outer wall of the cabinet 11, and the test device 13 is installed on the placement plate 12. Through the arrangement of the cabinet 11, the placement plate 12, and the test device 13, during use, the test device 13 is connected to the data center inside the cabinet 11 to start testing the aerospace software.

[0031] Furthermore, the main body 1 of the combined testing machine is equipped with a heat dissipation mechanism 3. The heat dissipation mechanism 3 includes a fixing groove 31, a shell 32, a fan 33, a dust cover 34, and heat dissipation holes 35. The outer wall of the cabinet 11 has a fixing groove 31. The shell 32 is installed inside the fixing groove 31. The fan 33 is installed inside the shell 32. The outer wall of the shell 32 is equipped with a dust cover 34. The dust cover 34 has heat dissipation holes 35. Through the arrangement of the fixing groove 31, the shell 32, the fan 33, the dust cover 34, and the heat dissipation holes 35, when in use, the fan 33 is installed in the shell 32, and then the dust cover 34 is installed in the air inlet of the shell 32. When using the main body 1 of the combined testing machine to test aerospace software, the fan 33 is started to dissipate heat from the cabinet 11.

[0032] Furthermore, the protective mechanism 2 is provided with a fixing component 4, which includes a cover plate 41 and a slide groove 42. The cover plate 41 is installed on the mounting shell 21, and the slide groove 42 is provided on the cover plate 41. With the cover plate 41 and the slide groove 42, when in use, the cover plate 41 is installed on the mounting shell 21, so that the mounting shell 21 is separated from the test equipment 13. The slide groove 42 ensures that the movement of the protective shell 28 is not affected.

[0033] Furthermore, a protective cover 5 is installed on the outer wall of the fixing groove 31. The protective cover 5 protects the fan 33 during use.

[0034] Furthermore, a support plate 6 is installed on the outer wall of the cabinet 11. The support plate 6 supports the placement plate 12 during use.

[0035] Furthermore, a telescopic plate 7 is installed on the bottom wall of the placement plate 12. With the telescopic plate 7, when software testing is not required, the input device 8 can be stored at the bottom of the placement plate 12 for the next use.

[0036] Furthermore, an input device 8 is installed on the telescopic plate 6. Through the setting of the input device 8, tests can be carried out in conjunction with the whole system during use.

[0037] A combined aerospace software testing system, the operation method of which includes the following steps:

[0038] S1. Project establishment and test environment configuration: Establish the test project in the test equipment 13 and build the corresponding server in the cabinet 11.

[0039] S2. Test case selection and adjustment, and parameter configuration: Select test cases that match the current test objectives from the server test case library, or create test cases temporarily based on requirements, and set input data, execution conditions, and expected output for the test cases;

[0040] S3. Real-time data acquisition and monitoring: The system automatically records software output data and simulation environment feedback during the test process, displays key indicators in real time through the dashboard, and stores the test data on the server.

[0041] S4. Test Report Generation and Export: Generate standardized templates based on test types and export them in various document formats.

[0042] Working principle: In use, the mounting shell 21 is installed on the outer wall of the cabinet 11, the slide rail 22 is installed inside the mounting shell 21, the first connecting plate 24 is then installed on the slide rail 22 via the slide block 23, the protective shell 28 is then installed on the first connecting plate 24, the connecting shaft 25 is installed at the center of the mounting shell 21, the second connecting plate 26 is installed on the connecting shaft 25, and the first connecting plate 24 and the second connecting plate 26 on both sides of the mounting shell 21 are connected by the connecting rod 27. When using the combined testing machine body 1 to test the aerospace software, one side of the protective shell 28 is pulled. At this time, under the action of the connecting rod 27 and the second connecting plate 26, the other side of the protective shell 28 moves outward synchronously, thereby exposing the testing equipment 13 for use. The fan 33 is installed in the outer shell 32, and the dust cover 34 is installed at the air inlet of the outer shell 32. When using the combined testing machine body 1 to test the aerospace software, the fan 33 is started to dissipate heat from the cabinet 11.

[0043] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A combined aerospace software testing system, comprising a combined testing machine body (1), characterized in that: The main body (1) of the combined testing machine is equipped with a protective mechanism (2); The protective mechanism (2) includes a mounting shell (21), a slide rail (22), a slide block (23), a first connecting plate (24), a connecting shaft (25), a second connecting plate (26), a connecting rod (27), and a protective shell (28). The outer wall of the main body (1) of the combined testing machine is provided with a mounting shell (21). The slide rail (22) is fixed inside the mounting shell (21). The slide block (23) is provided on the slide rail (22). The first connecting plate (24) is installed on the slide block (23). The connecting shaft (25) is fixed inside the mounting shell (21). One end of the connecting shaft (25) is connected through the second connecting plate (26). The outer wall of the second connecting plate (26) is provided with a connecting rod (27). The protective shell (28) is installed on the first connecting plate (24).

2. The combined aerospace software testing system according to claim 1, characterized in that: The main body (1) of the combined testing machine includes a cabinet (11), a placement plate (12) and a testing device (13). The outer wall of the cabinet (11) is equipped with the placement plate (12), and the testing device (13) is installed on the placement plate (12).

3. The combined aerospace software testing system according to claim 2, characterized in that: The main body (1) of the combined testing machine is provided with a heat dissipation mechanism (3). The heat dissipation mechanism (3) includes a fixing groove (31), a shell (32), a fan (33), a dust cover (34), and heat dissipation holes (35). The outer wall of the cabinet (11) is provided with a fixing groove (31). The shell (32) is installed inside the fixing groove (31). The fan (33) is installed inside the shell (32). The outer wall of the shell (32) is provided with a dust cover (34). The dust cover (34) is provided with heat dissipation holes (35).

4. The combined aerospace software testing system according to claim 1, characterized in that: The protective mechanism (2) is provided with a fixing component (4), which includes a cover plate (41) and a sliding groove (42). The cover plate (41) is installed on the mounting shell (21), and the sliding groove (42) is provided on the cover plate (41).

5. The combined aerospace software testing system according to claim 3, characterized in that: A protective cover (5) is installed on the outer wall of the fixing groove (31).

6. The combined aerospace software testing system according to claim 2, characterized in that: The outer wall of the cabinet (11) is fitted with a support plate (6).

7. A combined aerospace software testing system according to claim 3, characterized in that: The bottom wall of the placement plate (12) is equipped with a telescopic plate (7).

8. A combined aerospace software testing system according to claim 7, characterized in that: An input device (8) is installed on the telescopic plate (6).

9. A combined aerospace software testing system, the operation method of which is applicable to any one of claims 1-2. The combined aerospace software testing system is characterized by: The following steps are involved: S1. Project establishment and test environment configuration: Establish test projects in test equipment (13) and build corresponding servers in cabinet (11); S2. Test case selection and adjustment, and parameter configuration: Select test cases that match the current test objectives from the server test case library, or create test cases temporarily based on requirements, and set input data, execution conditions, and expected output for the test cases; S3. Real-time data acquisition and monitoring: The system automatically records software output data and simulation environment feedback during the test process, displays key indicators in real time through the dashboard, and stores the test data on the server. S4. Test report generation and export: Generate standardized templates based on test types and export them in various document formats.

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