A solid propellant in-situ loading test device based on synchrotron radiation source

Abstract

The present invention relates to the field of solid propellant testing technology, and in particular to a solid propellant in-situ loading test device based on a synchrotron radiation light source. The device comprises a housing, a control panel installed on the housing, a drive motor electrically connected to the control panel installed on the housing, a symmetrical threaded rod rotatably connected to the housing, a threaded rod on one side fixedly connected to the output shaft of the drive motor, a threaded rod threadedly engaged with a first threaded protrusion of an adjacent sliding plate, a first gear fixedly connected to one end of the threaded rod fixedly connected to the output shaft of the drive motor, and a second gear meshing with the first gear fixedly connected to the threaded rod on the other side. The present invention makes the number of teeth of the first gear less than the number of teeth of the second gear, so that the tensile degree of the solid propellant sample is different within the same time, thereby simulating the stress conditions of the solid propellant under different actual conditions, thereby improving the test diversity and improving the test effect.

Description

Technical Field

[0001] The present invention relates to the technical field of solid propellant testing, and in particular to a solid propellant in-situ loading test device based on a synchrotron radiation light source. Background Art

[0002] Solid propellant is a fuel composed of oxidizer, fuel and additives. It usually exists in solid form and has high energy density and long storage life. Due to its simple structure, high reliability and fast response speed, solid propellant is widely used in many space missions.

[0003] In order to evaluate the performance, reliability and safety of solid propellants, it is often necessary to conduct in-situ loading tests on them. This test simulates loading of solid propellants under actual usage conditions to verify whether their structure and material performance meet design requirements and detect potential defects or failures.

[0004] Most existing devices for testing solid propellants only perform a single stretch on a single solid propellant sample. However, during the actual operation of solid propellants, as the solid propellant continues to burn, the combustion conditions of the solid propellant in different environments are also different. With existing testing devices, it is difficult to simultaneously test solid propellants under different conditions. Summary of the Invention

[0005] In order to overcome the shortcoming of existing devices for testing solid propellants, which makes it difficult to simultaneously test solid propellants under different conditions, the present invention provides a solid propellant in-situ loading test device based on a synchrotron radiation light source.

[0006] The technical solution of the present invention is: a solid propellant in-situ loading test device based on a synchrotron radiation light source, comprising a shell, a control panel installed in the shell, a drive motor electrically connected to the control panel installed in the shell, a cover plate hingedly connected to the shell, a handle fixedly connected to the cover plate, symmetrical detection probes installed on the cover plate, the detection probes are connected to an external synchrotron radiation light source, and the symmetrical detection probes are both electrically connected to the control panel. Symmetrical guide rods are fixedly connected in the shell, the guide rods are slidably connected to symmetrical sliding plates, the sliding plates are slidably connected to the shell, the shell is rotatably connected to symmetrical threaded rods, the threaded rods are provided with symmetrical first threaded protrusions, the threaded rods on one side are fixedly connected to the output shaft of the drive motor, the threaded rods are threadedly matched with the first threaded protrusions of the adjacent sliding plates, the threaded rods on one side are fixedly connected to a first gear, and the threaded rods on the other side are fixedly connected to a second gear meshing with the first gear, the second gear and the first gear have different numbers of teeth, the sliding plate is rotatably connected to a sliding rod slidably connected to the shell, the sliding rods are provided with a second threaded protrusion, the sliding plate is provided with a clamping mechanism for clamping the solid propellant, and an adjustment mechanism for applying variable stress to the solid propellant is provided in the shell.

[0007] Preferably, when the cover plate and the housing are in a mating state, the detection probe is located above the adjacent solid propellant.

[0008] Preferably, the clamping block is threadedly matched with a threaded knob, and the threaded knob is threadedly matched with an adjacent sliding block.

[0009] Preferably, the clamping mechanism includes a sliding block, which is slidably connected to an adjacent sliding plate. The sliding block is fixedly connected to a moving block, which is threadedly engaged with an adjacent sliding rod. The sliding block is slidably connected to a clamping block, and the clamping block can be relatively replaced according to the shape of the solid propellant sample.

[0010] Preferably, the adjustment mechanism includes evenly distributed L-shaped limit rods, which are fixedly connected to the shell. The sliding rod is provided with a first limit groove at one end close to the adjacent L-shaped limit rod, and the first limit groove cooperates with the adjacent L-shaped limit rod.

[0011] Preferably, the first limiting groove is a spiral groove, and the pitch of the symmetrical first limiting groove gradually increases along the opposite direction thereof.

[0012] Preferably, a first elastic element is fixedly connected between the sliding plate and the adjacent sliding rod, for resetting the adjacent sliding rod.

[0013] Preferably, it also includes a limiting mechanism for limiting the cover plate, the limiting mechanism is arranged on the cover plate, the shell is provided with symmetrical limiting slots, the limiting mechanism includes symmetrical limiting blocks, the symmetrical limiting blocks are slidably connected to the cover plate, the limiting blocks cooperate with the limiting slots adjacent to the shell, a second elastic element is fixedly connected between the limiting blocks and the cover plate, and the handle is provided with an unlocking mechanism for causing the cover plate to lose its limit.

[0014] Preferably, a third elastic element is fixedly connected between the cover and the housing, for enabling the cover to open automatically after losing its limit.

[0015] Preferably, the unlocking mechanism includes symmetrical straight limit rods, which are slidably connected to the handle, and the end of the straight limit rod close to the cover plate is set as an inclined side. A moving rod is fixedly connected between the symmetrical straight limit rods, and a fourth elastic element is fixedly connected between the moving rod and the handle. The limit block is provided with a second limit groove, and the second limit groove cooperates with the adjacent straight limit rod.

[0016] Beneficial effects: The present invention makes the number of teeth of the first gear less than that of the second gear, so that the stretching degree of the solid propellant sample is different within the same time, thereby simulating the stress conditions of the solid propellant under different actual conditions, thereby improving the test diversity and improving the test effect; the pitch of the symmetrical first limit groove gradually increases along its opposite direction, so that the moving speed of the symmetrical moving block gradually increases in a nonlinear form, adding additional driving force to the solid propellant sample, thereby simulating the increase in load caused by the increase in the surface area of ​​the solid propellant during combustion, so that the test of the solid propellant is more close to the actual load condition; the symmetrical limit block is limited and matched with the limit slot adjacent to the shell, so that when the solid propellant sample is loaded, an accidental explosion is avoided, causing the cover to open, so that the parts damaged by the explosion in the shell are splashed outward under the action of the impact force, causing harm to the staff, thereby improving the safety during the loading test. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the overall front-view three-dimensional structure of the present invention;

[0018] Figure 2 It is a schematic diagram of the overall side perspective structure of the present invention;

[0019] Figure 3 This is a schematic diagram of the three-dimensional structure of the housing and its internal parts of the present invention;

[0020] Figure 4 This is a schematic diagram of the three-dimensional structure of the present invention when the first gear and the second gear are meshed;

[0021] Figure 5It is a schematic diagram of the three-dimensional structure of the L-shaped limiting rod of the present invention when it cooperates with the adjacent first limiting groove;

[0022] Figure 6 This is a schematic diagram of the three-dimensional structure of the movable rod of the present invention when it moves backward;

[0023] Figure 7 It is a schematic diagram of the three-dimensional structure of the straight limiting rod of the present invention when it cooperates with the adjacent second limiting groove.

[0024] Marked in the figure: 1-housing, 2-control panel, 3-drive motor, 4-cover, 5-handle, 6-detection probe, 7-guide rod, 8-sliding plate, 9-threaded rod, 10-first gear, 11-second gear, 12-sliding rod, 1301-sliding block, 1302-moving block, 1303-block, 1304-threaded knob, 1401-L-shaped limiting rod, 1402-first limiting groove, 1403-first elastic element, 1501-limiting block, 1502-second elastic element, 1503-third elastic element, 1601-straight limiting rod, 1602-moving rod, 1603-fourth elastic element, 1604-second limiting groove. DETAILED DESCRIPTION

[0025] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention. Although the embodiments of the present invention have been shown and described, it can be understood by ordinary technicians in this field that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the attached claims and their equivalents.

[0026] Example 1: A solid propellant in-situ loading test device based on a synchrotron radiation source, such as Figure 1-Figure 3As shown, it includes a shell 1, two symmetrical support plates are fixedly connected to the upper part of the rear side of the shell 1, a control panel 2 is installed on the upper part of the front side of the shell 1, a drive motor 3 electrically connected to the control panel 2 is installed on the left side of the shell 1, and the drive motor 3 is a synchronous motor, a cover plate 4 is hinged on the upper part of the rear side of the shell 1, and the cover plate 4 is sealed with the shell 1, and the cover plate 4 is limited with the support plate of the shell 1, and a handle 5 is fixedly connected to the front side of the cover plate 4, and two front-to-back symmetrical detection probes 6 are installed in the middle part of the cover plate 4, and the detection probes 6 are connected to the external synchrotron radiation light source for detecting the deformation of the solid propellant during the test. When the cover plate 4 and the shell 1 are in a matched state, the detection probes 6 are located above the adjacent solid propellants, and the two front-to-back symmetrical detection probes 6 are both electrically connected to the control panel 2, and the lower side of the shell 1 is fixedly connected with two front-to-back symmetrical guide rods 7, and the two front-to-back symmetrical guide rods 7 are both slidably connected with two left-right symmetrical sliding plates 8.

[0027] like Figure 3 and Figure 4 As shown, the sliding plate 8 is slidably connected to the housing 1, and the middle and lower part of the housing 1 is rotatably connected to two front-to-back symmetrical threaded rods 9, the threaded rod 9 is provided with two left-to-right symmetrical first threaded protrusions, the front threaded rod 9 is fixedly connected to the output shaft of the drive motor 3, the threaded rod 9 is threadedly matched with the first threaded protrusion of the adjacent sliding plate 8, the left end of the front threaded rod 9 is fixedly connected to the first gear 10, and the left end of the rear threaded rod 9 is fixedly connected to the second gear 11, the second gear 11 is meshed with the first gear 10, and the number of teeth of the second gear 11 is more than the number of teeth of the first gear 10, the upper part of the sliding plate 8 is rotatably connected to the sliding rod 12, and the sliding The rod 12 is provided with a second threaded protrusion, the sliding rod 12 is slidably connected to the shell 1, the sliding plate 8 is provided with a clamping mechanism for clamping the solid propellant, and an adjustment mechanism for applying variable stress to the solid propellant is provided in the shell 1. The pitch of the symmetrical first limiting groove 1402 gradually increases along its opposite direction, so that the moving speed of the two symmetrical moving blocks 1302 on the left and right gradually increases in a nonlinear form, adding additional driving force to the solid propellant sample, thereby simulating the increase in load caused by the increase in the surface area of ​​the solid propellant during combustion, so that the test on the solid propellant is more close to the actual load condition.

[0028] like Figure 4 and Figure 5As shown, the clamping mechanism includes a sliding block 1301, which is slidably connected to the upper side of the adjacent sliding plate 8, and a moving block 1302 is fixedly connected to the lower side of the sliding block 1301. The moving block 1302 is threadedly engaged with the adjacent sliding rod 12. The sliding block 1301 is slidably connected to a card block 1303, and the card block 1303 can be relatively replaced according to the shape of the solid propellant sample to increase the applicability of the device. The card block 1303 is threadedly engaged with a threaded knob 1304 that is threadedly engaged with the adjacent sliding block 1301. The adjustment mechanism includes four evenly distributed L-shaped limit rods 1401, and the four evenly distributed L-shaped limit rods 1401 are all fixedly connected to the housing 1. The sliding rod 12 is close to the card block 1303. A first limiting groove 1402 is provided at one end of the adjacent L-shaped limiting rod 1401. The first limiting groove 1402 is a spiral groove. The pitch of the symmetrical first limiting groove 1402 gradually increases along the opposite direction. The first limiting groove 1402 is limited and cooperated with the adjacent L-shaped limiting rod 1401. A first elastic element 1403 is fixedly connected between the sliding plate 8 and the adjacent sliding rod 12. The first elastic element 1403 is a coil spring, which is used to reset the adjacent sliding rod 12. The threaded knob 1304 is used to make the blocking block 1303 fit tightly with the adjacent sliding block 1301 to prevent the blocking block 1303 and the adjacent sliding block 1301 from relative displacement during the subsequent loading test, which affects the test results.

[0029] When it is necessary to use this device to perform an in-situ loading test on the solid propellant, the staff holds the handle 5 and flips the cover 4 upward until the cover 4 is flipped to contact the two support plates on the rear side of the shell 1. Then the staff selects the corresponding block 1303 according to the shape of the solid propellant sample. After the selection is completed, the staff places the block 1303 in the adjacent sliding block 1301. Then the staff turns the threaded knob 1304 to make the block 1303 fit tightly with the adjacent sliding block 1301 through the threaded knob 1304 to prevent the block 1303 and the adjacent sliding block 1301 from relative displacement during the subsequent loading test, which affects the test results. Then the staff places the two solid propellant samples between the corresponding two adjacent blocks 1303 on the left and right, and then the staff closes the cover 4.

[0030] The staff starts the drive motor 3 and the detection probe 6 through the control panel 2, and the output shaft of the drive motor 3 starts to rotate clockwise (compared with the servo motor, the synchronous motor has a more stable speed, and the speed change curve of the servo motor is also affected by factors such as load, inertia, and friction. Therefore, when the servo motor is used as the power source, the solid propellant will cause deviations in the test results due to the instability of the servo motor's speed change during the test process, making it difficult to simulate the load conditions of the solid propellant in actual combustion conditions). The output shaft of the drive motor 3 drives the adjacent threaded rods 9 to rotate clockwise together, and the front threaded rod 9 drives the first gear 10 to rotate clockwise together. The first gear 10 drives the second gear 11 to start rotating counterclockwise, and the second gear 11 drives the rear threaded rod 9 to rotate counterclockwise together. The two left-right symmetrical sliding plates 8 are on the first threaded rods of the adjacent threaded rods 9. Under the action of the protrusion, it begins to move backward, and the sliding plate 8 slides relative to the adjacent guide rod 7. The sliding plate 8 drives the adjacent sliding rod 12 to move together, and the sliding rod 12 slides relative to the shell 1. The sliding rod 12 drives the adjacent sliding block 1301 to move together, and the sliding block 1301 drives the adjacent clamping block 1303 to move together. The two left-right symmetrical clamping blocks 1303 begin to stretch the adjacent solid propellant samples. During the stretching process, the deformation of the solid propellant sample is recorded by the adjacent detection probe 6, and the detection probe 6 transmits the information to the control panel 2 for subsequent research by the staff. The number of teeth of the first gear 10 is less than the number of teeth of the second gear 11, so that the two solid propellant samples have different stretching degrees within the same time, thereby simulating the stress conditions of the solid propellant under different actual conditions, thereby improving the test diversity and improving the test effect.

[0031] In the process of the sliding plate 8 driving the adjacent sliding rod 12 to move, the L-shaped limiting rod 1401 slides in the adjacent first limiting groove 1402, and at the same time, the L-shaped limiting rod 1401 squeezes the adjacent first limiting groove 1402, and then the sliding rod 12 starts to rotate under the squeezing action of the adjacent L-shaped limiting rod 1401, and the sliding rod 12 causes the adjacent first elastic element 1403 to deform, and the left-right symmetrical moving block 1302 starts to move back to the adjacent sliding rod 12 under the action of the second threaded protrusion of the adjacent sliding rod 12, and the moving block 1302 drives the adjacent sliding block 1301 to move together, and the sliding block 1301 and the adjacent The sliding plates 8 slide relative to each other, and the sliding block 1301 drives the adjacent clamping block 1303 to move together. The two symmetrical clamping blocks 1303 further stretch the adjacent solid propellant samples. The pitch of the symmetrical first limiting groove 1402 gradually increases along its opposite direction, so that the moving speed of the two symmetrical moving blocks 1302 gradually increases in a nonlinear form, adding additional driving force to the solid propellant sample, thereby simulating the increase in load caused by the increase in the surface area of ​​the solid propellant during combustion, so that the test on the solid propellant is more close to the actual load condition, thereby improving the accuracy of the test results.

[0032] After the test is completed, the staff closes the detection probe 6 and opens the cover 4 through the control panel 2, and then uses the control panel 2 to reverse the output shaft of the drive motor 3. The output shaft of the drive motor 3 drives the adjacent threaded rod 9 to rotate together, and the front threaded rod 9 drives the first gear 10 to rotate together. The first gear 10 drives the second gear 11 to start rotating in the opposite direction, and the second gear 11 drives the rear threaded rod 9 to rotate together. The two symmetrical sliding plates 8 start to move in opposite directions under the action of the first threaded protrusions of the adjacent threaded rods 9. The sliding plate 8 slides relative to the adjacent guide rod 7, and the sliding plate 8 drives the adjacent sliding rod 12 to move together. The sliding rod 12 drives The adjacent sliding blocks 1301 move together, and the sliding blocks 1301 drive the adjacent clamping blocks 1303 to move together. The two symmetrical clamping blocks 1303 gradually reduce the stress applied to the adjacent solid propellant samples. When the two clamping blocks 1303 move to the point where they no longer apply tension to the adjacent solid propellant samples, the staff turns off the drive motor 3 through the control panel 2, and then the staff turns the four threaded knobs 1304 until the threaded knobs 1304 are disengaged from the adjacent sliding blocks 1301 and the clamping blocks 1303. Then the staff removes the two symmetrical clamping blocks 1303 and the solid propellant sample between them for subsequent testing.

[0033] Then the staff starts the drive motor 3 through the control panel 2. As the output shaft of the drive motor 3 continues to rotate, the two symmetrical sliding plates 8 continue to move towards each other. At the same time, the sliding rod 12 continues to rotate under the action of the adjacent L-shaped limit rod 1401, and the sliding rod 12 begins to reset. Since the pitch of the symmetrical first limit groove 1402 gradually increases along its opposite direction, during the process of resetting the sliding rod 12, the angle between the normals of the contact area between the adjacent L-shaped limit rods 1401 and the adjacent first limit groove 1402 side walls gradually decreases, making it difficult for the sliding rod 12 to completely reset. Torque is applied to the adjacent sliding rods 12 through the first elastic element 1403 to facilitate the resetting of the sliding rod 12. Until the sliding plate 8 and the parts thereon are completely reset, the staff can turn off the drive motor 3 through the control panel 2 and then close the cover 4.

[0034] Example 2: Based on Example 1, Figure 2 、 Figure 6 and Figure 7 As shown, it also includes a limiting mechanism for limiting the cover plate 4, the limiting mechanism is provided on the cover plate 4, and two symmetrical limiting slots are provided on the upper middle part of the front side of the shell 1. The limiting mechanism includes two symmetrical limiting blocks 1501, which are both slidably connected to the cover plate 4. The limiting blocks 1501 are limitedly matched with the limiting slots adjacent to the shell 1. A second elastic element 1502 is fixedly connected between the limiting block 1501 and the cover plate 4. The second elastic element 1502 is a spring. The handle 5 is provided with a plurality of symmetrical limiting blocks 1501. An unlocking mechanism is provided for causing the cover 4 to lose its limit. A third elastic element 1503 is fixedly connected between the cover 4 and the shell 1, which is used to automatically open the cover 4 after it loses its limit. The two limit blocks 1501 are limited in cooperation with the limit slots adjacent to the shell 1 to avoid accidental explosions during loading tests on solid propellant samples, causing the cover 4 to open, thereby causing parts damaged by the explosion in the shell 1 to splash outward under the action of the impact force, causing harm to the staff, thereby improving safety during the loading test.

[0035] like Figure 7 As shown, the unlocking mechanism includes two left-right symmetrical straight limit rods 1601, which are both slidably connected to the handle 5, and the rear ends of the straight limit rods 1601 are set as inclined side surfaces. A moving rod 1602 is fixedly connected between the front ends of the two left-right symmetrical straight limit rods 1601, and the distance between the two left-right symmetrical inclined side surfaces becomes larger from front to back. Two left-right symmetrical fourth elastic elements 1603 are fixedly connected between the moving rod 1602 and the handle 5, and the fourth elastic element 1603 is a spring. The limit block 1501 is provided with a second limit groove 1604, and the second limit groove 1604 is limited and matched with the adjacent straight limit rod 1601.

[0036] When the staff is closing the cover 4, the two third elastic elements 1503 are deformed. When the cover 4 flips down until the two limit blocks 1501 contact the shell 1, as the cover 4 continues to flip, the two limit blocks 1501 begin to move toward each other under the compression of the shell 1, and the limit blocks 1501 compress the adjacent second elastic elements 1502 until the limit blocks 1501 move to the adjacent limit slot area of ​​the shell 1. The two limit blocks 1501 begin to move backwards under the action of the elastic force of the adjacent second elastic elements 1502, forming a limit fit with the limit slot adjacent to the shell 1. At this time, the cover 4 and the shell 1 maintain a sealed fit. The two limit blocks 1501 are limited in fit with the limit slots adjacent to the shell 1 to avoid accidental explosion during the loading test of the solid propellant sample, causing the cover 4 to open, thereby causing the parts damaged by the explosion in the shell 1 to splash outward under the action of the impact force, causing harm to the staff, thereby improving the safety during the loading test.

[0037] When the loading test is completed, the staff pushes the moving rod 1602 backward, the two fourth elastic elements 1603 are compressed, and the moving rod 1602 drives the two straight limit rods 1601 to move backward together. When the two straight limit rods 1601 move backward until they contact the adjacent second limit grooves 1604, as the two straight limit rods 1601 continue to move backward, the two straight limit rods 1601 begin to squeeze the adjacent second limit grooves 1604 respectively, and the two limit blocks 1501 begin to move toward each other under the action of the adjacent straight limit rods 1601. The limit blocks 1501 compress the adjacent second elastic elements 1502. After the two limit blocks 1501 lose their limit fit with the limit slots adjacent to the shell 1, the cover 4 automatically opens under the action of the torque of the third elastic element 1503, and then the staff can perform subsequent operations. After the use of this device is completed, the staff reset all parts and disconnect the power supply.

[0038] The embodiments of the present invention are described in detail above with reference to the accompanying drawings. However, the present invention is not limited to the above embodiments. Various changes can be made within the scope of knowledge of those skilled in the art without departing from the spirit of the present invention.

Claims

1. A solid propellant in-situ loading test device based on a synchrotron radiation source, characterized by: The invention comprises a shell (1), the shell (1) is provided with a control panel (2), the shell (1) is provided with a driving motor (3) electrically connected to the control panel (2), the shell (1) is hinged with a cover plate (4) matched therewith, the cover plate (4) is fixedly connected with a handle (5), the cover plate (4) is provided with symmetrical detection probes (6), the detection probes (6) are connected to an external synchrotron radiation light source, the symmetrical detection probes (6) are all electrically connected to the control panel (2), a symmetrical guide rod (7) is fixedly connected inside the shell (1), the guide rod (7) is slidably connected with a symmetrical sliding plate (8), the sliding plate (8) is slidably connected to the shell (1), the shell (1) is rotatably connected with a symmetrical threaded rod (9), the threaded rod (9) is provided with symmetrical The first threaded protrusion of the drive motor (3) is fixedly connected to the threaded rod (9) on one side, and the threaded rod (9) is threadedly matched with the first threaded protrusion of the adjacent sliding plate (8). The threaded rod (9) on one side is fixedly connected to the first gear (10), and the threaded rod (9) on the other side is fixedly connected to the second gear (11) meshing with the first gear (10). The second gear (11) and the first gear (10) have different numbers of teeth. The sliding plate (8) is rotatably connected to a sliding rod (12) slidably connected to the housing (1). The sliding rod (12) is provided with a second threaded protrusion. The sliding plate (8) is provided with a clamping mechanism for clamping solid propellant. An adjusting mechanism for applying variable stress to the solid propellant is provided in the housing (1); The adjustment mechanism includes evenly distributed L-shaped limiting rods (1401), the L-shaped limiting rods (1401) are fixedly connected to the housing (1), and a first limiting groove (1402) is provided at one end of the sliding rod (12) close to the adjacent L-shaped limiting rod (1401), and the first limiting groove (1402) cooperates with the adjacent L-shaped limiting rod (1401); The first limiting groove (1402) is a spiral groove, and the pitch of the symmetrical first limiting groove (1402) gradually increases along the opposite direction thereof.

2. The solid propellant in-situ loading test device based on a synchrotron radiation source according to claim 1, characterized in that: The clamping mechanism includes a sliding block (1301), the sliding block (1301) is slidably connected to an adjacent sliding plate (8), the sliding block (1301) is fixedly connected to a moving block (1302), the moving block (1302) is threadedly engaged with a second threaded protrusion of an adjacent sliding rod (12), the sliding block (1301) is slidably connected to a clamping block (1303), the clamping block (1303) is used to clamp the solid propellant, and the clamping block (1303) can be relatively replaced according to the shape of the solid propellant sample.

3. The solid propellant in-situ loading test device based on a synchrotron radiation source according to claim 2, characterized in that: When the cover plate (4) and the shell (1) are in a mating state, the detection probe (6) is located above the adjacent solid propellant.

4. The solid propellant in-situ loading test device based on a synchrotron radiation source according to claim 3, characterized in that: The clamping block (1303) is threadedly engaged with a threaded knob (1304), and the threaded knob (1304) is threadedly engaged with an adjacent sliding block (1301).

5. The solid propellant in-situ loading test device based on a synchrotron radiation source according to claim 4, characterized in that: A first elastic element (1403) is fixedly connected between the sliding plate (8) and the adjacent sliding rod (12) and is used to reset the adjacent sliding rod (12).

6. The solid propellant in-situ loading test device based on a synchrotron radiation source according to claim 5, characterized in that: The invention also includes a limiting mechanism for limiting the cover plate (4), the limiting mechanism is provided on the cover plate (4), the housing (1) is provided with symmetrical limiting slots, the limiting mechanism includes symmetrical limiting blocks (1501), the symmetrical limiting blocks (1501) are all slidably connected to the cover plate (4), the limiting blocks (1501) cooperate with the limiting slots adjacent to the housing (1), a second elastic element (1502) is fixedly connected between the limiting blocks (1501) and the cover plate (4), and the handle (5) is provided with an unlocking mechanism for causing the cover plate (4) to lose its limit.

7. The solid propellant in-situ loading test device based on a synchrotron radiation source according to claim 6, characterized in that: A third elastic element (1503) is fixedly connected between the cover plate (4) and the housing (1), and is used to automatically open the cover plate (4) after it loses its limit.

8. The solid propellant in-situ loading test device based on a synchrotron radiation source according to claim 7, characterized in that: The unlocking mechanism includes symmetrical straight limit rods (1601), the symmetrical straight limit rods (1601) are all slidably connected to the handle (5), one end of the straight limit rod (1601) close to the cover plate (4) is set as an inclined side surface, a moving rod (1602) is fixedly connected between the symmetrical straight limit rods (1601), a fourth elastic element (1603) is fixedly connected between the moving rod (1602) and the handle (5), and the limit block (1501) is provided with a second limit groove (1604), and the second limit groove (1604) cooperates with the adjacent straight limit rod (1601).

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