Thermal examination test device for thermal structure material of hypersonic flight vehicle

Abstract

The invention belongs to the technical field of aerospace test equipment, and particularly relates to a thermal examination test device for a thermal structure material of a hypersonic aircraft, which comprises a heating box and a rotating assembly, and the rotating assembly comprises a double-shaft motor fixedly mounted at the top of the heating box. A rotating table is fixedly installed at the end, close to the heating box, of a bottom output shaft of the double-shaft motor, the outer wall of the rotating table is rotationally connected with the inner wall of the heating box, and a circular truncated cone is fixedly installed at the bottom of the rotating table. Through rotation of the material body, each position of the material is uniformly heated, the non-uniformity of temperature distribution is improved, the accuracy of test data is ensured, the heating efficiency is improved, and high-temperature gas is guided to the material body, so that better heating is performed; and the rotating airflow can be gathered to the middle position through the inclined surface of the drainage plate, and is matched with the fan blades to enable heat to be gathered to the position of the material body, so that the material body is better heated.

Description

Technical Field

[0001] The invention belongs to the technical field of aerospace test equipment, and in particular is a thermal assessment test device for thermal structural materials of a hypersonic aircraft. Background Art

[0002] Rockets and satellite launches are important components of the aerospace field. Together, they promote human exploration and use of space. A rocket is a vehicle that uses its own power to send payloads into space. Satellite launch refers to the process of using a rocket to send a satellite into a predetermined orbit. There are many types of satellites, including communication satellites, earth resources satellites, meteorological satellites, navigation satellites, reconnaissance satellites, etc. They each have different tasks and functions. During the flight, a rocket will generate relatively high temperatures. In order to ensure the safety of the rocket's flight, thermal assessment tests need to be conducted on the rocket's production materials.

[0003] A Chinese patent with the announcement number CN115445674B discloses a high and low temperature humidity test chamber. This patent uses a pair of limit plates to clamp the material being tested. When the material bursts, the limit plates can be used to block the laterally moving debris, thereby reducing the damage caused by the flying debris to the internal components of the test chamber body and not affecting subsequent testing.

[0004] In the current prior art, when conducting thermal tests, since the material itself has a certain volume, uneven heating often occurs when the material is heated by a heating device, which causes different temperatures at different locations of the material, directly affecting the accuracy and reliability of the test results.

[0005] To this end, the present invention provides a thermal assessment test device for thermal structure materials of a hypersonic aircraft. Summary of the invention

[0006] In order to make up for the deficiencies of the prior art, at least one technical problem raised in the background technology is solved.

[0007] The technical solution adopted by the present invention to solve its technical problems is: a thermal assessment test device for thermal structural materials of a hypersonic aircraft described in the present invention includes a heating box and a rotating assembly, the rotating assembly includes a dual-axis motor fixedly installed on the top of the heating box, a rotating table is fixedly installed on one end of the bottom output shaft of the dual-axis motor close to the heating box, the outer wall of the rotating table is rotatably connected to the inner wall of the heating box, a round table is fixedly installed on the bottom of the rotating table, a number of telescopic rods are evenly fixedly installed on the bottom of the round table, and a fixing assembly is fixedly installed on the ends of the telescopic rods away from the round table, a number of fan blades are evenly fixedly installed on the outer wall of the round table, and a lifting assembly is arranged above the dual-axis motor.

[0008] Preferably, the fixing assembly includes a fixing seat fixedly connected to the telescopic rod, the inner wall of the fixing seat is slidably connected to the material body, the inner wall of the fixing seat is plugged with a pin, the material body is fixed to the fixing seat by the set pin, and the inner wall of the heating box is evenly fixedly installed with a plurality of guide plates.

[0009] Preferably, the lifting assembly includes a traveling screw fixedly connected to the end of the dual-axis motor output shaft away from the heating box, the outer wall of the traveling screw is rotatably mounted with a lifting bracket, the inner walls at both ends of the lifting bracket are fixedly mounted with vertical rods, the end of the vertical rod away from the lifting bracket passes through the heating box and is fixedly mounted with a horizontal plate, a circular ring is fixedly mounted between the two horizontal plates, a clamping piece is fixedly mounted on the top of the fixing seat, the inner wall of the clamping piece is slidably connected to the outer wall of the circular ring, a cooling box is fixedly mounted on the bottom of the heating box, and the interior of the cooling box is filled with cooling water.

[0010] Preferably, a circular plate is rotatably mounted on the inner wall of the heating box, a connecting shaft is fixedly mounted at the axis of the circular plate, one end of the connecting shaft away from the circular plate is fixedly connected to the bottom of the truncated table, a plurality of through grooves are opened on the top of the circular plate, and the plurality of through grooves are respectively located below a plurality of material bodies.

[0011] Preferably, a sealing plate is provided on the inner side of several of the through grooves, a torsion spring shaft is fixedly installed on the inner wall of the sealing plate, both ends of the torsion spring shaft are fixedly connected to the inner wall of the through groove, a stop block is fixedly installed on the inner wall of the through groove, and the outer wall of the stop block is in conflict with the outer wall of the sealing plate.

[0012] Preferably, a positioning seat is fixedly installed at one end of the traveling screw away from the dual-axis motor, a plurality of elastic parts are fixedly installed at the bottom of the positioning seat, an extrusion seat is slidably installed on the outer wall of the traveling screw, one end of the elastic parts away from the positioning seat is fixedly connected to the extrusion seat, and the bottom of the extrusion seat is in conflict with the top of the lifting bracket.

[0013] Preferably, the inner wall of the heating box is provided with a collision assembly, and the collision assembly includes an adjusting screw threadedly mounted on the inner wall of the heating box, one end of the adjusting screw is located on the inner side of the heating box and is rotatably mounted with an impact block, the other end of the adjusting screw is located on the outer side of the heating box and is fixedly mounted with a rotating ring, a crank is fixedly mounted on the outer wall of the rotating ring, a limiting shaft is fixedly mounted on the outer wall of the impact block, and the outer wall of the limiting shaft is slidably connected to the inner wall of the heating box.

[0014] Preferably, the inner wall of the heating box is symmetrically provided with limiting slide grooves, the outer walls of the two horizontal plates are slidingly connected to the inner walls of the two limiting slide grooves respectively, and a stabilizing bracket is fixedly installed on the top of the heating box, and the inner wall of the stabilizing bracket is rotatably connected to the outer wall of the advancing screw.

[0015] Preferably, a sealed door is hinged on the inner wall of the heating box, and transparent observation windows are fixedly installed on the sealed door and the inner wall of the cooling box.

[0016] Preferably, a water inlet pipe and a drain pipe are fixedly installed on the inner walls of the cooling box near the top and the bottom respectively, a control valve is fixedly installed on the outer wall of the drain pipe, a support seat is fixedly installed on the outer wall of the heating box, and a plurality of support legs are fixedly installed on the bottom of the support seat.

[0017] The beneficial effects of the present invention are as follows: 1. The thermal assessment test device for the thermal structure material of a hypersonic aircraft described in the present invention drives the material body to rotate during heating by means of the structures such as the rotating component and the fixed component, so that each position of the material is heated evenly, the unevenness of the temperature distribution is improved, the accuracy of the test data is ensured, the heating efficiency is improved, and the high-temperature gas is guided to the material body, so as to better heat it. When the material body rotates, a rotating airflow is generated, and the rotating airflow can be converged to the middle position through the inclined surface of the guide plate, and the heat is gathered to the position of the material body in cooperation with the fan blades, so as to better heat the material body.

[0018] 2. The thermal assessment test device for the thermal structure material of a hypersonic aircraft described in the present invention, through the provision of structures such as a lifting assembly, allows the material body to move down to the inside of a cooling box after the material body is heated, and the cooling water in the cooling box is used to quickly cool the material body. Through the cycle of rapid heating and cooling, the extreme temperature change environment that the material body may encounter in actual aerospace applications can be simulated, and its thermal shock performance in such an environment can be evaluated, which not only helps to evaluate the thermal stability and durability of the material, but also can provide strong support for optimizing material performance, improving design, quality control and standard setting.

[0019] 3. The thermal assessment test device for the thermal structure material of a hypersonic aircraft described in the present invention, through the arrangement of structures such as collision components, after the material body is heated, utilizes the rotation of the material body to make it collide with the impact block, thereby simulating the state of the material body after being impacted at a high temperature. By impacting the material body and causing it to vibrate, the thermal shock effect caused by sudden temperature change can be simulated, thereby evaluating the thermal shock performance of the material body, providing strong support for the design and optimization of the material. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The present invention will be further described below in conjunction with the accompanying drawings.

[0021] Figure 1 It is a three-dimensional structural schematic diagram of the present invention; Figure 2It is a cross-sectional view of the heating box and cooling box structure of the present invention; Figure 3 is a cross-sectional view of the heating box structure of the present invention; Figure 4 It is a schematic diagram of the structure of the truncated cone of the present invention; Figure 5 It is a structural schematic diagram of the fixing seat of the present invention; Figure 6 It is a schematic diagram of the split structure at the fixing seat of the present invention; Figure 7 It is a structural schematic diagram of the traveling screw of the present invention; Figure 8 It is a schematic diagram of the structure of the ring of the present invention; Fig. 9 It is a schematic diagram of the structure of the circular plate of the present invention; Fig.10 It is a structural schematic diagram of the sealing plate of the present invention; Fig.11 It is a structural schematic diagram of the lifting bracket of the present invention; Fig.12 It is a schematic diagram of the structure of the impact block of the present invention; In the figure: 1. heating box; 2. double-axis motor; 3. rotating table; 4. round table; 5. telescopic rod; 6. fan blade; 7. fixed seat; 8. material body; 9. pin shaft; 10. travel screw; 11. lifting bracket; 12. vertical rod; 13. horizontal plate; 14. circular ring; 15. clamping part; 16. cooling box; 17. circular plate; 18. connecting shaft; 19. sealing plate; 20. torsion spring shaft; 21. block; 22. positioning seat; 23. elastic part; 24. extrusion seat; 25. adjusting screw; 26. impact block; 27. rotating ring; 28. crank; 29. ​​limit shaft; 30. limit slide; 31. stable bracket; 32. sealing door; 33. transparent observation window; 34. water inlet pipe; 35. drain pipe; 36. control valve; 37. support seat; 38. support leg; 39. drainage plate. DETAILED DESCRIPTION

[0022] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention is further explained below in conjunction with specific implementation methods.

[0023] like Figures 1 to 4As shown, a thermal assessment test device for thermal structural materials of a hypersonic aircraft described in an embodiment of the present invention comprises a heating box 1, and also comprises a rotating assembly, the rotating assembly comprises a dual-axis motor 2 fixedly mounted on the top of the heating box 1, a rotating table 3 is fixedly mounted on one end of the bottom output shaft of the dual-axis motor 2 close to the heating box 1, the outer wall of the rotating table 3 is rotatably connected to the inner wall of the heating box 1, a round table 4 is fixedly mounted on the bottom of the rotating table 3, a number of telescopic rods 5 are evenly fixedly mounted on the bottom of the round table 4, a number of telescopic rods 5 are fixedly mounted on one end away from the round table 4, a number of fan blades 6 are evenly fixedly mounted on the outer wall of the round table 4, and a lifting assembly is arranged above the dual-axis motor 2; when conducting a thermal assessment test, the dual-axis motor 2 is started for forward rotation, and the dual-axis motor 2 will drive the rotating table 3 to rotate When the rotating table 3 rotates, the circular table 4 will be driven to rotate. When the circular table 4 rotates, it will drive each fixed component to rotate through the telescopic rod 5. The material to be tested is fixed on the fixed component. As the fixed component rotates, the material will also rotate accordingly. By driving the material to rotate, each position of the material is heated evenly, the uneven temperature distribution is improved, and the accuracy of the test data is ensured. At the same time, the rotation of the material can make full use of the heat in the heating box 1 to improve the heating efficiency. When the circular table 4 rotates, the fan blades 6 will be driven to rotate. When the fan blades 6 rotate, they can promote gas circulation and guide the high-temperature gas in the heating box 1 to the material below, so as to better heat the material. There are multiple fixed components, so that multiple materials can be thermally tested at the same time to avoid accidents in the test.

[0024] like Figures 1 to 6 As shown, the fixing assembly includes a fixing seat 7 fixedly connected to the telescopic rod 5, the inner wall of the fixing seat 7 is slidably connected with a material body 8, the inner wall of the fixing seat 7 is plugged with a pin shaft 9, the material body 8 is fixed to the fixing seat 7 by the arranged pin shaft 9, and the inner wall of the heating box 1 is evenly and fixedly installed with a plurality of guide plates 39; the material body 8 is slid into the inner side of the fixing seat 7, and then the pin shaft 9 is inserted into the fixing seat 7 to limit the material body 8, thereby fixing the material body 8, and the material body 8 is arranged in a plate shape, and when the material body 8 rotates, the airflow will rotate, and the airflow close to the inner wall of the heating box 1 will hit the surface of the guide plate 39, and the inclined surface of the guide plate 39 can make the airflow converge to the middle position, and cooperate with the fan blades 6 to gather heat to the position of the material body 8, so that the airflow circulates through the material body 8, thereby better heating the material body 8.

[0025] like Figures 1 to 8As shown, the lifting assembly includes a traveling screw 10 fixedly connected to one end of the output shaft of the dual-axis motor 2 away from the heating box 1, a lifting bracket 11 is rotatably installed on the outer wall of the traveling screw 10, and vertical rods 12 are fixedly installed on the inner walls of both ends of the lifting bracket 11, and the end of the vertical rod 12 away from the lifting bracket 11 passes through the heating box 1 and is fixedly installed with a horizontal plate 13, and a circular ring 14 is fixedly installed between the two horizontal plates 13, and a clamping member 15 is fixedly installed on the top of the fixed seat 7, and the inner wall of the clamping member 15 is slidably connected with the outer wall of the circular ring 14, and a cooling box 16 is fixedly installed on the bottom of the heating box 1, and the interior of the cooling box 16 is filled with cooling water; because the lifting bracket 11 is located at the terminal end of the top of the thread of the traveling screw 10, a threaded section and a smooth section are provided on the traveling screw 10, and when the dual-axis motor 2 rotates forward, the thread of the traveling screw 10 will not act on the lifting bracket 11, and when the material body 8 is heated, the dual-axis The motor 2 reverses, and the dual-axis motor 2 reverses, causing the traveling screw 10 to reverse. When the traveling screw 10 reverses, the lifting bracket 11 moves downward under the action of the thread. When the lifting bracket 11 moves downward, the horizontal plate 13 is driven downward through the vertical rod 12. When the horizontal plate 13 moves downward, the circular ring 14 is driven downward. When the circular ring 14 moves downward, the fixing seat 7 is pushed downward through the clamp 15. The downward movement of the fixing seat 7 causes the material body 8 to move downward, and the material body 8 extends downward into the cooling water in the cooling box 16. The material body 8 can be quickly cooled by the cooling water. Through the cycle of rapid heating and cooling, the extreme temperature change environment that the material body 8 may encounter in actual aerospace applications can be simulated, and its thermal shock performance in such an environment can be evaluated. This not only helps to evaluate the thermal stability and durability of the material, but also can provide strong support for optimizing material performance, improving design, quality control and standard setting.

[0026] like Figures 1 to 9 As shown, a circular plate 17 is rotatably installed on the inner wall of the heating box 1, and a connecting shaft 18 is fixedly installed at the axis of the circular plate 17. The end of the connecting shaft 18 away from the circular plate 17 is fixedly connected to the bottom of the truncated table 4, and a plurality of through grooves are opened on the top of the circular plate 17, and the plurality of through grooves are respectively located below a plurality of material bodies 8; the circular plate 17 separates the heating box 1 and the cooling box 16 to prevent heat loss inside the heating box 1, and the circular plate 17 is connected to the truncated table 4 through the connecting shaft 18. When the truncated table 4 rotates, the circular plate 17 is driven to rotate with it through the connecting shaft 18. The rotation of the circular plate 17 ensures that the through grooves are always located below the material body 8 to prevent misalignment. When the material body 8 moves downward, it passes through the through grooves into the cooling box 16, thereby realizing cooling.

[0027] like Figures 9 and 10As shown, a sealing plate 19 is provided on the inner side of several through grooves, and a torsion spring shaft 20 is fixedly installed on the inner wall of the sealing plate 19. Both ends of the torsion spring shaft 20 are fixedly connected to the inner wall of the through groove, and a stop block 21 is fixedly installed on the inner wall of the through groove, and the outer wall of the stop block 21 is in conflict with the outer wall of the sealing plate 19; a sealing plate 19 is provided inside the through groove, and the through groove is sealed by the sealing plate 19 to prevent heat from being lost through the through groove. When the material body 8 moves down for cooling, the material body 8 will squeeze the sealing plate 19, and the sealing plate 19 will flip around the torsion spring shaft 20, thereby opening the through groove and providing conditions for the material body 8 to pass through the through groove. When the material body 8 moves up, the sealing plate 19 will flip in the opposite direction under the action of the torsion spring shaft 20 to reset, so that the through groove continues to remain sealed after the material body 8 is lifted, and the stop block 21 is used to limit the sealing plate 19 so that the sealing plate 19 remains horizontal after reset to ensure its sealing effect.

[0028] like Figure 7 and Fig.11 As shown, a positioning seat 22 is fixedly installed at one end of the traveling screw 10 away from the dual-axis motor 2, and a plurality of elastic members 23 are fixedly installed at the bottom of the positioning seat 22. An extrusion seat 24 is slidably installed on the outer wall of the traveling screw 10, and one end of the elastic member 23 away from the positioning seat 22 is fixedly connected to the extrusion seat 24, and the bottom of the extrusion seat 24 conflicts with the top of the lifting bracket 11; when the lifting bracket 11 is located at the top terminal of the thread of the traveling screw 10, the lifting bracket 11 will squeeze the extrusion seat 24, and the elastic member 23 is in a contracted state at this time. Therefore, under the action of the elastic member 23, the extrusion seat 24 will maintain a state of applying an extrusion force to the lifting bracket 11, and the extrusion of the extrusion seat 24 ensures that when the traveling screw 10 is reversed, the traveling screw 10 can drive the lifting bracket 11 to move downward through the thread to prevent idling when the traveling screw 10 is reversed.

[0029] like Figures 1 to 3 and Fig.12As shown, the inner wall of the heating box 1 is provided with a collision assembly, which includes an adjusting screw 25 threadedly mounted on the inner wall of the heating box 1, one end of the adjusting screw 25 is located on the inner side of the heating box 1 and is rotatably mounted with a collision block 26, the other end of the adjusting screw 25 is located on the outer side of the heating box 1 and is fixedly mounted with a rotating ring 27, a crank 28 is fixedly mounted on the outer wall of the rotating ring 27, a limiting shaft 29 is fixedly mounted on the outer wall of the collision block 26, and the outer wall of the limiting shaft 29 is slidably connected to the inner wall of the heating box 1; when the material body 8 is heated, the adjusting screw 25 is driven to rotate by rotating the crank 28 or the rotating ring 27, and the adjusting screw 25 is rotated by rotating the crank 28 or the rotating ring 27. The cooperation of the threads of the heating box 1 will drive the impact block 26 to extend toward the inside of the heating box 1. The impact block 26 is located on the inside of the heating box 1 near the bottom. In the vertical direction, the impact block 26 overlaps with the material body 8. The extended impact block 26 will be located on the movement path at the bottom of the material body 8. When the material body 8 rotates, it will collide with the impact block 26, thereby simulating the state of the material body 8 after being hit under high temperature. By colliding with the material body 8 and making it vibrate, the thermal shock effect caused by sudden temperature change can be simulated, thereby evaluating the thermal shock performance of the material body 8, and providing strong support for the design and optimization of the material.

[0030] like Figures 1 to 3 As shown, the inner wall of the heating box 1 is symmetrically provided with limiting grooves 30, the outer walls of the two cross plates 13 are respectively slidably connected to the inner walls of the two limiting grooves 30, and a stabilizing bracket 31 is fixedly installed on the top of the heating box 1, and the inner wall of the stabilizing bracket 31 is rotatably connected to the outer wall of the traveling screw 10; the cross plate 13 is limited by the limiting grooves 30 so that the cross plate 13 moves along a preset direction to ensure that the material body 8 can be effectively lifted and lowered, and the traveling screw 10 is limited by the stabilizing bracket 31 to increase the stability of the traveling screw 10 and prevent the traveling screw 10 from deflecting.

[0031] like Figure 1 As shown, the inner wall of the heating box 1 is hinged with a sealed door 32, and the sealed door 32 and the inner wall of the cooling box 16 are fixedly installed with a transparent observation window 33; by opening the sealed door 32, the material body 8 can be placed and taken out, and it is convenient to inspect and maintain the inside of the heating box 1. The transparent observation window 33 can be used to observe the working status inside the device.

[0032] like Figure 1 to Figure 2As shown, the inner walls of the cooling box 16 near the top and the bottom are respectively fixedly installed with a water inlet pipe 34 and a drain pipe 35, the outer wall of the drain pipe 35 is fixedly installed with a control valve 36, the outer wall of the heating box 1 is fixedly installed with a support seat 37, and the bottom of the support seat 37 is fixedly installed with a plurality of support legs 38; the water inlet pipe 34 is used to add cooling water for cooling work into the cooling box 16. When the cooling water needs to be replaced, the control valve 36 is opened to keep the drain pipe 35 in a smooth state, and the cooling water in the cooling box 16 will be discharged through the drain pipe 35, and then new cooling water can be added. The support legs 38 are connected to the heating box 1 through the support seats 37, and the device is supported by the support legs 38 so that the device is at a suitable working height for easy use of the device.

[0033] Working principle: When conducting a thermal assessment test, start the dual-axis motor 2 for forward rotation, and the dual-axis motor 2 will drive the rotating table 3 to rotate. When the rotating table 3 rotates, it will drive the round table 4 to rotate. When the round table 4 rotates, it will drive each fixed component to rotate through the telescopic rod 5. The material to be tested is fixed on the fixed component. As the fixed component rotates, the material will also rotate with it. By driving the material to rotate, each position of the material is heated evenly, the uneven temperature distribution is improved, and the accuracy of the test data is ensured. At the same time, the rotation of the material can make full use of the heat in the heating box 1 to improve the heating efficiency. When the round table 4 rotates, it will drive the fan blades 6 to rotate, and the rotation of the fan blades 6 can promote gas circulation. The high-temperature gas in the heating box 1 is guided to the material below, so as to better heat the material. There are multiple fixing components, so that multiple materials can be thermally tested at the same time to avoid accidents in the test. The material body 8 is slid into the inner side of the fixing seat 7, and then the pin shaft 9 is inserted into the fixing seat 7 to limit the material body 8, so as to fix the material body 8. The material body 8 is set to a plate shape. When the material body 8 rotates, a rotating airflow will be generated. The rotating airflow will hit the surface of the guide plate 39. The inclined surface of the guide plate 39 can make the airflow converge to the center position, and cooperate with the fan blades 6 to make the heat gather to the position of the material body 8, so as to better heat the material body 8.

[0034] Since the lifting bracket 11 is located at the terminal end at the top of the thread of the traveling screw 10, when the dual-axis motor 2 rotates forward, the thread of the traveling screw 10 will not affect the lifting bracket 11. When the material body 8 is heated, the dual-axis motor 2 reverses. When the dual-axis motor 2 reverses, the traveling screw 10 reverses. When the traveling screw 10 reverses, the lifting bracket 11 moves downward under the action of the thread. When the lifting bracket 11 moves downward, it drives the horizontal plate 13 to move downward through the vertical rod 12. When the horizontal plate 13 moves downward, it drives the ring 14 to move downward. When the ring 14 moves downward, it pushes the fixing seat 7 to move downward through the clamping member 15. The fixing seat 7 moves downward to move the material body 8 downward, and the material body 8 extends downward into The cooling water in the cooling box 16 can quickly cool the material body 8. Through the cycle of rapid heating and cooling, the extreme temperature change environment that the material body 8 may encounter in actual aerospace applications can be simulated to evaluate its thermal shock performance in such an environment. This not only helps to evaluate the thermal stability and durability of the material, but also provides strong support for optimizing material performance, improving design, quality control and standard setting. The circular plate 17 separates the heating box 1 and the cooling box 16 to prevent the heat inside the heating box 1 from dissipating. The circular plate 17 is connected to the round table 4 through the connecting shaft 18. When the round table 4 rotates, it will drive the circular plate 1 through the connecting shaft 18. 7 follows the rotation, and the through slot is always located below the material body 8 through the rotation of the circular plate 17 to prevent misalignment. When the material body 8 moves down, it will enter the cooling box 16 through the through slot, thereby realizing cooling. A sealing plate 19 is arranged inside the through slot, and the through slot is sealed by the sealing plate 19 to prevent heat from being lost through the through slot. When the material body 8 moves down for cooling, the material body 8 will squeeze the sealing plate 19, and the sealing plate 19 will flip around the torsion spring shaft 20, thereby opening the through slot and providing conditions for the material body 8 to pass through the through slot. When the material body 8 moves up, the sealing plate 19 will flip in the opposite direction under the action of the torsion spring shaft 20 to perform cooling. The stop block 21 is used to limit the sealing plate 19 so that the sealing plate 19 remains horizontal after being reset to ensure its sealing effect. When the lifting bracket 11 is located at the top terminal of the thread of the traveling screw 10, the lifting bracket 11 will squeeze the squeezing seat 24. At this time, the elastic member 23 is in a contracted state. Therefore, under the action of the elastic member 23, the squeezing seat 24 will maintain the state of applying squeezing force to the lifting bracket 11. The squeezing of the squeezing seat 24 ensures that when the traveling screw 10 is reversed, the traveling screw 10 can drive the lifting bracket 11 to move downward through the thread to prevent idling when the traveling screw 10 is reversed.

[0035] When the material body 8 is heated, the adjusting screw 25 is driven to rotate by turning the crank 28 or the rotating ring 27. The adjusting screw 25 will drive the impact block 26 to extend to the inside of the heating box 1 through the cooperation with the thread of the heating box 1. The extended impact block 26 will be located on the movement path at the bottom of the material body 8. When the material body 8 rotates, it will collide with the impact block 26, thereby simulating the state of the material body 8 after being hit under high temperature. By hitting the material body 8 and making it vibrate, the thermal shock effect caused by sudden temperature change can be simulated, thereby evaluating the thermal shock performance of the material body 8, providing strong support for the design and optimization of the material.

[0036] The above shows and describes the basic principles, main features and advantages of the present invention. It should be understood by those skilled in the art that the present invention is not limited to the above embodiments. The above embodiments and descriptions are only for explaining the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which fall within the scope of the present invention. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. A thermal assessment test device for a hypersonic vehicle thermal structure material, comprising a heating box (1), characterized in that: The invention also comprises a rotating assembly, wherein the rotating assembly comprises a double-axis motor (2) fixedly mounted on the top of the heating box (1); a rotating table (3) is fixedly mounted on one end of the bottom output shaft of the double-axis motor (2) close to the heating box (1); the outer wall of the rotating table (3) is rotatably connected to the inner wall of the heating box (1); a round table (4) is fixedly mounted on the bottom of the rotating table (3); a plurality of telescopic rods (5) are evenly fixedly mounted on the bottom of the round table (4); a fixing assembly is fixedly mounted on one end of the telescopic rods (5) away from the round table (4); a plurality of fan blades (6) are evenly fixedly mounted on the outer wall of the round table (4); and a lifting assembly is arranged above the double-axis motor (2).

2. The thermal assessment test device for thermal structural materials of hypersonic aircraft according to claim 1, characterized in that: The fixing assembly comprises a fixing seat (7) fixedly connected to the telescopic rod (5); a material body (8) is slidably connected to the inner wall of the fixing seat (7); a pin shaft (9) is inserted into the inner wall of the fixing seat (7); the material body (8) is fixed to the fixing seat (7) via the provided pin shaft (9); and a plurality of guide plates (39) are evenly fixedly mounted on the inner wall of the heating box (1).

3. A thermal assessment test device for thermal structural materials of hypersonic aircraft according to claim 2, characterized in that: The lifting assembly comprises a travel screw (10) fixedly connected to one end of the output shaft of the dual-axis motor (2) away from the heating box (1); a lifting bracket (11) is rotatably mounted on the outer wall of the travel screw (10); vertical rods (12) are fixedly mounted on the inner walls of both ends of the lifting bracket (11); one end of the vertical rod (12) away from the lifting bracket (11) passes through the heating box (1) and is fixedly mounted with a horizontal plate (13); a circular ring (14) is fixedly mounted between the two horizontal plates (13); a clamping member (15) is fixedly mounted on the top of the fixing seat (7); the inner wall of the clamping member (15) is slidably connected to the outer wall of the circular ring (14); a cooling box (16) is fixedly mounted on the bottom of the heating box (1), and the interior of the cooling box (16) is filled with cooling water.

4. The thermal assessment test device for thermal structural materials of hypersonic aircraft according to claim 3, characterized in that: A circular plate (17) is rotatably mounted on the inner wall of the heating box (1), a connecting shaft (18) is fixedly mounted at the axis of the circular plate (17), one end of the connecting shaft (18) away from the circular plate (17) is fixedly connected to the bottom of the truncated table (4), and a plurality of through grooves are formed on the top of the circular plate (17), and the plurality of through grooves are respectively located below a plurality of material bodies (8).

5. The thermal assessment test device for thermal structural materials of hypersonic aircraft according to claim 4, characterized in that: A sealing plate (19) is provided on the inner side of a plurality of the through grooves, a torsion spring shaft (20) is fixedly mounted on the inner wall of the sealing plate (19), both ends of the torsion spring shaft (20) are fixedly connected to the inner wall of the through groove, a stop block (21) is fixedly mounted on the inner wall of the through groove, and the outer wall of the stop block (21) abuts against the outer wall of the sealing plate (19).

6. The thermal assessment test device for thermal structural materials of hypersonic aircraft according to claim 5, characterized in that: A positioning seat (22) is fixedly mounted on one end of the advancing screw rod (10) away from the dual-axis motor (2), a plurality of elastic members (23) are fixedly mounted on the bottom of the positioning seat (22), an extrusion seat (24) is slidably mounted on the outer wall of the advancing screw rod (10), one end of the elastic member (23) away from the positioning seat (22) is fixedly connected to the extrusion seat (24), and the bottom of the extrusion seat (24) is in contact with the top of the lifting bracket (11).

7. The thermal assessment test device for thermal structural materials of hypersonic aircraft according to claim 6, characterized in that: The inner wall of the heating box (1) is provided with a collision assembly, the collision assembly comprising an adjusting screw (25) threadedly mounted on the inner wall of the heating box (1), an impact block (26) rotatably mounted on one end of the adjusting screw (25) and located on the inner side of the heating box (1), a rotating ring (27) fixedly mounted on the other end of the adjusting screw (25) and located on the outer side of the heating box (1), a crank (28) fixedly mounted on the outer wall of the rotating ring (27), a limiting shaft (29) fixedly mounted on the outer wall of the impact block (26), and the outer wall of the limiting shaft (29) is slidably connected to the inner wall of the heating box (1).

8. The thermal assessment test device for thermal structural materials of hypersonic aircraft according to claim 7, characterized in that: The inner wall of the heating box (1) is symmetrically provided with limit slide grooves (30), the outer walls of the two horizontal plates (13) are slidably connected to the inner walls of the two limit slide grooves (30) respectively, and a stabilizing bracket (31) is fixedly installed on the top of the heating box (1), and the inner wall of the stabilizing bracket (31) is rotatably connected to the outer wall of the advancing screw (10).

9. The thermal assessment test device for thermal structural materials of hypersonic aircraft according to claim 8, characterized in that: A sealed door (32) is hingedly connected to the inner wall of the heating box (1), and a transparent observation window (33) is fixedly mounted on the sealed door (32) and the inner wall of the cooling box (16).

10. The thermal assessment test device for thermal structural materials of hypersonic aircraft according to claim 9, characterized in that: A water inlet pipe (34) and a drain pipe (35) are fixedly mounted on the inner walls of the cooling box (16) near the top and bottom, respectively; a control valve (36) is fixedly mounted on the outer wall of the drain pipe (35); a support seat (37) is fixedly mounted on the outer wall of the heating box (1); and a plurality of support legs (38) are fixedly mounted on the bottom of the support seat (37).

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