Ultrahigh-temperature thermal examination test device for thermal protection structure of aircraft

Abstract

The invention belongs to the field of thermal protection structure detection, and particularly relates to an aircraft thermal protection structure ultrahigh-temperature thermal examination test device which comprises a portal frame. A sealed cabin is arranged on one side of the bottom of the portal frame; the sealed cabin is made of a fireproof thermal insulation material; the surface of a cross beam of the portal frame is slidably connected with a moving seat; the bottom surface of the moving seat is fixedly connected with a hydraulic cylinder; the telescopic end of the hydraulic cylinder is fixedly connected with a cabin cover; the bottom surface of the cabin cover is fixedly connected with a connecting assembly; the connecting assembly is used for fixing a to-be-detected sample, vertical movement and horizontal movement of the hatch cover are controlled through the hydraulic cylinder and the movable base respectively, the hatch cover is moved to one side of the sealed cabin, then the sample is fixedly connected to the bottom face of the hatch cover through the connecting assembly, and therefore the purpose that a tester does not need to enter the sealed cabin personally is achieved. Therefore, potential safety risks and inaccurate experimental data caused by mistakenly touching the nozzle when the sample is installed are avoided.

Description

Technical Field

[0001] The invention belongs to the field of thermal protection structure detection, in particular to an ultra-high temperature thermal assessment test device for a thermal protection structure of an aircraft. Background Art

[0002] When an aircraft enters the atmosphere, the air in front of it will be rapidly compressed due to its high speed when entering the atmosphere. At the same time, it will also rub against the surrounding air, causing the temperature of the aircraft to rise sharply, thus affecting the safety of the aircraft. For this reason, it is necessary to conduct ultra-high temperature assessment tests on the thermal protection structure of the aircraft.

[0003] The prior art also proposes some solutions. For example, a patent application with publication number CN115072012A discloses a thermal assessment test system for a hypersonic aircraft thermal protection structure, including a closed test cabin, a fuel storage tank, an air intake pipe and a gas generator. The gas generator transports high-temperature gas to the closed test cabin through a gas pipe; the closed test cabin includes a cabin body, a plurality of direct-flame burners and a plurality of observation window assemblies. The high-temperature gas generated by the direct-flame burners is used to heat the entire aircraft equipment test piece, and the maximum heating temperature can reach 1500K. This solution has the advantages of low test cost, large test structure size, wide applicability and short test preparation cycle.

[0004] The ultra-high temperature test device in the above technology is to install the sample to be tested in a fireproof and heat-insulating closed test chamber, and then directly spray flames at the sample through a direct flame burner, thereby realizing the test of the sample of the thermal protection structure. However, during the sample installation process, the experimenter needs to enter the closed test chamber to work, and the closed test chamber is surrounded by direct flame burners. Not only is the safety of the experimenter not guaranteed, but it is also easy to collide with the direct flame burner during the installation process, causing damage to the direct flame burner or change in angle, thereby affecting the test effect.

[0005] To this end, the present invention provides an ultra-high temperature thermal assessment test device for a thermal protection structure of an 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: the ultra-high temperature thermal assessment test device of the aircraft thermal protection structure described in the present invention comprises a gantry; a sealed cabin is arranged on one side of the bottom of the gantry; the sealed cabin is made of fireproof and heat-insulating material, and the hatch of the sealed cabin is located on its top surface; a moving seat is slidably connected to the surface of the crossbeam of the gantry, and the moving seat is driven by a motor; a hydraulic cylinder is fixedly connected to the bottom surface of the moving seat; a hatch cover is fixedly connected to the telescopic end of the hydraulic cylinder, and the hatch cover is made of fireproof and heat-insulating material; a connecting component is fixedly connected to the bottom surface of the hatch cover; the connecting component is used to fix the sample to be tested; a plurality of uniformly arranged nozzles are installed at the bottom of the sealed cabin, and the nozzles are connected to the external gas pipeline through a conduit; a plurality of uniformly arranged observation ports are opened around the sealed cabin; high-temperature resistant glass is installed in the observation port.

[0008] Preferably, a pair of high temperature resistant glasses are provided, and a gap is left between the high temperature resistant glasses; a suction pipe is fixedly connected to the side wall of the sealed cabin, and the suction pipe extends into the enclosed space formed by the two high temperature resistant glasses and the inner wall of the observation port; a vacuum pressure gauge is installed on the surface of the suction pipe outside the sealed cabin.

[0009] Preferably, the end of the suction tube away from the high temperature resistant glass is slidably connected to a sleeve; the end of the sleeve away from the suction tube is fixedly connected to a rubber pad; the side surface of the sleeve is provided with a plurality of evenly arranged air ports; the surface of the suction tube is threadedly connected to an extrusion cylinder, and the extrusion cylinder is located at the end of the sleeve away from the rubber pad.

[0010] Preferably, the connecting assembly includes two pairs of guide tubes; the guide tubes are evenly fixed to the bottom surface of the hatch cover, and the top of the guide tubes passes through the hatch cover; two pairs of servo motors are fixed to the top surface of the hatch cover; a winding drum is installed at the output end of the servo motor; a steel cable is fixed to the surface of the winding drum, and the steel cable passes through the guide tubes; a hook is fixed to the end of the steel cable away from the winding drum.

[0011] Preferably, a receiving plate is fixedly connected to the top surface of the guide tube; a limiting hole is opened on the top surface of the receiving plate at the position corresponding to the steel cable, and the steel cable passes through the limiting hole; a pair of symmetrically arranged arc plates are slidably arranged on the top surface of the receiving plate; one end of the paired arc plates is fixedly connected to a connecting plate; the paired connecting plates are commonly threadedly connected with a double-thread screw.

[0012] Preferably, the bottom surface of the hatch cover is fixedly connected with a support tube between each guide tube; the support tube is slidably connected with a push rod inside; the support tube is rotatably connected with a threaded rod inside; the push rod is provided with a clearance groove at the corresponding position of the threaded rod at one end of the push rod close to the threaded rod; the side surface of the support tube is rotatably connected with a drive rod, and the drive rod extends to the inside of the support tube; the drive rod is transmitted between the end of the drive rod located inside the support tube and the threaded rod through a gear set; the surface of the threaded rod is threadedly connected with a limit plate.

[0013] Preferably, the bottom surface of the push rod is rotatably connected to a push block; the side surface of the push block is provided with a pair of symmetrically arranged rotation grooves; a push rod is rotatably connected in the rotation groove; the surface of the push block is threadedly connected to a limiting cylinder, and the limiting cylinder is located at the top of the push rod Preferably, two pairs of symmetrically arranged support rods are installed on the bottom surface of the hatch cover, and the four support rods are respectively located at the four corners of the hatch cover; a pair of support plates are installed at one end of the support rod close to the top rod; a fixed pulley 1 is rotatably connected between the paired support plates; and a fixed pulley 2 is rotatably connected to one side of the guide tube close to the support rod.

[0014] Preferably, an adjusting rod is arranged between the support rod and the support plate; the adjusting rod is slidably connected to the support rod; a connecting seat is fixedly connected to one end of the adjusting rod close to the support plate; the connecting seat is fixedly connected to the support plate; a sliding groove is provided on the bottom surface of the hatch cover at a position corresponding to the adjusting rod, and the sliding groove is T-shaped; a screw rod is slidably connected to the surface of the connecting seat; a splint is fixedly connected to the top surface of the screw rod, and the splint is slidably connected in the sliding groove; a nut is threadedly connected to the surface of the threaded rod.

[0015] Preferably, one end of the support rod away from the top rod is fixedly connected to a telescopic rod; and the telescopic end of the telescopic rod is fixedly connected to the support rod.

[0016] The beneficial effects of the present invention are as follows: 1. The ultra-high temperature thermal assessment test device for the thermal protection structure of an aircraft described in the present invention controls the vertical and horizontal movements of the hatch cover respectively by means of a hydraulic cylinder and a movable seat to move the hatch cover to one side of the sealed cabin, and then securely connects the sample to the bottom surface of the hatch cover by a connecting assembly, thereby achieving the installation and removal of the sample without the need for the test personnel to personally enter the sealed cabin, thereby avoiding potential safety risks and inaccurate experimental data caused by accidentally touching the nozzle when installing the sample.

[0017] 2. The ultra-high temperature thermal assessment test device for the aircraft thermal protection structure described in the present invention is connected to an external vacuum pump through a suction pipe to suck the space between the two high temperature resistant glasses to ensure a vacuum environment between the two high temperature resistant glasses, thereby reducing the heat transfer, and further reducing the probability of the two high temperature resistant glasses being damaged at the same time, thereby improving the safety of the embodiments of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The present invention will be further described below in conjunction with the accompanying drawings.

[0019] Figure 1 is a stereogram of the present invention; Figure 2 is a state diagram of the hatch cover when it is opened in the present invention; Figure 3 is a partial cross-sectional view of the sealed cabin in the present invention; Figure 4 It is a schematic diagram of the structure of the suction pipe in the present invention; Figure 5 It is a structural schematic diagram of the hatch cover in the present invention; Figure 6 It is a structural schematic diagram of the curved plate in the present invention; Figure 7 It is a structural schematic diagram of the ejector rod in the present invention; Figure 8 It is a structural schematic diagram of the fixed pulley 1 in the present invention; Fig. 9 It is a schematic diagram of the structure of the support tube in the present invention; Fig.10 It is a structural schematic diagram of the ejector rod in the present invention; In the figure: 1. gantry; 2. sealed cabin; 3. moving seat; 4. hydraulic cylinder; 5. hatch; 6. nozzle; 7. observation port; 8. high temperature resistant glass; 9. suction pipe; 10. vacuum pressure gauge; 11. casing; 12. rubber pad; 13. air port; 14. extrusion cylinder; 15. guide tube; 16. servo motor; 17. winding cylinder; 18. steel cable; 19. hook; 20. receiving plate; 21. limit hole; 22. arc plate; 23. connecting plate ; 24. Double-thread screw; 25. Support tube; 26. Push rod; 27. Threaded rod; 28. Make way groove; 29. ​​Drive rod; 30. Limit plate; 31. Push block; 32. Rotation groove; 33. Push rod; 34. Limit cylinder; 35. Support rod; 36. Support plate; 37. Fixed pulley one; 38. Fixed pulley two; 39. Adjustment rod; 40. Connecting seat; 41. Slide groove; 42. Fixed screw; 43. Clamp; 44. Nut; 45. Telescopic rod. DETAILED DESCRIPTION

[0020] 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.

[0021] like Figures 1 to 3As shown, an ultra-high temperature thermal assessment test device for aircraft thermal protection structure according to an embodiment of the present invention comprises a gantry 1; a sealed cabin 2 is arranged on one side of the bottom of the gantry 1; the sealed cabin 2 is made of fireproof and heat-insulating material, and the hatch of the sealed cabin 2 is located on its top surface; a moving seat 3 is slidably connected to the surface of the crossbeam of the gantry 1, and the moving seat 3 is driven by a motor; a hydraulic cylinder 4 is fixedly connected to the bottom surface of the moving seat 3; a hatch cover 5 is fixedly connected to the telescopic end of the hydraulic cylinder 4, and the hatch cover 5 is made of fireproof and heat-insulating material; a connecting component is fixedly connected to the bottom surface of the hatch cover 5; the connecting component Used to fix the sample to be tested; a plurality of uniformly arranged nozzles 6 are installed at the bottom of the sealed cabin 2, and the nozzles 6 are connected to the external gas pipeline through a conduit; a plurality of uniformly arranged observation ports 7 are opened around the sealed cabin 2; a high-temperature resistant glass 8 is installed in the observation port 7; during operation, when the test personnel need to test the sample of the thermal protection structure to be tested, the embodiment of the present invention can be used. First, the test personnel need to control the hydraulic cylinder 4 to lift the hatch cover 5, and then the motor drives the moving seat 3 to move along the gantry 1, so as to move the moving seat 3, the hydraulic cylinder 4 and the hatch cover 5. To one side of the sealed cabin 2, the test personnel can then install the sample to be tested on the bottom of the hatch cover 5 through the connecting assembly at the bottom of the hatch cover 5, and then the test personnel use the moving seat 3 and the hydraulic cylinder 4 to cover the hatch cover 5 with the sample at the bottom to the top surface of the sealed cabin 2. After that, the test personnel pass the gas into the nozzle 6 and ignite it. At this time, the flame at the nozzle 6 can be directly sprayed on the surface of the sample to be tested. At the same time, the test personnel can also observe through the high-temperature resistant glass 8 at the observation port 7. After the ultra-high temperature thermal assessment test is completed, the test personnel control the hydraulic cylinder 4 and the moving seat 3 to lift the hatch cover 5 to the top surface of the sealed cabin 2. The cover 5 and the sample are moved to one side of the sealed cabin 2, so that the test personnel can directly detect various data of the thermal protection structure to facilitate the test personnel's subsequent evaluation. The test personnel control the vertical and horizontal movements of the hatch cover 5 by the hydraulic cylinder 4 and the moving seat 3 respectively to move the hatch cover 5 to one side of the sealed cabin 2, and then the sample is fixed to the bottom surface of the hatch cover 5 by the connecting assembly, thereby achieving the installation and removal of the sample without the need for the test personnel to personally enter the sealed cabin 2, thereby avoiding potential safety risks and inaccurate experimental data caused by accidentally touching the nozzle 6 when installing the sample.

[0022] like Figure 3 to Figure 4As shown, a pair of high temperature resistant glasses 8 are provided, and a gap is left between the high temperature resistant glasses 8; a suction pipe 9 is fixedly connected to the side wall of the sealed cabin 2, and the suction pipe 9 extends to the enclosed space formed by the two high temperature resistant glasses 8 and the inner wall of the observation port 7; a vacuum pressure gauge 10 is installed on the surface of the suction pipe 9 outside the sealed cabin 2; when working, before conducting the ultra-high temperature assessment test, the tester needs to observe the reading of the vacuum pressure gauge 10 to confirm whether the space between the two high temperature resistant glasses 8 is close to vacuum. If it is not vacuum, it needs to be connected to an external vacuum pump through the suction pipe 9. Then, the space between the two high-temperature resistant glasses 8 is sucked to ensure a vacuum environment between the two high-temperature resistant glasses 8, thereby reducing the heat transfer, and further reducing the probability of the two high-temperature resistant glasses 8 being damaged at the same time, thereby improving the safety of the embodiment of the present invention. At the same time, compared with the comparative document, in which cold air is introduced between the two high-temperature resistant glasses 8, the embodiment of the present invention directly draws the two high-temperature resistant glasses 8 into a vacuum, which can avoid a large temperature difference on both sides of the high-temperature resistant glass 8, and further avoid the high-temperature resistant glass 8 from breaking due to the large temperature difference, thereby improving the service life of the embodiment of the present invention.

[0023] like Figure 4 As shown, the end of the suction tube 9 away from the high-temperature resistant glass 8 is slidably connected with a sleeve 11; the end of the sleeve 11 away from the suction tube 9 is fixedly connected with a rubber pad 12; the side surface of the sleeve 11 is provided with a plurality of evenly arranged air ports 13; the surface of the suction tube 9 is threadedly connected with an extrusion cylinder 14, and the extrusion cylinder 14 is located at the end of the sleeve 11 away from the rubber pad 12; during operation, when the test personnel need to suck the air between the two high-temperature resistant glasses 8 through the suction tube 9, the test personnel need to first put the connecting pipe of the vacuum pump on the end of the suction tube 9 and perform the vacuum operation, and then the test personnel screw the extrusion cylinder 14 to squeeze the sleeve 11 and The sleeve 11 is driven to move, and finally the air port 13 on the surface of the sleeve 11 is moved to the pipe mouth at the end of the suction tube 9. At this time, the tester can evacuate the suction tube 9 through the air port 13, and the suction tube 9 is connected to the space between the two high-temperature resistant glasses 8, so that the air between the two high-temperature resistant glasses 8 can be extracted. When the reading of the vacuum pressure gauge 10 drops, the tester screws the extrusion cylinder 14 so that it no longer squeezes the extrusion cylinder 14, and then the tester quickly pulls out the connecting pipe of the vacuum pump. At this time, due to the effect of the external atmospheric pressure, the rubber pad 12 at the end of the extrusion cylinder 14 will be pressed toward the end of the suction tube 9, thereby ensuring the sealing of the suction tube 9.

[0024] like Figure 2 , Figure 5 and Figure 7As shown, the connection assembly includes two pairs of guide tubes 15; the guide tubes 15 are evenly fixed to the bottom surface of the hatch cover 5, and the top of the guide tubes passes through the hatch cover 5; two pairs of servo motors 16 are fixed to the top surface of the hatch cover 5; a winding drum 17 is installed at the output end of the servo motor 16; a steel cable 18 is fixed to the surface of the winding drum 17, and the steel cable 18 passes through the guide tube 15; a hook 19 is fixed to the end of the steel cable 18 away from the winding drum 17; when working, when the test personnel need to install the sample to be tested on the bottom surface of the hatch cover 5, the test personnel The servo motor 16 can be controlled to drive the winding drum 17 to rotate, thereby lowering the steel cable 18 passing through the guide tube 15, so that the test personnel can hang the hanging ring reserved on the top surface of the sample to be tested on the hook 19 at the bottom of the steel cable 18. After that, the test personnel can lift the steel cable 18 to a suitable height through the servo motor 16 and the winding drum 17. During the lifting process, the test personnel can also control the different lifting heights of the four corners of the four samples to adjust the inclination angle of the sample, and then measure whether the thermal protection structure can function stably under different heating angles.

[0025] like Figures 5 and 6 As shown, a receiving plate 20 is fixedly connected to the top surface of the guide tube 15; a limiting hole 21 is provided on the top surface of the receiving plate 20 at a position corresponding to the steel cable 18, and the steel cable 18 passes through the limiting hole 21; a pair of symmetrically arranged arc plates 22 are slidably arranged on the top surface of the receiving plate 20; one end of the paired arc plates 22 are fixedly connected to a connecting plate 23; the paired connecting plates 23 are commonly threadedly connected with a double-thread screw 24; during operation, after the test personnel have adjusted the length of the steel cable 18 in the sealed cabin 2, the test personnel need to screw the double-thread screw 24 on the receiving plate 20 so that it can drive the two connecting plates 23 to move toward each other, and then the two connecting plates 23 moving toward each other drive the arc plates 22 to move toward each other, so that the two arc plates 22 clamp the steel cable 18 and seal the limiting hole 21, thereby preventing high-temperature gas from escaping from the limit and causing safety hazards.

[0026] like Figure 7 and Fig. 9As shown, the bottom surface of the hatch cover 5 is fixedly connected with a support tube 25 between each guide tube 15; the support tube 25 is slidably connected with a push rod 26; the support tube 25 is rotatably connected with a threaded rod 27; the push rod 26 is provided with a clearance groove 28 at the corresponding position of the threaded rod 27 at one end thereof close to the threaded rod 27; the side surface of the support tube 25 is rotatably connected with a driving rod 29, and the driving rod 29 extends into the support tube 25; the end of the driving rod 29 located in the support tube 25 is driven by the threaded rod 27 through a gear set; the surface of the threaded rod 27 is threadedly connected with a limit plate 30; during operation, before the test personnel lift the sample to be tested through the steel cable 18, the test personnel need to first screw the support The driving rod 29 at the support tube 25 drives the threaded rod 27 to rotate through the driving rod 29, and the rotating threaded rod 27 drives its upper limit plate 30 to move to the top of the support tube 25, so that it will not hinder the sliding of the push rod 26 at the support tube 25, and then the test personnel lift the sample through the steel cable 18, and the top surface of the sample will squeeze the push rod 26, so that the push rod 26 is pressed into the support tube 25. After the sample is lifted to a suitable height, the test personnel screw the driving rod 29 to drive the threaded rod 27 to rotate, and then drive the limit plate 30 to fit against the top surface of the push rod 26, so that the push rod 26 can fix the sample, avoiding the impact force of the nozzle 6 when spraying flames, causing the sample to shake violently, thereby affecting the accuracy of the experimental data.

[0027] like Figures 9 and 10 As shown, the bottom surface of the push rod 26 is rotatably connected to the push block 31; the side surface of the top block 31 is provided with a pair of symmetrically arranged rotation grooves 32; the rotation groove 32 is rotatably connected to the push rod 33; the surface of the top block 31 is threadedly connected to the limiting cylinder 34, and the limiting cylinder 34 is located at the top of the push rod 33; during operation, when the test personnel need the push rod 26 to resist the sample, the test personnel can rotate the top block 31 so that the push rods 33 on both sides do not interfere with the inclination angle of the sample, and then the test personnel rotate the limiting cylinder 34 to squeeze the push rod 33 through the limiting cylinder 34, so that the push rod 33 is pressed against the top surface of the sample, thereby increasing the contact area between the top block 31 and the sample, and further improving the stability of the sample when it is impacted by flame.

[0028] like Figures 7 and 8As shown, two pairs of symmetrically arranged support rods 35 are installed on the bottom surface of the hatch cover 5, and the four support rods 35 are respectively located at the four corners of the hatch cover 5; a pair of support plates 36 are installed at one end of the support rod 35 close to the top rod 26; a fixed pulley 1 37 is rotatably connected between the paired support plates 36; a fixed pulley 2 38 is rotatably connected to one side of the guide tube 15 close to the support rod 35; during operation, when the test personnel need to suspend a larger sample, the test personnel can pass the steel cable 18 through the gap between the fixed pulley 1 37 and the support plate 36, so that the spacing between each steel cable 18 is increased to adapt to a larger sample, thereby improving the scope of application of the embodiment of the present invention, and the fixed pulley 2 38 at the bottom of the guide tube 15 can also avoid direct friction between the steel cable 18 and the guide tube 15, thereby reducing the wear of the guide tube 15 and improving its service life.

[0029] like Figures 7 and 8 As shown, an adjusting rod 39 is provided between the support rod 35 and the support plate 36; the adjusting rod 39 is slidably connected to the support rod 35; a connecting seat 40 is fixedly connected to the end of the adjusting rod 39 close to the support plate 36; the connecting seat 40 is fixedly connected to the support plate 36; a sliding groove 41 is provided on the bottom surface of the hatch cover 5 at a position corresponding to the adjusting rod 39, and the sliding groove 41 is T-shaped; a screw is slidably connected to the surface of the connecting seat 40; a clamping plate 43 is fixedly connected to the top surface of the screw, and the clamping plate 43 is slidably connected in the sliding groove 41; the surface of the threaded rod 27 is screwed The thread is connected with a nut 44; during operation, when the test personnel hoist samples of different sizes, the test personnel can adjust the length of each adjusting rod 39 extending out of the support rod 35 according to the different center of gravity of the samples. After the length of the adjusting rod 39 is adjusted, the test personnel screws the nut 44 again, and the nut 44 rotates on the fixing screw 42 to make the fixing screw 42 drive the clamping plate 43 to squeeze the inner wall of the slide groove 41, thereby fixing the position of the adjusting rod 39, thereby making it convenient for the test personnel to hoist samples of different sizes, further improving the scope of application of the embodiment of the present invention.

[0030] like Figures 7 and 8As shown, the end of the support rod 35 away from the top rod 26 is fixedly connected with a telescopic rod 45; the telescopic end of the telescopic rod 45 is fixedly connected to the support rod 35; during operation, when the test personnel need to pass the steel cable 18 through the gap between the fixed pulley 37 and the support plate 36, the test personnel can first screw the nut 44 to make the adjustment rod 39 and the support rod 35 descend, and drive the telescopic rod 45 to extend, thereby leaving enough space on the top of the fixed pulley 37 to facilitate the test personnel to pass the hook 19 at the end of the steel cable 18, and after the steel cable 18 passes through, the test personnel screw the nut 44 again to make the support rod 35 and the adjustment rod 39 rise, so as to reduce the distance from the support rod 35 and the adjustment rod 39 to the bottom surface of the hatch cover 5, so that the hook 19 at the end of the steel cable 18 cannot pass through the gap between the support plate 36 and the bottom surface of the hatch cover 5, thereby restricting the hook 19 and preventing the steel cable 18 from detaching from the fixed pulley 37 during the adjustment process.

[0031] During operation, when the test personnel need to test the sample of the thermal protection structure to be tested, the embodiment of the present invention can be used. First, the test personnel need to control the hydraulic cylinder 4 to lift the hatch cover 5, and then the motor drives the moving seat 3 to move along the gantry 1, so as to move the moving seat 3, the hydraulic cylinder 4 and the hatch cover 5 to one side of the sealed cabin 2. Then the test personnel can install the sample to be tested on the bottom of the hatch cover 5 through the connecting assembly at the bottom of the hatch cover 5, and then the test personnel use the moving seat 3 and the hydraulic cylinder 4 to cover the hatch cover 5 with the sample at the bottom to the top surface of the sealed cabin 2 again. After that, the test personnel pass the gas into the nozzle 6 and ignite it. At this time, the flame at the nozzle 6 can be directly sprayed on the surface of the sample to be tested. At the same time, the test personnel can also Observation is carried out through the high-temperature resistant glass 8 at the observation port 7. After the ultra-high temperature thermal assessment test is completed, the test personnel controls the hydraulic cylinder 4 and the moving seat 3 to move the hatch cover 5 and the sample to one side of the sealed cabin 2, so that the test personnel can directly detect various data of the thermal protection structure to facilitate the test personnel's subsequent evaluation. Therefore, the test personnel control the vertical and horizontal movements of the hatch cover 5 by the hydraulic cylinder 4 and the moving seat 3 respectively to move the hatch cover 5 to one side of the sealed cabin 2, and then fix the sample to the bottom surface of the hatch cover 5 by the connecting assembly, thereby achieving the installation and removal of the sample without the test personnel personally entering the sealed cabin 2, thereby avoiding potential safety risks and inaccurate experimental data caused by accidentally touching the nozzle 6 when installing the sample.

[0032] Before conducting the ultra-high temperature assessment test, the tester needs to first observe the reading of the vacuum pressure gauge 10 to confirm whether the space between the two high temperature resistant glasses 8 is close to a vacuum. If it is not a vacuum, it is necessary to connect to an external vacuum pump through a suction pipe 9 to suck the space between the two high temperature resistant glasses 8 to ensure a vacuum environment between the two high temperature resistant glasses 8, thereby reducing heat transfer, thereby reducing the probability of simultaneous damage to the two high temperature resistant glasses 8, and improving the safety of the embodiment of the present invention. At the same time, compared with the comparative document, in which cold air is introduced between the two high temperature resistant glasses 8, the embodiment of the present invention directly draws the two high temperature resistant glasses 8 into a vacuum, which can avoid a large temperature difference on both sides of the high temperature resistant glass 8, thereby avoiding the high temperature resistant glass 8 from breaking due to the large temperature difference, thereby improving the service life of the embodiment of the present invention.

[0033] When the tester needs to suck the air between the two high-temperature resistant glasses 8 through the suction tube 9, the tester needs to first put the connecting pipe of the vacuum pump on the end of the suction tube 9 and perform the vacuum operation. Then the tester screws the extrusion tube 14 to squeeze the sleeve 11 and drive the sleeve 11 to move, and finally moves the air port 13 on the surface of the sleeve 11 to the pipe mouth at the end of the suction tube 9. At this time, the tester can evacuate the suction tube 9 through the air port 13, and the suction tube 9 is connected to the space between the two high-temperature resistant glasses 8, so that the air between the two high-temperature resistant glasses 8 can be sucked away. When the reading of the vacuum pressure gauge 10 drops, the tester screws the extrusion tube 14 so that it no longer squeezes the extrusion tube 14. Then the tester quickly pulls out the connecting pipe of the vacuum pump. At this time, due to the effect of the external atmospheric pressure, the rubber pad 12 at the end of the extrusion tube 14 will be pressed toward the end of the suction tube 9, thereby ensuring the sealing of the suction tube 9.

[0034] When the test personnel need to install the sample to be tested on the bottom surface of the hatch cover 5, the test personnel can control the servo motor 16 to drive the winding drum 17 to rotate, thereby lowering the steel cable 18 passing through the guide tube 15, so as to facilitate the test personnel to hang the hanging ring reserved on the top surface of the sample to be tested on the hook 19 at the bottom of the steel cable 18. After that, the test personnel use the servo motor 16 and the winding drum 17 to lift the steel cable 18 to a suitable height. During the lifting process, the test personnel can also control the different lifting heights of the four corners of the four samples to adjust the inclination angle of the sample, and then measure whether the thermal protection structure can function stably under different heating angles.

[0035] After the test personnel have adjusted the length of the steel cable 18 in the sealed cabin 2, the test personnel need to screw the double-thread screw 24 on the receiving plate 20 so that it can drive the two connecting plates 23 to move toward each other, and then the two connecting plates 23 moving toward each other drive the arc plates 22 to move toward each other, so that the two arc plates 22 clamp the steel cable 18 and seal the limit hole 21, thereby preventing high-temperature gas from escaping from the limit and causing a safety hazard.

[0036] Before the test personnel lift the sample to be tested by the steel cable 18, the test personnel need to first screw the driving rod 29 at the support tube 25 to drive the threaded rod 27 to rotate by the driving rod 29, and the rotating threaded rod 27 will drive its upper limit plate 30 to move to the top of the support tube 25, so that it will not hinder the sliding of the push rod 26 at the support tube 25, and then the test personnel will lift the sample by the steel cable 18, and the top surface of the sample will squeeze the push rod 26, so that the push rod 26 is pressed into the support tube 25. After the sample is lifted to a suitable height, the test personnel screw the driving rod 29 again to drive the threaded rod 27 to rotate, and then drive the limit plate 30 to fit against the top surface of the push rod 26, so that the push rod 26 can fix the sample, avoiding the impact force of the nozzle 6 when spraying flames, causing the sample to shake violently, thereby affecting the accuracy of the experimental data.

[0037] When the test personnel need the top rod 26 to support the sample, the test personnel can rotate the top block 31 so that the support rods 33 on both sides do not interfere with the tilt angle of the sample. Then the test personnel rotates the limiting cylinder 34 to squeeze the support rod 33 through the limiting cylinder 34, thereby pressing the support rod 33 against the top surface of the sample, thereby increasing the contact area between the top block 31 and the sample, and further improving the stability of the sample when it is impacted by flames.

[0038] When the test personnel need to suspend a larger sample, the test personnel can pass the steel cable 18 through the gap between the fixed pulley 1 37 and the support plate 36, so that the spacing between each steel cable 18 is increased to adapt to larger samples, thereby improving the scope of application of the embodiment of the present invention. The fixed pulley 2 38 at the bottom of the guide tube 15 can also prevent the steel cable 18 from directly rubbing against the guide tube 15, thereby reducing the wear of the guide tube 15 and increasing its service life.

[0039] When the test personnel hoist samples of different sizes, the test personnel can adjust the length of each adjusting rod 39 extending out of the support rod 35 according to the different centers of gravity of the samples. After the length of the adjusting rod 39 is adjusted, the test personnel then screws the nut 44, and the nut 44 rotates on the fixing screw 42 to enable the fixing screw 42 to drive the clamping plate 43 to squeeze the inner wall of the slide groove 41, thereby fixing the position of the adjusting rod 39, thereby making it convenient for the test personnel to hoist samples of different sizes, further improving the scope of application of the embodiments of the present invention.

[0040] When the test personnel need to pass the steel cable 18 through the gap between the fixed pulley 37 and the support plate 36, the test personnel can first screw the nut 44 to make the adjusting rod 39 and the support rod 35 drop, and drive the telescopic rod 45 to extend, thereby leaving enough space on the top of the fixed pulley 37 for the test personnel to pass the hook 19 at the end of the steel cable 18. After the steel cable 18 passes through, the test personnel screw the nut 44 again to make the support rod 35 and the adjusting rod 39 rise to reduce the distance from the support rod 35 and the adjusting rod 39 to the bottom surface of the hatch cover 5, so that the hook 19 at the end of the steel cable 18 cannot pass through the gap between the support plate 36 and the bottom surface of the hatch cover 5, thereby restricting the hook 19 and preventing the steel cable 18 from detaching from the fixed pulley 37 during the adjustment process.

[0041] 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. An ultra-high temperature thermal assessment test device for aircraft thermal protection structures, characterized in that: It comprises a gantry (1); a sealed cabin (2) is arranged on one side of the bottom of the gantry (1); the sealed cabin (2) is made of a fireproof and heat-insulating material, and a hatch of the sealed cabin (2) is located on the top surface thereof; The surface of the crossbeam of the gantry (1) is slidably connected to a moving seat (3), and the moving seat (3) is driven by a motor; the bottom surface of the moving seat (3) is fixedly connected to a hydraulic cylinder (4); the telescopic end of the hydraulic cylinder (4) is fixedly connected to a hatch cover (5), and the hatch cover (5) is made of a fireproof and heat-insulating material; the bottom surface of the hatch cover (5) is fixedly connected to a connecting component; the connecting component is used to fix a sample to be tested; a plurality of uniformly arranged nozzles (6) are installed at the bottom of the sealed cabin (2), and the nozzles (6) are connected to an external gas pipeline through a conduit; a plurality of uniformly arranged observation ports (7) are opened around the sealed cabin (2); and high-temperature resistant glass (8) is installed in the observation port (7).

2. The ultra-high temperature thermal assessment test device for aircraft thermal protection structure according to claim 1, characterized in that: A pair of the heat-resistant glass (8) is provided, and a gap is left between the heat-resistant glass (8); a suction pipe (9) is fixedly connected to the side wall of the sealed cabin (2), and the suction pipe (9) extends into a closed space formed by the two pieces of heat-resistant glass (8) and the inner wall of the observation port (7); a vacuum pressure gauge (10) is installed on the surface of the suction pipe (9) outside the sealed cabin (2).

3. The ultra-high temperature thermal assessment test device for aircraft thermal protection structure according to claim 2, characterized in that: The end of the suction tube (9) away from the high temperature resistant glass (8) is slidably connected to a sleeve (11); the end of the sleeve (11) away from the suction tube (9) is fixedly connected to a rubber pad (12); a side surface of the sleeve (11) is provided with a plurality of evenly arranged air ports (13); the surface of the suction tube (9) is threadedly connected to an extrusion cylinder (14), and the extrusion cylinder (14) is located at the end of the sleeve (11) away from the rubber pad (12).

4. The ultra-high temperature thermal assessment test device for aircraft thermal protection structure according to claim 1, characterized in that: The connection assembly comprises two pairs of guide tubes (15); the guide tubes (15) are evenly fixed to the bottom surface of the hatch cover (5), and the top of the guide tubes passes through the hatch cover (5); two pairs of servo motors (16) are fixed to the top surface of the hatch cover (5); a winding drum (17) is installed at the output end of the servo motor (16); a steel cable (18) is fixed to the surface of the winding drum (17), and the steel cable (18) passes through the guide tube (15); and a hook (19) is fixed to one end of the steel cable (18) away from the winding drum (17).

5. The ultra-high temperature thermal assessment test device for aircraft thermal protection structure according to claim 4, characterized in that: A receiving plate (20) is fixedly connected to the top surface of the guide tube (15); a limiting hole (21) is provided on the top surface of the receiving plate (20) at a position corresponding to the steel cable (18), and the steel cable (18) passes through the limiting hole (21); a pair of symmetrically arranged arc plates (22) are slidably disposed on the top surface of the receiving plate (20); one end of the paired arc plates (22) is fixedly connected to a connecting plate (23); and a double-thread screw (24) is commonly threadedly connected between the paired connecting plates (23).

6. The ultra-high temperature thermal assessment test device for aircraft thermal protection structure according to claim 5, characterized in that: A support tube (25) is fixedly connected between each guide tube (15) on the bottom surface of the hatch cover (5); a push rod (26) is slidably connected inside the support tube (25); a threaded rod (27) is rotatably connected inside the support tube (25); an end of the push rod (26) close to the threaded rod (27) is provided with a clearance groove (28) at a corresponding position of the threaded rod (27); a driving rod (29) is rotatably connected to the side surface of the support tube (25), and the driving rod (29) extends into the inside of the support tube (25); a gear set is used to transmit power between one end of the driving rod (29) located inside the support tube (25) and the threaded rod (27); and a limit plate (30) is threadedly connected to the surface of the threaded rod (27).

7. The ultra-high temperature thermal assessment test device for aircraft thermal protection structure according to claim 6, characterized in that: The bottom surface of the push rod (26) is rotatably connected to a push block (31); a pair of symmetrically arranged rotation grooves (32) are formed on the side surface of the push block (31); a stop rod (33) is rotatably connected in the rotation groove (32); a limit cylinder (34) is threadedly connected to the surface of the push block (31), and the limit cylinder (34) is located at the top of the stop rod (33).

8. The ultra-high temperature thermal assessment test device for aircraft thermal protection structure according to claim 7, characterized in that: Two pairs of symmetrically arranged support rods (35) are installed on the bottom surface of the hatch cover (5), and the four support rods (35) are respectively located at the four corners of the hatch cover (5); a pair of support plates (36) are installed at one end of the support rod (35) close to the top rod (26); a fixed pulley 1 (37) is rotatably connected between the paired support plates (36); and a fixed pulley 2 (38) is rotatably connected to one side of the guide tube (15) close to the support rod (35).

9. The ultra-high temperature thermal assessment test device for aircraft thermal protection structure according to claim 8, characterized in that: An adjusting rod (39) is arranged between the support rod (35) and the support plate (36); the adjusting rod (39) is slidably connected to the support rod (35); a connecting seat (40) is fixedly connected to one end of the adjusting rod (39) close to the support plate (36); the connecting seat (40) is fixedly connected to the support plate (36); a sliding groove (41) is provided on the bottom surface of the hatch cover (5) at a position corresponding to the adjusting rod (39), and the sliding groove (41) is arranged in a T shape; a fixing screw (42) is slidably connected to the surface of the connecting seat (40); a clamping plate (43) is fixedly connected to the top surface of the fixing screw (42), and the clamping plate (43) is slidably connected in the sliding groove (41); a nut (44) is threadedly connected to the surface of the fixing screw (42).

10. The ultra-high temperature thermal assessment test device for aircraft thermal protection structure according to claim 9, characterized in that: One end of the support rod (35) away from the top rod (26) is fixedly connected to a telescopic rod (45); the telescopic end of the telescopic rod (45) is fixedly connected to the support rod (35).

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